Patent ID: 12195189

DETAILED DESCRIPTION OF THE BEST MODES AND PREFERRED EMBODIMENTS OF THE INVENTION

The present disclosure describes Applicant'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 system100. The initial section of the present disclosure will describe preferred aspects of near-space operations utilizing Applicant'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.1is a schematic diagram, depicting a preferred representative flight of stratospheric-visit vehicle102, according to a preferred embodiment of the present invention. Stratospheric-visit vehicle102(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 balloon104that 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 altitude138, 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, balloon104is released, and a pre-deployed parawing108is used to glide the vehicle to earth. Parawing108(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 capsule106to a selected landing site.

After capsule106is released, balloon104is 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, balloon104is equipped with valve142at the top of the envelope that opens to release the helium gas.

Prior to launch, capsule106is preferably placed in a wheeled launch cradle140to enable towing of capsule106to the launch-site location. The wheeled launch cradle140also preferably enables translational and rotational movement of capsule106during release of balloon104at launch. Preferably, launch cradle140separates from capsule106and remains on the ground after liftoff. Additional details of Applicant's preferred launch procedures are presented inFIG.13A through13E.

FIG.2shows a schematic diagram, illustrating a preferred stratospheric-visit vehicle102, according to preferred systems ofFIG.1.FIG.3shows a schematic diagram, illustrating the preferred stratospheric-visit vehicle102ofFIG.1, in a descent and recovery configuration, according to a preferred embodiment of the present invention.

Preferably, stratospheric-visit vehicle102comprises capsule106, 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.14A and14B) structured and arranged to provide the multiple humans with viewing of Earth. In addition, stratospheric-visit vehicle102preferably implements travel-control functions, communication functions, recovery functions, balloon-separator functions, landing functions, etc.

One preferred aspect of Applicant's near-space operation systems100is 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 parawing108. 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's development of the presently-disclosed recovery arrangements.

The preferred design of para wing108differs from conventional parafoil parachute technology in that Applicant's wing remains fixed in a “flight-ready” configuration at launch through flight and return to earth. Parawing108preferably does not require moving air to maintain an aerodynamic shape; rather, the preferred wing design utilizes a stiffening system to maintain parawing108in 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 parawing108. Alternately preferably, a stiffening frame composed of inflated cells is used.

Parawing108is preferably suspended from below the high-altitude balloon104and conformed to be fully deployed prior to release. The preferred use of a parawing108already deployed and in a near-flight configuration results in less of a “drop” feeling by the payload or passengers when released from balloon104(or other carrier). Furthermore, applicant'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.

Parawing108preferably remains open, ready to glide capsule106to a safe landing at any time during the flight. This provides a significant safety feature if balloon104does 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 alsoFIG.12).

FIG.4Ashows a high-level organizational overview of stratospheric-visit system100, including preferred function-enabling subsystems, according to preferred embodiments of the present invention.FIG.4Bshows a high-level organizational overview of stratospheric-visit system100, including preferred principal system functions, according to preferred embodiments of the present invention.

Stratospheric-visit System100is preferably enabled by implementation of a set of essential system functions, which are preferably implemented by the enabling subsystems outlined in system organization chart ofFIG.4A. Referring first to the organizational diagram ofFIG.4A, Stratospheric-visit System Architecture of Stratospheric-visit System100preferably comprises Stratospheric-flight Elements300and Ground Elements302, as shown. Preferably, Stratospheric-visit System100is further divided into Flight System211and Ground Support Equipment212, each with four system modules. Environmental-containment Module201preferably 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 Module201are generally mission specific and preferably include pressure-containment capsules106(seeFIG.2), pressure suits202(seeFIG.6), along with various components of an Environmental Control and Life Support System (ECLSS).

Equipment Module208preferably provides a mounting location for components from a variety of subsystems. The Flight Recovery module203preferably 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 module203includes everything needed to get the pilot away from balloon104and 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 Vehicle205preferably comprises the apparatus that lifts the payload to the target altitude and carries along with it supporting avionics105. As such, Flight Vehicle205interfaces with many aspects of stratospheric-visit system100. These interfaces preferably include atmospheric environment (physical/thermal), recovery systems (physical), ground infrastructure & 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 Vehicle205preferably interfaces the atmospheric environment in flight occurring in the Earth's atmosphere. Flight Vehicle205is in physical contact with the air, including buoyancy forces and wind. Flight Vehicle205preferably 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 Vehicle205to prepare it for launch, during launch, and during recovery; this preferably includes working with balloon104, avionics105, rigging, attachments to pilot and the launch system equipment. Data preferably is sent to the ground crew via avionics105. Further, mission control preferably can send commands to Flight Vehicle205through avionics105.

