Helicopter load suspending apparatus

• US 5,788,186 A
• Filed: 02/10/1997
• Issued: 08/04/1998
• Est. Priority Date: 02/10/1997
• Status: Expired due to Fees

• Current Assignee: Sail D White Enterprises Incorporated
• Original Assignee: Sail D White Enterprises Incorporated
• Inventors: White, Donald
• Primary Examiner(s): Mojica, Virna Lissi
• Application Number:
  US08/795,255
• Time in Patent Office: 540 Days
• Field of Search: 244/118.1, 244/137.4, 244/137.1, 244/138 R, 244/1 TD, 294/82.12
• US Class Current: 244/137.4
• CPC Class Codes: B60R 2019/266 using friction sufaces
• CPC Class Codes: B60R 2019/268 with rebound preventing means, e.g. ratchets
• CPC Class Codes: B64C 1/22 Other structures integral with fuselages to facilitate loading , e.g. cargo bays, cranes

Abstract

The apparatus stabilizes loads beneath helicopters to prevent undesirable load movement while allowing in-flight optimization of the load'"'"'s center of gravity to reduce drag and increase banking capability and top speed. An anchoring bracket secures the apparatus to the helicopter. The apparatus comprises an upper section that controls load pitch and lateral movement and a lower section that controls load height during unloading. A pitch regulator comprises a c-shaped yoke with upper and lower collars penetrated by a hollow shaft and elevator. A lateral movement regulator comprises a coupling and a y-shaped chassis. The coupling comprises a central sleeve captivated between the upper and lower collars and a motor permitting selective rotation about the elevator. The chassis secures to the coupling via a ball and socket and a middle suspension system captivated between coupling and suspension plates. Spaced apart terminal chassis arms support the load via a bearing wing. A winch spools a cable with an load stop resting on a foot. The foot front is pivotally secured to the pitch regulator while the back is pivotally secured to the wing. The wing and the elevator control load pitch. As the elevator retracts or extends, the wing moves arcuately upwardly or downwardly to move the load center of gravity longitudinally forwardly or rearwardly to control load pitch. An optional lower section controls load height during unloading. A hoist band passing through a pulley system with actuators that variably space the pulleys variably controlling effective band length.

Claims

1. Apparatus for controlling the pitch and lateral movement of a load held by a helicopter or aircraft, said apparatus comprising:

a pitch regulator adapted to be coupled to said structure, said regulator comprising a rigid yoke and an extensible elevator pivoted to the yoke;

a rigid chassis comprising a front, a rear, a pair of rearwardly extending, spaced apart arms, a cavity defined between said arms, and an elongated guide slot extending from said cavity towards said front;

a coupling pivoted to said pitch regulator for supporting the chassis, said coupling comprising an arm projecting towards the front of said chassis and captivated within said guide slot;

a flexible suspension resiliently connecting said chassis to said coupling;

a lateral movement regulator for twisting said coupling and thus said chassis relative to said yoke;

a displaceable wing pivotally suspended between said chassis arms, said wing comprising a load bearing foot that suspends the load; and

,

a junction between said foot and said pitch regulator enabling said elevator to pivot said wing.

2. The apparatus as defined in claim 1 further comprising hoist means for controlling the vertical height of said load.

3. The apparatus as defined in claim 2 wherein said hoist means comprises:

a band attached to said load for quickly raising or lowering said load;

at least two spaced apart pulleys about which said band is wound; and

,

means for varying the distance between said pulleys to lengthen or shorten said band to quickly raise or lower said load.

4. The apparatus as defined in claim 3 wherein said means for varying the distance between said pulleys comprises a hydraulic cylinder and a motor for actuating said cylinder.

5. The apparatus as defined in claim 1 wherein the means for varying the load is used to vary the moment arm relationship with the rotating lift blades to induce tight banking capability in turns.

6. The apparatus as defined in claim 1 wherein the lateral movement regulator is used to offset the load center of gravity toward the side of the advancing blades to essentially extend the cyclic control limits of the helicopter to optimize the center of air foil lift with the center of gravity of the entire helicopter including the load.

7. The apparatus as defined in claim 1 wherein the pitch regulator is used to offset the load center of gravity forwardly to enhance the speed capability of the helicopter.

