Rigidized assisted opening system for high altitude parafoils

Information

  • Patent Grant
  • 10787268
  • Patent Number
    10,787,268
  • Date Filed
    Wednesday, March 9, 2016
    8 years ago
  • Date Issued
    Tuesday, September 29, 2020
    4 years ago
Abstract
A parafoil for operation at high altitudes, in low density air, or at low airspeeds, and methods for opening same. Some versions of the parafoil comprise flexible members connected to the parafoil canopy. When the parafoil canopy is in a stowed configuration, the members are deformed, storing elastic energy. When the canopy is released from its stowed configuration, the members spring back to their undeformed shapes, thereby opening or assisting with opening the canopy. The flexible member may also be attached to a base structure, which is attached to the payload. The members may comprise rods or hollow tubes that can be flexed using a fulcrum near the base structure, or a spacer plate, so that the ends connected to the canopy are restrained by a parachute bag containing the stowed or packed canopy. The parachute bag can be opened prior to or during detachment of the parafoil from the flight vehicle.
Description
BACKGROUND OF THE INVENTION

1. Field of the Invention (Technical Field)


The present invention relates to a system to mechanically assist with opening a parafoil. More specifically, the present invention is related to assisting in the opening of a parafoil transitioning from a state where it is not flying to a state where it is flying, especially when that system is starting with little to no airspeed, starting in low density air, or both. Mechanically aiding in the opening of a parachute allows parafoils to inflate and fly in environments where they otherwise may not have been capable of opening and transitioning to flight reliably. Avoiding entanglement is also important during the period of low air speeds, in low density air (such as at high altitudes), or both, where there is no force of wind to hold the parachute fabric away from the payload and from entangling with itself. Thus embodiments of the present invention preferably serve a dual purpose both as a mechanism to assist in the opening of the parafoil envelope and as an anti-entanglement device holding the fabric, lines and payload away from each other so they cannot snag or tangle.


2. Background Art


Note that the following discussion may refer to a number of publications and references. Discussion of such publications herein is given for more complete background of the scientific principles and is not to be construed as an admission that such publications are prior art for patentability determination purposes.


The word parafoil is, appropriately, the combination of the words “parachute” and “airfoil”. A parafoil is essentially an inflatable wing combining the light weight and packability of a parachute with the cross-range, steerability and landability of an airfoil. A parafoil is often referred to as a parachute or a ram air parachute, and may be referred to as such herein. Parafoils comprise a fabric canopy and parachute lines. Parafoils have a much more complex opening and inflation dynamic than round parachutes do. Because the wing is typically inflated from the leading edge the inflation process happens in multiple stages. This opening dynamic is problematic at high altitudes. Because the air at high altitudes is thin, and the inflation ports of the canopy do not necessarily face the airstream, there is substantial risk when using parafoils at high altitude that they will fail to inflate for too long a period. At this point, once the canopy orients and finally does inflate, the airspeeds may be too high and the opening could destroy the parafoil or whatever is beneath it.


SUMMARY OF THE INVENTION
Disclosure of the Invention

The present invention is a method of opening a parafoil comprising a canopy and a plurality of flexible members, the method comprising deforming the flexible members, thereby storing elastic potential energy in the flexible members, wherein a top end of each flexible member is connected to the parafoil canopy; securing the parafoil canopy and the deformed flexible members in a stowed configuration; attaching the parafoil to a flight vehicle; detaching the parafoil from the flight vehicle; releasing the parafoil canopy and the flexible members; and the flexible members returning to their undeformed shape, thereby at least partially deploying the parafoil canopy. The base end of each flexible member is preferably connected to a base member, optionally via a hinge, with the base member connected to a payload. The method optionally comprises one or more suspension lines, but not all suspension lines, supporting the weight of the payload during flight of the flight vehicle, the suspension lines connecting the base member and the canopy. The deforming step preferably comprises bringing the top ends of the flexible members together, the flexible members bending around a plate or fulcrum disposed between the top ends and the base ends. After the releasing step, the flexible members preferably spread apart from each other past a vertical orientation, at which point gravity preferably continues to spread apart the flexible members until the parafoil canopy is completely deployed. The deforming step preferably comprises folding the parafoil canopy and the securing step comprises disposing the folded parafoil canopy in a parachute bag. The detaching and releasing steps are optionally performed at an altitude greater than approximately 25,000 feet, or greater than approximately 50,000 feet. The releasing step is optionally performed before or approximately simultaneously with the detaching step.


The present invention is also a parafoil comprising a canopy; a base member connected to the canopy via a plurality of suspension lines; and a plurality of flexible members attached to the canopy. The flexible members are preferably attached to the base member, optionally via a hinge. The base member optionally comprises a fulcrum for bending each flexible member; alternatively, the parafoil comprises a plate disposed between the base member and the canopy for bending the flexible members. Each flexible member optionally comprises a hollow tube, in which case each flexible member optionally comprises a telescoping end attached to the canopy or a suspension line disposed within each flexible member.


Objects, advantages and novel features, and further scope of applicability of the present invention will be set forth in part in the detailed description to follow, taken in conjunction with the accompanying drawings, and in part will become apparent to those skilled in the art upon examination of the following, or may be learned by practice of the invention. The objects and advantages of the invention may be realized and attained by means of the instrumentalities and combinations particularly pointed out in the appended claims.





BRIEF DESCRIPTION OF THE DRAWINGS

The accompanying drawings, which are incorporated into and form a part of the specification, illustrate the practice of embodiments of the present invention and, together with the description, serve to explain the principles of the invention. The drawings are only for the purpose of illustrating certain embodiments of the invention and are not to be construed as limiting the invention. In the figures:



FIG. 1 is a diagram of a deployed parafoil according to a first embodiment of the present invention.



FIG. 2 is a diagram of the wing tip supports of parafoil of FIG. 1 in their stowed configuration.



FIG. 3 is a diagram showing deployed wing tip supports.



FIG. 4 is a diagram detailing the base structure of the parafoil of FIG. 1.



FIG. 5 details the hinge bracket attachment of the wing tip supports to the base structure.



FIG. 6 shows telescoping wing tip supports.



FIG. 7 is a perspective view of a deployed parafoil according to a second embodiment of the present invention.



FIG. 8 is a front view of the deployed parafoil of FIG. 7.



FIG. 9 shows suspension lines and wing tip support of the parafoil of FIG. 7 in their stowed configuration.



FIG. 10 is a detail of the base structure of the parafoil of FIG. 7.



FIG. 11 shows a deployed parafoil in accordance with a third embodiment of the present invention.



FIG. 12 shows rigidized and non-rigidized parachute suspension lines of the parafoil of FIG. 11 in their stowed configuration.



FIG. 13 shows the attachment structure at the top of the stowed configuration of the parafoil of FIG. 11.



FIG. 14 shows an embodiment of a parafoil of the present invention comprising inflatable bladders or beams.



FIG. 15 shows an embodiment of a parafoil of the present invention utilizing compressed gas to directly inflate the canopy.



FIG. 16 shows an embodiment of a parafoil of the present invention comprising thrusters to help deploy the canopy.



FIG. 17 shows an embodiment of a parafoil of the present invention comprising telescoping rods to help deploy the canopy.



FIG. 18 shows an embodiment of a parafoil of the present invention comprising deployable beams to help deploy the canopy.