For recovery, Flight Vehicle205is physically attached to pilot release mechanism241(seeFIG.6C), which is in turn 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 Vehicle205preferably includes balloon104and all of its associated components, including dedicated avionics105. The other four modules remain on the ground. The balloon equipment module of Flight Vehicle205preferably supports flight avionics105, digital camera capture and transmission hardware, and mechanical and electrical interfaces to the Power, Avionics, Recovery, and Launch Balloon Subsystems.

Ground Support Equipment212preferably consists of all modules that remain on the ground during flight operations. Preferred modules of Ground Support Equipment212include Mobile Pre-flight Unit213including a Ground Cart214, Mission Control216, Balloon Launch Equipment218, and Ground Recovery220. Mission Control216preferably houses all of the equipment needed to track the mission and communicate with the crew and/or pilot. Ground Recovery212preferably includes a helicopter to pick up the crew and/or pilot and all equipment needed to recover and refurbish the parachute (parafoil/parawing) and balloon104. The Balloon Launch Equipment218preferably comprises all items needed to unfurl and inflate balloon104prior to launch. From an organizational standpoint, the Stratospheric-flight Elements300preferably comprise all of the system equipment that must be moved should a launch location change.

From a functional perspective, the Stratospheric-flight Elements300also 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 Module201preferably 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 ofFIG.4B, preferred system functions implemented within Stratospheric-visit System100preferably include payload functions101, launch functions103, environmental control functions107, travel control functions109, communication functions111, and recovery functions113, 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 functions101at least preferably provide for the transport of at least one human.

Preferred payload functions101further comprise actions relating to implementing the transport of system hardware that travels with the crewmember(s), including, for example, parachute apparatus supporting recovery functions113(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 functions103preferably include implementation of lighter-than-air propulsion functions115, tethering functions117, and un-tethering functions119, as shown. Lighter-than-air propulsion functions115are preferably enabled by balloon104(seeFIG.2), which preferably functions to “lighter-than-air-propel” the payload from the ground to a target altitude (see alsoFIG.4andFIG.5). Tethering functions117preferably include initial tethering of balloon104(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 functions119preferably include the action of un-tethering balloon104from the ground to initiate vehicle launch (see alsoFIG.2andFIG.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 functions107preferably control, during the stratospheric visit, at least one human-life-support environment of the flight crew and/or pilot. Travel control functions109preferably control, during the stratospheric visit, travel of the payload. Communication functions111preferably include system operations associated with flight and ground communication within stratospheric-visit system100.

Recovery functions113preferably enable recovery of the flight crew and/or pilot. Recovery functions preferably comprise balloon-separator functions121, parachute-related functions123, and landing functions125, as shown.

Balloon-separator functions121preferably implement separation operations of at least the flight crew and/or pilot from balloon104, or separation from similar lighter-than-air apparatus functioning to implement such lighter-than-air propulsion functions115. Parachute-related functions123preferably provide air-resistance-assisted deceleration of at least the flight crew and/or pilot after separation of the flight crew and/or pilot from balloon104. Preferred system embodiments enabling such parachute-related functions123preferably include parafoils108. Alternately preferably, parachute-related functions123are implemented by non-standard parawing of semi-rigid design. Furthermore, preferred parachute functions123, such payload descent stabilization, are preferably implemented by at least one drogue parachute130(seeFIG.9andFIG.12).

Landing functions125preferably 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 system100comprises operation-specific functions127for the implementation of mission-specific functions. Mission-specific subsystems127of stratospheric-visit system100will 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.5shows a schematic diagram, illustrating an alternate preferred flight of a single-pilot flight vehicle205, according to a preferred embodiment of the present invention.

