Modular integrated self-contained cargo deployment/retrieval system

• US 20030222177A1
• Filed: 05/28/2002
• Published: 12/04/2003
• Est. Priority Date: 05/28/2002
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Bonisch, Frank H.
• Granted Patent: US 6,708,926 B2
• Time in Patent Office: Days
• US Class Current: 244/137.1
• CPC Class Codes: B64C 1/22 Other structures integral with fuselages to facilitate loading , e.g. cargo bays, cranes
• CPC Class Codes: B64D 1/08 the articles being load-carrying devices
• CPC Class Codes: B64D 3/00 Aircraft adaptations to facilitate towing or being towed B64D39/00 takes precedence
• CPC Class Codes: B64D 7/00 Arrangements of military equipment, e.g. armaments, armament accessories, or military shielding, in aircraft; Adaptations of armament mountings for aircraft dropping bombs or the like B64D1/00; armaments or mountings therefor per se F41

Abstract

The present invention relates to a self contained, modular integrated deployment and retrieval system for use with an aircraft such as a helicopter. The deployment and retrieval system comprises a support frame, a winch connected to the support frame, a tow cable wound around the winch, which tow cable is connected to the external load, and a support structure connected to the support frame. The support structure is axially movable relative to the support frame for moving the external load so as to control the center of gravity of the aircraft and so as to deploy and retrieve the external load.

Claims

1. A system for deploying and retrieving an external load from an aircraft comprising:

a support frame;

a winch connected to said support frame;

a tow cable wound around said winch, said tow cable being connected to said external load; and

a support structure connected to said support frame, said support structure being axially movable relative to said support frame for moving said external load so as to control the center of gravity of said aircraft.

2. A system according to claim 1, further comprising means for moving said support structure relative to said support frame.

3. A system according to claim 2, wherein said moving means comprises a pair of actuators connected to said support structure and to said support frame.

4. A system according to claim 2, further comprising:

said support frame having a pair of spaced apart side rails;

each of said side rails having a track;

said support structure having a pair of spaced apart side elements; and

each of said side elements having means for engaging and cooperating with one of said tracks to allow said axial movement of said support structure.

5. A system according to claim 4, wherein each said track is formed by a longitudinally extending slot in a respective side rail.

6. A system according to claim 4, further comprising an energy absorbing member extending between said side rails, said energy absorbing member acting as a forward crash restraint for said external load.

7. A system according to claim 4, wherein said support structure further comprises a sheave over which said tow cable passes and a support arm extending from each of said side elements to support said sheave.

8. A system according to claim 1, further comprising side arms attached to said support frame to support said winch.

9. A system according to claim 1, further comprising control devices mounted to said support frame.

10. A system according to claim 9, further comprising:

said support structure including a sheave over which said tow cable passes; and

said control devices including rotational and linear sensors for synchronizing linear motion of said sheave with motion of said winch.

11. A system according to claim 10, wherein said control devices further comprises at least one video camera for monitoring deployment and retrieval of said external load.

12. A system according to claim 1, further comprising means for connecting said support frame to a floor of said aircraft.

13. A system according to claim 12, wherein said connecting means comprises at least one of shear and tension connections.

14. A system according to claim 1, wherein said support frame has a longitudinal axis and said longitudinal axis is coincident with a center line of said aircraft.

15. A system according to claim 1, further comprising a removable shield positioned over said support frame.

16. A system according to claim 1, further comprising a barrier in front of said support frame to reduce noise, reduce hazards and control helicopter environment.

17. A system according to claim 1, further comprising a tow boom pivotably movable relative to said aircraft.

18. A system according to claim 17, wherein said tow boom is pivotally connected to said support structure.

19. A system according to claim 17, wherein said tow boom includes a pair of support legs and a tow ball capture device connected to said support legs.

20. A system according to claim 19, wherein each of said support legs has a first leg portion and a second leg portion connected to said first leg portion by a pivotal connection.

21. A system according to claim 20, wherein at least one of said first and second leg portions of each of said support legs has a load cell and a yaw sensor incorporated therein to provide automatic tow tension indication.

22. A system according to claim 19, wherein said tow ball capture device includes a tow hook and a pyrotechnic cable cutter.

23. A system according to claim 17, further comprising pivotal connections for allowing pivotal movement of said tow boom and a pitch sensor incorporated into each of said pivotal connections.

