Method and apparatus for disabling pilot control of a hijacked aircraft

• US 7,837,143 B2
• Filed: 03/10/2006
• Issued: 11/23/2010
• Est. Priority Date: 03/14/2005
• Status: Active Grant

• Current Assignee: Karl F. Milde Jr
• Original Assignee: Karl F. Milde Jr
• Inventors: Matos, Jeffrey A.
• Primary Examiner(s): Collins; Timothy D
• Assistant Examiner(s): Xavier; Valentina
• Application Number:
  US11/373,712
• Publication Number:
  US 20060249625A1
• Time in Patent Office: 1,719 Days
• Field of Search: 244/231, 244/76.R, 244/175, 244/195, 244/220, 244/221, 244/228, 244/230, 244/234
• US Class Current: 244/75.1
• CPC Class Codes: B64C 13/24 Transmitting means
• CPC Class Codes: B64D 45/0015 Devices specially adapted for the protection against criminal attack, e.g. anti-hijacking systems
• CPC Class Codes: B64D 45/0031 means for overriding or restricting access to flight controls

Abstract

A method and apparatus are disclosed for disabling on-board pilot operation of an aircraft and transferring aircraft operation to an alternate source of control. The aircraft has at least one manually actuated control device for controlling at least one mechanical actuator, with the actuator causing movement of an aircraft attitude control surface or an aircraft engine throttle. The control device is mechanically connected to the actuator(s). The alternate source of control may be one or more of an autopilot, a flight control system and an off-aircraft human pilot. The method and apparatus for disabling on-board pilot operation provides for (a) receiving a signal indicative of an emergency condition requiring the disabling of on-board pilot control of the aircraft; (b) disconnecting the one or more control devices from their respective actuator(s) in response to the receipt of the emergency condition signal; and (c) connecting the actuator(s) to the alternate source of control.

Claims

1. Apparatus for disabling on-board pilot operation of an aircraft and transferring aircraft operation to an alternate source of control, said aircraft having at least one manually actuated control device for on-board human pilot control of at least one mechanical actuator, said actuator causing movement of one of (1) an aircraft engine throttle and (2) an aircraft attitude control surface, said at least one control device being mechanically connected to said at least one actuator, said alternate source of control comprising at least one of an autopilot, a flight control system and means for receiving control signals transmitted from a remote station, said signals representing commands by an off-aircraft human pilot, said apparatus comprising, in combination:

(a) means for receiving a first electric signal indicative of an emergency condition requiring the disabling of on-board pilot control of said aircraft;

(b) means for mechanically disconnecting said mechanical connection between said at least one control device and said at least one actuator in response to said first electric signal indicative of said emergency condition; and

(c) means for mechanically connecting said at least one actuator with said alternate source of control, in response to said first electric signal indicative of said emergency condition.

2. The apparatus defined in claim 1, wherein said at least one control device is at least one of a yoke, at least one pedal, a control stick and a throttle control member.

3. The apparatus defined in claim 1, wherein said control surface is at least one of an aileron, a flap, an elevator and a rudder.

4. The apparatus defined in claim 1, further comprising means for sensing said emergency condition relating to said aircraft from a location on board said aircraft and generating said first electric signal in response thereto.

5. The apparatus defined in claim 1, further comprising means for sensing said emergency condition relating to said aircraft from a location remote from said aircraft and generating and transmitting said first electric signal to said aircraft in response thereto.

6. The apparatus defined in claim 1, further comprising means for maintaining off-aircraft human pilot control of said aircraft by transmitting said control signals representing commands of said off-aircraft human pilot to said aircraft.

7. The apparatus defined in claim 1, wherein means (b) includes (1) at least one removable pin extending through holes in at least two mechanical movable members, each movable member forming a part of one of said at least one control device and said at least one actuator, respectively, and (2) means responsive to said first electric signal for removing said pin, thereby to sever the connection between said movable members.

8. The apparatus defined in claim 1, wherein means (b) includes (1) at least one de-couple-able segment linking two portions of a mechanical member that extends between said at least one control device and said at least one actuator, and (2) means responsive to said first electric signal for de-coupling said segment, thereby to de-couple the connection between said at least one control device and said at least one actuator.

9. The apparatus defined in claim 8, wherein de-coupling means includes means responsive to said first electric signal for severing said segment, thereby to sever the connection between said at least one control device and said at least one actuator.

10. The apparatus defined in claim 8, wherein said de-coupling means includes means responsive to said first electric signal for removing said segment, thereby to sever the connection between said at least one control device and said at least one actuator.

11. The apparatus defined in claim 1, further comprising:

(d) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition;

(e) means for disconnecting said at least one actuator from said alternate source of control in response to said second electric signal; and

(f) means for reconnecting said at least one control device to said at least one actuator in response to said second electric signal.

12. The apparatus defined in claim 1, wherein means (b) includes:

(1) two disks having parallel surfaces and a common center line, said disks each having one center hole and at least one non-center hole;

a first one of said disks being mechanically coupled to said mechanically actuated control device such that said first disk rotates in response to pilot actions upon said control device and a second one of said disks being mechanically coupled to said at least one actuator such that the rotation of said second disk causes said actuator to move said at least one of said throttle and said control surface;

(2) at least one movable rigid rod which may be positioned to pass through said non-center hole in at least one of said disks; and

(3) means responsive to said first electric signal for moving said rod;

wherein

(1) in a first position of said rod, said rod is positioned to pass through a non-center hole in each of said first disk and said second disk and thereby couple rotational motion from said first disk to said second disk and thereby mechanically couple onboard pilot actions to said at least one mechanical actuator;

(2) in a second position of said rod, said rod is positioned to not pass through both of (i) a non-center hole in said first disk and (ii) a non-center hole in said second disk, thereby preventing the coupling of rotational motion from said first disk to said second disk and disabling onboard pilot actions from moving said at least one mechanical actuator; and

(3) said first electric signal causes the movement of said rod from said first position to said second position.