FIG.5shows a diagrammatic depiction of a preferred example flight of a single-pilot flight vehicle205. During such flight, pilot preferably rises to target altitude138(generally above at least about 125,000 feet, more preferably at least about 135,000 feet above sea level) and maintains at target altitude138for a set duration. Pilot204then initiates a separation procedure to separate from balloon104allowing pilot204to 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 parachute130is preferably deployed at altitude143to stabilize and slow the descent velocity of pilot204. Pilot204preferably remains in controlled freefall until the main parachute206(preferably a parafoil) is deployed at altitude144. The pilot will then float down to earth to complete the flight. In one preferred return procedure, drogue parachute130is released shortly after release from balloon104and remains deployed during essentially the entire return phase. In such preferred return procedure, main parachute206is preferably deployed by pilot204at about 13,100 feet.

FIG.6AthroughFIG.6Cshows a series of diagrams, illustrating a preferred launch procedure for single-pilot flight vehicle205, according to preferred apparatus and methods of the present invention. Initially, the single-pilot flight vehicle205is preferably moored to launch platform234prior to launch. In this preferred arrangement, balloon104is preferably restrained to launch platform234using a tethering system230of Balloon Launch Equipment218, as shown. Tethering system230preferably comprises at least one lift-resisting ground restraint structured and arranged to resist upward lift imparted by balloon104. Tethering system230is preferably designed to tether balloon104to the ground, preferably using launch platform234as the mooring point. Tethering system230preferably includes Balloon Equipment Module (BEM232), which preferably functions to link balloon104to launch platform234, and later to pilot204(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).

Avionics105are preferably housed on the balloon equipment module (BEM232) 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. Avionics105preferably 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 Vehicle205and ECLSS (Environmental Control and Life Support System). One SkySite system will be placed on flight vehicle205, 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'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'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 platform234preferably comprises a ballast member or ground mounting. The process of filling and standing balloon104as described above requires that the base of balloon104be tethered to the ground. As previously shown inFIGS.6A-6C, the base of balloon104will be attached to the balloon equipment module (BEM232) 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 platform234preferably 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 turn 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 BEM232. 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, balloon104is filled with lighter-than-air gas enabling the lighter-than-air propulsion functions115of the single-pilot flight vehicle205. When sufficient balloon buoyancy has been achieved, spool vehicle236gradually approaches launch platform234and releases balloon104, which preferably lifts BEM232into flight position, as shown inFIG.6B.FIG.6B, shows the single-pilot flight vehicle205in a preferred pre-launch configuration. Preferably, pilot204has been preconditioned for flight at Ground Cart214. Preferably, a payload ground-traversing system238is used to transport pilot204across the ground to launch platform234after decoupling from Ground Cart214.

