Patent Publication Number: US-2023159173-A1

Title: Near-space operation systems

Description:
CROSS-REFERENCE TO RELATED APPLICATION 
     This application is a continuation of U.S. application Ser. No. 17/061,257, filed Oct. 1, 2020, entitled “NEAR-SPACE OPERATION SYSTEMS”, which is a continuation of U.S. application Ser. No. 15/616,758, filed Jun. 7, 2017, entitled “NEAR-SPACE OPERATION SYSTEMS”, which is a continuation of U.S. application Ser. No. 14/188,581, filed Feb. 24, 2014, entitled “NEAR-SPACE OPERATION SYSTEMS”, which claims the benefit of priority from U.S. provisional application No. 61/768,183, filed Feb. 22, 2013, entitled “NEAR-SPACE OPERATION SYSTEMS”; and of U.S. provisional application No. 61/813,918, filed Apr. 19, 2013, entitled “NEAR-SPACE OPERATION SYSTEMS”; and of U.S. provisional application No. 61/822,355, filed May 11, 2013, entitled “NEAR-SPACE OPERATION SYSTEMS”, the contents of all of which are incorporated herein by reference and are not admitted to be prior art with respect to the present invention by the mention in this cross-reference section. 
    
    
     BACKGROUND 
     This invention relates to providing a system for high altitude and near-space operations. More particularly, this invention relates to providing a system enabling safe manned and unmanned operations at extremely high altitudes (above about 70,000 feet). Even more particularly, this invention relates to providing such systems enabling stratospheric visits. And even more particularly, this invention relates to providing such systems enabling stratospheric visits using lighter-than-air vehicles. 
     There is increasing interest in technologies enabling high altitude and near space access for tourism, research, education and other scientific and commercial pursuits. As the introduction of the airplane, the computer, and the internet proved, making new regions of our planet accessible can bring about revolutionary scientific, social, and economic advances. A need exists for new technologies providing safe, low-cost, access to high altitude and near-space regions of the Earth&#39;s atmosphere. 
     OBJECTS AND FEATURES OF THE INVENTION 
     A primary object and feature of the present invention is to provide a system addressing the above-mentioned need(s). It is a further object and feature of the present invention to provide such a system enabling safe manned and unmanned operations at extremely high altitudes (above 70,000 feet). It is a further object and feature of the present invention to provide such a system enabling stratospheric visits using lighter-than-air vehicles. It is another object and feature of the present invention to provide such a system enabling a multi-crew, multi-passenger vehicle utilizing balloon accent and parawing recovery. It is a further object and feature of the present invention to provide such a system enabling “shirt-sleeve” crew/passenger operation. 
     It is another object and feature of the present invention to provide such a system enabling ultra-high altitude parachute/parawing primary and/or secondary recovery utilizing stabilized (stiffened) drogue parachute deployment. A further primary object and feature of the present invention is to provide such a system that is efficient, inexpensive, and useful. Other objects and features of this invention will become apparent with reference to the following descriptions. 
     SUMMARY OF THE INVENTION 
     In accordance with a preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; 
     wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and a parachute pre-deploying system structured and arranged to deploy, prior to the launch of the at least one payload, such parachute system. 
     Moreover, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. 
     Additionally, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. Also, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. In addition, it provides such a stratospheric-visit system: wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human. 
     And, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Further, it provides such a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. 
     Even further, it provides such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. 
     Moreover, it provides such a stratospheric-visit system wherein such parachute system comprises at least one parafoil. Additionally, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Also, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. 
     In addition, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. And, it provides such a stratospheric-visit system: wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human. 
     Further, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Even further, it provides such a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; 
     wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. 
     Moreover, it provides such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. Additionally, it provides such a stratospheric-visit system wherein such parachute system comprises at least one drogue chute. Also, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. 
     In addition, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. And, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. 
     Further, it provides such a stratospheric-visit system: wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human. 
     Even further, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Moreover, it provides such a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; 
     wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. Additionally, it provides such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; a launch system structured and arranged to launch the at least one 10 payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. 
     Also, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. In addition, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. 
     And, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Further, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. 
     Even further, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. Moreover, it provides such a stratospheric-visit system: wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human. 
     Additionally, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Also, it provides such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. 
     In addition, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. And, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. 
     Further, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. Even further, it provides such a stratospheric-visit system: wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human. 
     Moreover, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and wherein such tethering system comprises at least one lift-resisting ground restraint structured and arranged to resist upward lift imparted by such lighter-than-air propulsion system at least one balloon-to-restraint coupler structured and arranged to couple such lighter-than-air propulsion system to such at least one lift-resisting ground restraint; at least one payload coupler structured and arranged to couple the at least one payload to such at least one balloon-to-restraint coupler; wherein such un-tethering system comprises at least one restraint-decoupling system structured and arranged to decouple such at least one balloon-to-restraint coupler from such at least one lift-resisting ground restraint, wherein the at least one payload, after decoupling such at least one balloon-to-restraint coupler from such at least one lift-resisting ground restraint, remains coupled to such lighter-than-air propulsion system by such at least one balloon-to-restraint coupler. 
     Further, it provides such a stratospheric-visit system wherein the at least one payload launches with such lighter-than-air propulsion system. Additionally, it provides such a stratospheric-visit system wherein such payload system comprises a stratospheric-visit vehicle structured and arranged to transport multiple humans on the stratospheric visit; and wherein such stratospheric-visit vehicle comprises seating structured and arranged to serve the multiple humans environmental control structured and arranged to serve the multiple humans during a multiple hour stratospheric visit visual access structured and arranged to provide the multiple humans with viewing of Earth. 
     Also, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. 
     In addition, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. And, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. 
     Further, it provides such a stratospheric-visit system wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human. 
     Even further, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Moreover, it provides such a stratospheric-visit system further comprising a parachute pre-deploying system structured and arranged to deploy, prior to the launch of the at least one payload, such parachute system. 
     Additionally, it provides such a stratospheric-visit system wherein such parachute system comprises at least one parafoil. Also, it provides such a stratospheric-visit system wherein such parachute system comprises at least one drogue chute. In addition, it provides such a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. And, it provides such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human; wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch; wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply; and wherein the oxygen supply is positionable to be transported along the front torso of the at least one human. 
     Further, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Even further, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. Moreover, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and wherein such payload system comprises a stratospheric-visit vehicle structured and arranged to transport multiple humans on the stratospheric visit; wherein such stratospheric-visit vehicle comprises seating structured and arranged to serve the multiple humans, environmental control structured and arranged to serve the multiple humans during a multiple hour stratospheric visit, and visual access structured and arranged to provide the multiple humans with viewing of Earth. 
     Additionally, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Also, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. In addition, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. 
     And, it provides such a stratospheric-visit system: wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human. 
     Further, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. 
     Even further, it provides such a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. 
     Moreover, it provides such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. Additionally, it provides such a stratospheric-visit system further comprising a parachute pre-deploying system structured and arranged to deploy, prior to the launch of the at least one payload, such parachute system. Also, it provides such a stratospheric-visit system wherein such parachute system comprises at least one parafoil. In addition, it provides such a stratospheric-visit system wherein such parachute system comprises at least one drogue chute. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and deploying, prior to the step of launching, the parachute system. 
     And, it provides such a stratospheric-visit method wherein the parachute system comprises at least one parafoil system. Further, it provides such a stratospheric-visit method wherein the parachute system comprises at least one drogue system. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and coupling the parachute system within the at least one payload; distance-separating the parachute system from the at least one payload; and controlling compressive resistance of the distance separation of the parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. 
     Even further, it provides such a stratospheric-visit method wherein the step of distance-separating comprises the step of assisting prevention of tangling of the parachute system with the at least one payload. Even further, it provides such a stratospheric-visit method wherein the step of distance-separating comprises the step of assisting the parachute system to penetrate at least one burble confine during deployment of the parachute system. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and assisting traversing of at least the at least one human across the ground; supporting, during launch, at least the at least one human, wherein the step of supporting comprises the steps of minimizing injury, during launch, to at least the at least one human and at least one accompanying human life support environment, conforming support to at least the at least one human and the at least one accompanying human life support environment, cushioning at least the at least one human and the at least one accompanying human life support environment, and permitting movement in both rotational and translational directions. Even further, it provides such a stratospheric-visit method further comprising the step of terminating the step of supporting, during launch of the at least one payload. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of tethering comprises the steps of coupling the lighter-than-air propulsion system to at least one lift-resisting ground restraint with at least one balloon-to-restraint coupler; coupling the at least one payload to the at least one balloon-to-restraint coupler; wherein the step of un-tethering comprises the step of decoupling the at least one balloon-to-restraint coupler from the at least one lift-resisting ground restraint, wherein the at least one payload, after the step of decoupling the at least one balloon-to-restraint coupler from the at least one lift-resisting ground restraint, remains coupled to the lighter-than-air propulsion system. Wherein the at least one payload launches with the lighter-than-air propulsion system. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of controlling at least one human life support environment comprises the steps of coupling at least one equipment controller to a torso of the at least one human, providing a rigid adapter to closely abut a front of the torso of the at least one human, adjusting dimensions of the rigid adapter to fit the front of the torso of the at least one human prior to launch, rigidly attaching a mount, to attach an oxygen supply, to the rigid adapter, and wherein the oxygen supply is positionable to be transported along the front torso of the at least one human. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and providing a stratospheric-visit vehicle to transport multiple humans on the stratospheric visit; wherein the step of providing the stratospheric-visit vehicle comprises the steps of providing seating to serve the multiple humans, providing the at least one human life support environment to serve the multiple humans during a multiple hour stratospheric visit, and providing visual access to serve the multiple humans with viewing of Earth. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and a parachute deploying system structured and arranged to deploy, prior to the launch of the at least one payload, such parachute system. Moreover, it provides such a stratospheric-visit system wherein such parachute system comprises at least one parafoil. Additionally, it provides such a stratospheric-visit system wherein such parachute system comprises at least one drogue chute. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. 
     Also, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. In addition, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. 
     Additionally, it provides such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and wherein such tethering system comprises at least one lift-resisting ground restraint structured and arranged to resist upward lift imparted by such lighter-than-air propulsion system at least one balloon-to-restraint coupler structured and arranged to couple such lighter-than-air propulsion system to such at least one lift-resisting ground restraint; at least one payload coupler structured and arranged to couple the at least one payload to such at least one balloon-to-restraint coupler; wherein such un-tethering system comprises at least one restraint-decoupling system structured and arranged to decouple such at least one balloon-to-restraint coupler from such at least one lift-resisting ground restraint, wherein the at least one payload, after decoupling such at least one balloon-to-restraint coupler from such at least one lift-resisting ground restraint, remains coupled to such lighter-than-air propulsion system by such at least one balloon-to-restraint coupler, wherein the at least one payload launches with such lighter-than-air propulsion system. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human; wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch; wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply; and wherein the oxygen supply is positionable to be transported along the front torso of the at least one human. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit system, relating to a stratospheric visit using lighter-than-air travel, comprising: a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system; and a launch system structured and arranged to launch the at least one payload; wherein such launch system comprises a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload, a tethering system structured and arranged to tether, initially to ground, such lighter-than-air propulsion system, and an un-tethering system structured and arranged to un-tether, from the ground, such lighter-than-air propulsion system; and an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human; a travel control system structured and arranged to control, in the stratospheric visit, travel of the at least one payload; a communication system structured and arranged to communicate within such stratospheric-visit system; and a recovery system structured and arranged to recover at least the at least one human; wherein such recovery system comprises a separator system structured and arranged to perform separation of at least the at least one human from such lighter-than-air propulsion system, the parachute system structured and arranged to decelerate at least the at least one human after the separation of at least the at least one human from such lighter-than-air propulsion system, and a landing system structured and arranged to assist landing of at least the at least one human; and wherein such payload system comprises a stratospheric-visit vehicle structured and arranged to transport multiple humans on the stratospheric visit; wherein such stratospheric-visit vehicle comprises seating structured and arranged to serve the multiple humans, environmental control structured and arranged to serve the multiple humans during a multiple hour stratospheric visit, and visual access structured and arranged to provide the multiple humans with viewing of Earth. 
     Further, it provides such a stratospheric-visit system wherein such payload system comprises a stratospheric-visit vehicle structured and arranged to transport multiple humans on the stratospheric visit; and wherein such stratospheric-visit vehicle comprises seating structured and arranged to serve the multiple humans environmental control structured and arranged to serve the multiple humans during a multiple hour stratospheric visit visual access structured and arranged to provide the multiple humans with viewing of Earth. Even further, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. Moreover, it provides such a stratospheric-visit system wherein such distance separating means comprises anti-tangling means for assisting prevention of tangling of such coupling means with the at least one payload. Additionally, it provides such a stratospheric-visit system wherein such distance separating means comprises burble-confine penetrator means for assisting such parachute system to penetrate at least one burble confine during deployment of such parachute system. Also, it provides such a stratospheric-visit system wherein at least portions of such environmental control system and such communication system comprise at least one equipment module; wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple such at least one equipment module to a torso of the at least one human; wherein such torso-coupling system comprises a rigid adapter structured and arranged to closely abut a front of the torso of the at least one human wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch wherein such rigid adapter further comprises at least one oxygen-supply mount structured and arranged to be attached to an oxygen supply wherein the oxygen-supply is positionable to be transported along the front torso of the at least one human. In addition, it provides such a stratospheric-visit system further comprising: a payload ground-traversing system structured and arranged to assist traversing of at least the at least one human across the ground; wherein such payload ground-traversing system comprises a payload support system structured and arranged to support, during launch, at least the at least one human, wherein such payload support system comprises an injury-minimizing system structured and arranged to minimize injury, during launch, to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one configuration structured and arranged to conform to at least the at least one human and at least one accompanying such environmental control system, wherein such injury-minimizing system comprises at least one cushioning structured and arranged to cushion at least the at least one human and the at least one accompanying such environmental control system, and wherein such payload support system comprises a motion direction system structured and arranged to move in both rotational and translational directions. And, it provides such a stratospheric-visit system wherein such payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload. Further, it provides such a stratospheric-visit system further comprising a parachute deploying system structured and arranged to deploy, prior to the launch of the at least one payload, such parachute system. Even further, it provides such a stratospheric-visit system wherein such parachute system comprises at least one parafoil. Moreover, it provides such a stratospheric-visit system wherein such parachute system comprises at least one drogue chute. Additionally, it provides such a stratospheric-visit system further comprising: coupling means for coupling such parachute system within the at least one payload; wherein such coupling means comprises distance separating means for distance-separating such parachute system from the at least one payload; and wherein such distance separating means comprises compressive-resistance control means for controlling compressive resistance of such distance separating means to assist the distance separation of such parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and deploying, prior to the step of launching, the parachute system. Also, it provides such a method wherein the parachute system comprises at least one parafoil system. 
     In addition, it provides such a method wherein the parachute system comprises at least one drogue system. In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and coupling the parachute system within the at least one payload; distance-separating the parachute system from the at least one payload; and controlling compressive resistance of the distance separation of the parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. And, it provides such a stratospheric-visit method wherein the step of distance-separating comprises the step of assisting prevention of tangling of the parachute system with the at least one payload. 
     Further, it provides such a stratospheric-visit method wherein the step of distance-separating comprises the step of assisting the parachute system to penetrate at least one burble confine during deployment of the parachute system. In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and assisting traversing of at least the at least one human across the ground; supporting, during launch, at least the at least one human, wherein the step of supporting comprises the steps of minimizing injury, during launch, to at least the at least one human and at least one accompanying human life support environment, conforming support to at least the at least one human and the at least one accompanying human life support environment, cushioning at least the at least one human and the at least one accompanying human life support environment, and permitting movement in both rotational and translational directions. Even further, it provides such a stratospheric-visit method further comprising the step of terminating the step of supporting, during launch of the at least one payload. In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of tethering comprises the steps of coupling the lighter-than-air propulsion system to at least one lift-resisting ground restraint with at least one balloon-to-restraint coupler; coupling the at least one payload to the at least one balloon-to-restraint coupler; wherein the step of un-tethering comprises the step of decoupling the at least one balloon-to-restraint coupler from the at least one lift-resisting ground restraint, wherein the at least one payload, after the step of decoupling the at least one balloon-to-restraint coupler from the at least one lift-resisting ground restraint, remains coupled to the lighter-than-air propulsion system, wherein the at least one payload launches with the lighter-than-air propulsion system. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of controlling at least one human life support environment comprises the steps of coupling at least one equipment controller to a torso of the at least one human, providing a rigid adapter to closely abut a front of the torso of the at least one human, adjusting dimensions of the rigid adapter to fit the front of the torso of the at least one human prior to launch, rigidly attaching a mount, to attach an oxygen supply, to the rigid adapter, and wherein the oxygen supply is positionable to be transported along the front torso of the at least one human. 
     In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and providing a stratospheric-visit vehicle to transport multiple humans on the stratospheric visit; wherein the step of providing the stratospheric-visit vehicle comprises the steps of providing seating to serve the multiple humans, providing the at least one human life support environment to serve the multiple humans during a multiple hour stratospheric visit, and providing visual access to serve the multiple humans with viewing of Earth. 
     In accordance with a preferred embodiments hereof, this invention provides each and every novel feature, element, combination, step and/or method disclosed or suggested by this patent application. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG.  1    shows a schematic diagram, illustrating a preferred flight of a preferred high-altitude operations apparatus, according to a preferred embodiment of the present invention. 
         FIG.  2    shows a schematic diagram, illustrating the preferred high-altitude operations apparatus, according to preferred systems of  FIG.  1   . 
         FIG.  3    shows a schematic diagram, illustrating the preferred high-altitude operations apparatus of  FIG.  1   , in a descent and recovery configuration, according to a preferred embodiment of the present invention. 
         FIG.  4 A  shows a high-level organizational overview of a stratospheric-visit system, including preferred function-enabling subsystems, according to preferred embodiments of the present invention. 
         FIG.  4 B  shows a high-level organizational overview of a stratospheric-visit system, including preferred principal system functions, according to preferred embodiments of the present invention. 
         FIG.  5    shows a schematic diagram, illustrating an alternate preferred flight of a single pilot flight vehicle, according to a preferred embodiment of the present invention. 
         FIG.  6 A  through  FIG.  6 C  show a series of diagrams, illustrating a preferred launch procedure for the single-pilot flight vehicle, according to preferred apparatus and methods of the present invention. 
         FIG.  7    shows a front view of a pilot positioned within a payload ground-traversing system, according to a preferred embodiment of the present invention. 
         FIG.  8    shows side view of the pilot positioned within the payload ground-traversing system of  FIG.  7   . 
         FIG.  9    shows a preferred drogue parachute of single-pilot embodiments of the stratospheric-visit system, according to preferred apparatus and methods of the present invention. 
         FIG.  10    shows a diagrammatic rear view of a preferred stowed embodiment of the drogue parachute of  FIG.  9   . 
         FIG.  11    shows a diagrammatic rear view of another preferred stowed embodiment of the drogue parachute of  FIG.  9   . 
         FIG.  12    shows a preferred drogue parachute of the stratospheric-visit system, according to a preferred embodiment of the present invention. 
         FIG.  13 A  through  FIG.  13 E  show a series of diagrams, illustrating a preferred launch procedure for the preferred high-altitude operations apparatus of  FIG.  1   , according to preferred apparatus and methods of the present invention. 
         FIG.  14 A  and  FIG.  14 B  show a preferred multi-passenger capsule according to a preferred embodiment of  FIG.  3   .  30   
     