FIG. 19 shows an embodiment of a parafoil of the present invention comprising a lattice of rigid members.



FIG. 20 shows the parafoil of FIG. 19 folded along its shortest dimension.



FIG. 21 shows the parafoil of FIG. 20 spiraled in the lengthwise dimension for stowage.



FIG. 22 is a detail of the connection of the wing tip supports to the parachute bag.





DETAILED DESCRIPTION OF EMBODIMENTS OF THE INVENTION

The present invention pertains to the assisting in the opening of a parafoil either during or prior to separating from a supporting structure while in low density air, starting with little air speed, or both. Embodiments of the present invention use stored energy to assist in the opening of a parafoil. Some embodiments of the present invention include spring loaded rods pushing open the parafoil envelope, hinged rods that use potential energy of their weight in a stowed configuration to open a parafoil, or rods that use a combination of stored potential energy and spring energy to open a parafoil envelope. Other embodiments of the present invention include utilizing inflatable bladders to spread the parafoil envelope, inflating the parafoil directly with compressors or compressed gas, using the weight of the mass suspended beneath the parafoil to force a mechanical arm to open the parafoil, using thruster mechanisms to push the envelope open, using springs to open the bottom of the parafoil envelope or using deployable split-tube booms to assist in the opening of the canopy. One embodiment of the present invention utilizes flexible rods connected to a base structure with hinges to assist in opening a parafoil. The rods can be flexed using a fulcrum near the base structure to a central point where they are preferably restrained at the base of the packed parafoil. When released the rods preferably spring out and fall away from the central structure, optionally assisted by gravity, opening the parafoil envelope prior to, during, or after the release of the parafoil from the supporting structure. This embodiment can be operated using flexed rods acting like springs, hinged rods assisted by gravity, or preferably, a combination of both.


An embodiment of the present invention utilizes hinged flexible poles connected to a rigid base both supporting the poles and providing an attachment platform between a payload and a mechanism to lift the payload, such as a high altitude balloon. This embodiment is particularly useful for use with payloads having a mass greater than approximately 2,000 lbs., although it may be used with any payload. As shown in FIG. 1, supporting base structure 102, also referred to as a “riser bracket”, provides the structural hub where the supporting vehicle, such as a high altitude balloon, connects to parafoil envelope 100. A detail of base structure 102 is shown in FIG. 4. The connection to the balloon is preferably made via a release mechanism such as release hook 111. Parachute lines 103 preferably attach using a mechanism such as attachment shackle 109. The base structure attaches to a payload via attachment shackle 119 and payload support lines (not shown). Main structural beam 116 for all the structures preferably comprises an I-beam or any appropriate structure depending on the mass of the payload and specific structural specifications of the system. The release mechanism could attach to a flight vehicle, such as a high altitude balloon via a tether running from the release mechanism through the parafoil 100 to the flight vehicle. Release hook 111 preferably attaches to main structural beam 116 via structural rods 110. Main structural beam 116 also preferably supports any other required equipment for operation of the parafoil, such as one or more control motors 118. The structural rods and release mechanism are preferably aligned using cross brace 117. The parafoil is preferably assisted in opening or is opened prior to release in an action referred to hereafter as “predeploy” by long flexible rods 101, also referred to as “wing tip supports”. Centrally located wing tip supports 112 preferably support the nose and tail of the canopy during predeploy. In this embodiment the wing tip supports preferably comprise hollow poles which are aluminum, carbon fiber, or a combination thereof. The poles may be of any size, but in one embodiment they are 2.5″ in diameter, with a 0.065″ wall thickness. The tops of the wing tip supports preferably comprise aluminum to accommodate sliding of the plunger, as described below in reference to FIG. 6. The bottoms of the wing tip supports preferably comprise carbon fiber due to its lighter weight and higher strength. However, any combination, or any material by itself, may be used.


Base 120 of each wing tip support is preferably fastened to main structural beam 116 via hinge bracket 114, a detail of which is shown in FIG. 5. The hinge bracket preferably attaches to the beam via bolts through mounting holes 123. The bracket may be angled to direct the wing tip support outward during the deployment process, which angle is preferably achieved via bend 124 in the bracket. The angle in the bracket preferably points the outside wing tip supports approximately towards the corners of the canopy when it is deployed. Angle 124 is preferably, but not limited to, approximately 20 degrees to achieve a substantially open canopy when deployed. Base 120 is preferably attached to the bracket via hinging mechanism 122 that allows it to rotate freely against the bracket. The initial angle of the wing tip support is preferably fixed by fulcrum 125 to a specific angle that will govern the spring load on the wing tip support when flexed. The angle will be determined by the size, geometry and material of the wing tip support as well as the configuration of the main structural beam and size of the parafoil. This angle is preferably, but not limited to, approximately 22 degrees.


The top of the wing tip support preferably comprises a pole that is allowed to translate along the axis of wing tip support in a linear fashion as shown in FIG. 6. The moveable part of the wing tip support is referred to hereafter as a “plunger”. Plunger 127 slides in and out of the wing tip support by fitting inside it via sliding interface 126. This sliding contact can be achieved using a linear bearing, a free-fit interface, or any other mechanism that allows the plunger to translate in and out with respect to the wing tip support. The plunger preferably attaches to the canopy at attachment eye 128 that is fixed with respect to plunger 127. This linear freedom allows the canopy to fly in its natural shape. The design shape of the canopy is typically not identical to the actual shape of the canopy in flight, so some variability in the position of the wing tip support ends is preferable.


The packed configuration of the parafoil can be seen in FIG. 2. When the parafoil canopy is packed the wing tip supports will be bent in around the fulcrum 125 to a central location at the tops 104 of the wing tip supports where they will be collected at the base of the parachute bag. Riser bracket 102 is where the hinge brackets are preferably located. Wing tip supports 101 are preferably flexed in and collected at the base of the parachute bag, similar to that shown in FIG. 9. The parachute bag, which is not shown in FIG. 2, is preferably just above the tops 104 of the wing tip supports, similar to the configuration shown in FIG. 22.


When the stowed system shown in FIG. 2 is ready to be deployed, a closure loop could be cut or otherwise opened, similar to the opening as described in the second embodiment below, releasing the wing tip supports to spring and fall open. After being opened the wing tip supports preferably spread out in a similar fashion to that shown in FIG. 3. Riser bracket 102 holds the bases of wing tip supports 101. The parachute (not shown in FIG. 3) is preferably connected to the wing tip supports, the weight of which will hold the parachute open. The geometry of the parachute in the open state is shown in FIG. 1. Riser bracket 102 holds parachute lines 103 and the bases of wing tip supports 101. Parafoil envelope 100 is stretched out via the wing tip supports.


In another embodiment of the invention, the parafoil is predeployed or otherwise assisted in opening using flexed rods on hinged bases, similar to the previous embodiment. In this embodiment of the invention the wing tip supports are held by retention cords while stowed, instead of flexed around a fulcrum. This embodiment of the invention is suitable for, but not limited to, payload masses between approximately 500 and 2000 lbs. In this embodiment of the invention payload 200 can be functionally recovered from a starting condition where the system has little starting airspeed or is in low density air.