Balloon104preferably 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 11) BALLOONA) MANUFACTURER:B) MODELC) SERIALD) INCL. DATE OFINFORMATIONTIFR BALLOONNO: T8KNO.: 2-5/00MFR: JUNE 2000FACILITY2) FILMA) MANUFACTURER:B) NAME: SF372C) INCL DATE OFINFORMATIONWINZEN INTLMFR: APRIL/MAY19933) BALLOONA) TYPE NATURALB) VOLUME,C) SIGMA:D) BALLOON WT.:DESIGNSHAPE,Cu. M.,0.08232.0 KgTAPED, CAPPED7883E) GORE WIDTHSF) INFLATEDHEIGHT:24.9MTOP: 8.0 CmDIMENSIONSDIAMETER:26.3M.MAX: 104 CmNO. OF GORES: 81BASE: 12.0 CmG) NOMINAL LOAD:H) NOM. ALTITUDEI) RECOMMENDED2600 Kg.10400MSUSPENDED WEIGHTS, KG.Rec. Minimum: 2671 Kg.Maximum: 1551 KgSHELLCAP1CAP2CAP3J) FILM GUAGE,20.320.320.320.3MICRONSK) SURFACE AREA,1969196919691969SQ. M.L) LENGTH, M.39.539.539.539.5CAP 3 LOCATION:N: BALLOON WT.,—O)P) NOM. LAUNCHNAKg.: 232BUBBLEMARK: 18.0MMARKS:NIL4) LOAD TAPES:A) TYPE: LaminatedB) LOAD RATING:Total No.Polyester227 Kgf B. 3815) REEFINGA) FILM GUAGE:B) GOREDISTANCE FROM APEX:SLEEVETEAR PANEL: N/ASEAM NO.:N/ASLEEVE: N/AN/A6) INFLATIONA) QUALITY: 2 Nos.B) DST. FROMC) ON GORES:F) DIAMETER 24.2 Cm.TUBESAPEX, M: 18.02 & 42 D)LENGTH,40.0M E)GUAGE: 76Milo.7) VENTINGA) QUANTITY: 3 NosB) DIST. FROMC) TYPE:D) LENGTH, M: 13.5DUCTS:BASE, M: 14WINDOWTYPE SIDEESCAPEDUCT, TAGEDE) GUAGE: 60 MicronsF) AREA EACH:G) TOTALH) LOCATED ON GORE2.9 Sq. M.AREA: 8.7 Sq. M.SEAMS: 12, 13; 39, 40; & 66, 678) DESTRUCTA) RIP LINE RATING:B) BREAK LINEC) DISTANCED) GOREE) CUTTER: N/ADEVICE:320 Kg. TYPE:RATING: 8.0 Kg.FROM APEX:NO: 6BRAIDED NYLON4.48 M.9) VALVEA) WIRES: 6 Nos.DOUBLE BRAIDEDC) LOCATED ON SEAM NO: 6CABLEGAUGE: 19B) SHEATHGUAGE: 50 Microns10) TOPA) TYPE: PLATE,B) NO. OF PORTS:C) DIAMETER: 68.5 CmD) WEIGHT: 7.86 Kg.FITTING:HOOP & SEGMENTEDONECLAMP RING11) BOTTOMA) TYPE: COLLAR &B) LOAD ATTACH-C) DIAMETER: 152 Cm.D) WEIGHT: 3.0 Kg.FITTINGWEDGESMENT: ¾″ STUDWITH 16 TPI UNF,Available stud lengthfor payload hooking:30 mm12) PACKAGINGI) WRAPPER: PinkB) WEIGHT: 6.16 Kg.Polyethylene,75 MicronsINFORMATIONII) BOX: Weight:A) DIMENSIONS:B) VOLUME:C) GROSS WEIGHT:13.38 Kg.Cm. 123 × 123 × 1301968 Cu.M378.1 Kg13) OTHERPINK POLY STREAMER ATTACHED ON SEALS NO.: 2, 3, AND 42, 43FROM INFLATION TUBES ATTACHMENT POINT TO BASE