13. The apparatus defined in claim 1, wherein means (c) includes:

(1) two disks having parallel surfaces and a common center line, said disks each having one center hole and at least one non-center hole;

a first one of said disks being mechanically coupled to said alternate source of control such that said first disk rotates in response to actions of said alternate source of control, and a second one of said disks being mechanically coupled to said at least one actuator such that the rotation of said second disk causes said actuator to move said at least one of said throttle and said control surface;

(2) at least one movable rigid rod positioned to pass through said non-center hole in at least one of said disks; and

(3) means responsive to said first electric signal for moving said rod;

wherein

(1) in a first position of said rod, said rod is positioned to pass through a non-center hole in each of said first disk and said second disk and thereby couple rotational motion from said first disk to said second disk and thereby mechanically couple said alternate source of control to said at least one mechanical actuator;

(2) in a second position of said rod, said rod is positioned to not pass through both of (i) a non-center hole in said first disk and (ii) a non-center hole in said second disk, thereby preventing the coupling of rotational motion from said first disk to said second disk and thereby preventing the coupling of said alternate source of control to said at least one mechanical actuator; and

(3) said first electric signal causes the movement of said rod from said second position and said first position.

14. The apparatus defined in claim 1, wherein means (b) includes:

(1) two disks having parallel surfaces and a common center line, said disks each having one center hole, a first one of said disks being mechanically coupled to said mechanically actuated control device such that said disk rotates in response to pilot actions upon said control device, and a second one of said disks being mechanically coupled to said at least one actuator such that the rotation of said second disk causes said actuator to move said at least one of said throttle and said control surface;

(2) a rigid rod which is positioned to pass through said center holes in said disks; and

(3) means responsive to said first electric signal for reversibly coupling the rotational motion of at least one said disk to said rigid rod;

wherein

(1) in a first apparatus state, said reversible coupling means couples the rotation of said first disk to the rotation of said second disk via said rigid rod, thereby mechanically coupling onboard pilot actions to said at least one mechanical actuator;

(2) in a second apparatus state, said reversible coupling means de-couples the rotation of said first disk from the rotation of said second disk, thereby de-coupling onboard pilot actions from said at least one mechanical actuator; and

(3) said first electric signal causes the transition from said first apparatus state to said second apparatus state.

15. The apparatus defined in claim 1, wherein means (c) includes:

(1) two disks having parallel surfaces and identical center lines, said disks each having one center hole, a first one of said disks being mechanically coupled to said alternate source of control such that said disk rotates in response to actions of said alternate source of control, and a second one of said disks being mechanically coupled to said at least one actuator such that the rotation of said second disk causes said actuator to move said at least one of said throttle and said control surface;

(2) a rigid rod positioned to pass through said center holes in each of said disks; and

(3) means responsive to said first electric signal for reversibly coupling the rotational motion of at least one said disk to said rigid rod;

wherein

(1) in a first apparatus state, said reversible coupling means couples the rotation of said first disk to the rotation of said second disk via said rigid rod, and thereby mechanically couples said alternate source of control to said at least one mechanical actuator;

(2) in a second apparatus state, said reversible coupling means de-couples the rotation of said first disk from the rotation of said second disk, and thereby de-couples said alternate source of control from said at least one mechanical actuator; and

(3) said first electric signal causes the transition from said second apparatus state to said first apparatus state.

16. The apparatus defined in claim 12, further comprising:

(4) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(5) means responsive to said second electric signal for moving said rod;

wherein said second electric signal causes the movement of said rod from said second position to said first position.

17. The apparatus defined in claim 13, further comprising:

(4) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(5) means responsive to said second electric signal for moving said rod;

wherein said second electric signal causes the movement of said rod from said first position to said second position.

18. The apparatus defined in claim 14, further comprising:

(4) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(5) means responsive to said second electric signal for reversibly coupling the rotational motion of at least one said disk to said rigid rod;

wherein said second electric signal causes the transition from said second apparatus state to said first apparatus state.

19. The apparatus defined in claim 15, further comprising:

(4) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(5) means responsive to said second electric signal for reversibly coupling the rotational motion of at least one said disk to said rigid rod;

wherein said second electric signal causes the transition from said first apparatus state to said second apparatus state.

20. The apparatus defined in claim 1, wherein means (b) includes:

(1) two disks each having a center hole, a first one of said disks being mechanically coupled to said mechanically actuated control device such that said first disk rotates in response to pilot actions upon said control device, and a second one of said disks being mechanically coupled to said at least one actuator such that the rotation of said second disk causes said actuator to move said at least one of said throttle and said control surface;

(2) a first rigid rod positioned to pass through said center hole in said first disk, said first rigid rod being affixed to said first disk such that the angular rotation of said first rigid rod is identical to the angular rotation of said first disk;

(3) a second rigid rod positioned to pass through said center hole in said second disk, said second rigid rod being affixed to said second disk such that the angular rotation of said second rigid rod is identical to the angular rotation of said second disk;

(4) a mechanical connection between said first rigid rod and said second rigid rod such that the rotation of said first rigid rod causes the rotation of said second rigid rod; and

(5) means responsive to said first electric signal for uncoupling said mechanical connection so that the rotational motion of said first rigid rod does not cause rotation of said second rigid rod;

whereby said first electric signal causes the uncoupling of said mechanical connection between said first rigid rod and said second rigid rod, thereby de-coupling onboard pilot actions from said at least one mechanical actuator.

21. The apparatus defined in claim 20, wherein said mechanical connection includes a removable link which links said first rigid rod and said second rigid rod, and wherein means (5) cause the removal of said link in response to said first electric signal.

