Deployment brake release for a parachute

• US 7,648,105 B2
• Filed: 12/26/2006
• Issued: 01/19/2010
• Est. Priority Date: 12/26/2006
• Status: Active Grant

• Current Assignee: Airborne Systems North America of NJ, Inc. (Transdigm Group Incorporated)
• Original Assignee: Airborne Systems North America of NJ, Inc. (Transdigm Group Incorporated)
• Inventors: Gilbert, Martin, Dunker, Storm
• Primary Examiner(s): Mansen; Michael R
• Assistant Examiner(s): O'Hara; Brian M
• Application Number:
  US11/645,029
• Publication Number:
  US 20080149775A1
• Time in Patent Office: 1,120 Days
• Field of Search: 244/142, 244/147, 244/149, 244/150, 244/152, 294/82.25
• US Class Current: 244/152
• CPC Class Codes: B64D 17/34 adapted to control direction or rate of descent
• CPC Class Codes: B64D 17/62 Deployment
• CPC Class Codes: B64U 10/50 Glider-type UAVs, e.g. with parachute, parasail or kite for landing B64U70/83
• CPC Class Codes: B64U 2101/60 for transporting passengers; for transporting goods other than weapons
• CPC Class Codes: B64U 2201/104 using satellite radio beacon positioning systems, e.g. GPS
• CPC Class Codes: B64U 30/12 Variable or detachable wings, e.g. wings with adjustable sweep

Abstract

A deployment brake release system for use with an airborne guidance unit (AGU) of a parachute suitable for precision cargo delivery. The parachute includes deployment brake lines secured at one end to the edge of the canopy and connected at the other end through looped ends to motor control lines. The motor control lines are, in turn, engaged with the motor of the AGU. The deployment brake release system includes at least one hook mount having a hook secured to the AGU frame. The looped ends of the deployment brake lines are engaged with the hook during rigging so that, upon deployment, opening forces are applied to the hook mount rather than the motor. After full canopy inflation, the motor, via the motor control lines, pulls on the brake line looped ends to disengage them from the hook, transferring subsequent canopy loads to the AGU motor for the remainder of the flight. A method for releasing the deployment brake lines is also disclosed.

Claims

1. In combination with a parachute controlled by an unmanned aerial vehicle having an airborne guidance unit (AGU), a deployment brake release system comprising:

an AGU frame to which the parachute is coupled by a plurality of suspension lines that include at least one trailing edge line used to steer said parachute during steady flight state;

a motor and spool assembly controlled by the AGU, said at least one trailing edge line being windable on said spool by said motor;

a hook mount coupled to said AGU frame and associated with said motor and spool assembly, said hook mount including at least one hook having a neck around which the at least one trailing edge line is secured during parachute deployment so that opening canopy forces exerted on said at least one trailing edge line are taken by the hook mount and the AGU frame, said neck tapering to a downwardly directed nose that points in a direction substantially opposite the parachute when deployed;

said AGU being configured to activate said motor when said parachute has reached said steady flight state to wind said at least one trailing edge line onto said spool, said winding pulling said at least one trailing edge line downwardly away from said neck, toward and then off said nose so that, once said at least one trailing edge line is released from the hook, said motor and spool assembly bear steady flight state canopy forces exerted on said at least one trailing edge line and said at least one trailing edge line is controlled by said motor and spool assembly to steer said parachute during flight.

2. The combination as set forth in claim 1, further comprising a fastening element securing said at least one trailing edge line to said neck during rigging, said fastening element being configured to break in response to activation of said motor and resulting downward movement of said at least one trailing edge line off said nose after deployment.

3. The combination as set forth in claim 1, further comprising a second trailing edge line rigged so as to be secured to said hook upon deployment and releasable therefrom simultaneously with said at least one trailing edge line.

4. The combination as set forth in claim 1, further comprising a second trailing edge line rigged so as to be secured to said hook upon deployment and releasable therefrom sequentially with and prior to release of said at least one trailing edge line.

