Methods and apparatus for selectively attaching and releasing multiple payloads suspended from an aircraft

• US 5,593,113 A
• Filed: 02/06/1995
• Issued: 01/14/1997
• Est. Priority Date: 02/06/1995
• Status: Expired due to Fees

• Current Assignee: Cox, Donald P.
• Original Assignee: Cox, Donald P.
• Inventors: Cox, Donald P.
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US08/384,414
• Time in Patent Office: 708 Days
• Field of Search: 244/137.1, 244/137.4, 244/118.1, 294/82.15, 294/82.26, 294/82.24, 294/87.1, 294/86.4, 294/81.56, 177/245, 177/244, 73/862.621, 310/232, 310/90, 403/165, 403/164
• US Class Current: 244/137.1
• CPC Class Codes: B64D 1/08 the articles being load-carrying devices
• CPC Class Codes: B64D 1/22 Taking-up articles from earth's surface
• CPC Class Codes: B66C 1/22 Rigid members, e.g. L-shaped members, with parts engaging the under surface of the loads; Crane hooks
• CPC Class Codes: B66C 1/34 Crane hooks
• CPC Class Codes: Y10T 403/32983 Rod in socket

Abstract

A multiple payload system comprising a sling assembly and a frame assembly for suspension from an aircraft. The sling assembly includes an elongated load bearing cable having a first end and a second end. A stress sensor used in measuring the weight of the payloads extends between the aircraft and the first end of the load bearing cable. A payload hook is also attached to the sling assembly with an anti-torque device extending between the second end of the load bearing cable and the payload hook. The anti-torque device permits the payload hook to freely rotate relative to the longitudinal axis of the load bearing cable. The frame assembly is attached to the payload hook and comprises an airframe with a plurality of payload hooks secured thereto. The payload hooks are used for selectively attaching and releasing multiple payloads. A stabilizing wing and a plurality of legs are also attached to the airframe. Finally, electrical means are also provided to permit selective actuation of the payload hooks and the load cells from the aircraft.

Claims

1. An apparatus for selectively attaching and selectively releasing multiple payloads suspended from an aircraft, the apparatus comprising:

(a) an airframe capable of supporting multiple payloads;

(b) a plurality of payload hooks attached to the airframe;

(c) means mounted on each of the payload hooks for sensing the loading position of each of the plurality of payload hooks;

(d) means for suspending the airframe at a distance below the aircraft; and

(e) means for electrically and selectively actuating each of the payload hooks.

(f) means for supporting the plurality of payload hooks a distance off the ground during repetitive landing of the apparatus for attaching the individual payloads;

wherein the means for supporting the airframe off the ground comprises a plurality of legs attached to the airframe and extending below the airframe such that the plurality of legs support the payload hooks off the ground during landing of the apparatus.

2. An apparatus as recited in claim 1, wherein the plurality of legs can be selectively adjusted so as vary the distance that the payload hooks are off the ground.

3. An apparatus as recited in claim 1, further comprising means for retarding rotation of the airframe during suspended flight of the airframe.

4. An apparatus as recited in claim 3, wherein the means for retarding rotation comprises a stabilizing wing attached to the airframe, the stabilizing wing being vertically oriented and aligned with the longitudinal axis of the airframe.

5. An apparatus as recited in claim 1, wherein the airframe comprises a loading frame, a support frame, and a plurality of struts extending from the loading frame to the support frame.

6. An apparatus as recited in claim 5, wherein the support frame comprises a plurality of sides forming a polygon.

7. An apparatus as recited in claim 5, wherein the means for suspending the airframe comprises an eyelet attached to the loading frame.

8. An apparatus as recited in claim 5, wherein the plurality of payload hooks are attached to the support frame so as to extend below the support frame and further comprising an indicator lamp mounted on the support frame above each of the plurality of payload hooks, the indicator lamp electrically communicating with the payload hook which the indicator lamp is above such that when a payload hook is selected, the indicator lamp is illuminated.

9. An apparatus as recited in claim 1, wherein the means for electrically and selectively actuating each of the payload hooks comprises a logic circuit panel attached to the airframe and a plurality of electrical cables extending from the logic circuit panel to each of the payload hooks, the logic circuit panel being capable of receiving, analyzing, and transmitting electrical signals.

10. An apparatus as recited in claim 1, wherein the means for sensing the loading position of each of the plurality of payload hooks comprises each payload hook having a spring actuated hook arm designed for rotating between loading and unloading positions and a proximity detector positioned adjacent to the hook arm such that the proximity detector is actuated as the hook arm is rotated between the loading and unloading positions.

