External cargo hook system for rotary-wing aircraft

• US 8,636,250 B2
• Filed: 03/08/2010
• Issued: 01/28/2014
• Est. Priority Date: 05/12/2009
• Status: Active Grant

• Current Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Original Assignee: Sikorsky Aircraft Corporation (Martin Marietta Corporation)
• Inventors: Toni, Darryl M., McCarthy, Mary, Barr, Bruce H., Stobiecki, Anthony Z., Swift, Thomas, Dziekonski, Thomas
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Green, Richard R
• Application Number:
  US13/258,545
• Publication Number:
  US 20120018569A1
• Time in Patent Office: 1,422 Days
• Field of Search: 244/137.4, 244/137.1, 244/118.2, 244/118.1, 244/3, 244/1.TD, 244/127, 244/125, 244/26, 244/17.11, 294/82.24, 294/82.26, 258 12- 18, 212/180
• US Class Current: 244/118.2
• CPC Class Codes: B64C 1/061 Frames
• CPC Class Codes: B64C 27/06 with single rotor
• CPC Class Codes: B64C 27/14 Direct drive between power plant and rotor hub
• CPC Class Codes: B64D 1/22 Taking-up articles from earth's surface

Abstract

An external hook system for a rotary-wing aircraft includes a lower frame interface which accommodates longitudinal and lateral loads and an upper frame interface. A tension member is mountable between the lower frame interface and the upper frame interface to transfer tension loads between the lower frame interface and the upper frame interface.

Claims

1. An external hook system for a rotary-wing aircraft comprising:

a lower frame interface configured to accommodate longitudinal and lateral loads, said lower frame interface includes a lug fixed to a portion of an airframe frame and an axial support swing arm rotatably interlocked with said lug by a first pin, said axial support swing arm includes an aperture opposed from said lug and a spherical joint adjacent said aperture;

an upper frame interface; and

a tension member mountable between said lower frame interface and said upper frame interface, said tension member operable to transfer tension loads between said lower frame interface and said upper frame interface, said tension member rotatably mountable to said lower frame interface by a second pin extending through said aperture.

2. The system as recited in claim 1, wherein said deflection includes longitudinal and lateral deflections about said spherical joint to react said longitudinal and lateral loads.

3. The system as recited in claim 1, wherein said upper frame interface includes a lug fixed to a portion of an airframe frame, said tension member mountable to said lug.

4. The system as recited in claim 1, wherein said upper frame interface includes a lug fixed to a portion of an airframe frame and a swing arm mounted to said lug about an axis to permit fore and aft rotation of said swing arm relative to said lug, said tension member mountable to said lug.

5. The system as recited in claim 1, wherein said upper frame interface is mounted proximate a main rotor system of the rotary-wing aircraft.

6. The system as recited in claim 1, wherein said upper frame interface is mounted below a main rotor gearbox of the rotary-wing aircraft.

7. The system as recited in claim 1, wherein said lower frame interface is proximate a cabin floor of the rotary-wing aircraft.

8. The system as recited in claim 1, wherein said first pin defines a first central axis and said second pin defines a second central axis that is parallel to said first central axis.

9. The system as recited in claim 1, wherein said lower frame interface is within an opening of the airframe frame.

10. The system as recited in claim 9, wherein said lug is fixed to an inner periphery of said opening.

11. The system as recited in claim 1, wherein aperture is above said spherical joint.

12. The system as recited in claim 1, further comprising a cargo release system mounted to said spherical joint, said cargo release system selected from the group consisting of a cargo hook system, a hoist system and combinations thereof.

13. A rotary-wing aircraft comprising:

an airframe;

a main rotor system supported by said airframe;

a lower frame interface mounted to a lower portion of said airframe, said lower frame interface configured to accommodate longitudinal loads and lateral loads, said lower frame interface includes a lug fixed to a portion of an airframe frame and an axial support swing arm rotatably interlocked with said lug by a first pin, said axial support swing arm includes an aperture opposed from said lug and a spherical joint adjacent said aperture;

an upper frame interface mounted to an upper portion of said airframe adjacent said main rotor system; and

a tension member removably mountable between said lower frame interface and said upper frame interface through an aircraft cabin defined by said airframe, said tension member operable to transfer tension loads between said lower frame interface and said upper frame interface, said tension member rotatably mountable to said lower frame interface by a second pin extending through said aperture.

14. The rotary-wing aircraft as recited in claim 13, wherein said lower portion of said airframe and said upper portion of said airframe is defined by a single frame.

15. The rotary-wing aircraft as recited in claim 13, wherein said upper frame interface is mounted directly below a main rotor gearbox of the rotary-wing aircraft.

16. The rotary-wing aircraft as recited in claim 13, wherein said lower frame interface is mounted to said lower portion of said first frame proximate a cabin floor of the rotary-wing aircraft.