Abstract:
The present invention relates to a parachute deploying apparatus, comprising: a) a manifold with which is releasably coupled a single vessel within which pressurized gas is generated; b) a gas generator which cooperates with said vessel; c) a plurality of hollow tubes which extend obliquely and upwardly from, and are in communication with, said manifold; and d) a plurality of projectiles, each of which formed with a rod that is receivable in a corresponding tube and to each of which is connected a cord that is also connected to a corresponding portion of an undeployed parachute, wherein the pressurized gas which is generated upon triggering of said gas generator is flowable through each of said tubes to propel said plurality of projectiles in different directions and to cause said parachute to become deployed.

Description:
FIELD OF THE INVENTION 
       [0001]    The present invention relates to the field of parachutes. More particularly, the invention relates to an apparatus and method for rapid deployment of a parachute. 
       BACKGROUND OF THE INVENTION 
       [0002]    The deployment of a parachute according to prior art methods involves several steps, including a triggering action initiated by an operator or a user which causes the parachute canopy to be longitudinally extracted from the compartment in which it is stored, and a passive inflation process characterized by an influx of ambient air into the canopy which causes the latter to expand until achieving the desired canopy diameter. The canopy expansion is generally resisted by structural tension of the canopy fabric and by inertia, taking on the order of at least 5 seconds until fully expanded. Such a delay corresponds to a significant drop of tens of meters. 
         [0003]    During an foreseen skyscraper related catastrophic event, such as an earthquake or a terroristic activity, people entrapped within the skyscraper generally do not have time enough to escape imminent danger by descending a stairwell to a plaza surrounding the building. 
         [0004]    The most expedient way of escaping danger during such events would be by jumping from an upper story floor while deploying a parachute to slower the rate of descent. It would be desirable to provide apparatus by which a parachute could be rapidly deployed. 
         [0005]    Some prior art apparatus is known for rapidly deploying a parachute, such as EP 336910, U.S. Pat. No. 4,257,568, U.S. Pat. No. 5,516,903, and CN 101767651. However, the time needed for fully deploying such prior art apparatus until the canopy is sufficiently inflated and expanded is excessive, precluding the use thereof for parachuting from a relatively low story of a building. Also, the prior art apparatus is either heavy, complicated to deploy or expensive, and is therefore not suitable for large scale use during a catastrophic event. 
         [0006]    It is an object of the present invention to provide an apparatus and method for deploying a parachute at a significantly more rapid rate than what is achievable by prior art methods. 
         [0007]    It is an additional object of the present invention to provide apparatus for rapidly and reliably deploying a parachute that is light, of simple construction, and inexpensive. 
         [0008]    Other objects and advantages of the invention will become apparent as the description proceeds. 
       SUMMARY OF THE INVENTION 
       [0009]    Broadly speaking, the present invention is directed to a method for deploying a parachute, whereby a triggering action is performed which causes a plurality of projectiles to be propelled in different directions for a predetermined distance and to thereby urge a parachute canopy to be expanded to a full extent, whereupon said canopy is inflated by ambient air. 
         [0010]    In one aspect, the plurality of projectiles are propelled by generating pressurized gas in a vessel in fluid communication with a manifold and allowing said generated gas to flow through said manifold to each of a plurality of hollow tubes which extend obliquely and upwardly from, and are in communication with, said manifold. 
         [0011]    The present invention is also directed to parachute deploying apparatus, comprising a manifold with which is releasably coupled a single vessel within which pressurized gas is generated, a gas generator which cooperates with said vessel; a plurality of hollow tubes which extend obliquely and upwardly from, and are in communication with, said manifold, and a plurality of projectiles, each of which formed with a rod that is receivable in a corresponding tube and to each of which is connected a cord that is also connected to a corresponding portion of an undeployed parachute, wherein the pressurized gas which is generated upon triggering of said gas generator is flowable through each of said tubes to propel said plurality of projectiles in different directions and to cause said parachute to become deployed. 
         [0012]    As referred to herein, directional terms such as “bottom”, “top” and “upper” are described with respect to a normal orientation of the apparatus whereby the tubes extend upwardly from the manifold; however, the invention is also operable when the manifold is disposed at any other desired orientation. 
         [0013]    The generated pressurized gas is dischargeable from an aperture formed in the vessel to an interior of the manifold and is flowable from said manifold interior through of each of the tubes simultaneously. Each of the projectiles is preferably propelled a predetermined distance by the pressurized gas. 
