Aircraft airbag protection apparatus and method

• US 5,547,149 A
• Filed: 05/16/1994
• Issued: 08/20/1996
• Est. Priority Date: 05/16/1994
• Status: Expired due to Fees

• Current Assignee: Flight Safety Systems Incorporated
• Original Assignee: Flight Safety Systems Incorporated
• Inventors: Kalberer, Robert C., Goor, Dan
• Primary Examiner(s): Kashnikow, Andres
• Assistant Examiner(s): DINH, TIEN QUANG
• Application Number:
  US08/242,936
• Time in Patent Office: 827 Days
• Field of Search: 244/121, 244/118.5, 280/728.1, 280/728 R, 280/728 L, 280/728 A, 280/729, 280/730.1, 280/730 R, 280/730.2, 280/731
• US Class Current: 244/121
• CPC Class Codes: B64D 2201/00 Airbags mounted in aircraft for any use
• CPC Class Codes: B64D 25/00 Emergency apparatus or devices, not otherwise provided for parachutes B64D17/00, B64D19/00; jettisoning of fuel tanks or fuel per se B64D37/00; specially adapted for protection against criminal attack, e.g. anti-hijacking systems B64D45/0015 ; safety belts or body harnesses in general A62B35/00; safety belts or body harnesses for land vehicles B60R22/00; jettisonable parts of fuselage facilitating emergency escape B64C

Abstract

Airbags are positioned in a general aviation aircraft cockpit relative to a control yoke, a pilot, and a front seat passenger. Airbag actuation is controlled by a adaptive programmable controller such as a microcomputer. Airbag actuation is based upon information that the controller receives from multiple acceleration sensors. The outputs of the acceleration sensors are subjected to thresholding techniques, such as output signal weighting and/or majority voting. A programmable threshold is adaptively established for the controller based upon unique aircraft parameters, such as weight, altitude, angle of attack, ground and/or air speed, etc. The controller ignores all acceleration sensor inputs that do not meet this adaptive threshold. Thus, airbag actuation takes place only when a sufficient acceleration event occurs concurrently with the presence or absence of defined aircraft parameters that establish a proper threshold for the acceleration event. Airbag inflation includes a controllable delay that is used to customize airbag inflation to particular aircraft parameters, such as ground/air speed and weight.

Claims

1. Apparatus for controlling the inflation of an airbag in an aircraft, the aircraft including a control member for manual movement by a pilot to facilitate control of the aircraft, the apparatus comprising;

first means for sensing that the aircraft has experienced an excessive acceleration force, and for generating a control signal in response to said acceleration force,

an airbag mounted relative to said control member and relative to the pilot, said airbag being responsive to said control signal,

second means for sensing an aircraft operating parameter, and

means responsive to said second means and operable to prevent response of said airbag to said control signal as a function of the presence of said operating parameter.

2. The apparatus of claim 1 wherein said second means operates to sense aircraft altitude, said second means operating to prevent response of said airbag to said control signal as a function of said aircraft altitude.

3. The apparatus of claim 2 wherein said second means operates to sense aircraft speed, said second means operating to prevent response of said airbag to said control signal as a function of said aircraft speed.

4. The apparatus of claim 3 wherein said second means operates to sense the aircraft angle of attack relative to horizontal, said second means operating to prevent response of said airbag to said control signal as a function of said aircraft angle of attack.

5. The apparatus of claim 4 including means whereby response of said airbag to said control signal may be manually inhibited.

6. The apparatus of claim 4 including;

controllable delay means for controlling a time parameter in the inflation of said airbag, and

means responsive to an aircraft operating parameter for controlling said delay means.