    
    
     DETAILED DESCRIPTION OF THE BEST MODES AND PREFERRED EMBODIMENTS OF THE INVENTION 
     The present disclosure describes Applicant&#39;s preferred system apparatus and implementation methods enabling manned stratospheric operations using lighter-than-air travel, (above about 70,000 feet). For descriptive clarity, the present invention will be generally identified herein as stratospheric-visit system  100 . The initial section of the present disclosure will describe preferred aspects of near-space operations utilizing Applicant&#39;s preferred systems and methods. Subsequent sections will generally describe implementation of specific apparatus and methods relating to high-altitude delivery and recovery of multiple passengers and individual pilots between earth and the stratosphere. 
     In that regard,  FIG.  1    is a schematic diagram, depicting a preferred representative flight of stratospheric-visit vehicle  102 , according to a preferred embodiment of the present invention. Stratospheric-visit vehicle  102  (at least embodying herein wherein such payload system comprises a stratospheric-visit vehicle structured and arranged to go on the stratospheric visit) is preferably configured to transport multiple human passengers and crew members to the stratosphere, for example about 100,000 feet above the surface of the Earth, preferably using lighter-than-air propulsion. Lighter-than-air propulsion functions are preferably implemented by at least one balloon  104  that preferably is filled with at least one lighter-than-air gas, preferably helium. In a preferred flight, the crew and/or pilot preferably rise to a target altitude  138 , for example, above about 125,000 feet above the earth, and preferably remain there for a pre-determined duration. One preferred mission profile includes about a 90-minute ascent and flight duration of just over about two-hours (it is noted that longer flights are within the capability of the present system for science missions and special tours). 
     On descent, balloon  104  is released, and a pre-deployed parawing  108  is used to glide the vehicle to earth. Parawing  108  (at least embodying herein wherein the at least one payload launches with said lighter-than-air propulsion system and at least embodying herein wherein said parachute system comprises at least one parafoil) is preferably of a steerable design allowing a pilot to maneuver capsule  106  to a selected landing site. 
     After capsule  106  is released, balloon  104  is preferably deflated and brought to the ground to avoid it becoming an aviation hazard or falling into populated areas. This is preferably done with a ripping panel and line that are pulled when the payload is released. Additionally, balloon  104  is equipped with valve  142  at the top of the envelope that opens to release the helium gas. 
     Prior to launch, capsule  106  is preferably placed in a wheeled launch cradle  140  to enable towing of capsule  106  to the launch-site location. The wheeled launch cradle  140  also preferably enables translational and rotational movement of capsule  106  during release of balloon  104  at launch. Preferably, launch cradle  140  separates from capsule  106  and remains on the ground after liftoff. Additional details of Applicant&#39;s preferred launch procedures are presented in  FIG.  13 A through  13 E . 
       FIG.  2    shows a schematic diagram, illustrating a preferred stratospheric-visit vehicle  102 , according to preferred systems of  FIG.  1   .  FIG.  3    shows a schematic diagram, illustrating the preferred stratospheric-visit vehicle  102  of  FIG.  1   , in a descent and recovery configuration, according to a preferred embodiment of the present invention. 
     Preferably, stratospheric-visit vehicle  102  comprises capsule  106 , preferably a pressurized capsule, equipped with seating to serve multiple human passengers and crew, an Environmental Control and Life Support System (ECLSS) to maintain a habitable environment for the multiple humans during a multiple-hour stratospheric visit, and visual access (see, for example,  FIGS.  14 A and  14 B ) structured and arranged to provide the multiple humans with viewing of Earth. In addition, stratospheric-visit vehicle  102  preferably implements travel-control functions, communication functions, recovery functions, balloon-separator functions, landing functions, etc. 
     One preferred aspect of Applicant&#39;s near-space operation systems  100  is the ability of the recovery system to return the capsule/payload from extremely high altitude (above 70,000 ft) to the ground in a controlled fashion using parawing  108 . The need for a parafoil design capable of operating above a 50,000-foot altitude and capable of providing a precision return and gentle landing (rather than random dropped return and landing under a conventional round or semi-round parachute) was a driving factor for Applicant&#39;s development of the presently-disclosed recovery arrangements. 
     The preferred design of para wing  108  differs from conventional parafoil parachute technology in that Applicant&#39;s wing remains fixed in a “flight-ready” configuration at launch through flight and return to earth. Parawing  108  preferably does not require moving air to maintain an aerodynamic shape; rather, the preferred wing design utilizes a stiffening system to maintain parawing  108  in the preferred flight-ready configuration during the assent phase of a mission. This precludes the need for the system to withstand dynamic deployment forces and removes the uncertainty of deployment actuation, unfurling, and proper deployment control. Preferred stiffening systems utilize rigidizing members forming a geometry-controlling framework. Stiffening members may comprise adapted equivalents of one or more ribs, spars, struts, braces, etc. Preferred stiffening members may also utilize tension members to transfer force loads within parawing  108 . Alternately preferably, a stiffening frame composed of inflated cells is used. 
     Parawing  108  is preferably suspended from below the high-altitude balloon  104  and conformed to be fully deployed prior to release. The preferred use of a parawing  108  already deployed and in a near-flight configuration results in less of a “drop” feeling by the payload or passengers when released from balloon  104  (or other carrier). Furthermore, applicant&#39;s system allows for quick transition to controlled, directed flight. It is further noted that alternate preferred embodiments utilize an already descending balloon to further reduce the time from release to fully supported flight. 
     Parawing  108  preferably remains open, ready to glide capsule  106  to a safe landing at any time during the flight. This provides a significant safety feature if balloon  104  does not reach full altitude. In the unlikely event of a parawing failure, a drogue parachute and secondary parafoils are preferably deployed to provide backup recovery (see also  FIG.  12   ). 
       FIG.  4 A  shows a high-level organizational overview of stratospheric-visit system  100 , including preferred function-enabling subsystems, according to preferred embodiments of the present invention.  FIG.  4 B  shows a high-level organizational overview of stratospheric-visit system  100 , including preferred principal system functions, according to preferred embodiments of the present invention. 
     Stratospheric-visit System  100  is preferably enabled by implementation of a set of essential system functions, which are preferably implemented by the enabling subsystems outlined in system organization chart of  FIG.  4 A . Referring first to the organizational diagram of  FIG.  4 A , Stratospheric-visit System Architecture of Stratospheric-visit System  100  preferably comprises Stratospheric-flight Elements  300  and Ground Elements  302 , as shown. Preferably, Stratospheric-visit System  100  is further divided into Flight System  211  and Ground Support Equipment  212 , each with four system modules. Environmental-containment Module  201  preferably functions to enclose and contain a habitable environment around the human passengers, crew, and/or single pilot during a mission. Preferred implementations of the Environmental-containment Module  201  are generally mission specific and preferably include pressure-containment capsules  106  (see  FIG.  2   ), pressure suits  202  (see  FIG.  6   ), along with various components of an Environmental Control and Life Support System (ECLSS). 
     Equipment Module  208  preferably provides a mounting location for components from a variety of subsystems. The Flight Recovery module  203  preferably includes a parachute mounting structure or body harness, main parachute and reserve parachute. In the present disclosure, the term “parachute” or “chute” may be used to identify system parafoils, parawings, and other devices used to slow the motion of the payload through an atmosphere by creating drag. 
     Flight Recovery module  203  includes everything needed to get the pilot away from balloon  104  and safely back to the ground. The holding and release rigging preferably resides between the parachute container and the balloon(s). This connects the parachute harness (and the suit and pilot it is strapped to) to the balloon(s) and allows for the separation of the pilot from the balloon(s) at the appropriate time. 
     Flight Vehicle  205  preferably comprises the apparatus that lifts the payload to the target altitude and carries along with it supporting avionics  105 . As such, Flight Vehicle  205  interfaces with many aspects of stratospheric-visit system  100 . These interfaces preferably include atmospheric environment (physical/thermal), recovery systems (physical), ground infrastructure &amp; facilities (physical/procedural), ground crew (physical/data/procedural/visual), pilot (procedural/visual). Upon reading the teachings of this specification, those skilled in the art will now appreciate that, under appropriate circumstances, considering such issues as cost, operational parameters, etc., other interfaces, such as, for example, aircraft, air traffic control, the public, etc., may suffice. 
     Flight Vehicle  205  preferably interfaces the atmospheric environment in flight occurring in the Earth&#39;s atmosphere. Flight Vehicle  205  is in physical contact with the air, including buoyancy forces and wind. Flight Vehicle  205  preferably exchanges thermal energy through radiation exchange with the atmospheric environment, preferably through convection with surrounding air. 
     The ground crew works directly and in physical contact with Flight Vehicle  205  to prepare it for launch, during launch, and during recovery; this preferably includes working with balloon  104 , avionics  105 , rigging, attachments to pilot and the launch system equipment. Data preferably is sent to the ground crew via avionics  105 . Further, mission control preferably can send commands to Flight Vehicle  205  through avionics  105 . 
     For recovery, Flight Vehicle  205  is physically attached to pilot release mechanism  241  (see  FIG.  6 C ), which is in tum attached to the support harness that is strapped to the Pressure Suit-Equipment Module Assembly. This attachment provides the mechanism to release the suited pilot. 
     Flight Vehicle  205  preferably includes balloon  104  and all of its associated components, including dedicated avionics  105 . The other four modules remain on the ground. The balloon equipment module of Flight Vehicle  205  preferably supports flight avionics  105 , digital camera capture and transmission hardware, and mechanical and electrical interfaces to the Power, Avionics, Recovery, and Launch Balloon Subsystems. 
     Ground Support Equipment  212  preferably consists of all modules that remain on the ground during flight operations. Preferred modules of Ground Support Equipment  212  include Mobile Pre-flight Unit  213  including a Ground Cart  214 , Mission Control  216 , Balloon Launch Equipment  218 , and Ground Recovery  220 . Mission Control  216  preferably houses all of the equipment needed to track the mission and communicate with the crew and/or pilot. Ground Recovery  212  preferably includes a helicopter to pick up the crew and/or pilot and all equipment needed to recover and refurbish the parachute (parafoil/parawing) and balloon  104 . The Balloon Launch Equipment  218  preferably comprises all items needed to unfurl and inflate balloon  104  prior to launch. From an organizational standpoint, the Stratospheric-flight Elements  300  preferably comprise all of the system equipment that must be moved should a launch location change. 
     From a functional perspective, the Stratospheric-flight Elements  300  also consist of various subsystems. The Environmental Control and Life Support Subsystem (ECLSS) preferably provides thermal control, oxygen, pressurization and other functions to keep the crew and/or pilot alive and comfortable. The Launch Balloon Subsystem provides the preferred means for lifting the crew and/or pilot to a selected altitude. Environmental-containment Module  201  preferably isolates the crew and/or pilot from the outside environment. The Avionics subsystem preferably provides communication and tracking, receives and issues commands, and monitors sensors in other systems. 
     The Power subsystem preferably provides electrical power to all electrical components. The Recovery subsystem preferably includes the parachute harness, parachute, and reserve parachute, as well as all equipment necessary to recover the pilot, parachute, and balloon after landing. The Ground Elements preferably include all equipment and infrastructure to support the mission. This preferably includes cargo vans, helium trucks, storage facilities, helicopter pads, etc. 