TABLE 2T.I.F.R BALLOON FACILITYHYDERABAD-500 062BALLOON SPECIFICATIONS FOR PARAGON SPACE DEVELOPMENTCORPORATION, USA1) BALLOONA) MANUFACTURER:B) MODEL NO.:C) SERIAL NO.:D) INCL. DATE OFINFORMATIONTIFR BALLOONT22K4-8/12MFR: September 2012FACILITY2) FILMA) MANUFACTURER:B) NAME: ANTRIXC) INCL DATE OFINFORMATIONTIFR BALLOONMFR: February 2012FACILITY3) BALLOONA) TYPE NATURALB) VOLUME. Cu.M,D) SIGMA: 0.20D) BALLOON WT.:DESIGNSHAPE, TAPED21.740128 KgE) GORE WIDTHS:F) INFLATEDHEIGHT:32.4MTOP: 6.0 CmDIMENSIONS:DIAMETER:37.4M.MAX: 240 CmNO. OF CORES:49BASE: 28.0 CmG) NOMINAL LOAD:H) NOM. ALTTUDE:I) RECOMMENDED SUSPENDED276 Kg.w/ H2, 28000 (w/He)WEIGHTS, KG.SHELLCAPIRec. Minimum: 191 Kg.Maximum: 400 KgCAP2CAP3J) FILM GUAGE,20———MICRONSK) SURFACE AREA,3.832———SQ. M.L) LENGTH, M.54.1———CAP 3 LOCATION: NAN:—O) BUBBLEP) NOM. LAUNCHBALLOONMARKS: Every 1MARK: 16.2 MWT., Kg: 128m From filling tubeto 24 m4) LOAD TAPES:A) TYPE: LuminatedB) LOADTotalPolyesterRATING: 91No. 49Kgf B. 35) REEFINGA) FILM GAUGE:B) GORE SEAM NO.: 1DISTANCESLEEVETEAR PANEL: 6.0FROM APEX: 18.0MMicrons SLEEVE: 50.0Microns6) INFLATIONA) QUANTITY:B) DIST. FROMC) ON GORES: 2 &F) DIAMETERTUBES:2 Nos.APEX, M: 7.02824.2 Cm.D) LENGTH, 35.0M E)GUAGE: 75 Milo.7) VENTINGA) QUANTITY: 2 Nos.B) DIST. FROM BASE,C) TYPE: WINDOW SETD) LENGTH, M: 19.5DUCTS:M: 18E) GUAGE: 20 MicronsF) AREA EACH: 2.19G) TOTAL AREA:H) LOCATED ONSq. M.4.38 Sq. M.GORE SEAMS: 12,13 & 36, 378) DESTRUCTA) RIP LINE RATING:B) BREAK LINEC) DISTANCED) GORE NO.: 6E) CUTTER: N/ADEVICE:320 Kg. TYPE:RATING: 1.0 Kg.FROM APEX:BRAIDED NYLON3.0M.9) VALVEA) WIRES: 4 Nos. OFDOUBLE BRAIDEDC) LOCATED ON SEAM NO.: REEFING SLEEVECABLE67M LENGTHB) SHEATH GAUGE:SEAMLABELED A, B, C, D28/0.26 MM,RESISTENCE: AB:ANNELED TINNED1.8Ω; CD 2.0ΩCOPPER10) TOP FITTING:A) TYPE: PLATE,B) NO. OF PORTS:C) DIAMETER: 68.0 CmD) WEIGHT: 8.7 Kg.HOOP & SECMENTEDONECLAMP RING11) BOTTOMA) TYPE: COLLAR &B) LOADC) DIAMETER: 13.8 Cm.D) WEIGHT: 1.9 Kg.FITTING:WEDGESATTACHMENT: ½″STUD WITH 13 TPIUNC, Available studlength for payloadhooking: 38 mm12) PACKAGINGI) WRAPPER: Pink38 Micron Light YellowB) WEIGHT: 7.6 Kg.INFORMATIONPolyethylene, 75 MicronsColor wrapper fromApex to 19M enddistinctly marked, 1.32KG.II) BOX: Weight: 123 Kg.A) DIMENSIONS: Cm.B) VOLUME: 1398 Cu.MC) GROSS WEIGHT: 259.7 Kg152.2 × 91 × 10113) 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 3T.I.F.R BALLOON FACILITYHYDERABAD-500 062BALLOON SPECIFICATIONS FOR PARAGON SPACEDEVELOPMENT CORPORATION, USA1) BALLOONA) MANUFACTURER:B) MODELC) SERIALD) INCL. DATEINFORMATIONTIFR BALLOON FACILITYNO.: T120KNO.: 1-1/11OF MFR: FEB &MARCH 20112) FILMA) MANUFACTURER:B) NAME: ANTRIXC) INCL DATE OFINFORMATIONTIFR BALLOONMFR: JANUARYFACILITY20103) BALLOONA) TYPE NATURALB) VOLUME,D) SIGMA:D) BALLOON WT.:DESIGNSHAPE, TAPEDCu.M., 116.8380.36378.8 KgE) GORE WIDTHS:F) INFLATEDHEIGHT: 52.5TOP: 8.0 CmMDIAMETER: 66.8MAX: 250.0 CmDIMENSIONS:BASE: 24.6 CmM.NO. OF GORES:84G) NOMINAL LOAD:H) NOM.1) RECOMMENDED SUSPENDED WEIGHTS, KG.275 Kg.ALTITUDE,Rec, Minimum: 2581 Kg. Maximum: 1551 Kg10400MSHELLCAP1CAP2CAP3J) FILM GUAGE, MICRONS26N/AN/A20.3K) SURFACE AREA, SQ. M.11789N/AN/AN/AL) LENGTH, M.83.3N/AN/AN/ACAP 3 LOCATION: NAN:—O) BUBBLEP) NOM. LAUNCHBALLOONMARKS EVERYMARK: 18.0MWT., Kg.:1M FROM378.8FILLING TUBE4) LOADA) TYPE: Laminated PolyesterB) LOADTotalTAPES:RATING:No. 8491 KgfB.35) REEFINGA) FILM GAUGE: TEARB) GORE SEAM NO.: 1DISTANCE FROMSLEEVEPANEL: 6 MICRONSAPEX: 23MSLEEVE: 50 MICRONS6) INFLATIONA) QTY: 2 Nos.B) DIST. FROMC)ON GORES: 2 & 44F) DIAMETERTUBES:APEX, M: 11.0D) LENGTH, 32.0M24.2 Cm.E) GAUGE: 76 Milo.7) VENTINGA) QUANTITY: 2 NosB) DIST. FROMC) TYPE: WINDOWD) LENGTH, M:DUCTS:BASE, M: 31TYPE, TAGED32.5E) GUAGE: 26 MicronsF) AREA EACH:G) TOTAL AREA:H) LOCATED ON4.3 Sq. M.8.6 Sq. M.GORE SEAMS:23, 24 & 85, 868) DESTRUCTA) RIP LINE RATING:B) BREAK LINEC) DISTANCED) GORE NO.: 6E) CUTTER: N/ADEVICE320 KgRATING: 8.0 Kg.FROM APEX:TYPE: BRAIDED NYLON4.0M.9) VALVEA) WIRES: 4 Nos. OF 115MDOUBLE BRAIDEDC) LOCATED ON SEAM NO.: 1CABLE:LENGTH LABELEDB) SHEATH GAUGE:A, B, C, D RESISTANCE:28/0.26 MM, ANNEALEDAP: 3.8Ω; CD: 4.0ΩTINNED COPPER10) TOPA) TYPE: PLATE, HOOP &B) NO. OF PORTS: ONEC) DIAMETER:D) WEIGHT:SECMENTED CLAMP68.5 Cm7.85 Kg.RING11) BOTTOMA) TYPE: COLLAR &B) LOAD ATTACHMENT: 1/2″C) DIAMETERD) WEIGHT: 1.9 Kg.FITTING:WEDGESSTUD WITH 13 TPI UNC,13.6 Cm.Available stud length forpayload hooking: 27 mm12) PACKAGINGI) WRAPPER: Pink Polyethylene,38 Micron Light Yellow ColorB) WEIGHT: 15.8 Kg.INFORMATION75 Micronswrapper from Apex to 26M enddistinctly marked, 1.83 KG.II)BOX: Weight: 133.8 Kg.A) DIMENSIONS: Cm.B) VOLUME:C) GROSS WEIGHT:147.2 × 122 × 1122.01 Cu.M554.5 Kg13) 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 toFIG.6C, with the balloon104standing, pilot204is preferably wheeled to a position directly underneath BEM232and attached to the BEM232using pilot release mechanism241, 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 functions119of launch system are implemented by releasing each tether securing BEM232to the ground, thus allowing single-pilot flight vehicle205to lift pilot204out of payload ground-traversing system238and upward toward target altitude138. Each tether will be secured to BEM232with 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, balloon104pulls pilot204out of the launch sedan and both rise straight up. With a side wind, balloon104and payload will, after launch, have a tendency to rotate about the system'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 system238is preferably designed to accommodate such translational and rotational motions.

