Rigidized assisted opening system for high altitude parafoils

• US 9,561,858 B2
• Filed: 06/22/2016
• Issued: 02/07/2017
• Est. Priority Date: 03/09/2015
• Status: Active Grant

• Current Assignee: World view enterprises inc.
• Original Assignee: World view enterprises inc.
• Inventors: Bowen, Ty, Leidich, Jared, MacCallum, Taber Kyle
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Giczy, Alexander V
• Application Number:
  US15/189,850
• Publication Number:
  US 20160297537A1
• Time in Patent Office: 230 Days
• US Class Current: 1/1
• CPC Class Codes: B64B 1/40 Balloons B64B1/58 takes precedence; toy balloons A63H27/10
• CPC Class Codes: B64D 1/12 Releasing
• CPC Class Codes: B64D 17/025 for gliding chutes
• CPC Class Codes: B64D 17/24 Rigging lines
• CPC Class Codes: B64D 17/26 attached to hem of canopy
• CPC Class Codes: B64D 17/40 Packs
• CPC Class Codes: B64D 17/62 Deployment
• CPC Class Codes: B64D 17/70 by springs
• CPC Class Codes: B64D 17/72 by explosive or inflatable means
• CPC Class Codes: B64D 17/76 facilitated by method of folding or packing

Abstract

Described are a parafoil for operation at high altitudes, in low density air, or at low airspeeds, and methods for opening same. The parafoil comprises 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 members 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.

Claims

1. A parafoil comprising:

a base structure;

a first elongated wing tip support having a lower end and an upper end opposite the lower end, the lower end coupled with the base structure and extending outward relative to a vertical orientation, the first wing tip support comprising a first flexible rod configured to flex to store energy of flexure;

a second elongated wing tip support having a lower end and an upper end opposite the lower end, the lower end coupled with the base structure and extending outward relative to the vertical orientation, the second wing tip support comprising a second flexible rod configured to flex to store energy of flexure; and

a canopy extending between a first wingtip end and a second wingtip end opposite the first wingtip end, the first wingtip end of the canopy coupled with the upper end of the first wing tip support, and the second wingtip end of the canopy coupled with the upper end of the second wing tip support,

wherein the parafoil is configured to be restrained in a stowed configuration and to be released from the stowed configuration to spring open using at least in part the stored energy of flexure of the first and second flexible rods into a deployed flight configuration,

wherein, in the stowed configuration, the upper ends of the first and second wing tip supports are located above the respective lower ends and converge inward relative to the vertical orientation, and

wherein, in the deployed flight configuration, the canopy is spread open and the first and second wing tip supports extend outward relative to the vertical orientation.

2. The parafoil of claim 1, further comprising a restraint configured to restrain the first and second wing tip supports in the stowed configuration.

3. The parafoil of claim 2, wherein the restraint is a closure loop configured to restrain the canopy and the upper ends of the first and second wing tip supports in the stowed configuration.

4. The parafoil of claim 1, wherein the lower ends of the first and second wing tip supports are rotatably coupled with the base structure.

5. The parafoil of claim 4, further comprising:

a first hinge that couples the lower end of the first wing tip support with the base structure; and

a second hinge that couples the lower end of the second wing tip support with the base structure,

wherein the first wing tip support is configured to rotate about the first hinge as the first wing tip support springs open from the stowed configuration into the deployed flight configuration, and

wherein the second wing tip support is configured to rotate about the second hinge as the second wing tip support springs open from the stowed configuration into the deployed flight configuration.

6. The parafoil of claim 1, further comprising:

a first fulcrum coupled with the base structure near the lower end of the first wing tip support; and

a second fulcrum coupled with the base structure near the lower end of the second wing tip support,

wherein the first fulcrum is configured to fix an initial angle of the lower end of the first wing tip support in the stowed configuration, and

wherein the second fulcrum is configured to fix an initial angle of the lower end of the second wing tip support in the stowed configuration.

7. The parafoil of claim 1, further comprising:

a payload coupled with the base structure;

at least one suspension line having a lower end and an upper end, the lower end coupled with the base structure; and

a ring coupled with the upper end of the at least one suspension line,

wherein the ring is configured to couple with a connection device for connecting the parafoil to a flight vehicle located above the parafoil, and

wherein the suspension line is configured to transfer a load from the payload to the flight vehicle.

8. The parafoil of claim 1, further comprising:

a release mechanism coupled with the base structure; and

a tether releasably coupled with the base structure via the release mechanism,

wherein, in the stowed configuration, the tether extends from the release mechanism and through the canopy and is configured to couple with a connection device for connection to a flight vehicle located above the parafoil,

and wherein release of the tether from the release mechanism will release the parafoil from the flight vehicle.

9. The parafoil of claim 8, wherein the tether is connected to the connection device and wherein the flight vehicle is a balloon.