     Referring now to the relational diagram of  FIG.  4 B , preferred system functions implemented within Stratospheric-visit System  100  preferably include payload functions  101 , launch functions  103 , environmental control functions  107 , travel control functions  109 , communication functions  111 , and recovery functions  113 , as shown. The above-noted functions of the system preferably interact to enable delivery of payloads to the stratosphere and implement a safe return to Earth. 
     Payload functions  101  at least preferably provide for the transport of at least one human. 
     Preferred payload functions  101  further comprise actions relating to implementing the transport of system hardware that travels with the crewmember(s), including, for example, parachute apparatus supporting recovery functions  113  (i.e., parafoils/parawings). This arrangement at least embodies herein a payload system structured and arranged to provide at least one payload including at least one human, and at least one parachute system. Upon reading this specification, those with ordinary skill in the art will now appreciate that, under appropriate circumstances, considering such issues as mission objectives, etc., other payload arrangements such as, for example, implementation of unmanned scientific packages, high-altitude communication systems, intelligence-gathering apparatus, etc., may suffice. 
     Launch functions  103  preferably include implementation of lighter-than-air propulsion functions  115 , tethering functions  117 , and un-tethering functions  119 , as shown. Lighter-than-air propulsion functions  115  are preferably enabled by balloon  104  (see  FIG.  2   ), which preferably functions to “lighter-than-air-propel” the payload from the ground to a target altitude (see also  FIG.  4    and  FIG.  5   ). Tethering functions  117  preferably include initial tethering of balloon  104  (at least embodying herein a lighter-than-air propulsion system structured and arranged to lighter-than-air-propel the at least one payload) to the ground, prior to launch (this arrangement at least embodying herein a tethering system structured and arranged to tether, initially to ground, said lighter-than-air propulsion system). Un-tethering functions  119  preferably include the action of un-tethering balloon  104  from the ground to initiate vehicle launch (see also  FIG.  2    and  FIG.  3   ) (at least embodying herein an un-tethering system structured and arranged to un-tether, from the ground, said lighter-than-air propulsion system). This arrangement at least embodies herein a launch system structured and arranged to launch the at least one payload. 
     Environmental control functions  107  preferably control, during the stratospheric visit, at least one human-life-support environment of the flight crew and/or pilot. Travel control functions  109  preferably control, during the stratospheric visit, travel of the payload. Communication functions  111  preferably include system operations associated with flight and ground communication within stratospheric-visit system  100 . 
     Recovery functions  113  preferably enable recovery of the flight crew and/or pilot. Recovery functions preferably comprise balloon-separator functions  121 , parachute-related functions  123 , and landing functions  125 , as shown. 
     Balloon-separator functions  121  preferably implement separation operations of at least the flight crew and/or pilot from balloon  104 , or separation from similar lighter-than-air apparatus functioning to implement such lighter-than-air propulsion functions  115 . Parachute-related functions  123  preferably provide air-resistance-assisted deceleration of at least the flight crew and/or pilot after separation of the flight crew and/or pilot from balloon  104 . Preferred system embodiments enabling such parachute-related functions  123  preferably include parafoils  108 . Alternately preferably, parachute-related functions  123  are implemented by non-standard parawing of semi-rigid design. Furthermore, preferred parachute functions  123 , such payload descent stabilization, are preferably implemented by at least one drogue parachute  130  (see  FIG.  9    and  FIG.  12   ). 
     Landing functions  125  preferably implement landing of the flight crew and/or pilot. Upon reading this specification, those with ordinary skill in the art will now appreciate that, under appropriate circumstances, considering such issues as design preference, mission objectives, traveler preferences, marketing preferences, cost, structural requirements, available materials, technological advances, etc., other system functions such as, for example, powered booster-propulsion functions, water-landing functions (i.e., flotation), robotic-payload functions, etc., may suffice. 
     In addition, stratospheric-visit system  100  comprises operation-specific functions  127  for the implementation of mission-specific functions. Mission-specific subsystems  127  of stratospheric-visit system  100  will be described in the following sections, as examples of preferred implementation of preferred system embodiments. 
     The following teachings are directed primarily to a single-pilot mission. Although a single-pilot mission is disclosed, it is noted that aspects of the system are applicable to a multi-passenger capsule apparatus and flight operations. In that regard,  FIG.  5    shows a schematic diagram, illustrating an alternate preferred flight of a single-pilot flight vehicle  205 , according to a preferred embodiment of the present invention. 
       FIG.  5    shows a diagrammatic depiction of a preferred example flight of a single-pilot flight vehicle  205 . During such flight, pilot preferably rises to target altitude  138  (generally above at least about 125,000 feet, more preferably at least about 135,000 feet above sea level) and maintains at target altitude  138  for a set duration. Pilot  204  then initiates a separation procedure to separate from balloon  104  allowing pilot  204  to freefall back toward earth (at least embodying herein wherein said payload support system is further structured and arranged to be separated, during launch of the at least one payload, from the at least one payload). A special drogue parachute  130  is preferably deployed at altitude  143  to stabilize and slow the descent velocity of pilot  204 . Pilot  204  preferably remains in controlled freefall until the main parachute  206  (preferably a parafoil) is deployed at altitude  144 . The pilot will then float down to earth to complete the flight. In one preferred return procedure, drogue parachute  130  is released shortly after release from balloon  104  and remains deployed during essentially the entire return phase. In such preferred return procedure, main parachute  206  is preferably deployed by pilot  204  at about 13,100 feet. 
       FIG.  6 A  through  FIG.  6 C  shows a series of diagrams, illustrating a preferred launch procedure for single-pilot flight vehicle  205 , according to preferred apparatus and methods of the present invention. Initially, the single-pilot flight vehicle  205  is preferably moored to launch platform  234  prior to launch. In this preferred arrangement, balloon  104  is preferably restrained to launch platform  234  using a tethering system  230  of Balloon Launch Equipment  218 , as shown. Tethering system  230  preferably comprises at least one lift-resisting ground restraint structured and arranged to resist upward lift imparted by balloon  104 . Tethering system  230  is preferably designed to tether balloon  104  to the ground, preferably using launch platform  234  as the mooring point. Tethering system  230  preferably includes Balloon Equipment Module (BEM  232 ), which preferably functions to link balloon  104  to launch platform  234 , and later to pilot  204  (at least embodying herein at least one balloon-to-restraint coupler structured and arranged to couple said lighter-than-air propulsion system to said at least one lift-resisting ground restraint). 
     Avionics  105  are preferably housed on the balloon equipment module (BEM  232 ) at the base of the balloon assembly. The BEM support structure is attached directly to the balloon base fitting and is the physical interface to the payload, the deployable avionics module, ballast, radar reflector, and a radiosonde. Avionics  105  preferably includes: a SkySite computer equipped with two data acquisition boards (DAB), a transponder, two SPOT GPS units, a battery pack, a video camera, transmitter and antennae. SkySite will be programmed to respond to ground signals to activate the ballast release, emergency payload release, and balloon destruct. Balloon destruct is preferably accomplished by dropping the avionics module from the support structure. The avionics module will be tied to a special gore on the balloon, which when dropped will tear out a hole in the gore. SkySite will automatically generate a time-delayed signal to sever the line to the tear-away gore and a second time-delayed signal to release the parachute. Pyrocutters preferably are used to activate mechanical releases. Digital cameras preferably will also be used to capture images/video. 
     SkySite is a flight tested computer system designed and built by Space Data Corp. that was designed to provide all avionics functions of sounding balloon flights for data collection including lift gas vent and ballast control. This system is preferably being used with some modifications to perform telemetry and control functions for Flight Vehicle  205  and ECLSS (Environmental Control and Life Support System). One SkySite system will be placed on flight vehicle  205 , a second will be placed on the equipment module that supports the life support systems. Each SkySite computer is integrated with a GPS receiver and transceiver. Along with GPS data, internal temperature, battery state and other information is relayed to the ground. The GPS data is presented on mapping software to show trajectory information including heading, ascent rate, etc. 
     SkySite&#39;s original configuration is in part designed to control a servomotor for lift gas venting. The servomotor will for Space Dive be used to indirectly control the crown valve. The servomotor will be used to toggle between one of three switches that can be used to either open or close the crown valve. 
     SkySite&#39;s original implementation of ballast dispersal is based on a servomotor-powered auger. It is alternately preferred that this servomotor will be replaced by a simple electronic relay that can power hot-wire cutters for ballast release. 
     Launch platform  234  preferably comprises a ballast member or ground mounting. The process of filling and standing balloon  104  as described above requires that the base of balloon  104  be tethered to the ground. As previously shown in  FIGS.  6 A- 6 C , the base of balloon  104  will be attached to the balloon equipment module (BEM  232 ) which is designed to be tethered to the ground via attachment points on each end of the BEM I-beam. Tethering directly to the ground was considered to have uncertainty in ground conditions, which would vary from site to site, and uncertainty in wind direction, which would require different ground anchor positions. As such, Launch platform  234  preferably comprises a heavy Launch Plate to serve as the ground anchor. The launch plate preferably will support the lift and drag forces of the balloon under all but the most extreme conditions. To guard against the latter, the launch plate will preferably be in tum tethered to a set of secondary restraints. 
     The Launch Plate preferably comprises a weld assembly, comprising a 1¼″ thick, 8′×12′ steel plate. The Launch Plate preferably comprises a weight of approximately 4900 lbs. The launch plate will require several anchor points. The Launch Plate preferably comprises six tie-down rings welded at locations of three along each edge about one foot from the edges and three feet apart. The launch tethers will attach to the steel Launch Plate via a pair of ratchet load binders. The launch plate will be fitted with welded anchor points to which the ratchet load binders will attach. 
     Anchor points separated by 10 ft (one one each edge of launch plate) appear to provide sufficient space below the balloon-supported BEM  232 . The four corner rings will preferably be oriented at an angle of 31 degrees with respect to the preferred 8 foot-edges. The welds of the middle two rings are to run parallel to the 8 ft edges. Aside from handling, the corner rings preferably are used to anchor the plate for additional anchoring reinforcement. The middle two rings are preferably designated for balloon tethering. 
     Preferably, balloon  104  is filled with lighter-than-air gas enabling the lighter-than-air propulsion functions  115  of the single-pilot flight vehicle  205 . When sufficient balloon buoyancy has been achieved, spool vehicle  236  gradually approaches launch platform  234  and releases balloon  104 , which preferably lifts BEM  232  into flight position, as shown in  FIG.  6 B .  FIG.  6 B , shows the single-pilot flight vehicle  205  in a preferred pre-launch configuration. Preferably, pilot  204  has been preconditioned for flight at Ground Cart  214 . Preferably, a payload ground-traversing system  238  is used to transport pilot  204  across the ground to launch platform  234  after decoupling from Ground Cart  214 . 
     Balloon  104  preferably comprises an envelope, preferably comprising polyethylene, preferably balloon grade linear low density polyethylene film, preferably ANTRIX (developed by Tada Institute of Fundamental Research (TIFR)). Preferred specifications for 70,000 foot, 90,000 foot, and 120,000 foot balloons are shown in Table 1, Table 2, and Table 3, respectively. 
     