The system starts in a packed configuration as shown in FIG. 9. Payload 200 is suspended from structural platform or riser bracket 206, preferably attached thereto via payload riser 207. The riser bracket is preferably suspended from the parachute deployment bag 215 using the set of parachute suspension lines 223 which are taut by virtue of their lengths during ascent. Suspension lines 223 are preferably attached to parachute deployment bag 215 via rings 202, which together preferably carry the structural suspension load of the system via structural strap 213 that preferably attaches the system to the balloon via connection device 214 (such as a structural shackle or carabiner).


A detailed view of the attachment of wing tip supports 216 to parachute deployment bag 215 is shown in FIG. 22. A parachute container comprises a tubular parachute deployment bag that preferably houses the parachute in a typical “Proper Ram-air Orientation” PRO pack. The base of the bag preferably comprises fabric flaps 1001, preferably comprising metallic grommets 1000, used to hold the bag closed. Eyes 1002 on the top of wing tip supports 216 (or alternatively connected to the wing tip support plungers if used) are held together via closure loop 1004, thereby maintain the wing tip supports under stress in their flexure configuration. Closure loop 1004 weaves through grommets 1000 and wing tip support eyes 1002, preferably making a closed loop. That loop preferably both holds the wing tip supports in their flexed configuration and also holds the bag closed so the canopy cannot fall out. When the system is ready to deploy, closure loop 1004 is severed or otherwise released, opening the bag so that the canopy is free to open and allowing wing tip supports 216 to spring open due to their stored energy of flexure. The canopy is preferably connected to eyes 1002 inside parachute deployment bag 215, and thus is predeployed or deployed as the wing tip supports spring open and the bag is opened.


The canopy is preferably connected to eyes 1002 inside parachute deployment bag 205, and thus is predeployed or deployed as the wing tip supports spring open and the bag is opened.


A detailed view of riser bracket 220 can be seen in FIG. 10. Payload risers 231 attach the payload to separable structural shackles 228. The structural shackles connect to the riser bracket via “Y bridles” 227 connected to one or more riser bracket beams 221 via structural shackles 226, which preferably equalize the front-to back load and ensure that offsets in payload center of gravity do not create control inputs to the parafoil. If the system were tethered to the ground prior to a flight it could be tethered via ground support straps 229. Riser bracket beams 221 preferably hold any required support hardware such as an Aerial Guidance Unit 210. The system can be suspended from a flight vehicle, such as a high altitude balloon, using a set of parachute suspension lines 223. The remaining parachute suspension lines 222 are slack during ascent and taut after the parafoil is deployed. Wing tip supports 216 are preferably tethered to riser bracket beam 221 using restraint cords 225, which restrict the wing tip supports from falling inwards towards the canopy when released. The restraint cord may alternatively be set such that the wing tip supports naturally sit with an outward angle and must be bent inwards during the parachute packing process, thereby creating outward spring energy when released. In this embodiment the wing tip supports comprise hollow aluminum 1″ diameter poles, although any material in any size may be used. The wing tip supports in this embodiment of the invention may employ plungers at the top of the wing tip supports, as described above, to more easily accommodate packing and a natural flight geometry.


Once flying the system is preferably suspended under the parafoil as shown in FIG. 7 and FIG. 8. Parafoil canopy 203 is preferably connected to riser bracket 206 via suspension lines 222, 223. Wing tip supports 216 are preferably not active at this time. The system is preferably controlled in flight by aerial guidance unit 210. The system may be coupled with a traditional reserve parachute 209 for added redundancy.


Rings 202 are for attaching the parafoil to the base of the balloon during ascent. This transfers the load due to the payload through suspension lines 223 to the flight vehicle, such as a high altitude balloon. For predeploy, the parachute deployment bag can be opened by severing a loop that holds both the bag closed and the wing tip supports under stress due to their bending, allowing the parachute to spring open before the release of rings 202 from the balloon. The parafoil is then released from the balloon by the release of rings 202. Alternatively, the parachute bag can be opened at approximately the same time as the release of rings 202 from the balloon.


Another embodiment of the invention that allows a system to begin flight under a parafoil in situations where the system has little air speed, is in low density air, or both. This embodiment of the invention is suitable for, but not limited to, payloads having a mass less than approximately 500 lbs. In this embodiment of the invention select parachute suspension lines are rigidized (but still flexible) and flexed around a spreading plate to provide opening force. This embodiment of the invention does not comprise hinges or wing tip supports because the rigidized suspension lines are responsible for spreading the canopy. FIG. 12 shows this embodiment of the invention in its packed form. Non-rigidized parachute suspension lines 311 and rigidized parachute suspension lines 310 connect to a payload via payload risers 312 which preferably converge to triangular structural mounting plate 313. The rigidized suspension lines are preferably under stress, flexed outward by spreading plate 314. This spreading plate can be restricted using short tethers rigged to triangular structural mounting plate 313 so the spreading plate isn't vertically displaced during stowage. In this embodiment rigidized suspension lines 310 each preferably comprises a suspension line passed through a rigid tube, such as a 0.375″ diameter hollow carbon fiber tube, having an inner diameter slightly larger than that of the suspension line. A select set of suspension lines is attached to the bottom of parachute deployment bag 309. The structural load path goes through parachute deployment bag 309 and through structural strap 308 to connecting device 307 (such as a threaded connector, shackle or carabiner).


A detail of the deployment bag and attachment structure at the top of the system is shown in FIG. 13. The load from the suspension lines is preferably carried through deployment bag 309 through straps sewn into the bag 320. The top of the bag connects to attachment strap 308, which preferably supports any equipment needed above the parachute system, such as an avionics box 322 and communication antenna 321 for actuating the release of the system. Above that hardware high side structural tether 316 preferably attaches to connection hardware 307 to connect the parachute system to a flight vehicle such as a high altitude balloon.


The system is preferably released using a remote signal which activates a release mechanism that opens a deployment bag 309. Once released the system will begin to fall and the tensioned, rigidized suspension lines 310 pull the parafoil open, assisting in the parafoil deployment. Shortly after releasing a combination of the airflow and the rigidized suspension lines will open parafoil canopy 300 to a state where it is flying, as shown in FIG. 11. Rigidized lines 310 preferably act as ordinary suspension lines from this point forward. Non-rigidized suspension lines 311 are preferably unaffected by this process. Spreader plate 314 is preferably configured such that the lines are oriented correctly in flight. Structural base assembly 304 connects the parafoil suspension lines to the payload during the descent in the same fashion as during ascent. Payload risers 312 connect the payload to the suspension lines. This system may be coupled with traditional reserve parachute 303 for additional redundancy.


In any of the previous embodiments, once the wing tip supports (or rigidized lines) spring open and outward past vertical, the force of gravity can assist with them continuing to spread apart until the parafoil canopy is completely deployed.


In a different embodiment of the invention, shown in FIG. 14, a series of inflatable bladders or beams 400 physically spread open parafoil canopy 401. The beams optionally inflate using compressed gas to a pressure sufficient to physically push the canopy fabric out to its fully extended width so that inflation in flight can happen very quickly and efficiently. The beams optionally utilize the existing parafoil cross-ports (holes in the structural and non-structural ribs of the parafoil) to allow the use of inflatable beams without significant modifications to the parafoil.


In another embodiment of the invention, shown in FIG. 15, compressed gas canisters 501, or alternatively a compressor, directly inflate canopy envelope 500. This process may optionally occur before, during or after the system's release from the balloon to establish the shape of the canopy before aerodynamic forces are high enough to cause the canopy to inflate by itself. Compressed air, for example, can be injected into the canopy interior providing the energy to push the canopy into an open state. Optional valved canopy inflation ports, such as fabric-flap type valves, may be used to allow flow into the cells but not out of them.