11. An apparatus as recited in claim 1, further comprising means for selectively weighing each individual payload attached to the plurality of payload hooks.

12. An apparatus as recited in claim 11, wherein the means for selectively weighing each individual payload comprises a load cell extending between the airframe and each of the payload hooks.

13. An apparatus as recited in claim 11, wherein the means for selectively weighing each individual payload comprises:

(a) a housing having a first end, a second end, and an interior surface defining a chamber and a passage extending from the second end to the chamber, the first end of the housing being attached to the airframe;

(b) a loading member freely disposed within the passage and having a first end and a second end, the first end of the loading member being positioned in the chamber and the second end of the loading member being attached to one of the plurality of payload hooks; and

(c) a load cell extending between the interior surface of the chamber and the first end of the loading member, thereby all of the weight transferred by the loading member is transferred to the load cell.

14. An apparatus as recited in claim 13, wherein the first end of the loading member has a diameter greater than the diameter of the passage, thereby the housing holds the weight of the payload if the load cell fails.

15. An apparatus as recited in claim 1, wherein the means for sensing the loading position of each of the plurality of payload hooks comprises each payload hook having:

(a) a spring actuated hook arm designed for rotating between loading and unloading positions;

(b) a latch selectively movable to lock the hook arm in the loading position; and

(c) a proximity detector positioned adjacent to the latch such that the proximity detector is actuated as the latch is moved to allow the hook arm to move between the loading and unloading positions.

16. An apparatus as recited in claim 1, wherein the means for sensing the loading position of each of the plurality of payload hooks comprises each payload hook having:

(a) a spring actuated hook arm designed for rotating between a loading and unloading position;

(b) a safety latch selectively biased against the hook arm; and

(c) a proximity detector positioned adjacent to the safety latch such that the proximity detector is actuated as the safety latch is moved when the hook arm is moved between the loading and unloading positions.

45. A payload management system as defined in claim 1, further comprising an electrical cable extending from the aircraft to each of the plurality of payload hooks.

17. An apparatus for selectively attaching and selectively releasing a payload suspended from an aircraft, the apparatus comprising:

(a) a load bearing cable having a first end and a second end, the first end being for attachment to an aircraft;

(b) a payload hook being electrically actuated for selectively attaching and selectively releasing a payload attached thereto;

(c) means for attaching the second end of the load bearing cable to the payload hook such that the payload hook freely rotates relative to the longitudinal axis of the load bearing cable, the means for attaching comprising;

(i) a stator assembly comprising a first shaft, a second shaft, and a third shaft, the third shaft being aligned with and extending between the first shaft and the second shaft, the third shaft having a diameter smaller than the diameter of both the first shaft and the second shaft, the first shaft of the stator assembly being attached to the second end of the load bearing cable;

(ii) a rotor assembly comprising a housing having a first end, a second end, an interior surface defining a receiving chamber, and a lip radially extending inward from the interior surface near the first end defining an opening to the receiving chamber, the second shaft of the stator assembly being positioned within the receiving chamber with the third shaft passing through the opening, the second shaft of the stator assembly having a diameter greater than the diameter of the passage so that the second shaft is held within the receiving chamber, the second end of the rotor assembly being attached to the payload hook; and

(iii) a bearing assembly positioned between the stator assembly and the rotor assembly, thereby permitting the rotor assembly to freely rotate relative to the longitudinal axis of the load bearing cable; and

(d) means for electrically and selectively actuating the payload hook from the aircraft.

18. An apparatus as recited in claim 17, wherein the means for electrically and selectively actuating the payload hook from the aircraft comprises:

(a) an electrical cable for carrying an electrical signal extending from the aircraft to the stator assembly;

(b) means for transferring the electrical signal from the stator assembly to the rotor assembly; and

(c) an electrical cable extending from the stator assembly to the payload hook.

19. An apparatus as recited in claim 18, wherein the means for transferring the electrical signal from the stator assembly to the rotor assembly comprises a co-axial optical coupler having a first end positioned on the second shaft of the stator assembly along the longitudinal axis of the load bearing cable and a second end attached to the second end of the rotor assembly, the first end of the co-axial optical coupler being positioned adjacent to and aligned with the second end of the co-axial optical coupler.

20. An apparatus as recited in claim 19 further comprising a logic circuit board attached to the rotor assembly for processing electrical signals from the co-axial optical coupler.