       
         
           
               
               
               
               
               
             
               
                 TABLE 1 
               
               
                   
               
             
            
               
                 1) BALLOON 
                 A) MANUFACTURER 
                 B) MODEL 
                 C) SERIAL 
                 D) INCL. DATE OF 
               
               
                 INFORMATION 
                 TIFR BALLOON 
                 NO: T8K 
                 NO.: 2-5/00 
                 MFR: JUNE 2000 
               
               
                   
                 FACILITY 
                   
                   
                   
               
            
           
           
               
               
               
               
            
               
                 2) FILM 
                 A) MANUFACTURER 
                 B) NAME: SF372 
                 C) INCL DATE OF 
               
               
                 INFORMATION 
                 WINZEN INTL 
                   
                 MFR: APRIL/MAY 
               
               
                   
                   
                   
                 1993 
               
            
           
           
               
               
               
               
               
            
               
                 3) BALLOON 
                 A) TYPE NATURAL 
                 B) VOLUME, 
                 C) SIGMA: 
                 D) BALLOON WT.: 
               
               
                 DESIGN 
                 NATURAL SHAPE, 
                 Cu. m.,  
                 0.08 
                 232.0 Kg 
               
               
                   
                 TAPED, CAPPED 
                 7883 
                   
                   
               
               
                   
                 E) GORE WIDTHS 
                 F) INFLATED 
                 HEIGHT: 
                 24.9M 
               
               
                   
                 TOP: 8.0 Cm 
                 DIMENSIONS 
                 DIAMETER: 
                 26.3M. 
               
               
                   
                 MAX: 104 Cm 
                 NO. OF GORES: 81 
                   
                   
               
               
                   
                 BASE: 12.0 Cm 
                   
                   
                   
               
            
           
           
               
               
               
               
            
               
                   
                 G) NOMINAL LOAD: 
                 H) NOM. ALTITUDE 
                 I) RECOMMENDED  
               
               
                   
                 2600 Kg. 
                 10400M 
                 SUSPENDED WEIGHTS, KG. 
               
               
                   
                   
                   
                 Rec. Minimum: 2671 Kg. 
               
               
                   
                   
                   
                 Maximum: 1551 Kg 
               
            
           
           
               
               
               
               
               
               
            
               
                   
                   
                 SHELL 
                 CAP1 
                 CAP2 
                 CAP3 
               
               
                   
                 J) FILM GUAGE, 
                 20.3 
                 20.3 
                 20.3 
                 20.3 
               
               
                   
                 MICRONS 
                   
                   
                   
                   
               
               
                   
                 K) SURFACE AREA, 
                 1969 
                 1969 
                 1969 
                 1969 
               
               
                   
                 SQ. M. 
                   
                   
                   
                   
               
               
                   
                 L) LENGTH, M. 
                 39.5 
                 39.5 
                 39.5 
                 39.5 
               
               
                   
                 CAP 3 LOCATION: 
                 N: BALLOON WT, 
                 — 
                 O)  
                 P) NOM. LAUNCH 
               
               
                   
                 NA 
                 Kg: 232 
                   
                 BUBBLE 
                 MARK: 18.0M 
               
               
                   
                   
                   
                   
                 MARKS: 
                   
               
               
                   
                   
                   
                   
                 NIL 
                   
               
               
                 4) LOAD TAPES: 
                 A) TYPE: Laminated  
                 B) LOAD RATING: 
                 Total No. 
                   
                   
               
               
                   
                 Polyester 
                 227 Kgf B. 3 
                 81 
                   
                   
               
            
           
           
               
               
               
               
            
               
                 5) REEFING 
                 A) FILM GUAGE: 
                 B) GORE  
                 DISTANCE FROM APEX: 
               
               
                 SLEEVE 
                 TEAR PANEL: N/A 
                 SEAM NO.: 
                 N/A 
               
               
                   
                 SLEEVE: N/A 
                   
                   
               
            
           
           
               
               
               
               
               
            
               
                 6) INFLATION 
                 A) QUALITY: 2 Nos. 
                 B) DST. FROM 
                 C) ON GORES: 
                 F) DIAMETER 24.2 Cm. 
               
               
                 TUBES 
                   
                 APEX, M: 18.0 
                 2 &amp; 42 D) 
                   
               
               
                   
                   
                   
                 LENGTH,  
                   
               
               
                   
                   
                   
                 40.0M E) 
                   
               
               
                   
                   
                   
                 GUAGE: 76 
                   
               
               
                   
                   
                   
                 Milo. 
                   
               
               
                 7) VENTING  
                 A) QUANTITY: 3 Nos 
                 B) DIST. FROM  
                 C) TYPE: 
                 D) LENGTH, M: 13.5 
               
               
                 DUCTS. 
                   