22. The apparatus defined in claim 21, wherein means (5) includes means for preventing re-coupling of said mechanical connection until after the termination of said emergency condition, whereby said first electric signal causes the removal of onboard pilot control of at least one manually actuated control device until after the termination of said emergency condition.

23. The apparatus defined in claim 20, further comprising:

(6) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(7) means responsive to said second electric signal for re-coupling a previously uncoupled mechanical connection, so that said rotational motion of said first rigid rod causes rotation of said second rigid rod;

whereby said second electric signal causes the re-coupling of said mechanical connection between said first rigid rod and said second rigid rod, thereby re-coupling onboard pilot actions to said at least one mechanical actuator.

24. The apparatus defined in claim 21, further comprising:

(6) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(7) means responsive to said second electric signal for re-inserting said removable link, thereby re-establishing the state in which said rotational motion of said first rigid rod causes rotation of said second rigid rod;

whereby said second electric signal causes the re-coupling of said mechanical connection between said first rigid rod and said second rigid rod, thereby re-coupling onboard pilot actions to said at least one mechanical actuator.

25. The apparatus defined in claim 20, wherein

said disks have parallel surfaces and a common center line.

26. The apparatus defined in claim 20, wherein

said disks have parallel surfaces and differing center lines.

27. The apparatus defined in claim 1, wherein means (b) includes:

(1) two disks each having a center hole, a first one of said disks being linked by a first mechanical coupling to said mechanically actuated control device such that said first disk rotates in response to pilot actions upon said control device, and a second one of said disks being mechanically coupled to said at least one actuator such that the rotation of said second disk causes said actuator to move said at least one of said throttle and said control surface;

(2) a rod positioned to pass through said center hole in each of said first disk and said second disk, said rod fixed to said first disk and said second disk such that the angular rotation of said first disk is identical to the angular rotation of said second disk;

(3) a first mechanical coupling including at least one of a cable and a belt for transmitting torque from said mechanically actuated control device to said first disk;

(4) tension controlling means positioned to control the path of said at least one cable and belt such that said tension controlling means controls whether said at least one cable and belt are held in a taut state; and

(5) means responsive to said first electric signal for controlling said mechanical connection by controlling said tension controlling means;

wherein

(1) In a taut state, said at least one cable and belt transmit torque from said mechanically actuated control device to said first disk;

(2) In a slack state, said at least one cable and belt do not transmit torque from said mechanically actuated control device to said first disk; and

(3) said first electric signal causes said tension controlling means to cause the transition from a taut state to a slack state, thereby de-coupling onboard pilot actions from said at least one mechanical actuator.

28. The apparatus defined in claim 27, wherein said tension controlling means includes:

(1) at least one wheel with a circumferential groove through which said at least one cable and belt pass; and

(2) an electromagnetic actuating mechanism, which causes said first electric signal to alter the position of said at least one wheel;

wherein

(1) the position of the center of said at least one wheel determines the tension of said at least one cable and belt;

and

(2) said first electric signal causes said electromagnetic actuating mechanism to alter the position of said wheel such that said at least one cable and belt transition from a taut state to a slack state.

29. The apparatus defined in claim 1, wherein means (c) includes:

(1) two disks each having a center hole, a first one of said disks being linked by a first mechanical coupling to said alternate source of control such that said first disk rotates in response to actions of said alternate source of control, and a second one of said disks being mechanically coupled to said at least one actuator such that the rotation of said second disk causes said actuator to move said at least one of said throttle and said control surface;

(2) a rod positioned to pass through said center hole in each of said first disk and said second disk, said rod fixed to said first disk and said second disk such that the angular rotation of said first disk is identical to the angular rotation of said second disk;

(3) a first mechanical coupling including at least one of a cable and a belt for transmitting torque from said alternate source of control to said first disk;

(4) tension controlling means positioned to control the path of said at least one cable and belt such that said tension controlling means controls whether said at least one cable and belt are held in a taut state; and

(5) means responsive to said first electric signal for controlling said mechanical connection by controlling said tension controlling means;

wherein

(1) In a taut state, said at least one cable and belt transmit torque from said alternate source of control to said first disk;

(2) In a slack state, said at least one cable and belt do not transmit torque from said alternate source of control to said first disk; and

(3) said first electric signal causes said tension controlling means to cause the transition from a slack state to a taut state, thereby coupling said alternate source of control to said at least one mechanical actuator.

30. The apparatus defined in claim 29, wherein said tension controlling means includes:

(1) at least one wheel with a circumferential groove through which said at least one cable and belt pass; and

(2) an electromagnetic actuating mechanism, which causes said electric signal to alter the position of said at least one wheel;

wherein

(1) the position of the center of said at least one wheel determines the tension of said at least one cable and belt; and

(2) said first electric signal causes said electromagnetic actuating mechanism to alter the position of said wheel such that said at least one cable and belt transition from a slack state to a taut state.

31. The apparatus defined in claim 27, further comprising:

(6) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(7) means responsive to said second electric signal for controlling said mechanical connection by controlling said tension controlling means;

wherein said second electric signal causes said tension controlling means to cause the transition from a slack state to a taut state, thereby re-coupling said mechanically actuated control device to said at least one mechanical actuator.

32. The apparatus defined in claim 31, wherein said tension controlling means includes:

(1) at least one wheel with a circumferential groove through which said at least one cable and belt pass; and

(2) an electromagnetic actuating mechanism, which causes said electric signal to alter the position of said at least one wheel;

wherein

(1) the position of the center of said at least one wheel determines the tension of said at least one cable and belt; and

(2) said second electric signal causes said electromagnetic actuating mechanism to alter the position of said wheel such that said at least one cable and belt transition from a slack state to a taut state.