In yet another embodiment of the invention, shown in FIG. 16, thrusters 600 are used to spread the canopy open during or immediately after release. Cold gas thrusters, chemical thrusters or any device capable of creating a linear force could be used to push canopy 601 into a deployed state.


In another embodiment of the invention, shown in FIG. 17, telescoping rods 701 push canopy 700 into a deployed state. The telescoping rods can be deployed using internal bladders, by compressed gas acting directly on the interior surface of the telescoping rod, or by any type of mechanical spring or stored energy device. The telescoping rods are preferably nested while the canopy is not being used, allowing it to be small. When actuated the rods preferably create a continuous member spanning some or all of the canopy width.


In a different embodiment of the invention, shown in FIG. 18, a parachute system employs deployable beams to spread out the parafoil fabric before, during or immediately after separation from a flight vehicle. Parafoil 800 can be stowed when not in use. When needed, deployable beam mechanism 801 deploys, thereby causing the parafoil to deploy. The deployable beam preferably comprises split-tube technology to allow a stowed, small beam to erect into a long rigid boom. The deployable beam optionally utilizes smart materials that change shape from a stowed condition to a rigid beam configuration when electricity, heat or both are applied. The rigid beams hold the canopy fabric open while the parafoil begins flying.


In another embodiment of the invention, shown in FIGS. 19, 20, and 21, a framework of rigidly flexible members 901, 902 make a rigidized lattice inside the canopy to keep its shape while the system is in a condition where it has little airspeed, is in low density air or both. In this embodiment of the invention, flexible spanwise members 901 run spanwise from wingtip to wingtip of canopy 900, and rigidly flexible cross members 902 run cordwise from nose to tail of canopy 900. To stow the canopy it is preferably first folded across its shortest dimension, connecting the nose of the canopy to the tail, such that cross members 902 make a partial tube shape or loop as shown in FIG. 20, while the two spanwise members 901 meet up in parallel and are not yet bent. The final stage in stowing the canopy is twisting spanwise members 901 into a spiral, as shown in FIG. 21, with canopy 900 spiraled along with the rigidizers. This system may be held in the stowed configuration using a closure loop. When ready to deploy the closure loop would be cut or otherwise opened, allowing the rigidizers to spring the canopy into the final flight configuration. In this embodiment the flexible members preferably comprise 0.156″ diameter solid carbon fiber poles, although any material and size of pole, or hollow poles, may be used.


Although the invention has been described in detail with particular reference to the disclosed embodiments, other embodiments can achieve the same results. Variations and modifications of the present invention will be obvious to those skilled in the art and it is intended to cover all such modifications and equivalents. The entire disclosures of all patents and publications cited above are hereby incorporated by reference.

Claims
  • 1. A method of opening a parafoil comprising a canopy and a plurality of flexible members, the method comprising: deforming elongated portions of the flexible members, thereby storing elastic potential energy along the length of the elongated portions of the flexible members, wherein a top end of each flexible member is connected to the parafoil canopy;securing the parafoil canopy and the deformed flexible members in a stowed configuration;attaching the parafoil to a flight vehicle;detaching the parafoil from the flight vehicle;releasing the parafoil canopy and the flexible members from the stowed configuration; andreleasing the stored elastic potential energy stored along the length of the elongated portions of the flexible members to cause the flexible members to return to their undeformed shape, thereby at least partially deploying the parafoil canopy.
  • 2. The method of claim 1 wherein the deforming step comprises folding the parafoil canopy and the securing step comprises disposing the folded parafoil canopy in a parachute bag.
  • 3. The method of claim 1 wherein the detaching and releasing steps are performed at an altitude greater than 25,000 feet.
  • 4. The method of claim 3 wherein the detaching and releasing steps are performed at an altitude greater than 50,000 feet.
  • 5. The method of claim 1 wherein the releasing step is performed before the detaching step.
  • 6. The method of claim 1 wherein the releasing step is performed simultaneously with the detaching step.
  • 7. The method of claim 1 wherein deforming the flexible members comprises deforming elongated portions of the flexible members.
  • 8. The method of claim 1 wherein the flexible members comprise flexible rods.
  • 9. The method of claim 1, further comprising connecting a base end of each flexible member to a base member connected to a payload.
  • 10. The method of claim 9, wherein the connecting step comprises rotatably connecting the base end of each flexible member to the base member.
  • 11. The method of claim 9, the parafoil comprising one or more suspension lines, but not all suspension lines, supporting the weight of the payload during flight of the flight vehicle and before releasing the parafoil canopy from the stowed configuration, the suspension lines connecting the base member and the canopy.
  • 12. The method of claim 9 wherein the deforming step comprises bringing the top ends of the flexible members together, the flexible members bending around a plate or fulcrum disposed between the top ends and the base ends.
  • 13. The method of claim 12 further comprising: after the releasing step, initially spreading the flexible members apart from each other past a vertical orientation; andafter the initially spreading step, gravity continuing to spread apart the flexible members until the parafoil canopy is completely deployed.
CROSS-REFERENCE TO RELATED APPLICATIONS

This application claims priority to and the benefit of the filing of U.S. Provisional Patent Application Ser. No. 62/130,395, entitled “Rigidized Assisted Opening System For High Altitude Parafoils”, filed on Mar. 9, 2015 and U.S. Provisional Patent Application Ser. No. 62/239,154, entitled “Rigidized Assisted Opening System For High Altitude Parafoils”, filed on Oct. 8, 2015, and the specifications and claims thereof are incorporated herein by reference.