                 BASE, M: 14 
                 WINDOW  
                   
               
               
                   
                   
                   
                 TYPE SIDE 
                   
               
               
                   
                   
                   
                 ESCAPE 
                   
               
               
                   
                   
                   
                 DUCT, TAGED 
                   
               
               
                   
                 E) GUAGE: 60 Microns 
                 F) AREA EACH: 
                 G) TOTAL 
                 H) LOCATED ON GORE 
               
               
                   
                   
                 2.9 Sq. M. 
                 AREA: 8.7 Sq M. 
                 SEAMS: 12, 13, 39, 40, &amp; 66, 67 
               
            
           
           
               
               
               
               
               
               
            
               
                 8) DESTRUCT 
                 A) RIP LINE RATING: 
                 B) BREAK LINE 
                 C) DISTANCE 
                 D) GORE 
                 E) CUTTER-N/A 
               
               
                 DEVICE: 
                 320 Kg TYPE:  
                 RATING: 8.0 Kg 
                 FROM APEX: 
                 NO: 6 
                   
               
               
                   
                 BRAIDED NYLON 
                   
                 4.48 M. 
                   
                   
               
            
           
           
               
               
               
               
            
               
                 9) VALVE  
                 A) WIRES: 6 Nos. 
                 DOUBLE BRAIDED 
                 C) LOCATED ON SEAM NO: 6 
               
               
                 CABLE 
                 GAUGE: 19 
                 B) SHEATH  
                   
               
               
                   
                   
                 GUAGE: 50 Microns 
                   
               
            
           
           
               
               
               
               
               
            
               
                 10) TOP  
                 A) TYPE: PLATE, 
                 B) NO. OF PORTS. 
                 C) DIAMETER: 68.5 Cm 
                 D) WEIGHT: 7.86 Kg 
               
               
                 FITTING: 
                 HOOP &amp; SEGMENTED 
                   
                   
                   
               
               
                   
                 CLAMP RING 
                   
                   
                   
               
               
                 11) BOTTOM 
                 A) TYPE: COLLAR &amp; 
                 B) LOAD ATTACH- 
                 C) DIAMETER: 152 Cm 
                 D) WEIGHT: 3.0 Kg. 
               
               
                 FITTING 
                 WEDGES 
                 MENT: ¾″ STUD  
                   
                   
               
               
                   
                   
                 WITH 16 TPI UNF, 
                   
                   
               
               
                   
                   
                 Available stud length 
                   
                   
               
               
                   
                   
                 for payload hooking 
                   
                   
               
               
                   
                   
                 30 mm 
                   
                   
               
            
           
           
               
               
               
               
            
               
                 12) PACKAGING 
                 1) WRAPPER: Pink 
                   
                 B) WEIGHT: 6.16 Kg. 
               
            
           
           
               
               
               
               
               
            
               
                 INFORMATION 
                 H) BOX: Weight  
                 A) DIMENSIONS: 
                 B) VOLUME: 
                 C) GROSS WEIGHT: 
               
               
                   
                 13.38 Kg. 
                 Cm. 123 × 123 × 130 
                 1968 Cu.M 
                 378.1 Kg 
               
            
           
           
               
               
            
               
                 13) OTHER 
                 PINK POLY STREAMER ATTACHED ON SEALS NO.: 2, 3, AND 42, 43  
               
               
                   
                 FROM INFLATION TUBES ATTACHMENT POINT TO BASE 
               
               
                   
               
            
           
         
       
     
     
       
         
           
               
             
               
                 TABLE 2 
               
               
                   
               
               
                 T.I.F.R BALLOON FACILITY 
               
               
                 HYDERABAD-500 062 
               
               
                 BALLOON SPECIFICATIONS FOR PARAGON SPACE DEVELOPMENT  
               
               
                 CORPORATION, USA 
               
               
                   
               
             
            
               
                   
               
            
           
           
               
               
               
               
               
            
               
                 1) BALLOON  
                 A) MANUFACTURER: 
                 B) MODEL NO.: 
                 C) SERIAL NO.: 
                 D) INCL. DATE OF 
               
               
                 INFORMATION 
                 TIFR BALLOON  
                 T22K 
                 4-8/12 
                 MFR: September 2012 
               
               
                 2) FILM  
                 A) MANUFACTURER: 
                 B) NAME: ANTRIX 
                   
                 C) INCL DATE OF 
               
               
                   
                 TIFR BALLOON 
                   
                   
                 MFR: February 2012 
               
               
                   
                 FACILITY  
                   
                   
                   
               
               
                 3) BALLOON 
                 A) TYPE NATURAL 
                 B) VOLUME. Cu.M, 
                 D) SIGMA: 0.20 
                 D) BALLOON WT.:  
               
               
                 DESIGN 
                 SHAPE, TAPED 
                 21.740 
                   
                 128 Kg 
               
               
                   
                 E) GORE WIDTHS: 
                 F) INFLATED  
                 HEIGHT: 
                 32.4M 
               
               
                   
                 TOP: 6.0 Cm 
                 DIMENSIONS: 
                 DIAMETER: 
                 37.4M. 
               
               
                   
                 MAX: 240 Cm 
                   
                 NO. OF CORES: 
                 49 
               
            
           
           
               
               
               
               
            
               
                   
                 G) NOMINAL LOAD: 
                 H) NOM. ALTTUDE: 
                 I) RECOMMENDED SUSPENDED  
               
               
                   
                 276 Kg. 
                 w/ H2, 28000 (w/He) 
                 WEIGHTS, KG.  
               
            
           
           
               
               
               
               
               
            
               
                   
                   
                 SHELL 
                 CAPI 
                 Rec. Minimum: 191 Kg.  
               
               
                   
                   
                   
                   
                 Maximum: 400 Kg 
               
            
           
           
               
               
               
               
               
               
            
               
                   
                   
                   
                   
                 CAP2 
                 CAP3 
               
               
                   
                 J) FILM GUAGE, 
                 20 
                 — 
                 — 
                 — 
               
               
                   
                 MICRONS 
                   
                   
                   
                   
               
               
                   
                 K) SURFACE AREA, 
                 3.832 
                 — 
                 — 
                 — 
               
               
                   
                 SQ. M. 
                   
                   
                   
                   
               
               
                   
                 L) LENGTH, M. 
                 54.1 
                 — 
                 — 
                 — 
               
               
                   
                 CAP 3 LOCATION: NA 
                 N:  
                 — 
                 O) BUBBLE 
                 P) NOM. LAUNCH 
               
               
                   
                   
                 BALLOON 
                   
                 MARKS: Every 1 
                 MARK: 16.2 M 
               
               
                   
                   
                 WT., Kg: 128 
                   
                 m From filling tube 
                   
               
               
                   
                   
                   
                   
                 to 24 m 
                   
               
               
                 4) LOAD TAPES: 
                 A) TYPE: Luminated 
                 B) LOAD  
                 Total 
                   
                   
               
               
                   
                 Polyester 
                 RATING: 91 
                 No. 49 
                   
                   
               
               
                   
                   
                 Kgf B. 3 
                   
                   
                   
               
            
           
           
               
               
               
               
            
               
                 5) REEFING 
                 A) FILM GAUGE: 
                 B) GORE SEAM NO.: 1 
                 DISTANCE 
               
               
                 SLEEVE 
                 TEAR PANEL: 6.0 
                   
                 FROM APEX: 18.0M 
               
               
                   
                 Microns SLEEVE: 50.0 
                   
                   
               
               
                   
                 Microns 
                   
                   
               
            
           
           
               
               
               
               
               
            
               
                 6) INFLATION 
                 A) QUANTITY: 
                 B) DIST. FROM 
                 C) ON GORES: 2 &amp; 
                 F) DIAMETER 
               
               
                 TUBES: 
                 2 Nbs. 
                 APEX, M: 7.0 
                 28  
                 24.2 Cm. 
               
               
                   
                   
                   
                 D) LENGTH 35.0M E) 
                   
               
               
                   
                   
                   
                 GUAGE: 75 Milo. 
                   
               
               
                 7) VENTING 
                 A) QUANTITY: 2 Nos. 
                 B) DIST. FROM BASE, 
                 C) TYPE: WINDOW SET 
                 D) LENGTH, M: 19.5 
               
               
                 DUCTS 
                   
                 M: 18 
                   
                   
               
               
                   
                 E) GUAGE: 20 Microns 
                 F) AREA EACH: 2.19 
                 G) TOTAL AREA: 
                 H) LOCATED ON 
               
               
                   
                   
                 Sq. M. 
                 4.38 Sq. M. 
                 GORE SEAMS: 12, 
               
               
                   
                   
                   
                   
                 13 &amp; 36, 37 
               
            
           
           
               
               
               
               
               
               
            
               
                 8) DESTRUCT 
                 A) RIP LINE RATING: 
                 B) BREAK LINE  
                 C) DISTANCE  
                 D) GORE NO.: 6 
                 E) CUTTER N/A 
               
               
                 DEVICE: 
                 320 Kg. TYPE:  
                 RATING: 1.0 Kg 
                 FROM APEX: 
                   
                   
               
               
                   
                   
                   
                 3.0M 
                   
                   
               
            
           
           
               
               
               
               
            
               
                 9) VALVE 
                 A) WIRES: 4 Nos. OF 
                 DOUBLE BRAIDED  
                 C) LOCATED ON SEAM NO.: REEFING SLEEVE 
               
               
                 CABLE 
                 67M LENGTH 
                 B) SHEATH GAUGE: 
                 SEAM 
               
               
                   
                 LABELED A, B, C, D 
                 28/0.26 MM,  
                   
               
               
                   
                 RESISTENCE: AB: 
                 ANNELED TINNED 
                   
               
               
                   
                 1.8Ω; CD 2.0Ω 
                 COPPER 
                   
               
            
           
           
               
               
               
               
               
            
               
                 10) TOP FITTING: 
                 A) TYPE: PLATE, 
                 B) NO. OF PORTS:  
                 C) DIAMETER: 68.0 Cm 
                 D) WEIGHT: 8.7 Kg 
               
               
                   
                 HOOP &amp; SECMENTED 
                 ONE 
                   
                   
               
               
                   
                 CLAMP RING  
                   
                   
                   
               
               
                 11) BOTTOM 
                 A) TYPE: COLLAR &amp; 
                 B) LOAD  
                 C) DIAMETER: 13.8 Cm. 
                 D) WEIGHT: 1.9 Kg. 
               
               
                   
                 WEDGES 
                 ATTACHMENT: ½″ 
                   
                   
               
               
                   
                   
                 STUD WITH 13 TPI 
                   
                   
               
               
                   
                   
                 UNC, Available stud  
                   
                   
               
               
                   
                   
                 length for payload  
                   
                   
               
               
                   
                   
                 hooking: 38 mm 
                   
                   
               
               
                 12) PACKAGING 
                 I) WRAPPER: Pink  
                 38 Micron Light Yellow 
                 B) WEIGHT: 7.6 Kg. 
                   
               
               
                 INFORMATION 
                 Polyethylene, 75 Microns 
                 Color wrapper from 
                   
                   
               
               
                   
                   
                 Apex to 19M end  
                   
                   
               
               
                   
                   
                 distinctly marked, 1.32 
                   
                   
               
               
                   
                   
                 KG. 
                   
                   
               
               
                   
                 H) BOX: Weight: 123 Kg. 
                 A) DIMENSIONS: Cm. 
                 B) VOLUME 1398 Cu.M 
                 C) GROSS WEIGHT: 259.7 Kg 
               
               
                   
                   
                 152.2 × 91 × 101 
                   
                   
               
            
           
           
               
               
            
               
                 13) OTHER 
                 * No radar Reflecting Yam in Load Tape.*Marks on Wrapper: 8M, 9M, 10M, . . . ,24M 
               
               
                   
                 *After inflation and before launch, initiate tear about 2M in the tear panel indicated by Red arrow strip. 
               