33. The apparatus defined in claim 29, further comprising:

(6) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(7) means responsive to said second electric signal for controlling said mechanical connection by controlling said tension controlling means;

wherein said second electric signal causes said tension controlling means to cause the transition from a taut state to a slack state, thereby de-coupling said alternate source of control from said at least one mechanical actuator.

34. The apparatus defined in claim 33 wherein said tension controlling means includes:

(1) at least one wheel with a circumferential groove through which said at least one cable and belt pass; and

(2) an electromagnetic actuating mechanism, which causes said electric signal to alter the position of said at least one wheel;

wherein

(1) the position of the center of said at least one wheel determines the tension of said at least one cable and belt; and

(2) said second electric signal causes said electromagnetic actuating mechanism to alter the position of said wheel such that said at least one cable and belt transition from a taut state to a slack state.

35. The apparatus defined in claim 1, wherein means (b) includes:

(1) two disks each having parallel surfaces and a common center line, a first one of said disks being mechanically coupled to said mechanically actuated control device such that said first disk rotates in response to on-board pilot actions upon said control device, and a second one of said disks being mechanically coupled to said at least one actuator such that the rotation of said second disk causes said actuator to move said at least one of said throttle and said control surface;

(2) first mechanical means for the transmission of torque from the rotation of said first disk to said second disk;

(3) second mechanical means for selectively controlling the transmission of said torque from said first disk to said second disk; and

(4) means responsive to said first electric signal for controlling said second mechanical means for selectively coupling the rotational motion of said first disk to said second disk;

wherein

(1) in a first apparatus state, said second mechanical means couples the rotation of said first disk to the rotation of said second disk via said first mechanical means, thereby mechanically coupling onboard pilot actions to said at least one mechanical actuator;

(2) in a second apparatus state, said second mechanical means de-couples the rotation of said first disk from the rotation of said second disk, thereby de-coupling onboard pilot actions from said at least one mechanical actuator; and

(3) said first electric signal causes said second mechanical means to cause the transition from said first apparatus state to said second apparatus state.

36. The apparatus defined in claim 35, wherein said first mechanical means comprises a fluid containing chamber allowing the transmission of torque from said first disk, to said fluid and thence to said second disk, and wherein said second mechanical means:

(1) in a first chamber state allows said transmission; and

(2) in a second chamber state does not allow said transmission.

37. The apparatus defined in claim 36, wherein said fluid containing chamber forms a clutch.

38. The apparatus defined in claim 1, wherein means (c) includes:

(1) two disks each having parallel surfaces and a common center line, a first one of said disks being mechanically coupled to said alternate source of control such that said first disk rotates in response to actions of said alternate source of control, and a second one of said disks being mechanically coupled to said at least one actuator such that the rotation of said second disk causes said actuator to move said at least one of said throttle and said control surface;

(2) first mechanical means for the transmission of torque from the rotation of said first disk to said second disk;

(3) second mechanical means for selectively controlling the transmission of said torque from said first disk to said second disk; and

(4) means responsive to said first electric signal for controlling said second mechanical means for selectively coupling the rotational motion of said first disk to said second disk;

wherein

(1) in a first apparatus state, said second mechanical means de-couples the rotation of said first disk from the rotation of said second disk via said first mechanical means, thereby mechanically uncoupling said alternate source of control from said at least one mechanical actuator;

(2) in a second apparatus state, said second mechanical means couples the rotation of said first disk to the rotation of said second disk, thereby coupling said alternate source of control to said at least one mechanical actuator; and

(3) said first electric signal causes said second mechanical means to cause the transition from said first apparatus state to said second apparatus state.

39. The apparatus defined in claim 38, wherein said first mechanical means comprises a fluid containing chamber allowing the transmission of torque from said first disk, to said fluid and thence to said second disk, and wherein said second mechanical means:

(1) in a first chamber state allows said transmission; and

(2) in a second chamber state does not allow said transmission.

40. The apparatus defined in claim 39, wherein said fluid containing chamber forms a clutch.

41. The apparatus defined in claim 35, further comprising:

(5) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(6) means responsive to said second electric signal for controlling said second mechanical means for re-coupling the rotational motion of said first disk to said second disk;

wherein said second electric signal causes said second mechanical means to cause the transition from said second apparatus state to said first apparatus state.

42. The apparatus defined in claim 41, wherein said first mechanical means comprises a fluid containing chamber allowing the transmission of torque from one of said first disk, to said fluid and thence to said second disk, and wherein said second mechanical means:

(1) in a first chamber state allows said transmission; and

(2) in a second chamber state does not allow said transmission.

43. The apparatus defined in claim 42, wherein said fluid containing chamber forms a clutch.

44. The apparatus defined in claim 38, further comprising:

(5) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(6) means responsive to said second electric signal for controlling said second mechanical means for de-coupling the rotational motion of said first disk from said second disk;

wherein said second electric signal causes said second mechanical means to cause the transition from said second apparatus state to said first apparatus state.

45. The apparatus defined in claim 44, wherein said first mechanical means comprises a fluid containing chamber allowing the transmission of torque from said first disk, to said fluid and thence to said second disk, and wherein said second mechanical means:

(1) in a first chamber state allows said transmission; and

(2) in a second chamber state does not allow said transmission.