8. An apparatus for controlling the pitch and lateral movement of a load suspended by a cable from a helicopter or aircraft, said apparatus comprising:

winch means for spooling said cable;

a stabilizer secured to said helicopter and adapted to support said winch means, said stabilizer comprising;

a pitch regulator depending from said helicopter and adapted to selectively transversely relocate the center of gravity of said load;

a lateral movement regulator pivotally secured to said pitch regulator, said lateral movement regulator adapted to support said load;

first sensor means for detecting undesirable load lateral movement;

first motor means responsive to said first sensor means for pivoting said lateral movement regulator about said pitch regulator to transversely relocate said load center of gravity to eliminate said undesirable load lateral movement;

means secured to said pitch regulator for relocating said load center of gravity longitudinally rearwardly or forwardly;

second sensor means for detecting undesirable load pitch; and

,

second motor means responsive to said second sensor means for activating said means secured to said pitch regulator to longitudinally relocate said load center of gravity to eliminate said undesirable load pitch.

9. The apparatus as defined in claim 8 wherein said pitch regulator further comprises a yoke depending downwardly from and pivotally secured to said helicopter, said yoke comprising a top and a spaced apart bottom collars and wherein said lateral movement regulator is rotatably coupled to said yoke top and supports said load by securing said cable.

10. The apparatus as defined in claim 9 further comprising wing means pivotally secured to said yoke and said chassis for securing said cable to support said load.

11. The apparatus as defined in claim 8 further comprising hoist means for controlling the vertical height of said load.

12. The apparatus as defined in claim 11 wherein said hoist means comprises:

a band attached to said load for quickly raising or lowering said load;

at least two spaced apart pulleys about which said band is wound; and

,

means for varying the distance between said pulleys to lengthen or shorten said band to quickly raise or lower said load.

13. The apparatus as defined in claim 12 wherein said means for varying the distance between said pulleys comprises a hydraulic cylinder and a motor for actuating said cylinder.

14. An apparatus for controlling the pitch and lateral movement of a load suspended by a cable from a helicopter or aircraft, said apparatus comprising:

winch means for spooling said cable;

a stabilizer secured to said helicopter and adapted to support said winch means, said stabilizer comprising;

a pitch regulator depending from said helicopter and adapted to selectively transversely relocate the center of gravity of said load;

a lateral movement regulator pivotally secured to said pitch regulator, said lateral movement regulator adapted to support said load;

first sensor means for detecting undesirable load lateral movement;

first motor means responsive to said first sensor means for pivoting said lateral movement regulator about said pitch regulator to transversely relocate said load center of gravity to eliminate said undesirable load lateral movement;

means secured to said pitch regulator for relocating said load center of gravity longitudinally rearwardly or forwardly;

second sensor means for detecting undesirable load pitch;

second motor means responsive to said second sensor means for activating said means secured to said pitch regulator to longitudinally relocate said load center of gravity to eliminate said undesirable load pitch; and

,

hoist means for controlling the vertical height of said load.

15. The apparatus as defined in claim 14 wherein said pitch regulator further comprises a yoke depending downwardly from and pivotally secured to said helicopter, said yoke comprising a top and a spaced apart bottom collars and wherein said lateral movement regulator is rotatably coupled to said yoke top and supports said load by securing said cable.

16. The apparatus as defined in claim 15 further comprising wing means pivotally secured to said yoke and said chassis for securing said cable to support said load.

17. The apparatus as defined in claim 16 wherein said hoist means comprises:

a band attached to said load for quickly raising or lowering said load;

a first set of at least two spaced apart pulleys about which said band is wound;

a second set of at least two spaced apart pulleys about which said band is wound after said first set;

first means for varying the distance between said first set of pulleys to lengthen or shorten said band to quickly raise or lower said load; and

,

second means for varying the distance between said second set of pulleys to fine tune the load height.

18. The apparatus as defined in claim 17 wherein said first and second means for varying the distance between said pulleys comprises a hydraulic cylinder and a motor for actuating said cylinder.

19. The apparatus as defined in claim 18 wherein said pitch regulator and said lateral movement regulator cooperatively selectively offset the center of induced parasitic drag by the load as in towing tag lines and as with use in anti-submarine warfare as the helicopter moves.