               
                   
                 *Inflution tubes fan folded and kept at attachment points (7.0M from top Apex) for depolyment. 
               
               
                   
               
            
           
         
       
     
     
       
         
           
               
             
               
                 TABLE 3 
               
               
                   
               
               
                 T.I.F.R BALLOON FACILITY  
               
               
                 HYDERABAD-500 062 
               
               
                 BALLOON SPECIFICATIONS FOR PARAGON SPACE 
               
               
                 DEVELOPMENT CORPORATION, USA 
               
               
                   
               
             
            
               
                   
               
            
           
           
               
               
               
               
               
            
               
                 1) BALLOON 
                 A) MANUFACTURER: 
                 B) MODEL 
                 C) SERIAL 
                 D) INCL. DATE 
               
               
                 INFORMATION 
                 TIFR BALLOON FACILITY 
                 NO.: T120K 
                 NO.: 1-1/11 
                 OF MFR: FEB &amp; 
               
               
                   
                   
                   
                   
                 MARCH 2011 
               
            
           
           
               
               
               
               
            
               
                 2) FILM  
                 A) MANUFACTURER: 
                 B) NAME: ANTRIX 
                 C) INCL DATE OF 
               
               
                 INFORMATION 
                 TIFR BALLOON 
                   
                 MFR: JANUARY 
               
               
                   
                 FACILITY 
                   
                 2010 
               
            
           
           
               
               
               
               
               
            
               
                 3) BALLOON 
                 A) TYPE NATURAL 
                 B) VOLUME 
                 D) SIGMA: 
                 D) BALLOON WT.: 
               
               
                 DESIGN 
                 SHAPE TAPED 
                 Cu.M., 116.838 
                 0.36 
                 378.8 Kg 
               
               
                   
                 E) GORE WIDTHS: 
                 F) INFLATED  
                   
                 HEIGHT: 52.5  
               
               
                   
                 TOP: 8.0 Cm 
                 M 
                   
                 DIAMETER: 66.8 
               
               
                   
                 MAX: 250.0 Cm 
                 DIMENSIONS: 
                   
                   
               
               
                   
                   
                 M. 
                 NO. OF GORES: 
                 84 
               
            
           
           
               
               
               
               
               
               
            
               
                   
                 G) NOMINAL LOAD:  
                 SHELL 
                 CAP1 
                 CAP2 
                 CAP3 
               
               
                   
                 275 Kg. 
                   
                   
                   
                   
               
               
                   
                 J) FILM GUAGE, MICRONS 
                 26 
                 N/A 
                 N/A 
                 20.3 
               
               
                   
                 K) SURFACE AREA, SQ. M. 
                 11789 
                 N/A 
                 N/A 
                 N/A 
               
               
                   
                 L) LENGTH, M. 
                 83.3 
                 N/A 
                 N/A 
                 N/A 
               
               
                   
                 CAP 3 LOCATION: NA 
                 N: 
                 — 
                 O) BUBBLE 
                 P) NOM. LAUNCH 
               
               
                   
                   
                 BALLOON 
                   
                 MARKS EVERY 
                 MARK: 18.0M 
               
               
                   
                   
                 WT., Kg.: 
                   
                 1M FROM 
                   
               
               
                   
                   
                 378.8 
                   
                 FILLING TUBE 
                   
               
               
                 4) LOAD  
                 A) TYPE: Laminated Polyester 
                 B) LOAD 
                 Total 
                   
                   
               
               
                 TAPES: 
                   
                 RATING: 
                 No. 84 
                   
                   
               
               
                   
                   
                 91 Kgf  
                   
                   
                   
               
               
                   
                   
                 B.3 
                   
                   
                   
               
            
           
           
               
               
               
               
            
               
                 5) REEFING  
                 A) FILM GAUGE: TEAR 
                 B) GORE SEAM NO.: 1 
                 DISTANCE FROM 
               
               
                 SLEEVE 
                 PANEL: 6 MICRONS 
                   
                 APEX: 23M 
               
               
                   
                 SLEEVE: 50 MICRONS 
                   
                   
               
            
           
           
               
               
               
               
               
            
               
                 6) INFLATION 
                 A) QTY: 2 Nos. 
                 B) DIST. FROM 
                 C)ON GORES: 2 &amp; 44 
                 F) DIAMETER 
               
               
                 TUBES: 
                   
                 APEX, M: 11.0 
                 D) LENGTH, 32.0M 
                 24.2 Cm. 
               
               
                   
                   
                   
                 E) GAUGE: 76 Milo. 
                   
               
               
                 7) VENTING  
                 A) QUANTITY: 2 Nos 
                 B) DIST. FROM 
                 C) TYPE: WINDOW 
                 D) LENGTH, M: 
               
               
                 DUCTS: 
                   
                 BASE, M: 31 
                 TYPE, TAGED 
                 32.5 
               
               
                   
                 E) GUAGE: 26 Microns 
                 F) AREA EACH: 
                 G) TOTAL AREA: 
                 H) LOCATED ON 
               
               
                   
                   
                 4.3 Sq. M. 
                 8.6 Sq. M. 
                 GORE SEAMS: 
               
               
                   
                   
                   
                   
                 23, 24 &amp; 85, 86 
               
            
           
           
               
               
               
               
               
               
            
               
                 8) DESTRUCT 
                 A) RIP LINE RATING:  
                 B) BREAK LINE 
                 C) DISTANCE 
                 D) GORE NO.: 6 
                 E) CUTTER: N/A 
               
               
                 DEVICE 
                 320 Kg 
                 RATING: 8.0 Kg. 
                 FROM APEX: 
                   
                   
               
               
                   
                 TYPE: BRAIDED NYLON 
                   
                 4.0M 
                   
                   
               
            
           
           
               
               
               
               
            
               
                 9) VALVE 
                 A) WIRES: 4 Nos. OF 115M 
                 DOUBLE BRAIDED  
                 C) LOCATED ON SEAM NO.: 1 
               
               
                 CABLE: 
                 LENGTH LABELED 
                 B) SHEATH GAUGE: 
                   
               
               
                   
                 A, B, C, D RESISTANCE: 
                 28/0.26 MM, ANNEALED 
                   
               
               
                   
                 AP: 3.8Ω CD: 4.0Ω 
                 TINNED COPPER 
                   
               
            
           
           
               
               
               
               
               
            
               
                 10) TOP 
                 A) TYPE: PLATE, HOOP &amp; 
                 B) NO. OF PORTS: ONE 
                 C) DIAMETER: 
                 D) WEIGHT: 
               
               
                   
                 SECMENTED CLAMP 
                   
                 68.5 Cm 
                 7.85 Kg. 
               
               
                   
                 RING 
                   
                   
                   
               
               
                 11) BOTTOM 
                 A) TYPE: COLLAR &amp;  
                 B) LOAD ATTACHMENT: 1/2″ 
                 C) DIAMETER 
                 D) WEIGHT: 1.9 Kg 
               
               
                   
                 WEDGES 
                 STUD WITH 13 TPI UNC,  
                 13.6 Cm 
                   
               
               
                   
                   
                 Available stud length for  
                   
                   
               
               
                   
                   
                 payload hooking: 27 mm 
                   
                   
               
               
                 12) PACKAGING 
                 I) WRAPPER: Pink Polyethylene, 
                 38 Micron Light Yellow Color 
                   
                 B) WEIGHT: 15.8 Kg 
               
               
                 INFORMATION 
                 75 Microns 
                 wrapper from Apex to 26M end 
                   
                   
               
               
                   
                   
                 distinctly marked, 1.83 KG. 
                   
                   
               
               
                   
                 H)BOX: Weight: 133.8 Kg. 
                 A) DIMENSIONS: Cm. 
                 B) VOLUME: 
                 C) GROSS WEIGHT: 
               
               
                   
                   
                 147.2 × 122 × 112 
                 2.01 Cu.M 
                 554.5 Kg 
               
            
           
           
               
               
            
               
                 13) OTHER 
                 * No Radar Reflecting yarn in Load Tape. * Marks on wrapper:  
               
               
                   
                 * After inflation and before launch, initiate tear about 2M in the tear panel indicated by Red arrow strip. 
               
               
                   
                 * Inflation tubes fan folded and kept at attachment point (11.0M from top Apex) for deployment. 
               
               
                   
                 * SET duets ends at 0.5 m from bottom apex. * Balloon top reinforced with 3″ Fixon tape up to 55 cms. 
               
               
                   
                 * Apex valve clamped at top and bottom fittings. 
               
               
                   
               
            
           
         
       
     