5. The combination as set forth in claim 4, wherein said at least one trailing edge line is secured to said spool by a motor control line that includes a looped portion positioned along a length thereof, said looped portion being secured during rigging to said hook in between said at least one trailing edge line and said second trailing edge line such that removal of said looped portion from said hook also removes said second trailing edge line from said hook.

6. The combination as set forth in claim 5, further comprising a securing line connected to said second trailing edge line and to said AGU frame for restraining free movement of said second trailing edge line upon release thereof from said hook.

7. The combination as set forth in claim 5, wherein said motor control line includes a plurality of additional looped portions positioned in spaced relationship along a length thereof, said additional looped portions being secured during rigging to said hook in alternating fashion with a plurality of additional trailing edge lines such that removal of each additional looped portion from said hook also removes one of said additional trailing edge lines from said hook.

8. The combination as set forth in claim 7, further comprising a securing line connected to said additional trailing edge lines and to said AGU frame for restraining free movement of said additional trailing edge lines upon release thereof from said hook.

9. The combination as set forth in claim 1, wherein said hook mount includes a plurality of hooks each configured to secure trailing edge lines.

10. The combination as set forth in claim 1, wherein said deployment brake release system includes a left hook mount and a right hook mount each having a hook, a left outer trailing edge line being secured to the hook of said left hook mount and a right outer trailing edge line being secured to the hook of said right hook mount prior to and during deployment, said left and right outer trailing edge lines acting as left and right steering lines upon release of said left and right outer trailing edge lines from said hooks.

11. A method for the release of a trailing edge of a parachute, deployed with the trailing edge deflected by a plurality of trailing edge suspension lines, after full inflation of the parachute in a UAV system having an AGU which comprises:

securing at least one trailing edge suspension line to an actuator system mounted to a frame of said AGU;

rigging a looped portion of said at least one trailing edge suspension line onto a downwardly directed projection of a projection mount connected to said AGU frame so as to direct canopy opening loads to said AGU frame during deployment; and

activating said actuator system when said UAV system reaches steady state flight to pull said at least one trailing edge suspension line loop downwardly in a direction substantially opposite said parachute to pull said loop off of said projection and transfer canopy loading to said actuator system such that said at least one trailing edge suspension line can be used to steer said parachute in flight using said actuator system.

12. The method as set forth in claim 11, wherein said actuator system includes a spool and a motor, said step of securing including spooling an end of said at least one trailing edge suspension line onto said spool.

13. The method as set forth in claim 11, further comprising, before the step of rigging a looped portion of said at least one trailing edge suspension line, the step of rigging a further looped portion of at least one additional trailing edge suspension line onto said downwardly directed projection;

said step of activating said actuator system then including first pulling said further looped portion of said at least one additional trailing edge suspension line downwardly off of said projection before said at least one trailing edge suspension line is pulled downwardly off of said projection.

14. The method as set forth in claim 11, wherein said downwardly directed projection is a hook having a neck portion and a downwardly depending nose portion extending in a direction substantially opposite said parachute, said step of rigging including passing said looped portion over said nose portion and upwardly toward said parachute onto said neck portion.

15. The method as set forth in claim 14, further comprising the step of securing said looped portion on said neck portion using a fastening element that is configured to break in response to activation of said actuator system.

16. A method for deflecting a trailing edge of a parachute for deployment and of then releasing said trailing edge after full inflation of the parachute during steady state flight in a UAV having an airborne guidance unit (AGU) supported on an AGU frame;

securing a parachute having a canopy to said AGU frame by a plurality of suspension lines that include at least one trailing edge line used to steer said UAV during steady flight state;

coupling said at least one trailing edge line to an actuator system supported on said AGU frame and controlled by the AGU;

securing a portion of said at least one trailing edge line to a neck portion of a hook mount coupled to said AGU frame and associated with said actuator system, said at least one trailing edge line portion being between said actuator system and a connection point of said at least one trailing edge line to said canopy, said hook mount including a nose in fixed relationship to said neck portion, said nose projecting downwardly from said neck portion in a direction substantially opposite the canopy when deployed so that said neck portion is closer to said canopy than is said nose, said at least one trailing edge line remaining secured to said hook mount neck during parachute deployment so that opening canopy forces exerted on said at least one trailing edge line are taken by the hook mount and the AGU frame;

following deployment of said UAV, said AGU activating said actuator system when said UAV has reached said steady flight state;

said actuator assembly pulling said at least one trailing edge line downwardly away from said neck, toward and then off said nose so that said at least one trailing edge line is released from the hook mount;

said actuator system thereafter bearing steady flight state canopy forces exerted on said at least one trailing edge line and controlling said at least one trailing edge line to steer said UAV during flight.

