Aircraft and a system including aircraft borne apparatus

• US 4,746,082 A
• Filed: 02/13/1986
• Issued: 05/24/1988
• Est. Priority Date: 07/15/1983
• Status: Expired due to Fees

• Current Assignee: Flight Refuelling Limited (Eaton Corporation PLC.), GEC Avionics Ltd
• Original Assignee: Flight Refuelling Limited (Eaton Corporation PLC.), GEC Avionics Ltd
• Inventors: Taylor, Douglas R., Syms, Philip W.
• Primary Examiner(s): NOT, DEFINED
• Assistant Examiner(s): Corl, Rodney
• Application Number:
  US06/829,291
• Time in Patent Office: 831 Days
• Field of Search: 244/93, 244/118.2, 244/118.1, 244/137 A, 244/190, 244/17.11, 343/705, 343/717, 354/65, 354/70, 354/74
• US Class Current: 244/137.4
• CPC Class Codes: B64D 47/08 Arrangements of cameras

Abstract

A fixed wing aircraft comprises two major components, namely an airframe and a payload carrier which are articulated. The airframe is equipped with all the essentials for independent flight. The attitude of the payload carrier can be controlled independently of the attitude of the airframe.

Claims

1. An aircraft comprising a first airframe portion including wings, power plant, and control means and systems required for independent flight, and another portion which is a payload carrier and which is supported from said first airframe portion, outside said first airframe portion from which it is spaced, by support means which allow angular movement, at least in roll, of said payload carrier portion relative to said first airframe portion whereby the attitude of said payload carrier portion can be controlled independently of the attitude of said first airframe portion, each said portion having an external surface which is a respective part of the external surface of the aircraft that is exposed to the atmosphere when the aircraft is in flight.

2. An aircraft according to claim 1, wherein stabilization means are provided whereby the attitude of said payload carrier portion is maintained substantially constant relative to the horizontal at least in roll, regardless of the attitude of said first airframe portion, at least within a certain range of movement of said first airframe portion relative to said payload carrier portion.

3. An aircraft according to claim 2, wherein the stabilization means comprises a mechanical drive arrangement operable to effect controlled rotation of said payload carrier portion about its fore and aft axis through its center of gravity.

4. An aircraft according to claim 3, wherein the mechanical drive arrangement comprises a servomotor carried by said first airframe portion and a transmission by which the servomotor output is transmitted to said payload carrier portion to effect controlled rotation of said payload carrier portion.

5. An aircraft according to claim 4, including control means operable in response to signals from an automatic pilot of the aircraft to control operation of the servomotor, the signals being dependent upon the rate of roll of said first airframe portion and the attitude of said first airframe portion at any one instant.

6. An aircraft according to claim 4, including a feedback device responsive to the condition of the servomotor at any one instant and incorporated in the mechanical drive arrangement.

7. An aircraft according to claim 1, wherein said payload carrier portion is fitted detachably to said first airframe portion and is part of a detachable assembly including the support means.

8. An aircraft according to claim 7, wherein the detachable assembly is provided with a locking mechanism operable, when the assembly is detached from said first airframe portion, to lock said payload carrier portion against angular movement relative to the remainder of the assembly.

9. A fixed wing aircraft comprising two major components which are articulated, one of the major components comprising an airframe portion including the wings, power plant, and control means and systems required for independent flight, the other component being a payload carrier portion which is outside said airframe portion, the aircraft having means for articulating the payload carrier portion in relation to said airframe portion so that its attitude can be controlled independently of the attitude of said airframe portion, each said major component having an external surface which is a respective part of the external surface of the aircraft that is exposed to the atmosphere when the aircraft is in flight.

10. A system including aircraft borne apparatus which, in operation, is in signal communication with the ground through free space, and which has transmitting and/or receiving means on or in open communication with an external surface of structure on which it is mounted, said apparatus being mounted within a portion of a fixed wing aircraft which is articulated to an airframe portion of the fixed wing aircraft by support means which allow angular movement, at least in roll, of the first mentioned portion relative to said airframe portion, said airframe portion including the wings, power plant, control means and systems essential for independent flight, stabilization means being provided so that the attitude of said first mentioned portion is maintained substantially constant relative to the horizontal, at least in roll, regardless of the attitude of said airframe portion, at least within a certain range of movement of said airframe portion relative to said first mentioned portion, each said portion having an external surface which is a respective part of the external surface of the aircraft that is exposed to the atmosphere when the aircraft is in flight.

11. An aircraft comprising two major components which are articulated one outside the other, each said major component having an external surface which is a respective part of the external surface of the aircraft that is exposed to the atmosphere when the aircraft is in flight, one of the major components comprising an airframe portion including wings, power plant and control means and systems required for independent flight, the other component being a payload carrier portion which is outside said airframe portion, the aircraft having means for articulating the payload carrier in relation to said airframe portion so that its attitude can be controlled independently of the attitude of said airframe portion and including stabilization means operable to maintain an axis of the payload carrier portion substantially vertical in flight.

12. An aircraft according to claim 11, wherein said articulation means provides that relative angular movement between said payload carrier and airframe portions is about the center of gravity of said payload carrier portion.