46. The apparatus defined in claim 45, wherein said fluid containing chamber forms a clutch.

47. The apparatus defined in claim 1, further comprising:

(1) three disks, a first one of said disks being mechanically coupled to said mechanically actuated control device such that said first disk rotates in response to onboard pilot actions upon said control device, a second one of said disks being mechanically coupled to said alternate source of control, a third one of said disks being mechanically coupled to said at least one actuator such that the rotation of said third disk causes said actuator to move said at least one of said throttle and said control surface;

(2) first mechanical means for the transmission of torque from the rotation of said first disk to said third disk, and from said second disk to said third disk;

(3) second mechanical means for selectively controlling the transmission of said torque from said first disk to said third disk, and from said second disk to said third disk; and

(4) means responsive to said first electric signal for controlling said second mechanical means;

wherein,

(1) in a first apparatus state, said second mechanical means couples the rotation of said first disk to the rotation of said third disk via said first mechanical means, thereby mechanically coupling said on-board pilot to said at least one mechanical actuator;

(2) in a second apparatus state, said second mechanical means couples the rotation of said second disk to the rotation of said third disk via said first mechanical means, thereby mechanically coupling said alternate source of control to said at least one mechanical actuator;

(3) said first electric signal causes said second mechanical means to cause a transition from said first apparatus state to said second apparatus state, thereby disabling on-board pilot control and enabling said alternate source of control.

48. The apparatus defined in claim 47, wherein said first mechanical means comprises a fluid containing chamber, said chamber allowing the transmission of torque from said first disk to said fluid and thence to said third disk, and from said second disk to said fluid and thence to said third disk, and wherein said second mechanical means:

(1) in a first apparatus state allows transmission of torque from said first disk to said third disk, and does not allow transmission of torque from said second disk to said third disk; and

(2) in a second apparatus state allows transmission of torque from said second disk to said third disk, and does not allow transmission of torque from said first disk to said third disk.

49. The apparatus defined in claim 48, wherein said fluid containing chamber forms a clutch.

50. The apparatus defined in claim 47, wherein:

(a) said first disk is further mechanically coupled to a first gear wheel such that rotation of said first disk causes rotation of said first gear wheel;

(b) said second disk is further mechanically coupled to a second gear wheel such that rotation of said second disk causes rotation of said second gear wheel;

(c) said third disk is further mechanically coupled to a third gear wheel such that rotation of said third gear wheel causes rotation of said third disk;

(d) said first mechanical means controls the relative position of said first gear wheel and said third gear wheel, and the relative position of said second gear wheel and said third gear wheel;

(e) said second mechanical means;

(1) in a first apparatus state causes transmission of torque from said first gear wheel to said third gear wheel by causing the meshing of said respective gear wheels, thereby mechanically coupling said on-board pilot to said at least one mechanical actuator; and

(2) in a second apparatus state causes transmission of torque from said second gear wheel to said third gear wheel by causing the meshing of said respective gear wheels, thereby mechanically coupling said alternate source of control to said at least one mechanical actuator.

51. The apparatus defined in claim 20, wherein:

(a) said first disk is further mechanically coupled to a first gear wheel such that rotation of said first disk causes rotation of said first gear wheel;

(b) said second disk is further mechanically coupled to a second gear wheel such that rotation of said second gear wheel causes rotation of said second disk;

(c) said first mechanical connection controls the relative position of said first gear wheel and said second gear wheel;

(d) said means (5);

in a first apparatus state causes transmission of torque from said first gear wheel to said second gear wheel by causing the meshing of said gear wheels, thereby mechanically coupling said on-board pilot to said at least one mechanical actuator; and

(2) in a second apparatus state prevents transmission of torque from said first gear wheel to said second gear wheel by preventing the meshing of said gear wheels, thereby mechanically uncoupling said on-board pilot from said at least one mechanical actuator.

52. The apparatus defined in claim 47, further comprising:

(5) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(6) means responsive to said second electric signal for controlling said second mechanical means;

wherein said second electric signal causes said second mechanical means to cause the transition from said second apparatus state to said first apparatus state, thereby re-enabling on-board pilot control and disabling said alternate source of control.

53. The apparatus defined in claim 52, wherein said first mechanical means comprises a fluid containing chamber, said chamber allowing the transmission of torque from said first disk to said fluid and thence to said third disk, and from said second disk to said fluid and thence to said third disk, and wherein said second mechanical means:

(1) in a first apparatus state allows transmission of torque from said first disk to said third disk; and

(2) in a second apparatus state allows transmission of torque from said second disk to said third disk.

54. The apparatus defined in claim 53, wherein said fluid containing chamber forms a clutch.

55. The apparatus define in claim 35, further comprising:

(1) two alternate source disks each having parallel surfaces and a common center line, a first one of said alternate source disks being mechanically coupled to said alternate source of control such that said first alternate source disk rotates in response to actions of said alternate source of control, and a second one of said alternate source disks being mechanically coupled to said at least one actuator such that the rotation of said second alternate source disk causes said actuator to move said at least one of said throttle and said control surface;

(2) third mechanical means for the transmission of torque from the rotation of said first alternate source disk to said second alternate source disk;

(3) fourth mechanical means for selectively controlling the transmission of said torque from said first alternate source disk to said second alternate source disk; and

(4) two remote pilot disks each having parallel surfaces and identical center lines, a first remote pilot disks being mechanically coupled to said electromechanical actuator such that said first remote pilot disk rotates in response to actions of said receiving means, and a second remote pilot disk being mechanically coupled to said alternate source of control;

(5) fifth mechanical means for the transmission of torque from the rotation of said first remote pilot disk to said second remote pilot disk;

(6) sixth mechanical means for selectively controlling the transmission of torque from said first remote pilot disk to said second remote pilot disk; and

(7) two autopilot/flight control system disks, said autopilot/flight control system disks having parallel surfaces and identical center lines, a first autopilot/flight control system disk being mechanically coupled to at least one of said autopilot and said flight control system such that said first autopilot/flight control system disk rotates in response to actions of said at least one autopilot and flight control system, and a second autopilot/flight control system disk being mechanically coupled to said alternate source of control;

(8) seventh mechanical means for the transmission of torque from the rotation of said first autopilot/flight control system to said second autopilot/flight control system disk;

(9) eighth mechanical means for selectively controlling the transmission of torque from said first autopilot/flight control system disk to said second autopilot/flight control system disk;

(10) means further responsive to said first electric signal for coupling the rotational motion of said first alternate source disk to said second alternate source disk;