     Referring to  FIG.  6 C , with the balloon  104  standing, pilot  204  is preferably wheeled to a position directly underneath BEM  232  and attached to the BEM  232  using pilot release mechanism  241 , as shown (at least embodying herein at least one payload coupler structured and arranged to couple the at least one payload to such at least one balloon-to-restraint coupler). In addition to this physical connection, one or more electrical connection(s) are preferably made between the avionics module (AM) and the primary (remote) payload release pyrocutter. 
     Preferably, un-tethering functions  119  of launch system are implemented by releasing each tether securing BEM  232  to the ground, thus allowing single-pilot flight vehicle  205  to lift pilot  204  out of payload ground-traversing system  238  and upward toward target altitude  138 . Each tether will be secured to BEM  232  with an interfacing 3-ring release mechanism. The trigger line for each 3-ring release mechanism will be coupled together such that a single action (pull) will simultaneously disengage both 3-ring release mechanisms. This concept has been successfully tested by applicant. (at least embodying herein wherein said un-tethering system comprises at least one restraint-decoupling system structured and arranged to decouple said at least one balloon-to-restraint coupler from said at least one lift-resisting ground restraint, wherein the at least one payload, after decoupling said at least one balloon-to-restraint coupler from said at least one lift-resisting ground restraint, remains coupled to said lighter-than-air propulsion system by said at least one balloon-to-restraint coupler). 
     Upon release, under ideal conditions, balloon  104  pulls pilot  204  out of the launch sedan and both rise straight up. With a side wind, balloon  104  and payload will, after launch, have a tendency to rotate about the system&#39;s center of gravity until the crown of the balloon and the payload form a vector approximately parallel with that formed by gravity and drag. Payload ground-traversing system  238  is preferably designed to accommodate such translational and rotational motions. 
       FIG.  7    shows a front view of pilot  204  positioned within payload ground-traversing system  238 , according to a preferred embodiment of the present invention.  FIG.  8    shows side view of pilot  204  positioned within payload ground-traversing system  238 . Payload ground-traversing system  238  preferably comprises payload support system  240  configured to support, during launch, the human pilot  204 . Preferably, payload support system  240  comprises an injury-minimizing system  243  structured and arranged to minimize injury, during launch, to pilot  204  and their accompanying environmental control system equipment. Preferably, such injury-minimizing system  243  comprises at least one configuration that shape-conforms to pilot  204  and the accompanying ECLSS/Avionics hardware. Preferably, such injury-minimizing system  243  comprises at least one cushioning configured to cushion at least the pilot  204  and the accompanying ECLSS/Avionics hardware. 
     Preferably, payload support system  240  comprises a motion direction system structured and arranged permit pilot  204  to move in both rotational and translational directions. Such preferred motion direction system is enabled by wheels  242 . All wheels are preferably of swivel design to maximize the ground maneuverability of pilot  204  during liftoff. Upon reading this specification, those with ordinary skill in the art will now appreciate that, under appropriate circumstances, considering such issues as design preference, user preferences, marketing preferences, cost, structural requirements, available materials, technological advances, etc., other low-friction arrangements such as, for example, skids, low-friction plates, rollers, etc., may suffice. 
     The preferred single-pilot system architecture has pilot  204  “directly” attached to the balloon; that is, unlike the preferred embodiment of  FIG.  1   , pilot  204  is preferably protected inside of pressure suit  202  and will carry all needed equipment in an Equipment Module  208  that is preferably located adjacent the chest of pilot  204 . Equipment Module  208  preferably contains oxygen, communication equipment, electrical power and a heater and pump that will circulate warm water around the body of pilot  204 . 
     In the presently-disclosed single-pilot mode, the Stratospheric-flight Elements preferably comprise the collection of all modules that leave the ground: the Environmental-containment Module  201  (in this case pressure suit  202 ), Equipment Module  208 , Flight Recovery Module  203 , and Flight Vehicle  205 . 
     Flight Vehicle  205  preferably comprises balloon  104  and all other components that adapt balloon  104  to manned flight. This preferably includes rigging and valving as well as avionics that announce the location of the balloon per Federal Aviation Administration (FAA) regulations. Flight Vehicle avionics  105  are preferably housed on the balloon equipment module (BEM  232 ) at the base of the balloon assembly.  FIG.  6 C  shows BEM  232  secured to the base fitting of balloon  104 . 
     Environmental-containment Module  201  preferably consists of pressure suit  202  (at least embodying herein an environmental control system structured and arranged to control, during the stratospheric visit, at least one human-life-support environment of the at least one human), but also includes all ECLSS (Environmental Control and Life Support System) and avionics equipment inside of the suit. Preferred ECLSS components include a neck dam, regulators, relief valves and water supply, etc. Preferred avionics equipment include the microphone and headset that allow pilot  204  to communicate with the ground. 
     Equipment Module  208  consists of a frame that preferably serves as a mounting location for components of various subsystems. Preferred example subsystems include the ECLSS oxygen tanks and components of the thermal fluid loop such as the pump, cold plate, heater and oxygen heat exchanger. The avionics boxes preferably mount to the frame or the ECLSS cold plate. The batteries are also preferably attached to the frame. 
     The Flight Recovery Module  203  preferably consists of the parachute harness, parachute components and the separation mechanism. The harness is preferably placed on pressure suit  202 . In one preferred embodiment of the present system, Equipment Module  208  is attached to the front of the harness similar to a tandem skydiver. In this arrangement, the harness is preferably similar to a tandem sky-dive harness. The harness is also the component that preferably functions to directly connected pilot  204  to Flight Vehicle  205 . Alternately preferably, Equipment Module  208  is rigidly mounted to pressure suit  202 . 
     Ground Support Equipment  212  preferably consists of all modules that remain on the ground during flight operations. Preferred modules of Ground Support Equipment  212  include Ground Cart  214 , Mission Control  216 , Balloon Launch Equipment  218 , and Ground Recovery  220 . 
     Preferably, Ground Cart  214  provides oxygen, cooling, electrical power and communications for pilot  204  while the pre-breathe process is taking place. The Pilot is preferably disconnected from Ground Cart  214  approximately 15 minutes before launch. 
     Preferably, Mission Control  216  is where all data from the Flight System will be received, processed and interpreted. Preferably, multiple people monitor computers to evaluate the data from Flight System  222 . This is also where direct verbal communication with the pilot will preferably take place. Balloon Launch Equipment  218  preferably comprises apparatus needed to unfurl balloon  104 , inflate it, keep it moored to the ground, and initiate release. 
     Ground Recovery  220  preferably includes all items needed to find the pilot  204  after landing, take pilot  204  to a medical center and to recover and refurbish all parachute and balloon components. Equipment module  208  preferably includes the physical container that resides on the chest of pilot  204 , the structure that attaches that container to pilot  204  and any tubes or wires extending to interfaces on other systems. Equipment Module  208  preferably serves as the structural support for many of the components of the various subsystems of Flight System  211 . These subsystems preferably include Avionics, Power and ECLSS. The equipment is rather heavy, requiring significant structure. Preferred equipment is bulky and irregularly shaped; therefore, a neoprene cover  304  is preferably placed over the equipment held by Equipment Module  208  to improve the aerodynamic characteristics of the assembly. Additional “spacers” are preferably provided, as required, to further smooth the shape underneath the cover to prevent aerodynamic moment forces. 
     In one preferred embodiment of the present system, Equipment Module  208  is preferably attached to the Recovery System harness via multiple hooks and straps. The intention is for the Equipment Module to be supported by the harness during ascent and loiter rather than being suspended from the pilot (in other words, the pilot is not part of the load path). 
     A primary component of Equipment Module  208  is the frame. The frame is preferably constructed from 8020 extrusions which are cut to length and connected with standard fittings. Hooks are preferably attached to provide a mounting location to the harness of the Flight Recovery System  203 . There are three sections of the frame with pivots that allow the shape to be adjusted to fit pilot  204 . 
     The frame Is alternately preferably a hard-mounted design using structural pick-up points on the torso region of pressure suit  202 , as shown (at least embodying herein wherein such at least one equipment module comprises a torso-coupling system structured and arranged to couple said at least one equipment module to a torso of the at least one human). It is preferred that frame (at least embodying herein a torso-coupling system) fit closely about a front of the torso of pilot  204 . Because pressure suit  202  is composed of soft goods, the manufacturing process does not produce a known location of structural pick-up points, with relation to individual suit components when the suit is inflated. This drove the need for about a I-inch degree of adjustability in the up-down and forward-back translation modes. An adaptor plate was preferably implemented to allow for such large size adjustments in the main frame system (at least embodying herein wherein such rigid adapter comprises at least one size adjuster structured and arranged to adjust dimensions of such rigid adapter to the front of the torso of the at least one human prior to launch). The adaptor plate also allows for adjustment in the roll and pitch translation modes (with the pilot&#39;s chest being “forward”). 
     There are three systems that are contained partially or in total within the Pressure Suit Module, which preferably include pressure suit  202 , the ECLSS, and the avionics subsystem. The ECLSS of the pressure suit module preferably implements environmental control functions  107  to maintain the health of pilot  204  by supplying heating and cooling, providing oxygen and removing carbon dioxide, and maintaining a pressurized environment. An avionics system preferably monitors sensors and preferably provides uplink and downlink communications. Equipment Module  208  preferably houses a majority of the ELCSS components &amp; oxygen storage, avionics, and batteries for the mission. 
     The ECLSS Is preferably built on the heritage of the S1034 Pilot&#39;s Protective Assembly (PP A) and NASA&#39;s S1035 Advanced Crew Escape Suit (ACES). These ECLSS oxygen flow and pressure systems have similar features and in most cases similar components that are used in these heritage systems. The S1034 PP A oxygen system is described in DN OOPSTP PP A O2 System. The NASA ACES is described in some detail in USA009026, Crew Escape System 21002. 
     The ECLSS oxygen flow system preferably uses some of the same components (demand regulator and exhalation valves) as the S1034 PPA and S1035 ACES except that the ACES use a single demand regulator rather than a dual regulator. The ECLSS of stratospheric-visit system  100  is more like the ACES system in that it preferably incorporates a neck dam and a larger helmet volume rather than the face seal and smaller oral/nasal cavity of the S1034 PP A. Unlike ACES or PPA, the ECLSS of stratospheric-visit system  100  also includes a respiration mask to minimize the risk of fogging and encourage CO2 washout. To maintain pressure, the ECLSS pressure system preferably uses the same dual suit controller as used in both the PPA and ACES systems, and a pressure relief valve similar to the ACES system. 
     Ground Cart preferably provides oxygen, cooling, electrical power and communications while pilot  204  undergoes a preferred pre-breathe process to reduce nitrogen loading in body. The Ground Cart provides oxygen, cooling, electrical power and communications for the pilot while the pre-breathe process is taking place. The pilot is disconnected from the ground cart approximately 15 minutes before launch. 
     Prior to launch, pilot  204  must carry out a pre-breathe process. Because the absolute pressure inside of pressure suit  202  will be around 3.5 psi when at maximum mission altitude, any nitrogen in the pilot&#39;s blood stream will come out of solution and create gas bubbles. These bubbles can cause pain and even death. To prevent this, the pilot must breathe pure oxygen until the nitrogen is purged from his body. This means pilot  204  must don the pressure suit module to isolate himself from the ambient ground atmosphere. As a result, pilot  204  requires a supply of oxygen and requires heating and/or cooling via the liquid thermal garment and will need to communicate with the ground crew. 
     The preferred pre-breathe process lasts up to three hours and consumes a large amount of oxygen as well as electrical power. Cooling may be needed, but the preferred Flight System ECLSS is designed only to provide heating. Therefore, Ground Cart  214  is preferably designed to provide oxygen, cooling, power and communications without using the consumables intended for flight and adding complexity to Flight System  211 . 
     The preferred ECLSS is designed to allow connections into the oxygen lines. The oxygen is preferably supplied at 80 psi so that the 65 psi regulators of Flight System  211  do not open and expel oxygen from the flight tanks. Preferably, quick disconnect connections are provided in the water loop such that Ground Cart  214  can preferably provide water for cooling and/or warming. Electrical power is preferably supplied to run the avionics so that communication can take place and all systems can be checked on the ground prior to flight, again preserving the battery power of Flight System  211 . Mission Control preferably encompasses the hardware, software, and personnel involved in directing the execution of all flight procedures from flight planning through recovery. Preferred Mission Control personnel include a flight director, mission meteorologist, medical specialist, ECLSS specialist, recovery system specialist, avionics specialist and flight vehicle specialist. The flight director is preferably responsible for communication with ATC, launch director and with mobile (recovery) operations. Preferred procedures to be executed include, but are not limited to, weather forecasting, medical oversight, flight, ECLSS, recovery and launch hardware check and preparation, launch operations, system monitoring, and ground and air-based flight recovery. 
       FIG.  9    shows a preferred drogue parachute  130  of the single-pilot embodiments of stratospheric-visit system  100 .  FIG.  10    shows a diagrammatic rear view of a preferred stowed embodiment of drogue parachute  130  of  FIG.  9   .  FIG.  11    shows a diagrammatic rear view of another preferred stowed embodiment of drogue parachute  130  of  FIG.  9   . Flight Recovery Module  203  preferably includes deceleration components, preferably including drogue parachute  130  that preferably functions to stabilize pilot  204  during descent and pulls main parachute  206  from parachute container  210  (see  FIG.  9   ,  FIG.  10   , and  FIG.  11   ). Should there be a problem with main parachute  206 , a reserve parachute is automatically deployed. 
     Further, ground control preferably can activate any of the parachute systems should the pilot be unable. The parachute activation system preferably comprises a line restraining a spring that upon release pulls the parachute release cord. The system is preferably activated (by ground command) by a hotwire cutting the spring retaining line. The pull cords and restraint cords are all held by passing through holes in the top plate and then tying a knot to keep the cords from passing back through. The restrained spring load is ˜13 lbf and the actuation stroke is ˜3.0 inches, and it weighs about 0.3 lbs. 
     Referring to  FIG.  9    through  FIG.  11   , drogue parachute  130  is preferably deployed to both stabilize and slow the descent velocity of pilot  204 . Main parachute  206  is preferably deployed using the drogue to pull main parachute  206  from the rear-mounted parachute container  210 . After release from balloon  104 , pilot  204  preferably remains in a controlled freefall using drogue parachute  130  to both stabilize the pilot and limit the descent velocity. In developing drogue parachute  130 , Applicant considered the dynamics of the freefall at the transonic velocities experienced by pilot  204  during the descent. Applicant determined that implementation of a stabilization parachute is preferred during the descent; however, the preferred point of deployment was selected only after significant research and experimental testing. Several critical issues relating to drogue deployment were identified by Applicant; these include, how to mitigate the potential for the drogue wrapping around the pilot due to the low dynamic pressure environment occurring in the period immediately following the high-altitude balloon release (i.e., anywhere above about 60,000 feet), how to reliably deploy drogue parachute  130  beyond the payload&#39;s wake (burble) at transonic velocities, and how the subsequent high-pressure period of the descent potentially impacts mechanical parachutes. The result was the development of an unusual drogue configuration. 
     Drogue parachute  130  of parachute system  123  preferably comprises means for coupling drogue parachute  130  with the payload (in this case, pilot  204 ). In the present preferred embodiment such coupling is performed by parachute bridle line  226 . A key feature of parachute bridle line  226  is the preferred incorporation of at least one drogue stiffener  224  used to stiffen portions of parachute bridle line  226 . Drogue stiffener  224  preferably functions to provide a means for distance-separating drogue parachute  130  from pilot  204  (at least embodying herein wherein such coupling means comprises distance separating means for distance-separating of parachute system from the payload) and further provides a means for controlling compressive resistance of the stiffened parachute bridle line  226  to assist implementation of physical-distance separation of drogue parachute  130  from pilot  204  (at least embodying herein compressive-resistance control means for controlling compressive resistance of distance separating means to as sist the distance separation of such parachute system from the payload). This preferred arrangement prevents entanglement of drogue parachute  130  and preferably functions to push drogue parachute  130  beyond the wake (burble) at transonic velocities. 
     Preferably, drogue stiffener  224  functions to restrict the bridle from wrapping around a falling vehicle structure, payload structure, parachutist&#39;s body, etc. Applicant&#39;s preferred drogue parachute design is preferably configured to move in a relative manner with the vehicle structure/payload structure/parachutist as it spins or tumbles. This feature preferably prevents the drogue parachute from wrapping and tangling around the vehicle structure/payload structure/parachutist during high altitude freefall (at least embodying herein wherein said distance separating means comprises anti-tangling means for assisting prevention of tangling of said coupling means with the at least one payload). This is highly useful in that should a bridle line wrap around an adjacent structure, it could potentially disable the system preventing it from stabilizing the user and in an extreme situation even restrict the deployment of the main or reserve parachutes, which could result in a catastrophic and/or fatal malfunction. 
     Preferred drogue stiffeners  224  preferably comprise a carbon fiber slit cylinder having a length of about 10 feet, or alternately preferably, three carbon-fiber rods, having a diameter of about 0.125 inch, such rods located inside a Kevlar sleeve. In each embodiment, the stiffening member is long enough so that the drogue parachute will not touch pilot  204  when the parachute folds back. 
     Three preferred examples of applicant&#39;s supported drogue are as follows:
         A static embodiment where the stiffener is always deployed and is ejected upon release from the supporting structure. This requires an overhead structure to hold the stiff rod prior to deployment. Preferred rods are preferably tapered for a continuous moment resistance proportional to the length of the moment arm.   An ejecting style embodiment, which can be coiled to fit inside a parachute pack (see  FIG.  11   ). The coiled rod preferably comprises a diameter sufficiently small to fit inside of parachute container  210  (i.e., 12-inch diameter or smaller is preferred for a container supporting a single human parachutist) can be placed inside the pack under tension; and, when parachute container  210  is opened, the coil will spring straight keeping the parachute bag and drogue parachute a safe distance from the falling parachutist, even if they are spinning or tumbling. A preferred material for this type of rod is carbon fiber. Alternately preferably, spring steel or a variety of composites is also sufficient.   A telescoping style ejection system (see  FIG.  10   ) where the rod is a short set of nestled rods which telescope out when pulled, this could nestle down to a size where it could fit on or in parachute container  210 .       