7. Processor controlled aircraft airbag actuation apparatus selectively operable to determine if aircraft operation conditions are appropriate for activating an airbag assembly, the apparatus comprising;

an airbag assembly mounted relative to an aircraft seat,

first sensing means for sensing that the aircraft has experienced an excessive acceleration force, and for generating a first control signal in response to said excessive force,

second sensing means for sensing an operating parameter of the aircraft, and for providing a second control signal as a function of said operating parameter,

processor means receiving said first control signal and said second control signal as first and second inputs, and having an output for actuating said airbag assembly in response to said first and second inputs, and

programmed means for said processor means operable to cause said processor means to respond to said second control signal in a manner to prevent actuation of said airbag assembly in response to said first control signal when said aircraft operating parameter indicates a likelihood for continued control of the aircraft.

8. The apparatus of claim 7 wherein said operating parameter is selected from the group aircraft weight, aircraft altitude, aircraft speed, and/or aircraft angle of attack.

9. The apparatus of claim 7 wherein said second sensing means comprises;

a plurality of acceleration force sensors, and

verification means for providing said second control signal as a function of a majority of said plurality of force sensors detecting an aircraft acceleration force.

10. The apparatus of claim 7 including delay means for delaying actuation of said airbag.

11. The apparatus of claim 10 wherein said delay means is a controllable delay means wherein said delay means is controlled as a function of an aircraft operating parameter.

12. The apparatus of claim 7 including;

emergency locator means, and

said processor means having a second output operable to activate said emergency locator means upon the occurrence of said first control signal.

13. The apparatus of claim 7 wherein said operating parameter of the aircraft is sensed in real time.

14. A method for controlling aircraft airbag inflation, the aircraft including a control member for manual movement by a pilot to facilitate control of the aircraft, the apparatus comprising;

providing first means for sensing that the aircraft has experienced an acceleration force, and for generating a control signal in response to said force,

providing an airbag mounted relative to said control member and relative to the pilot, said airbag normally being responsive to said control signal,

providing second means for sensing an operating parameter of the aircraft, and

providing means responsive to said second means and operable to prevent response of said airbag to said control signal as a function of said operating parameter.

15. The method of claim 14 wherein said second means operates to sense aircraft altitude, and wherein said second means operates to prevent response of said airbag to said control signal as a function of aircraft altitude.

16. The method of claim 15 wherein said second means also operates to sense aircraft speed, and wherein said second means operates to prevent response of said airbag to said control signal as a function of both aircraft altitude and aircraft speed.

17. The method of claim 16 wherein said second means also operates to sense aircraft angle of attack relative to horizontal, and wherein said second means operates to prevent response of said airbag to said control signal as a function of aircraft weight, altitude, aircraft speed, and/or aircraft angle of attack.

18. The method of claim 14 including the steps of;

providing a controllable delay means for controlling the response of said airbag to said control signal, and

controlling said delay means as a function of an aircraft operating parameter.

19. The method of claim 14 including the step of;

providing a manual override whereby response of said airbag to said control signal may be selectively inhibited.

20. The method of claim 19 including the step of;

providing means indicating that response of said airbag to said control signal has been inhibited.

21. The method of claim 14 including the steps of;

providing an emergency locator transmitter, and

activating said transmitter as a function of said control signal.

22. A method for selectively inhibiting activation of an aircraft airbag assembly when aircraft operation conditions are appropriate for enabling a pilot to attempt to retain aircraft control, comprising the steps of;

providing an airbag assembly mounted relative to the pilot,

providing first sensing means for sensing that the aircraft has experienced an excessive acceleration force, and for generating a first control signal in response to said force,

providing second sensing means for sensing an operating parameter of the aircraft, and for providing a second control signal in response to said operating parameter,

providing control means receiving said first control signal and said second control signal as first and second inputs, said control means having an output for actuating said airbag assembly in response to said first and second inputs, and

providing means whereby said control means operates to respond to said second control signal in a manner to prevent actuation of said airbag assembly in response to said first control signal when said aircraft operating parameter indicates a likelihood that the pilot can retain control of the aircraft.

23. The method of claim 22 wherein said operating parameter is selected from the group aircraft weight, aircraft altitude, aircraft speed, aircraft angle of attack.