FIG.7shows a front view of pilot204positioned within payload ground-traversing system238, according to a preferred embodiment of the present invention.FIG.8shows side view of pilot204positioned within payload ground-traversing system238. Payload ground-traversing system238preferably comprises payload support system240configured to support, during launch, the human pilot204. Preferably, payload support system240comprises an injury-minimizing system243structured and arranged to minimize injury, during launch, to pilot204and their accompanying environmental control system equipment. Preferably, such injury-minimizing system243comprises at least one configuration that shape-conforms to pilot204and the accompanying ECLSS/Avionics hardware. Preferably, such injury-minimizing system243comprises at least one cushioning configured to cushion at least the pilot204and the accompanying ECLSS/Avionics hardware.

Preferably, payload support system240comprises a motion direction system structured and arranged permit pilot204to move in both rotational and translational directions. Such preferred motion direction system is enabled by wheels242. All wheels are preferably of swivel design to maximize the ground maneuverability of pilot204during 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 pilot204“directly” attached to the balloon; that is, unlike the preferred embodiment ofFIG.1, pilot204is preferably protected inside of pressure suit202and will carry all needed equipment in an Equipment Module208that is preferably located adjacent the chest of pilot204. Equipment Module208preferably contains oxygen, communication equipment, electrical power and a heater and pump that will circulate warm water around the body of pilot204.