(11) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition;

(12) means responsive to said second electric signal for (i) re-coupling the rotational motion of said first disk to said second disk, and (ii) de-coupling the rotational motion of said first alternate source disk from said second alternate source disk;

(13) means for producing a third electric signal to cause a remote pilot control state during an emergency condition;

(14) means for producing fourth electric signal to cause an autopilot/flight control system control state during an emergency condition;

(15) means responsive to said third electric signal for (i) reversibly coupling the rotational motion of said first remote pilot disk to said second remote pilot disk, and (ii) de-coupling the rotational motion of said first autopilot/flight control system disk from said second autopilot/flight control system disk; and

(16) means responsive to said fourth electric signal for (i) reversibly coupling the rotational motion of said first autopilot/flight control system disk to said second autopilot/flight control system disk, and (ii) de-coupling the rotational motion of said first remote pilot disk from said second remote pilot disk;

wherein

(1) in a first apparatus state, said fourth mechanical means de-couples the rotation of said first alternate source disk to the rotation of said second alternate source disk via said third mechanical means, thereby mechanically de-coupling said alternate source of control from said at least one mechanical actuator;

(2) in a second apparatus state, said fourth mechanical means couples the rotation of said first alternate source disk to the rotation of said second alternate source disk, thereby coupling said alternate source of control to said at least one mechanical actuator;

(3) said first electric signal further causes said fourth mechanical means to cause the transition from said first apparatus state to said second apparatus state;

(4) said second electric signal causes the transition from said second apparatus state to said first apparatus state;

(5) in a first alternate source state, said sixth mechanical means couples the rotation of said first remote pilot disk to the rotation of said second remote pilot disk via said fifth mechanical means, thereby mechanically coupling said electromechanical actuator to said alternate source of control, and said eighth mechanical means de-couples the rotation of said first autopilot/flight control system disk from the rotation of said second autopilot/flight control system disk via said seventh mechanical means, thereby mechanically de-coupling said autopilot/flight control system from said alternate source of control;

(6) in a second alternate source state said sixth mechanical means de-couples the rotation of said first remote pilot disk from the rotation of said second disk via said fifth mechanical means, thereby mechanically de-coupling said electromechanical actuator from said alternate source of control, and said eighth mechanical means couples the rotation of said first autopilot/flight control system disk to the rotation of said second autopilot/flight control system disk via said seventh mechanical means, thereby mechanically coupling said autopilot/flight control system to said alternate source of control;

(7) said third electric signal causes the transition from said second alternate source state to said first alternate source state; and

(8) said fourth electric signal causes the transition from said first alternate source state to said second alternate source state.

56. The apparatus defined in claim 55, wherein

(1) said first mechanical means comprises a fluid containing chamber, said chamber allowing the transmission of torque from said first disk, to said fluid and thence to said second disk, and wherein said second mechanical means:

(a) in a first apparatus state allows said transmission from said first disk to said second disk; and

(b) in a second apparatus state does not allow said transmission from said first disk to said second disk;

(2) said third mechanical means comprises a fluid containing chamber, said chamber allowing the transmission of torque from said first alternate source disk, to said fluid and thence to said second alternate source disk, and wherein said fourth mechanical means;

(a) in a second apparatus state allows said transmission from said first alternate source disk, to said second alternate source disk; and

(b) in a first apparatus state does not allow said transmission from said first alternate source disk, to said second alternate source disk;

(3) said fifth mechanical means comprises a fluid containing chamber, said chamber allowing the transmission of torque from said first remote pilot disk, to said fluid and thence to said second remote pilot disk, and wherein said sixth mechanical means;

(a) in a first alternate source state allows said transmission from said first remote pilot disk, to said second remote pilot disk; and

(b) in a second alternate source state does not allow said transmission from said first remote pilot disk, to said second remote pilot disk;

(4) said seventh mechanical means comprises a fluid containing chamber, said chamber allowing the transmission of torque from said first autopilot/flight control system pilot disk, to said fluid and thence to said second autopilot/flight control system disk; and

(5) said eighth mechanical means;

(a) in a second alternate source state allows said transmission from said first autopilot/flight control system pilot disk, to said second autopilot/flight control system disk; and

(b) in a first alternate source state does not allow said transmission from said first autopilot/flight control system pilot disk, to said second autopilot/flight control system disk;

wherein

(1) in a first control state, said second mechanical means and said fourth mechanical means are in a first apparatus state, allowing on-board pilot control of said aircraft;

(2) in a second control state, said second mechanical means and said fourth mechanical means are in a second apparatus state, and said sixth mechanical means and said eighth mechanical means are in a first alternate source state, allowing remote pilot control of said aircraft; and

(3) in a third control state, said second mechanical means and said fourth mechanical means are in a second apparatus state, and said sixth mechanical means and said eighth mechanical means are in a second alternate source state, allowing at least one of said autopilot and said flight control system control of said aircraft.

57. The apparatus defined in claim 56, wherein each of said fluid containing chambers forms a clutch.

58. The apparatus defined in claim 1, further comprising:

(1) three disks, a first disk being mechanically coupled to said mechanically actuated control device such that said first disk rotates in response to on-board pilot actions upon said control device, a second disk being mechanically coupled to said alternate source of control, a third disk being mechanically coupled to said at least one actuator such that the rotation of said third disk causes said actuator to move said at least one of said throttle and said control surface;

(2) first mechanical means for the transmission of torque from the rotation of said first disk to said third disk, and from said second disk to said third disk;

(3) second mechanical means for selectively controlling the transmission of said torque from said first disk to said third disk, and from said second disk to said third disk;

(4) means further responsive to said first electric signal for controlling said second mechanical means;