         [0014]    In one aspect, the vessel contains a solid propellant consisting of materials that normally do not chemically react with each other and a pyrotechnic device for initiating a reaction with said propellant. 
         [0015]    In one aspect, the vessel contains a compressed or liquid gas and the gas generator is a spring loaded puncturing mechanism for generating pressurized gas upon puncturing the vessel. 
         [0016]    In one aspect, the parachute is fully deployable within less than a second, e.g. within less than 0.3 sec, following a gas generator triggering event. By virtue of such a rapid parachute deploying operation, a user will be assured of being protected by the apparatus even when jumping from a low story of a building, for example 20 m above ground level. 
         [0017]    In one aspect, each of the projectiles is sealingly engageable with a corresponding tube. 
     
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         [0018]    In the drawings: 
           [0019]      FIG. 1  is a perspective cross sectional view of a portion of parachute deploying apparatus, according to one embodiment of the present invention; 
           [0020]      FIG. 2  is an exploded, perspective view of the parachute deploying apparatus of  FIG. 1 ; 
           [0021]      FIG. 3  is a vertical cross sectional view of a portion of the parachute deploying apparatus of  FIG. 1 , showing vessel comprising a gas generator coupled therewith; 
           [0022]      FIG. 4  is a schematic illustration of a parachute deploying event involving the vessel of  FIG. 3 ; 
           [0023]      FIG. 5  is a method for deploying a parachute, according to one embodiment of the invention; 
           [0024]      FIG. 6  is a block diagram of safety apparatus including an undeployed parachute assembly and the apparatus of  FIG. 1 ; 
           [0025]      FIG. 7  is a schematic illustration of a parachute deploying event involving the safety apparatus of  FIG. 6 ; 
           [0026]      FIG. 8  is a perspective view of parachute deploying apparatus, according to another embodiment of the invention; 
           [0027]      FIG. 9  is a schematic, perspective view of the apparatus of  FIG. 8  when the spring housing is removed, showing a vertically displaceable hammer for initiating a gas generation event; 
           [0028]      FIG. 10  is a side view of the apparatus of  FIG. 8  when the hammer and manifold tubes are removed, showing the striking pin in a vertically displaced position; 
           [0029]      FIG. 11  is a perspective view from the top of the apparatus of  FIG. 8  when the manifold and spring housing are removed, showing the hammer in a restrained position; 
           [0030]      FIG. 12  is a perspective view of the apparatus of  FIG. 8  when the manifold is removed, showing a disengaging unit for initiating rotation of a rotatable element; and 
           [0031]      FIG. 13  is a perspective view of a chamber within which the apparatus of  FIG. 8  is positioned and an undeployed parachute canopy is stored. 
       
    
    
     DETAILED DESCRIPTION OF PREFERRED EMBODIMENTS 
       [0032]    The present invention provides novel apparatus comprising propellable projectiles for rapidly deploying a parachute within a time period significantly less than a second, and even as less as 0.3 sec, to ensure a life saving parachute deployment operation when located at a relatively low altitude such as 20 m above ground level. 
         [0033]      FIG. 1  illustrates apparatus  10 , according to one embodiment of the present invention. Apparatus  10  comprises a substantially vertically disposed manifold  3  from which obliquely and upwardly extend a plurality of hollow tubes  8 , e.g. three or four, in communication with the interior  4  of manifold  3  via a corresponding aperture  16  formed in the inner surface of the manifold. A rod  11  terminating with a larger surface projectile  13 , e.g. with an arrow-shaped or tear-shaped head, is inserted into a corresponding tube  8 . A draw cord is attached between each projectile  13  and a corresponding peripheral portion of the parachute canopy. These draw cords are in addition to the suspension lines that connect the canopy to the object to be parachuted, as well known to those skilled in the art. 
         [0034]    To prevent tearing, the canopy may be made of reinforced netting, for example Nylon 66 ripstop fabric The undeployed parachute canopy is folded on top of manifold  3 , and is retained in a chamber illustrated in  FIG. 13 . 
         [0035]    Manifold  3  may have a rectangular vertical cross section as shown, or may be configured in other ways as well. 