24. The method of claim 22 wherein said step of providing said second sensing means comprises the steps of;

providing a plurality of acceleration sensors, and

providing majority voting means for generating said second control signal as a function of a majority of said plurality of acceleration sensors detecting an excessive aircraft acceleration force.

25. The method of claim 24 including the step of;

providing delay means for delaying actuation of said airbag.

26. The method of claim 24 including the steps of;

providing emergency aircraft locator means, and

providing a second output for said control means operable to activate said emergency aircraft locator means upon the occurrence of said first control signal.

27. The method of claim 22 wherein said operating parameter is sensed in real time.

28. A method for determining when an aircraft airbag assembly is to be activated, comprising the steps of;

providing first means for sensing that the aircraft has experienced an excessive acceleration force, and for generating a control signal in response to said acceleration force,

providing an airbag that is mounted relative to said control member and relative to the pilot, said airbag being responsive to said control signal,

providing second means for sensing an aircraft operating parameter, and

providing means responsive to said second means and operable to prevent response of said airbag to said control signal as a function of the presence of said operating paramter.

29. The method of claim 28 wherein said aircraft first means comprises a plurality of individual aircraft acceleration sensors, each of which provides an acceleration output signal indicative of the magnitude of an aircraft acceleration event, and including the step of;

subjecting said plurality of acceleration output signals from said plurality of acceleration sensors to a signal verification procedure prior to providing said acceleration output signal.

30. The method of claim 29 wherein said signal verification procedure comprises a majority voting procedure.

31. The method of claim 30 including the step of;

providing an output acceleration signal upon the concurrent occurrence of an aircraft acceleration event that is above a given magnitude, and upon said verification procedure indicating that a majority of said sensors have sensed said deceleration event above said given magnitude.

32. The method of claim 31 including the steps of;

providing a controllable time delay for activating said airbag assembly,

providing a plurality of aircraft operational parameter signals that are indicative of a plurality of different aircraft operating parameters, and

controlling said time delay as a function of at least one of said plurality of aircraft operational parameters.

35. The apparatus of claim 32 wherein said second sensing means comprises;

a plurality of acceleration force sensors, and

verification means for providing said second control signal as a function of a majority of said plurality of force sensors detecting excessive aircraft acceleration.

36. The apparatus of claim 35 wherein said second means includes a controllable delay means whose delay time period is controlled as a function of an aircraft operating parameter.

33. Processor controlled aircraft apparatus for activating an airbag assembly and an extendable aircraft control yoke, comprising;

an airbag assembly mounted relative to an extendable aircraft control yoke,

first sensing means for sensing an excessive acceleration force, and for providing a first control signal in response to said force,

second sensing means for sensing an aircraft operating parameter, and for providing a second control signal as a function of said operating parameter,

processor means receiving said first control signal and said second control signal as first and second inputs, said processor means having an output,

said processor means being operable to respond to said first and second control signals to provide a processor output signal only when said aircraft operating parameter indicates that continued aircraft control is unlikely after the occurrence of said force,

first means connecting said processor means output signal to said control yoke to produce extension of said control yoke generally concurrently with the occurrence of said processor means output signal, and

second means connecting said processor means output signal to said airbag assembly to activate said airbag assembly with a time delay relative to the occurrence of said processor means output signal.

34. The apparatus of claim 33 wherein said aircraft operating parameter is selected from the group aircraft weight, aircraft altitude, aircraft speed, aircraft angle of attack.

37. The apparatus of claim 33 wherein said aircraft operating parameter is sensed in real time.

38. Apparatus for activating an aircraft airbag assembly and an extendable aircraft control yoke, comprising;

sensing means for sensing an excessive acceleration force and providing a control signal in response to said force,

first means connecting said control signal to said control yoke to produce extension of said control yoke generally concurrently with the occurrence of said control signal, and

second means connecting said control signal to said airbag assembly to activate said airbag assembly with a time delay relative to the occurrence of said control signal.