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 Module201(in this case pressure suit202), Equipment Module208, Flight Recovery Module203, and Flight Vehicle205.

Flight Vehicle205preferably comprises balloon104and all other components that adapt balloon104to 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 avionics105are preferably housed on the balloon equipment module (BEM232) at the base of the balloon assembly.FIG.6Cshows BEM232secured to the base fitting of balloon104.

Environmental-containment Module201preferably consists of pressure suit202(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 pilot204to communicate with the ground.

Equipment Module208consists 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 Module203preferably consists of the parachute harness, parachute components and the separation mechanism. The harness is preferably placed on pressure suit202. In one preferred embodiment of the present system, Equipment Module208is 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 pilot204to Flight Vehicle205. Alternately preferably, Equipment Module208is rigidly mounted to pressure suit202.

Ground Support Equipment212preferably consists of all modules that remain on the ground during flight operations. Preferred modules of Ground Support Equipment212include Ground Cart214, Mission Control216, Balloon Launch Equipment218, and Ground Recovery220.

Preferably, Ground Cart214provides oxygen, cooling, electrical power and communications for pilot204while the pre-breathe process is taking place. The Pilot is preferably disconnected from Ground Cart214approximately 15 minutes before launch.

Preferably, Mission Control216is where all data from the Flight System will be received, processed and interpreted. Preferably, multiple people monitor computers to evaluate the data from Flight System222. This is also where direct verbal communication with the pilot will preferably take place. Balloon Launch Equipment218preferably comprises apparatus needed to unfurl balloon104, inflate it, keep it moored to the ground, and initiate release.

Ground Recovery220preferably includes all items needed to find the pilot204after landing, take pilot204to a medical center and to recover and refurbish all parachute and balloon components. Equipment module208preferably includes the physical container that resides on the chest of pilot204, the structure that attaches that container to pilot204and any tubes or wires extending to interfaces on other systems. Equipment Module208preferably serves as the structural support for many of the components of the various subsystems of Flight System211. 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 cover304is preferably placed over the equipment held by Equipment Module208to 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 Module208is 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 Module208is 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 System203. There are three sections of the frame with pivots that allow the shape to be adjusted to fit pilot204.

The frame Is alternately preferably a hard-mounted design using structural pick-up points on the torso region of pressure suit202, 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 pilot204. Because pressure suit202is 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's chest being “forward”).

There are three systems that are contained partially or in total within the Pressure Suit Module, which preferably include pressure suit202, the ECLSS, and the avionics subsystem. The ECLSS of the pressure suit module preferably implements environmental control functions107to maintain the health of pilot204by 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 Module208preferably houses a majority of the ELCSS components & oxygen storage, avionics, and batteries for the mission.

The ECLSS Is preferably built on the heritage of the S1034 Pilot's Protective Assembly (PP A) and NASA'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 system100is 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 system100also 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 pilot204undergoes 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, pilot204must carry out a pre-breathe process. Because the absolute pressure inside of pressure suit202will be around 3.5 psi when at maximum mission altitude, any nitrogen in the pilot'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 pilot204must don the pressure suit module to isolate himself from the ambient ground atmosphere. As a result, pilot204requires 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 Cart214is preferably designed to provide oxygen, cooling, power and communications without using the consumables intended for flight and adding complexity to Flight System211.

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 System211do not open and expel oxygen from the flight tanks. Preferably, quick disconnect connections are provided in the water loop such that Ground Cart214can 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 System211. 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.9shows a preferred drogue parachute130of the single-pilot embodiments of stratospheric-visit system100.FIG.10shows a diagrammatic rear view of a preferred stowed embodiment of drogue parachute130ofFIG.9.FIG.11shows a diagrammatic rear view of another preferred stowed embodiment of drogue parachute130ofFIG.9. Flight Recovery Module203preferably includes deceleration components, preferably including drogue parachute130that preferably functions to stabilize pilot204during descent and pulls main parachute206from parachute container210(seeFIG.9,FIG.10, andFIG.11). Should there be a problem with main parachute206, 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 toFIG.9throughFIG.11, drogue parachute130is preferably deployed to both stabilize and slow the descent velocity of pilot204. Main parachute206is preferably deployed using the drogue to pull main parachute206from the rear-mounted parachute container210. After release from balloon104, pilot204preferably remains in a controlled freefall using drogue parachute130to both stabilize the pilot and limit the descent velocity. In developing drogue parachute130, Applicant considered the dynamics of the freefall at the transonic velocities experienced by pilot204during 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 parachute130beyond the payload'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 parachute130of parachute system123preferably comprises means for coupling drogue parachute130with the payload (in this case, pilot204). In the present preferred embodiment such coupling is performed by parachute bridle line226. A key feature of parachute bridle line226is the preferred incorporation of at least one drogue stiffener224used to stiffen portions of parachute bridle line226. Drogue stiffener224preferably functions to provide a means for distance-separating drogue parachute130from pilot204(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 line226to assist implementation of physical-distance separation of drogue parachute130from pilot204(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 parachute130and preferably functions to push drogue parachute130beyond the wake (burble) at transonic velocities.