(5) three additional disks, a first additional disk being mechanically coupled to said receiving means such that said first additional disk rotates in response to remote pilot actions, a second additional disk being mechanically coupled to said autopilot/flight control system, a third additional disk being mechanically coupled to said alternate source of control such that the rotation of said third additional disk causes said alternate source of control to cause the rotation of said second disk;

(6) third mechanical means for the transmission of torque from the rotation of said first additional disk to said third additional disk, and from said second additional disk to said third additional disk;

(7) fourth mechanical means for selectively controlling the transmission of said torque from said first additional disk to said third additional disk, and from said second additional disk to said third additional disk; and

(8) means for producing a remote pilot enabling electric signal to cause a remote pilot control state during an emergency condition;

(9) means for producing an autopilot/flight control system enabling electric signal to cause an autopilot/flight control system control state during an emergency condition; and

(10) means further responsive to said remote pilot enabling electric signal and said autopilot/flight control system enabling signals for controlling said second and said fourth mechanical means;

wherein,

(1) in an on-board pilot control state, said second mechanical means couples the rotation of said first disk to the rotation of said third disk via said first mechanical means, thereby mechanically coupling said on-board pilot to said at least one mechanical actuator;

(2) in a remote pilot control state, (a) said first electric signal causes said second mechanical means to couple the rotation of said second disk to the rotation of said third disk via said first mechanical means, thereby mechanically coupling said alternate source of control to said at least one mechanical actuator; and

(b) said remote pilot enabling electric signal causes said fourth mechanical means to couple the rotation of said first additional disk to the rotation of said third additional disk via said third mechanical means, thereby mechanically coupling said receiving means to said alternate source of control; and

(3) in an autopilot/flight control system control state, (a) said first electric signal causes said second mechanical means to couple the rotation of said second disk to the rotation of said third disk via said first mechanical means, thereby mechanically coupling said alternate source of control to said at least one mechanical actuator; and

(b) said autopilot/flight control system enabling signal causes said fourth mechanical means to couple the rotation of said second additional disk to the rotation of said third additional disk via said third mechanical means, thereby mechanically coupling said autopilot/flight control system to said alternate source of control.

59. The apparatus defined in claim 58, wherein

(a) said first mechanical means comprises a first fluid-containing chamber, said first fluid-containing chamber allowing the transmission of torque from said first disk to a first fluid and thence to said third disk, and from said second disk to said first fluid and thence to said third disk;

(b) said second mechanical means;

(1) in an onboard pilot control state allows transmission of torque from said first disk to said third disk and does not allow transmission of torque from said second disk to said third disk; and

(2) in a remote pilot control state and in an autopilot/flight control system control state, allows transmission of torque from said second disk to said third disk and does not allow transmission of torque from said first disk to said third disk;

(c) said third mechanical means comprises a second fluid-containing chamber, said second fluid-containing chamber allowing the transmission of torque from said first additional disk to a second fluid and thence to said third additional disk, and from said second additional disk to said second fluid and thence to said third additional disk;

(d) said fourth mechanical means;

(1) in a remote pilot control state allows transmission of torque from said first additional disk to said third additional disk and does not allow transmission of torque from said second additional disk to said third additional disk; and

(2) in an autopilot/flight control system control state, allows transmission of torque from said second additional disk to said third additional disk and does not allow transmission of torque from said first additional disk to said third additional disk.

60. The apparatus defined in claim 59, wherein each of said fluid containing chambers forms a clutch.

61. The apparatus defined in claim 58, further comprising:

(11) means for producing a second electric signal indicative of an all-clear condition upon the termination of said emergency condition; and

(12) means responsive to said second electric signal for controlling said second mechanical means;

wherein said second electric signal causes said second mechanical means to cause the transition from said remote pilot control state to said on-board pilot control state, and from said autopilot/flight control system control state to said on-board pilot control state, thereby re-enabling on-board pilot control.

62. The apparatus defined in claim 61, wherein

(a) said first mechanical means comprises a first fluid-containing chamber, said first fluid-containing chamber allowing the transmission of torque from said first disk to a first fluid and thence to said third disk, and from said second disk to said first fluid and thence to said third disk;

(b) said second mechanical means;

(1) in an onboard pilot control state allows transmission of torque from said first disk to said third disk and does not allow transmission of torque from said second disk to said third disk; and

(2) in a remote pilot control state and in an autopilot/flight control system control state, allows transmission of torque from said second disk to said third disk and does not allow transmission of torque from said first disk to said third disk;

(c) said third mechanical means comprises a second fluid-containing chamber, said second fluid-containing chamber allowing the transmission of torque from said first additional disk to a second fluid and thence to said third additional disk, and from said second additional disk to said second fluid and thence to said third additional disk;

(d) said fourth mechanical means;

(1) in a remote pilot control state allows transmission of torque from said first additional disk to said third additional disk and does not allow transmission of torque from said second additional disk to said third additional disk; and

(2) in an autopilot/flight control system control state, allows transmission of torque from said second additional disk to said third additional disk and does not allow transmission of torque from said first additional disk to said third additional disk.