         [0036]    Tubes  8  are all oriented at the same angle, e.g. 30 degrees relative to a vertical plane, to ensure uniform opening of the parachute. An intermediate tube  14  of shorter length and oriented at a larger angle than the rod receiving tubes  8  may extend from manifold  3  to a corresponding tube  8 . 
         [0037]    As shown in the exploded version of apparatus  10  in  FIG. 2 , a single, small sized pressure vessel  47  constituting a micro gas generator (MGG) is threadedly engageable, by external threading  42  formed in a bottom region of cylinder  41  which defines the vessel, with internal threading formed within cylinder  24  integral with, and extending downwardly from, manifold  3 . Projectile  13  is shown to be integrally formed with a corresponding rod  11 . All components of apparatus  10  that are exposed to the generated gas, including manifold  3 , tubes  8 , rods  11  and projectiles  13  are made of heat resistant material. By employing a single MGG that efficiently deploys a parachute, the weight and therefore the cost of the apparatus are significantly reduced with respect to the prior art. 
         [0038]    As shown in  FIG. 3 , an aperture  49  is formed in an upper region of vessel  47 , e.g. in its circumferential wall, through which the generated gas is dischargeable into the interior of manifold  3 , when the vessel is fully received within the interior of the manifold, and then through the interior of each tube  8 , in order to cause the projectiles to be propelled a predetermined distance. 
         [0039]    Alternatively, pressure vessel  47  may be positioned on top of the manifold and the aperture through which the generated gas is dischargeable may be formed in a lower region of the vessel. 
         [0040]    Referring now to  FIG. 4 , vessel  47  contains a solid propellant  48  consisting of materials that normally do not chemically react with each other and a pyrotechnic device  51  for initiating a reaction with propellant  48 . 
         [0041]    The vessel  47  is of sufficiently small dimensions, e.g. having a diameter of 2 cm and a length of 7 cm, in order to be compactly retained in the manifold cylinder when not in use, yet is highly efficient in terms of its gas generating capability. A vessel  47  is replaceable upon conclusion of a parachute deployment operation. 
         [0042]    Pyrotechnic device  51  may be activated by an electrical current source  54  for heating a conductor of the device above the ignition temperature of a combustible material in contact therewith. Ignition of the combustible material initiates the MGG, causing a rapid chemical reaction involving propellant  48  that generates a large volume of pressurized gas G, e.g. nitrogen, within the manifold interior. The materials of propellant  48  and the current and voltage supplied by electrical current source  54  may be selected so as cause a highly exothermic reaction. 
         [0043]    In operation as illustrated in  FIG. 5 , a user desiring to deploy a parachute according to the teachings of the present invention triggers the MGG in step  31  by electrical or mechanical means well known to those skilled in the art, which need not be described for purposes of brevity. As a result of the triggering operation, the pyrotechnic device becomes activated in step  32 , causing the constituent components of the propellant to react and to generate energy intensive gas. The generated gas simultaneously flows through each tube extending from the manifold in step  33 , applying an explosive force onto a corresponding projectile. The explosive force is converted into momentum, and each projectile is therefore propelled in a different direction for a predetermined distance in step  34 . This distance, which is generally the sum of the length of the draw cord and the canopy radius, is reliably achieved by providing a sufficient dose of combustible material and a sufficient amount of activation current, to cause the parachute to be deployed in step  35  by being expanded to the desired canopy diameter. 
         [0044]    After being deployed, ambient air is received in the interior of the parachute, causing the latter to be retained in a buoyancy generating inflated condition. While the canopy is fully expanded, the projectiles remain attached thereto by a corresponding draw cord after having transferring their kinetic energy to the canopy to urge the latter to an expanded condition. The weight of each projectile, e.g. 23 gm, is negligible with respect to the buoyancy force generated by the parachute, and therefore will not significantly impact the buoyancy of the parachute. A parachuting operation is then commenced in step  36 . 
         [0045]    In one embodiment, the projectile head is sealed within the inclined tube. In this fashion, the gas pressure within the tube can be increased, to allow the projectile to be propelled a further distance. 
         [0046]    It will be appreciated that the various components that are exposed to the generated gas need not be made of heat resistant material when other types of gas such as carbon dioxide or nitrogen are employed. 