US Referenced Citations (296)
Number Name Date Kind
1012559 Kalaba Dec 1911 A
1056503 Cooper Mar 1913 A
1091895 Schaaf Mar 1914 A
1093311 Chaumeret Apr 1914 A
1108484 Banic Aug 1914 A
1178864 Loson Apr 1916 A
1277892 Evans Sep 1918 A
1299123 Calthrop Apr 1919 A
1303474 Hall May 1919 A
1308033 Benton Jul 1919 A
1314446 Webb, Sr. Aug 1919 A
1329359 Berg Feb 1920 A
1477338 Finley Dec 1923 A
1646586 Loth Oct 1927 A
1656780 Diago Jan 1928 A
1682509 Harwick Aug 1928 A
1705854 Coughlin Mar 1929 A
1826245 Hammerle Oct 1931 A
1829561 Knight Oct 1931 A
2008107 Norden Jul 1935 A
2083743 Poole Jun 1937 A
2708082 Moore et al. May 1955 A
2740598 Van Krevelen Apr 1956 A
2756948 Winzen et al. Jul 1956 A
2771256 Ryan Nov 1956 A
2865581 Froehlich Dec 1958 A
2929065 Kreinheder Mar 1960 A
2949263 Steinthal Aug 1960 A
2950881 Schwoebel Aug 1960 A
2954187 Winzen Sep 1960 A
2977069 Huch et al. Mar 1961 A
3015456 Deisinger Jan 1962 A
3045952 Underwood Jul 1962 A
3073040 Schueller Jan 1963 A
3087696 Sepp, Jr. Apr 1963 A
3093346 Faget et al. Jun 1963 A
3098630 Conners Jul 1963 A
3135163 Mechlin, Jr. et al. Jun 1964 A
3141640 Sutliff et al. Jul 1964 A
3142063 Goetzmann, Jr. Jul 1964 A
3146500 Volkert Sep 1964 A
3195834 Huch et al. Jul 1965 A
3260480 Ash et al. Jul 1966 A
3270908 Faget et al. Sep 1966 A
3312427 Yost Apr 1967 A
3424405 Struble, Jr. Jan 1969 A
3432122 Flickinger et al. Mar 1969 A
3434680 Ferguson Mar 1969 A
3446458 Rogallo May 1969 A
3465482 Chandler Sep 1969 A
3558083 Conley et al. Jan 1971 A
3606212 Paine Sep 1971 A
3698281 Brandt et al. Oct 1972 A
3778010 Potts et al. Dec 1973 A
3814353 Nelson Jun 1974 A
3906970 Saito et al. Sep 1975 A
4105173 Bucker Aug 1978 A
4113206 Wheeler Sep 1978 A
4134227 Kupperman et al. Jan 1979 A
4204213 Wheeler et al. May 1980 A
4215834 Dunlap Aug 1980 A
4361295 Wenzel Nov 1982 A
RE31205 Jalbert Apr 1983 E
4424945 Dell Jan 1984 A
4529153 Conn Jul 1985 A
4581897 Sankrithi Apr 1986 A
4586456 Forward May 1986 A
4601443 Jones et al. Jul 1986 A
4657207 Poling Apr 1987 A
4664343 Lofts et al. May 1987 A
4711416 Regipa Dec 1987 A
4828207 Haynes May 1989 A
4865274 Fisher Sep 1989 A
4889394 Ruspa Dec 1989 A
4936528 Butner et al. Jun 1990 A
5028018 Krebber Jul 1991 A
5111213 Jahoda et al. May 1992 A
5149015 Davis Sep 1992 A
5217186 Stewart Jun 1993 A
5232184 Reuter Aug 1993 A
5244169 Brown et al. Sep 1993 A
5251850 Noren Oct 1993 A
5274976 Burkhart Jan 1994 A
5327904 Hannum Jul 1994 A
5333817 Kalisz et al. Aug 1994 A
5362017 Puckett Nov 1994 A
5511748 Scott Apr 1996 A
5620153 Ginsberg Apr 1997 A
5718399 Cheng Feb 1998 A
5884981 Ichikawa Mar 1999 A
5893536 Lee et al. Apr 1999 A
6116538 Häfelfinger Sep 2000 A
6220547 Smith et al. Apr 2001 B1
6234425 Rand et al. May 2001 B1
6237241 Aaron et al. May 2001 B1
6250227 Salort Jun 2001 B1
6290172 Yajima et al. Sep 2001 B1
6360988 Monroe Mar 2002 B1
6364251 Yim Apr 2002 B1
6425640 Hussaini Jul 2002 B1
6527223 Mondale Mar 2003 B1
6565042 Yamada May 2003 B1
6596370 Hyuga et al. Jul 2003 B2
6604333 Schiedeggr et al. Aug 2003 B1
6626400 Booth Sep 2003 B1
6648272 Kothman Nov 2003 B1
6705572 Christopher May 2004 B1
6799810 Wang Oct 2004 B1
6883756 Preston Apr 2005 B2
6889942 Preston May 2005 B2
7168922 Stagg et al. Jan 2007 B2
D557817 Verfuerth Dec 2007 S
7313362 Sainct Dec 2007 B1
D575410 Best Aug 2008 S
7469857 Voss Dec 2008 B2
7530527 Kelleher May 2009 B2
7556040 Meyer et al. Jul 2009 B2
7584928 Hoffman Sep 2009 B2
7775604 Chen Aug 2010 B2
D632804 Afasano Feb 2011 S
8091826 Voorhees Jan 2012 B2
8100367 Rousseau Jan 2012 B1
8116763 Olsen Feb 2012 B1
8167240 Greiner May 2012 B2
8267348 Alavi Sep 2012 B2
8286910 Alavi Oct 2012 B2
8403268 Suze et al. Mar 2013 B2
8448898 Frolov et al. May 2013 B1
8505847 Ciampa et al. Aug 2013 B2
8622338 Ciampa et al. Jan 2014 B2
8718477 DeVaul et al. May 2014 B2
8777156 Piini et al. Jul 2014 B2
8781727 Bonawitz et al. Jul 2014 B1
8804228 Biffle et al. Aug 2014 B1
8812176 Biffle et al. Aug 2014 B1
8814084 Shenhar Aug 2014 B2
8820678 DeVaul et al. Sep 2014 B2
8833696 Teller et al. Sep 2014 B1
8849571 Bonawitz et al. Sep 2014 B1
8862403 Piponi et al. Oct 2014 B1
8874356 Bonawitz Oct 2014 B1
8880326 Bonawitz et al. Nov 2014 B1
8897933 Teller et al. Nov 2014 B1
8910905 DeVaul et al. Dec 2014 B2
8917995 Biffle et al. Dec 2014 B1
8918047 Teller et al. Dec 2014 B1
8948927 Piponi Feb 2015 B1
8971274 Teller et al. Mar 2015 B1
8988253 Teller et al. Mar 2015 B2
8996024 Teller et al. Mar 2015 B1
8998128 Ratner Apr 2015 B2
9010691 Ratner et al. Apr 2015 B1
9016634 Ratner et al. Apr 2015 B1
9027874 Roach et al. May 2015 B1
9033274 DeVaul et al. May 2015 B2
9033281 Adams May 2015 B1
9045213 DeVaul Jun 2015 B1
9067666 Roach et al. Jun 2015 B1
9085348 Roach et al. Jul 2015 B1
9090323 Ratner Jul 2015 B1
9093754 Behroozi et al. Jul 2015 B2
9096301 Biffle et al. Aug 2015 B1
9097361 Ratner Aug 2015 B1
9106336 Brouillet Aug 2015 B1
9114866 Roach Aug 2015 B1
9120551 Ratner Sep 2015 B1
9139278 Roach et al. Sep 2015 B1
9139279 Heppe Sep 2015 B2
9148215 Bonawitz Sep 2015 B1
9153854 Biffle et al. Oct 2015 B1
9174718 Roach et al. Nov 2015 B1
9174720 Ratner Nov 2015 B1
9174738 Roach et al. Nov 2015 B1
9193480 Smith et al. Nov 2015 B2
9195938 Bonawitz et al. Nov 2015 B1
9201426 Bonawitz Dec 2015 B1
9203148 Teller et al. Dec 2015 B1
9211942 Roach Dec 2015 B1
9221531 Brookes Dec 2015 B1
9233746 DeVaul et al. Jan 2016 B2
9242712 Ratner Jan 2016 B1
9254906 Behroozi et al. Feb 2016 B1
9266598 DeVaul Feb 2016 B1
9275551 Bonawitz et al. Mar 2016 B2
9281554 Behroozi et al. Mar 2016 B1
9285450 DeVaul et al. Mar 2016 B2
9290258 DeVaul Mar 2016 B1
9296461 Roach Mar 2016 B1
9296462 Brookes et al. Mar 2016 B1
9300388 Behroozi et al. Mar 2016 B1
9306271 Biffle et al. Apr 2016 B1
9306668 DeVaul et al. Apr 2016 B2
9318789 Henrich et al. Apr 2016 B1
9321517 DeVaul Apr 2016 B1