24. A system according to claim 17, wherein said tow boom is positioned above said external load when said external load is in a transport mode and said tow boom moves into a rigid truss configuration when said external load is being deployed.

25. A system according to claim 17, further comprising at least one remote video camera attached to said tow boom for monitoring deployment and retrieval of said external load.

26. A system according to claim 17, wherein a portion of said tow boom forms an aperture guard for said tow cable.

27. A system according to claim 17, further comprising a containment device attached to said tow boom.

28. A system according to claim 1, wherein said system is modular and self-contained.

32. A method according to claim 27, wherein said external load comprises a towed body used in a mine hunting operation and said lowering step comprises lowering said towed body into contact with water beneath the aircraft.

33. A method according to claim 32, further comprising moving said aircraft so as to tow said towed body through said body of water.

29. A method for deploying and retrieving an external load from an aircraft comprising the steps of:

providing a self contained modular deployment and retrieval system which includes a support frame, a winch connected to said support frame, and an axially movable support structure for supporting a sheave;

passing a tow cable on said winch over said sheave and connecting an end of said tow cable to said external load; and

moving said support structure from a retracted position to a deployed position so that the external load passes through an opening in said aircraft.

30. A method according to claim 29, wherein said moving step comprises moving said support structure along an axis coincident with a center line of said aircraft.

31. A method according to claim 29, further comprising lowering said external load to a desired position.

34. A method according to claim 31, wherein said external load comprises a rescue basket and said lowering step comprises lowering said rescue basket.

35. A method according to claim 29, wherein said external load comprises firefighting equipment and said lowering step comprises lowering said firefighting equipment.

37. A method according to claim 29, further comprising retrieving said external load by winding said tow cable onto said winch.

38. A method according to claim 37, further comprising moving said support structure from said deployed position to said retracted position after said external load has been aligned with said opening in said aircraft.

39. A method according to claim 37, further comprising providing a tow boom and positioning said tow boom above said external load when said external load is in a transport mode.

40. A method according to claim 39, further comprising pivoting said tow boom downwardly into a lockable truss configuration during said external load lowering step.

41. A method according to claim 40, further comprising capturing said tow cable with said tow boom as said external load is being lowered.

42. A method according to claim 40, further comprising folding said tow boom as said external load is being retrieved into said aircraft and moving said folded tow boom to said position above said external load.

43. A helicopter having a fuselage and an opening in said fuselage through which an external load is deployed, said helicopter comprising:

a self contained, modular deployment and retrieval system secured to said fuselage; and

said self contained, modular deployment and retrieval system including a support frame secured to said fuselage and a movable support structure for supporting a sheave connected to said support frame for movement relative to said support frame between a retracted position and a deployed position where said external load extends through said opening.

44. A helicopter according to claim 43, wherein said support frame has a longitudinal axis and said longitudinal axis is aligned with a center line of said aircraft.

45. A helicopter according to claim 43, wherein said deployment and retrieval system further comprising a winch attached to said support frame and said winch having a tow cable which is connected at one end to said external load and which passes over said sheave.

46. A helicopter according to claim 43, wherein said deployment and retrieval system further comprises a pair of actuators for moving said support structure relative to said support frame.

47. A helicopter according to claim 46, wherein said deployment and retrieval system further comprises control devices mounted to said support frame.

48. A helicopter according to claim 43, wherein said deployment and retrieval system further comprises:

said support frame having a pair of spaced apart side rails;

each of said side rails having a track;

said support structure having a pair of side elements; and

each of said side elements having means for engaging and cooperating with said track of a respective one of said side rails.

49. A helicopter according to claim 43, wherein said deployment and retrieval system further comprises a winch having a tow cable wound thereon, said tow cable being connected to said winch and to said external load, and a tow boom for capturing said tow cable as said external load is being deployed.

50. A helicopter according to claim 49, wherein said tow boom has a tow hook and a pyrotechnic cable cutter.

51. A helicopter according to claim 49, wherein said tow boom has means for detecting tow tension in said cable.

52. A helicopter according to claim 51, wherein said detecting means comprises at least one load cell and at least one yaw sensor.

53. A helicopter according to claim 49, further comprising means for detecting the pitch of said tow boom.

54. A helicopter according to claim 49, further comprising at least one video camera attached to said tow boom.

55. A helicopter according to claim 43, wherein said external load comprises a towed body for use in a mine hunting operation.