         [0047]    A parachute deployment operation may be initiated by a user who is entrapped within a skyscraper during a catastrophic event. As no other means of rescue is anticipated, the user mounts a harness to which is attached the apparatus of the present invention onto his upper torso. After the user jumps from an upper story, the MGG is triggered in midair while the projectiles are propelled behind, and rearwardly from, the user, allowing the parachute to be deployed within 0.3 sec following the triggering action due to the fast acting apparatus. This parachute deploying duration corresponds to a falling distance of only approximately 2 m. By virtue of the fast acting apparatus, a user will be assured of being protected even when jumping from a relatively low altitude such as 20 m above ground level, i.e. at a low story of a building. After descending to safety, the used vessel that generated the projectile propelling gas is replaced and the deployed parachute is folded, in anticipation of another parachute deployment operation, if necessary. 
         [0048]    It will be appreciated that a parachute deployment operation may be initiated in response to many other scenarios that require an object to be parachuted. 
         [0049]    Alternatively, the parachute deploying apparatus may be provided on light aviation aircraft, including an unmanned aerial vehicle (UAV) and Personal Aerial Vehicle (PAV), regardless of shape, construction material and geometry. 
         [0050]    In this embodiment, as schematically illustrated in  FIGS. 6 and 7 , safety apparatus  15  is retained within a chamber  17  attached to a support element  14  of the aircraft and has a detachable lid  18 . Safety apparatus  15  may comprise expandable parachute assembly  20  shown in a folded condition, parachute deploying apparatus  10  for instantly deploying parachute assembly  20 , e.g. made of Kevlar, upon demand, a wireless communication unit  27  for remotely controlling operation of the safety apparatus, and a rotor deactivation unit  29  synchronized with parachute deploying apparatus  10  for preventing damage to the parachute when being expanded. Lid  18  becomes detached from chamber  17  when the parachute becomes sufficiently expanded so as to apply a force onto the lid. 
         [0051]    An operator interacting with a remote flight controller may transmit a wireless duress indicating signal W to the transceiver of communication unit  27  upon detection that the UAV has been subjected to conditions of duress requiring deployment of the parachute. After receiving signal W, communication unit  27  transmits a deactivation signal D for operating rotor deactivation unit  29 , which is in electrical communication with a controller of the rotor drive means. Deactivation of the rotors will ensure that the expanding parachute will not become entangled with the rotating blades. Simultaneously with the transmission of signal D, or shortly thereafter, communication unit  27  transmits an initiation signal I to current source  54 , which in turn generates a suitable current C for activating pyrotechnic device  51 . Current C flows to the pyrotechnic device  51  of vessel  47  via contacts  61  extending from the bottom end of the vessel. Activation of pyrotechnic device  51  causes the constituent components of propellant  48  to react and to generate gas G, which is discharged into manifold  3  in order to propel the plurality of projectiles. 
         [0052]    The fully deployed parachute will be able to intercept moving aircraft fragments, if any, and to sufficiently slow the descent of the disabled aircraft so as to minimize damage of a collision involving the aircraft. 
         [0053]    The entire safety apparatus may weigh as little as 1-1.5 kg when the object to be parachuted is a human, or even less for lighter parachuted objects. For example, the safety apparatus may weigh 260 gm for a parachuted object weighing 3.5 kg or 450 gm for a parachuted object weighing 7 kg. 
         [0054]      FIGS. 8-13  illustrate another embodiment of the invention whereby the pressurized gas is generated by means of a spring loaded puncturing mechanism for generating pressurized gas, e.g. carbon dioxide, on demand upon puncturing a vessel containing compressed or liquid gas. 
         [0055]      FIG. 8  illustrates an assembled, ready to trigger parachute deploying apparatus  80 , which comprises manifold  83  having three inclined tubes  8  into each of which a corresponding arrow-headed projectile  13  is inserted, compressed gas vessel  87  releasably engaged with the top of manifold  83 , hollow spring housing  89  threadedly engageable with manifold  83  and in which is housed a spring and hammer for driving the puncturing mechanism, an outer tubular rotatable element  91  for encircling spring housing  89  and for selectively releasing a vertically displaceable hammer, and a bottom circular plate  95  positioned above larger circular plate  84  and below rotatable element  91  which is formed with a groove  96  for limiting angular displacement of element  91 . At the mouth  88  of vessel  87  is formed a pierceable metallic diphragm, generally near the threading of the vessel. 