9327816 Mathe et al. May 2016 B1
9327817 Roach May 2016 B1
9327818 Roach May 2016 B1
9329600 DeVaul et al. May 2016 B2
9340272 DeVaul et al. May 2016 B1
9346531 Washburn et al. May 2016 B1
9346532 Ratner May 2016 B1
9424752 Bonawitz Aug 2016 B1
9463863 Roach et al. Oct 2016 B1
9540091 MacCallum et al. Jan 2017 B1
9561858 Leidich Feb 2017 B2
9669918 Fourie et al. Jun 2017 B1
9694910 MacCallum et al. Jul 2017 B2
9834297 Brookes Dec 2017 B2
9868537 Leidich et al. Jan 2018 B2
9908609 Fourie Mar 2018 B1
10124875 Farley et al. Nov 2018 B1
10336432 Farley et al. Jul 2019 B1
20020096599 McDermott Jul 2002 A1
20020175243 Black et al. Nov 2002 A1
20020179771 Senepart Dec 2002 A1
20020190161 Patel et al. Dec 2002 A1
20030016186 Watanabe et al. Jan 2003 A1
20030020322 Zaniboni Jan 2003 A1
20030040273 Seligsohn et al. Feb 2003 A1
20030111577 Yajima et al. Jun 2003 A1
20030127560 Liss Jul 2003 A1
20030197095 Preston Oct 2003 A1
20030234320 Colting Dec 2003 A1
20040059476 Nichols Mar 2004 A1
20040089763 Redmond May 2004 A1
20040135033 Hung Jul 2004 A1
20040218397 Luo Nov 2004 A1
20050040290 Suhami Feb 2005 A1
20050121968 McCaster, III et al. Jun 2005 A1
20050288114 Meadows Dec 2005 A1
20060065777 Walden et al. Mar 2006 A1
20060284006 Chasman et al. Dec 2006 A1
20070164600 Chiu Jul 2007 A1
20070272801 Hilliard Nov 2007 A1
20080029649 Sadeck Feb 2008 A1
20090045284 Chu Feb 2009 A1
20090108135 Shaw Apr 2009 A1
20090134277 Kim et al. May 2009 A1
20090206196 Parks et al. Aug 2009 A1
20090220726 Liggett et al. Sep 2009 A1
20090224094 Lachenmeier Sep 2009 A1
20100012772 Izutsu et al. Jan 2010 A1
20100163682 Jameson Jul 2010 A1
20100257983 Jordan et al. Oct 2010 A1
20110147513 Surmont Jun 2011 A1
20110198437 Brandon Aug 2011 A1
20110220764 Suh Sep 2011 A1
20110233325 Kramer Sep 2011 A1
20120049005 Suh Mar 2012 A1
20120091261 Lee Apr 2012 A1
20120133197 Mengle et al. May 2012 A1
20120168565 Berland Jul 2012 A1
20120228434 Lopez Urdiales Sep 2012 A1
20120234965 Heppe Sep 2012 A1
20120273620 Culbreath Nov 2012 A1
20120312919 Heppe Dec 2012 A1
20120312929 Gratzer Dec 2012 A1
20130037654 Zhang et al. Feb 2013 A1
20130043341 Tai et al. Feb 2013 A1
20130049440 Morse et al. Feb 2013 A1
20130062458 Shenhar Mar 2013 A1
20130177322 DeVaul et al. Jul 2013 A1
20130238784 Teller et al. Sep 2013 A1
20130303218 Teller et al. Nov 2013 A1
20140014770 Teller et al. Jan 2014 A1
20140155093 Teller Jun 2014 A1
20140159965 Le Jun 2014 A1
20140171075 Teller Jun 2014 A1
20150024653 Huebl Jan 2015 A1
20150042521 Hazen Feb 2015 A1
20150061937 Bonawitz et al. Mar 2015 A1
20150225091 Ratner Aug 2015 A1
20150284065 MacCallum et al. Oct 2015 A1
20150336653 Anderson et al. Nov 2015 A1
20150360763 Smith et al. Dec 2015 A1
20150367928 Crites Dec 2015 A1
20160018823 Longmier et al. Jan 2016 A1
20160052614 Longmier et al. Feb 2016 A1
20160083068 Crites Mar 2016 A1
20160090179 Childress et al. Mar 2016 A1
20160096612 Longmier et al. Apr 2016 A1
20160154085 DeVaul et al. Jun 2016 A1
20160156405 Teller et al. Jun 2016 A1
20160176531 Biehl Jun 2016 A1
20160207605 Jensen et al. Jul 2016 A1
20160263815 Roach et al. Sep 2016 A1
20160368202 Crites Dec 2016 A1
20170050716 Smith et al. Feb 2017 A1
20170129579 de Jong May 2017 A1
20170160741 Knoblach et al. Jun 2017 A1
20170233054 MacCallum et al. Aug 2017 A1
20170297724 Leidich et al. Oct 2017 A1
20170331177 MacCallum et al. Nov 2017 A1
20170349291 MacCallum et al. Dec 2017 A1
20180093750 Svoboda, Jr. Apr 2018 A1
20190193828 Ponda et al. Jun 2019 A1
Foreign Referenced Citations (51)
Number Date Country
2844003 Dec 2006 CN
200988579 Dec 2007 CN
202765296 Mar 2013 CN
102673770 Mar 2015 CN
204937453 Jan 2016 CN
223241 Jul 1909 DE
38 05 645 Jul 1988 DE
39 27 297 Feb 1991 DE
19634017 Feb 1998 DE
10 2008 035 028 Jan 2010 DE
0 401 891 Dec 1992 EP
3 268 279 Jan 2018 EP
3 414 157 Dec 2018 EP
2 320 229 Mar 1977 FR
2 724 909 Mar 1996 FR
2 834 966 Jul 2003 FR
191207587 Sep 1912 GB
2 184 699 Jul 1987 GB
2244962 Dec 1993 GB
2002-096798 Apr 2002 JP
10-1699797 Feb 2017 KR
2 028 962 Feb 1995 RU
2 112 709 Jun 1998 RU
2 186 003 Jul 2002 RU
WO 199009830 Sep 1990 WO
WO 1997015992 May 1997 WO
WO 2004106156 Dec 2004 WO
WO 2005012086 Feb 2005 WO
WO 2006119056 Nov 2006 WO
WO 2007079788 Jul 2007 WO
WO 2009129642 Oct 2009 WO
WO 2010130043 Nov 2010 WO
WO 2011160172 Dec 2011 WO
WO 2013041820 Mar 2013 WO
WO 2014025622 Feb 2014 WO
WO 2014193711 Dec 2014 WO
WO 2015031165 Mar 2015 WO
WO 2015076899 May 2015 WO
WO 2015094534 Jun 2015 WO
WO 2015094941 Jun 2015 WO
WO 2015102813 Jul 2015 WO
WO 2015122988 Aug 2015 WO
WO 2015130414 Sep 2015 WO
WO 2015157237 Oct 2015 WO
WO 2015196216 Dec 2015 WO
WO 2016081345 May 2016 WO
WO 2016145130 Sep 2016 WO
WO 2016209762 Dec 2016 WO
WO 2017127746 Jul 2017 WO
WO 2017139283 Aug 2017 WO
WO 2017180780 Oct 2017 WO
Non-Patent Literature Citations (67)
Entry
International Preliminary Report on Patentability in International Application No. PCT/US2016/021635, dated Sep. 21, 2017.
U.S. Appl. No. 15/401,447, filed Jan. 9, 2017 (Unpublished).
U.S. Appl. No. 15/411,841, filed Jan. 20, 2017 (Unpublished).
Browne, M.: “Balloon Teams Vie to be First Around World”, The New York Times, published Jun. 7, 1994, in 6 pages.
De Jong, M., Venus Altitude Cycling Balloon, Venus Lab and Technology Workshop, paper 4030, Apr. 7, 2015, in 1 page.
Gorham, P.:“NASA long duration balloon program”, Nov. 7, 2012, presented at SpacePart12—4th International Conference on Particle and Fundamental Physics in Space, CERN, Nov. 5-7, 2012, accessed Nov. 8, 2016. http://indico.cern.ch/event/197799/contributions/371922/.
Hanagud, A.V. et al.: “A Solar Pointing System for the Long Duration Balloon Missions”, AIAA—97—1516, 1997, accessed on Nov. 8, 2016. http://arc.aiaa.org/doi/pdf/10.2514/6.1997-1516.