39. The apparatus of claim 38 wherein said sensing means comprises;

a plurality of acceleration force sensors, and

verification means for providing said control signal as a function of a majority of said plurality of force sensors detecting an excessive aircraft acceleration force.

40. The apparatus of claim 38 wherein said second means includes a controllable delay means whose delay time period is controlled as a function of an aircraft operating parameter.

41. The apparatus of claim 40 wherein said aircraft operating parameter is sensed in real time.

42. Processor controlled aircraft apparatus for activating an airbag assembly and an extendable aircraft control yoke, comprising;

an airbag assembly mounted relative to an extendable aircraft control yoke,

first sensing means for sensing an excessive acceleration force, and for providing a first control signal in response to said force,

second sensing means for sensing an aircraft operating parameter, and for providing a second control signal as a function of said operating parameter,

a plurality of processor means, each of said processor means receiving said first control signal and said second control signal as first and second inputs, and each of said processor means having an output,

a first of said processor means being operable to respond to said first and second control signals to provide a first processor output signal only when said aircraft operating parameter indicates that continued aircraft control is unlikely after the occurrence of said force,

first means connecting said first processor output signal to said control yoke to produce extension of said control yoke generally concurrently with the occurrence of said first processor output signal,

a second of said processor means receiving said first processor output signal as an enable input, and said second processor means then being operable to respond to said first and second control signals to provide a second processor output signal only when said aircraft operating parameter indicates that continued aircraft control is unlikely after the occurrence of said force, and

processor output signal verification means connecting said first and second processor means output signals to said airbag assembly to activate said airbag assembly with a time delay relative to the occurrence of said first processor means output signal.

43. The apparatus of claim 42 wherein said aircraft operating parameter is selected from the group aircraft weight, aircraft altitude, aircraft speed, aircraft angle of attack.

44. The apparatus of claim 42 wherein said second sensing means comprises;

a plurality of acceleration force sensors, and

verification means for providing said second control signal as a function of a majority of said plurality of force sensors detecting an excessive aircraft acceleration force.

45. The apparatus of claim 42 wherein said processor output signal verification means includes a controllable time delay means whose delay time period is controlled as a function of an aircraft operating parameter.

46. The apparatus of claim 42 wherein said aircraft operating parameter is sensed in real time.

47. Processor controlled aircraft apparatus for activating an airbag assembly and an extendable aircraft control yoke, comprising;

first sensing means for sensing an excessive acceleration force, and for providing a first control signal as a function of said force,

second sensing means for sensing an aircraft operating parameter, and for providing a second control signal as a function of said operating parameter,

a plurality of series arranged processors,

each of said processors receiving said first control signal and said second control signal as first and second inputs, and each of said processors having an output,

each of said processors being operable to respond to said first and second control signals to provide a processor output signal only when said aircraft operating parameter indicates that continued aircraft control is unlikely after the occurrence of said force,

means connecting the processor output signal of said plurality of processors as an enable input to the next processor in said series arranged processors,

means connecting a processor output signal from one of said series arranged processors to said control yoke to produce extension of said control yoke generally concurrently with the occurrence of said first processor output signal, and

processor output signal verification means connecting said processor output signals to said airbag assembly to activate said airbag assembly with a time delay relative to telescoping of said control yoke.

48. The apparatus of claim 47 wherein the processor output signal from said first of said series arranged processors is connected to said control yoke, and wherein the processor output signal from said first of said series arranged processors and the processor output signal from the last of said series arranged processors is connected to said signal verification means.

49. The apparatus of claim 47 wherein the processor output signal from all of said series arranged processors is connected to said signal verification means.

50. The apparatus of claim 47 wherein said processor output signal verification means includes a controllable time delay means whose delay time period is controlled as a function of an aircraft operating parameter.

51. The apparatus of claim 50 wherein said aircraft operating parameter is sensed in real time.