         [0056]      FIG. 9  schematically illustrates apparatus  80  when the spring housing is removed, showing hammer  94  positioned internally to rotatable element  91  and which is vertically displaceable, on release of the spring force provided within the spring housing, at a sufficiently high speed to upwardly drive the bottom of pointed striking pin  81  so as to pierce the diaphragm and cause the liquid gas to change state in order to suitably propel the projectiles. Striking pin  81  is normally positioned within manifold  83  below the diaphragm of the gas generating vessel. 
         [0057]      FIG. 10  illustrates striking pin  81  after it has been upwardly driven. As shown, spring housing  89  is formed with two opposed vertical grooves  97  through each of which a corresponding arm of the hammer is able to pass. 
         [0058]      FIG. 11  illustrates the means for selectively releasing hammer  94 . Rotatable element  91  has two opposed restrainers  92  circumferentially extending a limited distance along its inner face  86 , adjacent to its rim  85 . After the spring within the spring housing is tensed by an external tensioning device, as well known to those skilled in the art, hammer  94  is positioned such that the two protrusions  99  terminating at the end of a corresponding arm  98  which radially extends from the main central portion of the hammer are below a corresponding restrainer  92  and prevented from moving. When rotatable element  91  is circumferentially shifted, protrusions  99  become unrestrained, allowing hammer  94  to be vertically displaced. 
         [0059]      FIG. 12  illustrates the disengaging unit, for initiating rotation of rotatable element  91  and the resulting forceful vertical displacement of the hammer. External spring  112  is attached at one end to bottom plate  84  and at the other end to rod  108  horizontally extending from rotatable element  91 , for example from block  111  attached to the outer wall of rotatable element  91 . After upper plate  95  is rotated to extend external spring  112 , vertically oriented pin  103  in releasable engagement with ring  107  ( FIG. 9 ) protruding outwardly from rotatable element  91  is inserted within an aperture formed in plate  95 , to secure rotatable element  91  while external spring  112  is tensed. Electrical motor  107 , e.g. a servomotor, rotatably drives cam  109 , when activated, to disengage pin  103  from plate  95  and to enable angular displacement of rotatable element  91  upon release of the spring force applied by external spring  112 . 
         [0060]      FIG. 13  illustrates circular chamber  122  in which the undeployed parachute is stored. Chamber  122  has a discontinuous wall, which is provided with a plurality of circumferentially spaced U-shaped portions  126  extending vertically along the entire height of chamber  122 . Manifold  83  is positioned within the interior of chamber  122 , internally to each of the U-shaped portions  126 . To facilitate positioning of each projectile rod  8  within the interior of a corresponding U-shaped portion  126  in preparation to be propelled, the internal wall of each U-shaped portion  126  facing manifold  83  may be formed with a bottom groove. Chamber is connected to the object to be parachuted. 
         [0061]    Alternatively, the puncturing mechanism is also operable when the compressed gas vessel is releasably engaged with the bottom of the manifold. 
       EXAMPLE 
       [0062]    The parachute deploying apparatus weighing 450 gm was carried by a multi-rotor UAV having a weight of 7 kg, a diameter of 1.10 m and a height of 0.5 m. The canopy was made of Nylon 66 ripstop fabric, and had a diameter of 1.75 m. Six suspension lines, each having a length of 1.6 m, were connected to the aircraft. Three draw cords, each having a length of 25 cm, were connected to a corresponding projectile configured with an arrow-shaped head. 
         [0063]    Three inclined tubes extended from the manifold. A projectile having a weight of 23 gm, and an arrow-shaped head connected to a rod having a length of 6 cm was inserted within a corresponding tube. Flexible polymeric material was applied to the tubes, providing sealing after insertion of the corresponding projectile therewithin. 
         [0064]    The single MGG that was threadedly engageable with the manifold was the Autoliv A7Zr2.1, IMI-Type 610258300, manufactured by Autoliv, Ogden, Utah. The MGG had a diameter of 1.5 cm and a length of 4 cm. The pyrotechnic device produced 8 liters of nitrogen. 
         [0065]    The projectiles were propelled a distance of 112.5 cm within a time period of 0.28 seconds after the trigger was initiated. 
         [0066]    While some embodiments of the invention have been described by way of illustration, it will be apparent that the invention can be carried out with many modifications, variations and adaptations, and with the use of numerous equivalents or alternative solutions that are within the scope of persons skilled in the art, without exceeding the scope of the claims.