21. An apparatus as recited in claim 18, wherein the means for transferring the electrical signal from the stator assembly to the rotor assembly comprises:

(a) a slip ring encircling the third shaft of the stator assembly, the slip ring being electrically connected to the electrical cable extending from the aircraft; and

(b) a brush contact positioned on the interior surface of the rotor assembly so that the brush contact is biased against the slip ring, the brush contact being electrically connected to the electrical cable extending to the payload hook.

22. An apparatus for selectively attaching and selectively releasing multiple payloads suspended from an aircraft, the apparatus comprising:

(a) a load bearing cable having a first end for attachment to the aircraft and a second end;

(b) a payload hook attached to the second end of the load bearing cable;

(c) an airframe capable of supporting multiple payloads, the airframe being independently carried by and selectively connected to the payload hook at the second end of the load bearing cable;

(d) a plurality of payload hooks mounted on the airframe, each of the payload hooks being configured to hold a discrete payload directly beneath the airframe; and

(e) means for electrically and selectively actuating each of the payload hooks from the aircraft.

23. An apparatus as recited in claim 22, wherein the means for electrically and selectively actuating each of the payload hooks from the aircraft comprises an electrical cable extending from the aircraft to each of the payload hook.

24. An apparatus as recited in claim 22, further comprising means for attaching the second end of the load bearing cable to the payload hook such that the payload hook freely rotates relative to the longitudinal axis of the load bearing cable.

25. An apparatus as recited in claim 24, wherein the means for attaching the second end of the load bearing cable to the payload hook such that the payload hook freely rotates relative to the longitudinal axis of the load bearing cable comprises:

(a) a stator assembly comprising a first shaft, a second shaft, and a third shaft, the third shaft being aligned with and extending between the first shaft and the second shaft, the third shaft having a diameter smaller than the diameter of both the first shaft and the second shaft, the first shaft of the stator assembly being attached to the second end of the load bearing cable;

(b) a rotor assembly comprising a housing having a first end, a second end, an interior surface defining a receiving chamber, and a lip radially extending inward from the interior surface near the first end defining an opening to the receiving chamber, the second shaft of the stator assembly being positioned within the receiving chamber with the third shaft passing through the opening, the second shaft of the stator assembly having a diameter greater than the diameter of the passage so that the second shaft is held within the receiving chamber, the second end of the rotor assembly being attached to the payload hook; and

(c) a bearing assembly positioned between the stator assembly and the rotor assembly, thereby permitting the rotor assembly to freely rotate relative to the longitudinal axis of the load bearing cable.

26. An apparatus as recited in claim 22, wherein the means for electrically and selectively actuating the payload hook from the aircraft comprises:

(a) an electrical cable for carrying an electrical signal extending from the aircraft to the stator assembly;

(b) means for transferring the electrical signal between the stator assembly and the rotor assembly; and

(c) an electrical cable extending from the stator assembly to the payload hook.

27. An apparatus as recited in claim 22, further comprising means for weighing the payloads when suspended from an aircraft.

28. An apparatus as recited in claim 27, wherein the means for weighing the payloads when suspended from the aircraft comprises a load cell extending between the aircraft and the first end of the load bearing cable.

29. An apparatus as recited in claim 27, wherein the means for weighing the payloads when suspended from the aircraft comprises a stress sensor including:

(a) a housing having a first end, a second end, and an interior surface defining a chamber and a passage extending from the second end to the chamber;

(b) a loading rod freely disposed within the passage and having a first end and a second end, the first end of the loading rod being positioned in the chamber and the second end of the loading rod being attached to the first end of the load bearing cable; and

(c) a load cell extending between the interior surface of the chamber and the first end of the loading rod, thereby all of the weight transferred by the loading rod is transferred to the load cell.

30. An apparatus as recited in claim 29, wherein the first end of the loading rod has a diameter greater than the diameter of the passage, thereby the housing supports the payload if the load cell fails.

31. A payload management system for selectively attaching and selectively releasing multiple payloads suspended from an aircraft, the payload management system comprising:

(a) an airframe capable of supporting multiple payloads, the airframe comprising a loading frame, a support frame, and a plurality of struts extending from the loading frame to the support frame;

(b) a plurality of payload hooks attached to the loading frame of the airframe, the payload hooks being electrically actuated for selectively attaching and selectively releasing individual payloads attached thereto;

(c) a load bearing cable having a first end for attachment to an aircraft and a second end attached to the airframe; and

(d) means for enabling the airframe to freely rotate relative to the load bearing cable.