Ondish, A.: “Multi-stage pumps can deliver efficiency gains”, Plant Engineering, Aug. 24, 2010, accessed Nov. 8, 2016. http://www.plantengineering.com/home/single-article/multi-stage-pumps-can-deliver-efficiency-gains-4623b966532d8cf9bba82d407aa82416.html.
Wikipedia Commons: “File: Le premier parachute de Jacques Garnerin, ca. 1799.jpg”, uploaded Aug. 12, 2010, in 3 pages. https://en.wikipedia.org/wiki/File:Le_premier_parachute_de_Jacques_Garnerin,_ca._1799.jpg.
Amendment in Response to Office Action dated Apr. 14, 2016, in U.S. Appl. No. 14/188,581, filed Aug. 15, 2016.
Office Action in U.S. Appl. No. 14/188,581, dated Apr. 14, 2016.
Final Office Action in U.S. Appl. No. 14/188,581, dated Dec. 27, 2016.
Etherington, D.: “World View's ‘stratollites’ and new spaceport aim to change the business of space”, TechCrunch, posted Feb. 23, 2017, in 9 pages. URL: https://techcrunch.com/2017/02/23/world-views-stratollites-and-new-spaceport-aim-to-change-the-business-of-space/.
PR Newswire: “World View and Ball Aerospace Demonstrate Persistent Remote Sensing from Stratollite Platform”, Yahoo Finance, posted Feb. 23, 2017, in 8 pages. URL: http://finance.yahoo.com/news/world-view-ball-aerospace-demonstrate-220000300.html.
International Search Report and Written Opinion in International Application No. PCT/US2017/014432, dated Apr. 6, 2017.
International Search Report and Written Opinion in International Application No. PCT/US2017/016861, dated Apr. 14, 2017.
U.S. Appl. No. 15/065,828, filed Sep. 15, 2016, MacCallum et al.
Aerospace-Technology.com: “World View Successfully Completes Test Flight for Commercial Balloon Flights,” Aerospace-Technology.com, online article dated Oct. 27, 2015. http://www.aerospace-technology.com/news/newsworld-view-test-flights-commercial-balloon-flight-4702892.
Aljazeera America: “Space tourism company breaks record with high-altitude balloon flight”, online article dated Jun. 25, 2014. http://america.aljazeera.com/articles/2014/6/25/balloonspace-tourism.html.
Benton, J. et al.: “On Development of Autonomous HAHO Parafoil System for Targeted Payload Return”, AIAA Aerodynamic Decelerator Systems (ADS) Conference, Mar. 2013, in 26 pages.
Berger, E.: “Record-Breaking Balloon Flight”, Outside Online, online article dated Jun. 25, 2014. http://www.outsideonline.com/1804196/record-breakingballoon-flight.
Boyle, A.: “Heads Up, Strato-Tourists: World View Begins High-Flying Tests”, NBC News, online article dated Jun. 24, 2014. http://www.nbcnews.com/science/space/heads-stratotourists-world-view-begins-high-flying-tests-n138986.
Boyle, A.: “World View Balloon Lofts NASA Experiments to Near-Space Heights,” NBC News, online article dated Mar. 9, 2015. http://www.nbcnews.com/science/space/world-view-balloon-lofts-nasa-experiments-near-space-heights-n320216.
Clausing, J.: “Arizona company successfully tests high-altitude balloon for space tourism”, US News, online article dated Jun. 24, 2014. http://www.usnews.com/news/business/articles/2014/06/24/company-successfully-tests-space-tourism-balloon.
Denuder, M.: “Development of a Paraglide-Deployment System for a Base Jumping Robot”, Bachelor-Thesis, Swiss Federal Institute of Technology Zurich, Jun. 2011, in 111 pages.
Foust, J.: “World View tests scale model of its high-altitude balloon system”, NewSpace Journal, online article dated Jun. 24, 2014. http://www.newspacejournal.com/2014/06/24/worldview-tests-scale-model-of-its-high-altitude-balloon-system/.
Gannon, M.: “World View Launches Test Balloon to Edge of Space, Breaks Record”, Space.com, online article dated Jun. 24, 2014. http://www.space.com/26340-world-view-balloon-testflight-record.html.
Haugen, J.: “After Successful Flight Test, World View Ready for Next Phase: The Stratospheric Tourism Company Is Setting Its Sights High,” Popular Science, online article dated Oct. 26, 2015. http://www.popsci.com/world-view-completes-first.
Howell, E.: “World View Makes Record-Setting Parafoil Flight from Near Edge of Space,” Space.com, online article dated Feb. 21, 2015. http://www.space.com/28626-world-view-parafoil-record-flight.html.
Howell, E.: “World View Parafoil Test Flight Touches Edge of Space,” Discovery News, online article dated Feb. 23, 2015. http://www.seeker.com/world-view-parafoil-test-flight-touches-edge-of-space-1769541739.html#news.discovery.com.
Klotz, I.: “World View Prototype Balloon Reaches for Edge of Space”, Seeker, online article dated Jun. 25, 2014. http://www.seeker.com/world-view-prototype-balloon-reaches-for-edge-of-space-1768745428.html#news.discovery.com.
Knapp, A.: “World View Has a Successful Scaled Test Flight of Its Balloon to Space”, Forbes, online article dated Jun. 24, 2014. http://www.forbes.com/sites/alexknapp/2014/06/24/world-view-has-a-successful-scaled-test-flight-of-its-balloon-tospace/#4e726063f229.
Larimer, S.: “Company takes test flight to the least-crowded tourism hot spot: space”, The Washington Post, online article dated Jun. 27, 2014. http://www.washingtonpost.com/news/postnation/wp/2014/06/27/company-takes-test-flight-to-theleast-crowded-tourism-hot-spot-space/.
Logan, M.: “Flight Brings Us Closer to Balloon-Powered Space Tourism”, online article dated Feb. 3, 2015. http://www.wired.com/2015/03/parafoil-world-view/.
Moon, M.: “World View Tests a Small Version of Its Balloon-powered Spacecraft,” MSN News, online article dated Oct. 27, 2015. http://www.msn.com/en-us/news/technology/world-view-tests-a-small-version-of-its-balloon-powered-spacecraft/ar-BBmtkdA.
O'Callaghan, J.: “Balloon Capsule That Will Take People to the Edge of Space Completes Test Flight,” IFLSCIENCE!, online article dated Oct. 28, 2015. http://www.iflscience.com/space/balloon-will-take-people-edge-space-capsule-completes-test-flight/.
Photograph of a parafoil in high altitude flight (assumed to be prior art, but applicant reserves right to confirm actual date of photograph and to dispute status as prior art).