     It is noted that Applicant&#39;s drogue stiffeners  224  are generally useful in broader parachuting activities where the recovery profile includes periods of zero-gravity freefall. This occurs, for example, during high-altitude return-to-earth operations or any high atmospheric free-fall procedure. 
       FIG.  12    shows a preferred drogue parachute  130  of a backup recovery system of the multi-passenger capsule  106  of  FIG.  1   . Referring to  FIG.  12    and with continued reference to  FIG.  1   , in the unlikely event of a failure of the primary parawing  108 , a drogue parachute  130  and secondary parafoils are preferably deployed to provide backup recovery. As in the single-pilot embodiment, drogue parachute  130  utilizes drogue stiffener  224  to restrict the bridle from wrapping around tumbling vehicle structures and preferably functions to assist drogue parachute  130  penetrate outward beyond the wake (burble) of the falling capsule  106  (at least embodying herein wherein said distance separating means comprises burble-confine penetrator means for assisting said parachute system to penetrate at least one burble confine during deployment of said parachute system). 
       FIG.  13 A  through  FIG.  13 E  show a series of diagrams, illustrating a preferred launch procedure for stratospheric-visit vehicle  102  of  FIG.  1   , according to preferred apparatus and methods of the present invention. Initially, balloon  104  is preferably restrained by spool vehicle  236  of Balloon Launch Equipment  218 , as shown, as shown. Balloon  104  is preferably coupled to parawing  108 , which is preferably pre-deployed and is resting near the ground, as shown. Parawing  108  is preferably coupled to capsule  106 , which is preferably resting in wheeled launch cradle  140 , as shown. A second hold down  320  is preferably located between parawing  108  and capsule  106 , as shown. The second hold down  320  may preferably comprise a fixed ballast member or may alternately preferably be designed to be movable relative to the ground during launch procedures. 
     Preferably, balloon  104  is filled with lighter-than-air gas enabling the lighter-than-air propulsion functions  115  of stratospheric-visit vehicle  102 . When sufficient balloon buoyancy has been achieved, spool vehicle  236  gradually approaches parawing  108 , as shown in  FIG.  13 B  and releases balloon  104 , which preferably lifts parawing  108  into flight position, as shown in  FIG.  13 C . Next, at least one or both of stratospheric-visit vehicle  102  and second hold down  320  move together as shown in  FIG.  13 C . Next, second hold down  320  is released, as shown in  FIG.  13 D , and stratospheric-visit vehicle  102  is preferably lifted away from wheeled launch cradle  140 , as shown in  FIG.  13 E . Upon reading this specification, those with ordinary skill in the art will now appreciate that, under appropriate circumstances, considering such issues as design preference, user preferences, marketing preferences, cost, structural requirements, available materials, technological advances, etc., other launch arrangements such as, for example, the use of additional launch vehicles, the use of manual and/or automated launch gantries, etc., may suffice. 
     Thus, in accordance with preferred embodiments of the present invention, there is provided, relating to stratospheric-visit system  100 , a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and deploying, prior to the step of launching, the parachute system. Also, it provides such a method wherein the parachute system comprises at least one parafoil system. 
     In addition, stratospheric-visit system  100  preferably provides such a method wherein the parachute system comprises at least one drogue system. In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and coupling the parachute system within the at least one payload; distance-separating the parachute system from the at least one payload; and controlling compressive resistance of the distance separation of the parachute system from the at least one payload; wherein controlling distance separation of such parachute system from the at least one payload is achieved. And, it provides such a stratospheric-visit method wherein the step of distance-separating comprises the step of assisting prevention of tangling of the parachute system with the at least one payload. 
     Further, stratospheric-visit system  100  preferably provides such a stratospheric-visit method wherein the step of distance-separating comprises the step of assisting the parachute system to penetrate at least one burble confine during deployment of the parachute system. In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and assisting traversing of at least the at least one human across the ground; supporting, during launch, at least the at least one human, wherein the step of supporting comprises the steps of minimizing injury, during launch, to at least the at least one human and at least one accompanying human life support environment, conforming support to at least the at least one human and the at least one accompanying human life support environment, cushioning at least the at least one human and the at least one accompanying human life support environment, and permitting movement in both rotational and translational directions. 
     Even further, stratospheric-visit system  100  preferably provides such a stratospheric-visit method further comprising the step of terminating the step of supporting, during launch of the at least one payload. In accordance with another preferred embodiment hereof, this invention provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of tethering comprises the steps of coupling the lighter-than-air propulsion system to at least one lift-resisting ground restraint with at least one balloon-to-restraint coupler; coupling the at least one payload to the at least one balloon-to-restraint coupler; wherein the step of un-tethering comprises the step of decoupling the at least one balloon-to-restraint coupler from the at least one lift-resisting ground restraint, wherein the at least one payload, after the step of decoupling the at least one balloon-to-restraint coupler from the at least one lift-resisting ground restraint, remains coupled to the lighter-than-air propulsion system, wherein the at least one payload launches with the lighter-than-air propulsion system. 
     In accordance with another preferred embodiment hereof, stratospheric-visit system  100  preferably provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and wherein the step of controlling at least one human life support environment comprises the steps of coupling at least one equipment controller to a torso of the at least one human, providing a rigid adapter to closely abut a front of the torso of the at least one human, adjusting dimensions of the rigid adapter to fit the front of the torso of the at least one human prior to launch, rigidly attaching a mount, to attach an oxygen supply, to the rigid adapter, and wherein the oxygen supply is positionable to be transported along the front torso of the at least one human. 
     In accordance with another preferred embodiment hereof, stratospheric-visit system  100  preferably provides a stratospheric-visit method, relating to a stratospheric visit using lighter-than-air travel, comprising the steps of: providing at least one payload comprising at least one human, and at least one parachute system; launching the at least one payload; wherein the step of launching comprises the steps of lighter-than-air-propelling the at least one payload with a lighter-than-air propulsion system, tethering, initially to ground, the lighter-than-air propulsion system, and un-tethering, from the ground, the lighter-than-air propulsion system; controlling, during the stratospheric visit, at least one human life support environment of the at least one human; controlling travel, in the stratospheric visit, of the at least one payload; communicating, during the stratospheric visit, with the at least one payload; and recovering the at least one human; wherein the step of recovering comprises the steps of performing separation of at least the at least one human from the lighter-than-air propulsion system, decelerating, with the at least one parachute system, at least the at least one human after the separation of at least the at least one human from the lighter-than-air propulsion system, and landing of at least the at least one human; and providing a stratospheric-visit vehicle to transport multiple humans on the stratospheric visit; wherein the step of providing the stratospheric-visit vehicle comprises the steps of providing seating to serve the multiple humans, providing the at least one human life support environment to serve the multiple humans during a multiple hour stratospheric visit, and providing visual access to serve the multiple humans with viewing of Earth. 
       FIG.  14 A  and  FIG.  14 B  show a preferred multi-passenger capsule according to a preferred embodiment of  FIG.  3   . When multiple persons utilize stratospheric-visit system  100 , stratospheric-visit vehicle  102  preferably comprises capsule  106 . Capsule  106  preferably permits at least one pilot to take additional passengers in a stratospheric visit. Capsule  106  preferably comprises a habitable environment for the multiple humans during a multiple-hour stratospheric visit. Capsule  106  preferably further comprises at least one view-port  410  to permit viewing the external environment while on stratospheric visit. Capsule  106  preferably further comprises at least one landing system, preferably comprising landing gear  420 . Capsule  106  preferably further comprises avionics and recovery subsystems similar to single-pilot mission. Capsule  106  preferably further comprises rigging couple points  430 , permitting coupling to said lighter-than-air propulsion system, preferably balloon  104 , and parawing  108 . 
     Although applicant has described applicant&#39;s preferred embodiments of this invention, it will be understood that the broadest scope of this invention includes modifications such as diverse shapes, sizes, and materials. Such scope is limited only by the below claims as read in connection with the above specification. Further, many other advantages of applicant&#39;s invention will be apparent to those skilled in the art from the above descriptions and the below claims.