17. The method as set forth in claim 16, wherein said actuator system includes a spool and a motor, said step of coupling including spooling an end of said at least one trailing edge suspension line onto said spool.

18. The method as set forth in claim 16, further comprising, before the step of securing a portion of said at least one trailing edge suspension line, the step of rigging a further looped portion of at least one additional trailing edge suspension line onto said hook mount neck portion;

said step of activating said actuator system then including first pulling said further looped portion of said at least one additional trailing edge suspension line downwardly off of the nose of said hook mount before said at least one trailing edge suspension line is pulled downwardly off of said hook mount.

19. The method as set forth in claim 16, further comprising the step of securing said portion of said at least one trailing edge line on said neck portion using a fastening element that is configured to break in response to activation of said actuator system.

20. An unmanned aerial vehicle (UAV) comprising:

an airborne guidance unit (AGU) supported on an AGU frame;

a parachute secured to said AGU frame and controlled by said AGU during deployment, said parachute having a canopy coupled to said AGU frame by a plurality of suspension lines that include at least one trailing edge line used to steer said UAV during steady flight state;

an actuator system controlled by the AGU, said at least one trailing edge line being coupled to said actuator system;

a hook mount coupled to said AGU frame and associated with said actuator system, said hook mount including at least one hook having a neck and a nose in fixed relationship to one another, said nose projecting downwardly from said neck in a direction substantially opposite the canopy when deployed so that said neck is closer to said canopy than is said nose;

said at least one trailing edge line being secured to said hook neck during parachute deployment so that opening canopy forces exerted on said at least one trailing edge line are taken by the hook mount and the AGU frame;

said AGU being configured to activate said actuator system when said parachute has reached said steady flight state to pull said at least one trailing edge line downwardly away from said neck and in a direction opposite to said canopy, toward and then off said nose so that, once said at least one trailing edge line is released from the hook, said actuator system bears steady flight state canopy forces exerted on said at least one trailing edge line and said at least one trailing edge line is controlled by said actuator system to steer said UAV during flight.

21. The UAV as set forth in claim 20, wherein said actuator system includes a motor and spool assembly, said at least one trailing edge line being coupled to said spool and windable thereon by said motor.

22. The UAV as set forth in claim 21, wherein said at least one trailing edge line is secured to said hook neck by a fastening element that is configured to break in response to retraction of said at least trailing edge line when said motor winds said at least one trailing edge line onto said spool and thereby pulls the at least one trailing edge line downwardly off said hook nose.

23. The UAV as set forth in claim 22, wherein said fastening element includes a breakable cord passed through an aperture in said hook mount.

24. The UAV as set forth in claim 21, further comprising a second trailing edge line rigged so as to be secured to said hook mount during deployment and releasable therefrom sequentially with and prior to release of said at least one trailing edge line.

25. The UAV as set forth in claim 24, wherein said at least one trailing edge line is secured to said spool by a motor control line that includes a looped portion positioned along a length thereof, said looped portion being secured during rigging to said hook mount in between said at least one trailing edge line and said second trailing edge line such that removal of said looped portion from said hook mount also removes said second trailing edge line from said hook mount.

26. The UAV as set forth in claim 20, wherein said AGU frame includes a left hook mount and a right hook mount each having a hook with a generally downwardly directed nose, said at least one trailing edge line being attached to a left side of the canopy and being secured to said left hook mount and a second trailing edge line attached to a right side of the canopy being attached to said right hook mount prior to and during deployment.