63. The apparatus defined in claim 62, wherein each of said fluid containing chambers forms a clutch.

64. The apparatus defined in claim 1, further comprising:

(1) four disks, a first one of said disks being mechanically coupled to said mechanically actuated control device such that said first disk rotates in response to on-board pilot actions upon said control device, a second one of said disks being mechanically coupled to said receiving means, a third one of said disks being mechanically coupled to at least one of said autopilot and said flight control system, and a fourth one of said disks being mechanically coupled to said at least one actuator such that the rotation of said fourth disk causes said actuator to move said at least one of said throttle and said control surface;

(2) first mechanical means for the transmission of torque from the rotation of said first disk to said fourth disk, said second disk to said fourth disk, and said third disk to said fourth disk;

(3) second mechanical means for selectively controlling the transmission of said torque from said first disk to said fourth disk, from said second disk to said fourth disk and from said third disk to said fourth disk;

(4) means for producing a second electric signal indicative of the choice of said alternate source of control; and

(5) means responsive to said first, and said second electric signals for controlling said second mechanical means;

wherein,

(1) in a first apparatus state, said second mechanical means couples the rotation of said first disk to the rotation of said fourth disk via said first mechanical means, thereby mechanically coupling said on-board pilot to said at least one mechanical actuator;

(2) in a second apparatus state, said second mechanical means couples the rotation of said second disk to the rotation of said fourth disk via said first mechanical means, thereby mechanically coupling said remote pilot to said at least one mechanical actuator;

(3) in a third apparatus state, said second mechanical means couples the rotation of said third disk to the rotation of said fourth disk via said first mechanical means, thereby mechanically coupling said at least one of said autopilot and said flight control system to said at least one mechanical actuator;

(4) a first type of said second electric signal causes said second mechanical means to transmit torque from said second disk to said fourth disk;

thereby allowing said remote pilot to control said aircraft;

(5) a second type of said second electric signal causes said second mechanical means to transmit torque from said third disk to said fourth disk, thereby allowing at least one of said autopilot and said flight control system to control said aircraft.

65. The apparatus defined in claim 64, wherein said first mechanical means comprises a fluid containing chamber, said chamber allowing the transmission of torque from one of said first disk, said second disk and said third disk to said fluid and thence to said fourth disk and wherein said second mechanical means selects one of said first disk, said second disk and said third disk for said transmission.

66. The apparatus defined in claim 65, wherein said fluid containing chamber forms a clutch.

67. The apparatus defined in claim 64, wherein:

(a) said first disk is further mechanically coupled to a first gear wheel such that rotation of said first disk causes rotation of said first gear wheel;

(b) said second disk is further mechanically coupled to a second gear wheel such that rotation of said second disk causes rotation of said second gear wheel;

(c) said third disk is further mechanically coupled to a third gear wheel such that rotation of said third disk causes rotation of said third gear wheel;

(d) said fourth disk is further mechanically coupled to a fourth gear wheel such that rotation of said fourth gear wheel causes rotation of said fourth disk;

(e) said first mechanical means controls the relative position of said first gear wheel and said fourth gear wheel, the relative position of said second gear wheel and said fourth gear wheel, and the relative position of said third gear wheel and said fourth gear wheel;

whereby;

(1) in a first apparatus state said second mechanical means causes transmission of torque from said first gear wheel to said fourth gear wheel by causing the meshing of said respective gear wheels, thereby mechanically coupling said on-board pilot to said at least one mechanical actuator;

(2) in a second apparatus state said first type of second electric signal causes said second mechanical means to cause transmission of torque from said second gear wheel to said fourth gear wheel by causing the meshing of said respective gear wheels, thereby mechanically coupling said remote pilot to said at least one mechanical actuator; and

(3) in a third apparatus state said second type of second electric signal causes said second mechanical means to cause transmission of torque from said third gear wheel to said fourth gear wheel by causing the meshing of said respective gear wheels, thereby mechanically coupling said autopilot/flight control system to said at least one mechanical actuator.

68. Apparatus for disabling on-board pilot operation of an aircraft and transferring aircraft operation to an alternate source of control, said aircraft having at least one manually actuated control device for on-board human pilot control of at least one mechanical actuator, said actuator causing movement of one of (1) an aircraft engine throttle and (2) an aircraft attitude control surface, said at least one actuator being mechanically connected to both (1) said at least one control device, and (2) said alternate source of control, said alternate source of control comprising at least one of an autopilot, a flight control system and means for receiving control signals transmitted from a remote station, said signals representing commands by an off-aircraft human pilot, said apparatus comprising, in combination:

(a) means for producing a first electric signal indicative of an emergency condition requiring the disabling of on-board pilot control of said aircraft;

(b) means for mechanically disconnecting said mechanical connection between said at least one control device and said at least one actuator in response to said first electric signal indicative of said emergency condition; and

wherein said alternate source of control controls said aircraft following the receipt of said first electric signal.

69. The apparatus defined in claim 68, wherein means (b) includes (1) at least one removable pin extending through holes in at least two mechanical movable members, each movable member forming a part of one of said at least one control device and said at least one actuator, respectively, and (2) means responsive to said first electric signal for removing said pin, thereby to sever the connection between said movable members, wherein the connection between said alternate source of control and said at least one actuator is maintained following the removal of said at least one pin.

70. The apparatus defined in claim 68, wherein means (b) includes (1) at least one de-couple-able segment linking two portions of a mechanical member that extends between said at least one control device and said at least one actuator, and (2) means responsive to said first electric signal for de-coupling said segment, thereby to de-couple the connection between said at least one control device and said at least one actuator, wherein the connection between said alternate source of control and said at least one actuator is maintained following the de-coupling of said segment.

71. The apparatus defined in claim 70, wherein de-coupling means includes means responsive to said first electric signal for severing said segment, thereby to sever the connection between said at least one control device and said at least one actuator.

72. The apparatus defined in claim 70, wherein said de-coupling means includes means responsive to said first electric signal for removing said segment, thereby to sever the connection between said at least one control device and said at least one actuator.

73. The apparatus defined in claim 68, wherein said receiving means further comprises converting means for converting said received control signals to at least one of translational and rotational motion.

74. The apparatus defined in claim 73 wherein said converting means includes a servo motor linked to said at least one actuator by at least one of a cable, a chain, a cord, and at least one gear.

75. The apparatus defined in claim 68, wherein said mechanical actuator is at least one of a hydraulic and a pneumatic actuator which receives a fluid under pressure from a fluid line, and wherein means (b) includes a valve arranged in said fluid line, responsive to said first electric signal, for interrupting the flow of fluid.