Aircraft electrical power transfer assembly

• US 8,371,536 B2
• Filed: 12/16/2011
• Issued: 02/12/2013
• Est. Priority Date: 07/29/2009
• Status: Expired due to Fees

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE)
• Inventors: Soenarjo, Mochamad Agoes
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Fabula, Michael A
• Application Number:
  US13/328,164
• Publication Number:
  US 20120168567A1
• Time in Patent Office: 424 Days
• Field of Search: 244/213, 244/214, 244/215, 244/134.D, 244/135.A, 242/378, 242/378.1, 242/378.2, 242/388, 242/388.1
• US Class Current: 244/213
• CPC Class Codes: B64C 9/22 at the front of the wing
• CPC Class Codes: B64D 15/12 by electric heating electric heating elements in general H05B
• CPC Class Codes: H02G 11/02 using take-up reel or drum
• CPC Class Codes: Y02T 50/30 Wing lift efficiency

Abstract

An assembly for an aircraft including a first structure mounted to a second structure, and a power transfer assembly electrically connecting the first and second structures. The first structure is movable relative to the second structure between a retracted and an extended position. The power transfer assembly includes a housing, a spool mounted for rotation relative to the housing and biased to rotate in a first direction, and an electrical cable adapted to be wound around the spool when the spool rotates, such that movement of the first structure from its retracted to its extended position causes the cable to be unwound from the spool by rotation of the spool in a second direction opposite the first. Also, a method of electrically connecting the first and second structures. The invention may be applied to an aircraft wing to electrically connect a leading edge slat to a fixed aerofoil portion.

Claims

1. An aircraft assembly comprising a flight control surface mounted to a fixed aerofoil structure, and a power transfer assembly electrically connecting the flight control surface and fixed aerofoil structure, wherein the flight control surface is movable translationally relative to the fixed aerofoil structure between a retracted and an extended position, and wherein the power transfer assembly comprises a housing mounted to the flight control surface, a spool mounted for rotation with respect to the housing and biased to rotate in a first direction, and an electrical cable wound around the spool when the spool rotates in the first direction, wherein movement of the flight control surface from its retracted to its extended position causes the cable to be unwound from the spool by rotation of the spool in a second direction opposite the first.

2. An assembly according to claim 1, wherein the power transfer assembly further comprises a spiral spring connected to the spool and to the housing for biasing the spool to rotate in the first direction.

3. An assembly according to claim 1, wherein the power transfer assembly further comprises an electrical connection terminal having a first portion fixed to the housing and a second portion rotatable with the spool, wherein the first and second portions are electrically connected, and the second portion is physically connected to one end of the cable.

4. An assembly according to claim 1, wherein the cable is wound with a single full turn around the spool when the first structure is in its retracted position.

5. An assembly according to claim 1, wherein the housing includes a pair of side plates one on either side of the spool.

6. An assembly according to claim 1, wherein the cable includes a bundle of power and signal routes.

7. An assembly according to claim 1, wherein a free end of the cable has an electrical connection terminal

8. An assembly according to claim 1, wherein the power transfer assembly has a modular construction.

9. An assembly according to claim 1, wherein the flight control surface and fixed aerofoil structure are electrically connected by a plurality of the power transfer assemblies.

10. An assembly according to claim 1, further comprising an actuator connected between the flight control surface and fixed aerofoil structure for moving the flight control surface between its retracted and extended positions.

11. An assembly according to claim 1, wherein unwinding of the cable from the spool is driven passively by movement of the flight control surface from its retracted to its extended position.

12. An assembly according to claim 1, wherein the fixed aerofoil structure includes a cut-out in its aerodynamic leading edge through which the cable passes.

13. An assembly according to claim 12, wherein the cut-out is sealed around the cable.

14. A method of electrically connecting a flight control surface mounted to a fixed aerofoil structure, wherein the flight control surface is movable translationally relative to the fixed aerofoil structure between a retracted and an extended position, the method comprising:

physically and electrically connecting a power transfer assembly between the flight control surface and fixed aerofoil structure, the power transfer assembly comprising a housing mounted to the flight control surface, a spool mounted for rotation with respect to the housing and biased to rotate in a first direction, and an electrical cable wound around the spool when the spool rotates in the first direction; and

moving the flight control surface from its retracted to its extended position accompanied by corresponding unwinding of the cable from the spool by rotation of the spool in a second direction opposite the first.