10. The parafoil of claim 1, further comprising:

a first plunger moveably coupled with the upper end of the first wing tip support; and

a second plunger moveably coupled with the upper end of the second wing tip support,

wherein the first plunger is configured to vary the position of the upper end of the first wing tip support along a first longitudinal axis of the first wing tip support in the deployed flight configuration, and

wherein the second plunger is configured to vary the position of the upper end of the second wing tip support along a second longitudinal axis of the second wing tip support in the deployed flight configuration.

11. The parafoil of claim 1, further comprising:

a third elongated wing tip support having a lower end and an upper end opposite the lower end, the lower end coupled with the base structure and extending outward relative to a vertical orientation, the upper end coupled with the canopy, and the third wing tip support comprising a third flexible rod configured to flex to store energy of flexure;

a fourth elongated wing tip support having a lower end and an upper end opposite the lower end, the lower end coupled with the base structure and extending outward relative to a vertical orientation, the upper end coupled with the canopy, and the fourth wing tip support comprising a fourth flexible rod configured to flex to store energy of flexure;

a fifth elongated wing tip support having a lower end and an upper end opposite the lower end, the lower end coupled with the base structure and extending outward relative to a vertical orientation, the upper end coupled with the canopy, and the fifth wing tip support comprising a fifth flexible rod configured to flex to store energy of flexure; and

a sixth elongated wing tip support having a lower end and an upper end opposite the lower end, the lower end coupled with the base structure and extending outward relative to a vertical orientation, the upper end coupled with the canopy, and the sixth wing tip support comprising a sixth flexible rod configured to flex to store energy of flexure.

12. The parafoil of claim 11, wherein the canopy further comprises:

a nose extending between the first and second wingtip ends of the canopy and coupled with the upper end of the fifth wing tip support; and

a tail extending between the first and second wingtip ends of the canopy, the tail located opposite the nose and coupled with the upper end of the sixth wing tip support,

wherein the first wingtip end of the canopy is further coupled with the upper end of the third wing tip support, and the second wingtip end of the canopy is further coupled with the upper end of the fourth wing tip support.

13. A parafoil for releasably supporting a payload from a flight vehicle, the parafoil comprising:

a canopy coupled with a base structure via first and second elongated wing tip supports, the first and second wing tip supports each comprising a flexible rod configured to flex to store energy of flexure in a stowed configuration and to spring open using at least in part the stored energy of flexure of the flexible rods from the stowed configuration into a deployed flight configuration wherein the canopy is spread open,

wherein, in the stowed configuration, lower ends of the first and second elongated wing tip supports extend outward relative to a vertical orientation and upper ends of the first and second elongated wing tip supports are located above the respective lower ends and converge inward relative to the vertical orientation; and

a tether releasably coupled with the base structure, the tether extending through the canopy in the stowed configuration and configured to couple with a connection device for connection to a flight vehicle that is located above the parafoil,

wherein releasing the tether from the base structure will release the parafoil from the flight vehicle.

14. The parafoil of claim 13, further comprising a restraint configured to restrain the first and second wing tip supports in the stowed configuration, wherein release of the restraint allows the first and second wing tip supports to spring open from the stowed configuration into the deployed flight configuration.

15. The parafoil of claim 14, wherein the restraint comprises a closure loop configured to restrain the canopy and the upper ends of the first and second elongated wing tip supports in the stowed configuration.

16. The parafoil of claim 15, further comprising a parachute bag, wherein a base of the bag comprises flaps that comprise grommets, and wherein the upper ends of the first and second elongated wing tip supports comprise wing tip support eyes, and the closure loop weaves through the grommets and the wing tip support eyes in the stowed configuration.

17. A method of using a parafoil comprising a canopy coupled with a base structure via first and second elongated wing tip supports comprising respectively a first flexible rod and a second flexible rod, the method comprising:

flexing the first and second wingtip supports into a stowed configuration, wherein in the stowed configuration the first and second flexible rods are flexed to store energy of flexure such that lower ends of the first and second wingtip supports extend outward from the base structure at an initial angle relative to a vertical orientation and upper ends of the first and second wingtip supports are located above the respective lower ends and converge inward relative to the vertical orientation;

restraining the first and second wingtip supports in the stowed configuration;

storing the canopy of the parafoil in a parachute bag;

attaching the parafoil to a flight vehicle; and

attaching the base structure to a payload.

18. The method of claim 17, further comprising:

releasing the first and second wingtip supports from the stowed configuration;

springing open the first and second wingtip supports to deployed positions using at least in part the stored energy of flexure of the first and second flexible rods; and

spreading open the canopy to a deployed flight configuration.

19. The method of claim 18, further comprising detaching the parafoil from the flight vehicle after the canopy spreads open to the deployed flight configuration.

20. The method of claim 18, further comprising detaching the parafoil from the flight vehicle simultaneously with spreading open the canopy to the deployed flight configuration.