World View: “Major World View Test Flight Readies the Company to Begin Full Scale Flight Testing for Human Private Spaceflights”, World View, press release dated Oct. 26, 2015.
World View: “World View Breaks World Record with Successful Test Flight for 2016 Journeys to Edge of Space”, World View, press release dated Jun. 24, 2014.
World View: “World View One Step Closer to Manned Near-Space Voyages with Record-Breaking Flight”, World View, press release dated Feb. 20, 2015.
International Search Report and Written Opinion in International Application PCT/US2016/021635, dated Jun. 16, 2016.
“Homepage”, World View Website, http://worldview.space, May 8, 2015, 1 page.
Bil, C.: “Lighter-Than-Air Stationary Observation Platforms”, 15th Australian International Aerospace Congress (AIAC15), Feb. 2013, pp. 97-103.
Cherry, N. J. et al.: “Characteristics and Performance of Three Low-Cost Superpressure Balloon (Tetroon) Systems”, Journal of Applied Meteorology, vol. 10, 1971, pp. 982-990.
Coldiron, et al., “Crew Escape Systems 21002”, https://www.nasa.gov/ . . ./383443main_crew_escape_workbook.pdf, Jan. 17, 2005.
Epley, L.E: “A System Architecture for Long Duration Free Floating Flight for Military Applications”, Cirrus Aerospace Corporation, Aug. 31, 1990, in 65 pages.
Jones, J.: “Long-Life Stratospheric Balloon System With Altitude Control”, NASA Tech Briefs, online article posted Jan. 1, 2002. http://www.techbriefs.com/component/content/article/ntb/tech-briefs/physical-sciences/2248.
Lachenmeier, T.T. : “Design of a Trans-Global Manned Balloon System With Relevance to Scientific Ballooning”, American Institute of Aeronautics and Astronautics, Inc., DOI: 10.2514/6.1991-3687, Oct. 1991.
Lawler, R.: “Google exec sets a new record for highest-altitude jump (video)”, Engadget, online article published Oct. 24, 2014. https://www.engadget.com/2014/10/24/google-exec-alan-eustace-stratex-high-altitude-jump/.
Longhetto, A.: “Some Improvements in the Balanced Pilot Balloons Technique”, Atmospheric Environment Pergamon Press, vol. 5, 1971, pp. 327-331.
Markoff, J.: “Parachutist's Record Fall: Over 25 Miles in 15 Minutes”, The New York Times, online article published Oct. 24, 2014. http://www.nytimes.com/2014/10/25/science/alan-eustace-jumps-from-stratosphere-breaking-felix-baumgartners-world-record.html?_r=1.
New Atlas: “Google exec sets new high-altitude skydiving world record”, New Atlas, online article published Oct. 26, 2014. http://newatlas.com/alan-eustace-world-record-skydive-stratex/34423/pictures.
Nobuyuki, Yajima, et al: “Dual Balloon Systems”, Scientific Ballooning: Technology and Applications of Exploration Balloons Floating in the Stratosphere and the Atmospheres of Other Planets. Springer Science & Business Media, Apr. 2009, pp. 48-52 (via Google Books). https://books.google.com.sg/books?id=_iEHI7Nh6yYC&Ipg-PA51&dq-(super%20pressure%20and%2 Ozero%20pressure%20balloon)%20(tandem%200R%20buoyant)&pg-PR1#v=onepage&q=(super%20 pressure%20and%20zero%20pressure%20balloon)%20(tandem%200R%20buoyant)&f=false.
Noor, A. et al.: “Stratospheric Aircraft”, Future Aeronautical and Space Systems. American Institute of Aeronautics and Astronautics, Inc., vol. 172, 1997, p. 241 (via Google Books). https://books.google.com.sg/books?id=uuR5yBwvhsQC&Ipg-PA241&dq=(super%20pressure%20and %20zero%20pressu re%20bal loon)%20(tandem%200R%20buoyant)&pg=PA241#v=onepage&q=(supe r%20pressure%20and%20zero%20pressure%20balloon)%20(tandem%200R%20buoyant)&f=false.
NuancedAdmin: “Paragon Completes Record-Breaking Near-Space Dive Via High-Altitude Balloon”, Paragon Space Development Corporation, press release dated Oct. 20, 2015.
Red Bull Stratos: “High Altitude Balloon”, Red Bull Stratos, [date posted unknown], accessed online on Jul. 1, 2016. http://www.redbullstratos.com/technology/high-altitude-balloon/.
Saito, Y. et al.: “Properties of tandem balloons connected by extendable suspension wires”, Advances in Space Research, vol. 45, 2010, pp. 482-489.
Saito, Y. et al: “Development of a tandem balloon system with a super-pressure balloon and a zero-pressure balloon I”, JAXA Research and Development Report, Japan Aerospace Exploration Agency, JAXA-RR-11-008, Mar. 2012, in 16 pages.
Saito, Y. et al: “Development of a tandem balloon system with a super-pressure balloon and a zero-pressure balloon II”, Jaxa Research and Development Report, Japan Aerospace Exploration Agency, JAXA-RR-13-011, Mar. 2014, in 36 pages.
Smith, M.S. et al.: “Optimum Designs for Superpressure Balloons”, Advances in Space Research, vol. 33, Iss. 10, Dec. 2004, in 9 pages.
Stratocat: “News Archive—Jun. 2012”, StratoCat, page generated Aug. 2, 2015. http://stratocat.com.adnews0612e.htm.
Wikipedia: “Sky anchor”, Wikipedia, accessed May 21, 2016, in 1 page.
Winzen et al.: “Operation Manhigh II”, Journal of Jet Propulsion, vol. 28, No. 8, 1958, pp. 523-532.
World View: “Landmark Space Dive Sets Stage for World View Space Flights”, World View, press release dated Oct. 24, 2014.
World View: “Oct. 24, 2015 Milestone 10% Scale Test Flight”, YouTube, published Oct. 24, 2015 (footage of parafoil seen in video), video can be accessed at https://www.youtube.com/watch?v=1-PpJHKHAQc (last accessed: Jul. 13, 2016).
World View: “The Stratollite”, YouTube, published Feb. 23, 2017, video can be accessed at https://www.youtube.com/watch?v=GFdXBQPuznU (last accessed May 20, 2019).
World View: “World View Breaks World Record with Successful Test Flight”, YouTube, published Jun. 23, 2014 (footage of parafoil in space seen in video), video can be accessed at https://www.youtube.com/watch?v=sdsVwN-ICX8 (last accessed: Jul. 13, 2016).
Related Publications (1)
Number Date Country
20160264248 A1 Sep 2016 US
Provisional Applications (2)
Number Date Country
62130395 Mar 2015 US
62239154 Oct 2015 US