32. A payload management system as defined in claim 31, further comprising a plurality of legs attached to and extending below the airframe such that the plurality of legs support the payload hooks off the ground.

33. A payload management system as defined in claim 31, further comprising a stabilizing wing attached to the airframe, the stabilizing wing being vertically oriented and aligned with the longitudinal axis of the airframe.

34. A payload management system as defined in claim 31, wherein the support frame comprises a plurality of sides forming a polygon.

35. A payload management system as defined in claim 31, further comprising a payload hook connected to the second end of the load bearing cable and attached to the airframe, the payload hook being electrically actuated for selectively attaching and selectively releasing the airframe.

36. A payload management system as defined in claim 31, further comprising a load cell extending between the aircraft and the first end of the load bearing cable to determine the weight of the payload management system.

37. A payload management system as defined in claim 31, further comprising:

(a) a housing having a first end, a second end, and an interior surface defining a chamber and a passage extending from the second end to the chamber, the first end of the housing being attached to the aircraft;

(b) a loading rod freely disposed within the passage and having a first end and a second end, the first end of the loading rod being positioned in the chamber and the second end of the loading rod being attached to the first end of the load bearing cable; and

(c) a load cell extending between the interior surface of the chamber and the first end of the loading rod, thereby all of the weight transferred by the loading rod is transferred to the load cell.

38. A payload management system as defined in claim 37, wherein the first end of the loading rod has a diameter greater than the diameter of the passage, thereby the housing holds the weight of the payload management system if the load cell fails.

39. A payload management system as defined in claim 31, wherein the means for enabling the airframe to freely rotate relative to the load bearing cable comprises:

(a) a stator assembly comprising a first shaft, a second shaft, and a third shaft, the third shaft being aligned with and extending between the first shaft and the second shaft, the third shaft having a diameter smaller than the diameter of both the first shaft and the second shaft, the first shaft of the stator assembly being attached to the second end of the load bearing cable;

(b) a rotor assembly comprising a housing having a first end, a second end, an interior surface defining a receiving chamber, and a lip radially extending inward from the interior surface near the first end defining an opening to the receiving chamber, the second shaft of the stator assembly being positioned within the receiving chamber with the third shaft passing through the opening, the second shaft of the stator assembly having a diameter greater than the diameter of the passage so that the second shaft is held within the receiving chamber, the second end of the rotor assembly being attached to the payload hook; and

(c) a bearing assembly positioned between the stator assembly and the rotor assembly, thereby permitting the rotor assembly to freely rotate relative to the longitudinal axis of the load bearing cable.

40. A payload management system as defined in claim 39, further comprising:

(a) an electrical cable for carrying an electrical signal extending from the aircraft to the stator assembly;

(b) means for transferring the electrical signal between the stator assembly and the rotor assembly; and

(c) means for transferring the electrical signal between the rotor assembly and the plurality of payload hooks.

41. A payload management system as defined in claim 40, wherein the means for transferring the electrical signal from the stator assembly to the rotor assembly comprises a co-axial optical coupler having a first end positioned on the second shaft of the stator assembly along the longitudinal axis of the second shaft and a second end attached to the second end of the rotor assembly, the first end of the co-axial optical coupler being positioned adjacent to and aligned with the second end of the co-axial optical coupler.

42. A payload management system as defined in claim 40, wherein the means for transferring the electrical signal between the rotor assembly and the plurality of payload hooks comprises:

(a) a logic circuit panel attached to the airframe, the logic circuit panel being capable of receiving, analyzing, and transmitting electrical signals;

(b) an electrical cable extending from the pickup end of the co-axial optical coupler to the logic circuit; and

(c) a plurality of electrical cables extending from the logic circuit panel to each of the payload hooks.

43. A payload management system as defined in claim 40, wherein the means for transferring the electrical signal between the stator assembly and the rotor assembly comprises

(a) a slip ring encircling the third shaft of the stator assembly, the slip ring being electrically attached to the cable extending from the aircraft;

and

(b) a brush contact positioned on the interior surface of the rotor assembly so that the brush contact is biased against the slip ring, the brush contact being electrically connected to the electrical cable extending to the payload hook.

44. A payload management system as defined in claim 41, further comprising a transmit coil attached to the stator assembly and a pickup coil attached to the rotor assembly, the transmit coil and the pickup coil being positioned such that an electrical current passed through transmit coil will create a current in the pickup coil for energizing the logic circuit panel.

46. A payload management system as recited in claim 31, further comprising a load cell extending between the airframe and each of the plurality of payload hooks for weighing each of the individual payloads.