Preferably, drogue stiffener224functions to restrict the bridle from wrapping around a falling vehicle structure, payload structure, parachutist's body, etc. Applicant'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 stiffeners224preferably 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 pilot204when the parachute folds back.

Three preferred examples of applicant'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 (seeFIG.11). The coiled rod preferably comprises a diameter sufficiently small to fit inside of parachute container210(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 container210is 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 (seeFIG.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 container210.

It is noted that Applicant's drogue stiffeners224are 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.12shows a preferred drogue parachute130of a backup recovery system of the multi-passenger capsule106ofFIG.1. Referring toFIG.12and with continued reference toFIG.1, in the unlikely event of a failure of the primary parawing108, a drogue parachute130and secondary parafoils are preferably deployed to provide backup recovery. As in the single-pilot embodiment, drogue parachute130utilizes drogue stiffener224to restrict the bridle from wrapping around tumbling vehicle structures and preferably functions to assist drogue parachute130penetrate outward beyond the wake (burble) of the falling capsule106(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.13AthroughFIG.13Eshow a series of diagrams, illustrating a preferred launch procedure for stratospheric-visit vehicle102ofFIG.1, according to preferred apparatus and methods of the present invention. Initially, balloon104is preferably restrained by spool vehicle236of Balloon Launch Equipment218, as shown, as shown. Balloon104is preferably coupled to parawing108, which is preferably pre-deployed and is resting near the ground, as shown. Parawing108is preferably coupled to capsule106, which is preferably resting in wheeled launch cradle140, as shown. A second hold down320is preferably located between parawing108and capsule106, as shown. The second hold down320may preferably comprise a fixed ballast member or may alternately preferably be designed to be movable relative to the ground during launch procedures.

Preferably, balloon104is filled with lighter-than-air gas enabling the lighter-than-air propulsion functions115of stratospheric-visit vehicle102. When sufficient balloon buoyancy has been achieved, spool vehicle236gradually approaches parawing108, as shown inFIG.13Band releases balloon104, which preferably lifts parawing108into flight position, as shown inFIG.13C. Next, at least one or both of stratospheric-visit vehicle102and second hold down320move together as shown inFIG.13C. Next, second hold down320is released, as shown inFIG.13D, and stratospheric-visit vehicle102is preferably lifted away from wheeled launch cradle140, as shown inFIG.13E. 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 system100, 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 system100preferably 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 system100preferably 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 system100preferably 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 system100preferably 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 system100preferably 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.14AandFIG.14Bshow a preferred multi-passenger capsule according to a preferred embodiment ofFIG.3. When multiple persons utilize stratospheric-visit system100, stratospheric-visit vehicle102preferably comprises capsule106. Capsule106preferably permits at least one pilot to take additional passengers in a stratospheric visit. Capsule106preferably comprises a habitable environment for the multiple humans during a multiple-hour stratospheric visit. Capsule106preferably further comprises at least one view-port410to permit viewing the external environment while on stratospheric visit. Capsule106preferably further comprises at least one landing system, preferably comprising landing gear420. Capsule106preferably further comprises avionics and recovery subsystems similar to single-pilot mission. Capsule106preferably further comprises rigging couple points430, permitting coupling to said lighter-than-air propulsion system, preferably balloon104, and parawing108.

Although applicant has described applicant'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's invention will be apparent to those skilled in the art from the above descriptions and the below claims.