Shock detector and distress beacon for an aircraft incorporating such a detector

• US 5,394,142 A
• Filed: 08/27/1993
• Issued: 02/28/1995
• Est. Priority Date: 09/08/1992
• Status: Expired due to Term

• Current Assignee: Airbus Operations SAS (Airbus SE)
• Original Assignee: Aerospatiale Societe Nationale Industrielle
• Inventors: Dusart, Gerard
• Primary Examiner(s): Swarthout, Brent
• Application Number:
  US08/113,595
• Time in Patent Office: 550 Days
• Field of Search: 340/945, 340/963, 340/981, 340/968, 340/429, 340/467, 340/436, 324/207.24, 73/517 R, 280/735
• US Class Current: 340/981
• CPC Class Codes: G01S 1/68 Marker, boundary, call-sign, or like beacons transmitting signals not carrying directional information
• CPC Class Codes: G08B 1/08 using electric transmission ; transformation of alarm signals to electrical signals from a different medium, e.g. transmission of an electric alarm signal upon detection of an audible alarm signal

Abstract

In order that safety systems, such as distress beacon emitters carried on board an aircraft, can be triggered beth in the case of a very short, violent shock or impact and during a longer, but less violent shock or impact, a shock or impact detector is proposed, which takes into account both the amplitude and the duration of a possible shock or impact. This detector comprises an electromagnetic transducer (50), whose coil supplies a pulse signal having an amplitude and duration proportional to the amplitude and to the duration of the shock. An integrator (80) makes it possible to obtain an integrated signal, whose amplitude is proportional both to the amplitude and the duration of the shock. A comparator (82) then makes it possible to control safety systems, if said integrated signal exceeds a preferably regulatable threshold.

Claims

1. Shock detector which can be carried on a vehicle for automatically triggering, in the case of a shock or impact, at least one safety system, said detector comprising a shock transducer able to emit, in the case of a shock, a pulse signal having an amplitude and a duration respectively proportional to the amplitude and duration of the shock, integration means, sensitive to said pulse signal, for supplying an integrated signal having an amplitude which increases with the amplitude and duration of the shock and detection and control means sensitive to said integrated signal for triggering the safety system when the amplitude of said integrated signal exceeds a predetermined threshold;

said shock detector further comprising amplification means and shaping means for the pulse signal, interposed between the shock transducer and the integration means; and

wherein the pulse signal shaping means incorporate a non-linear amplifier and inverted clipping diodes having calibrated thresholds.

2. Shock detector according to claim 1 also comprising automatic zeroing means for the detection and control means following the reception by the latter of an integrated signal.

3. Shock detector according to claim 1, wherein the detection and control means incorporate means for regulating said predetermined threshold.

4. Shock detector according to claim 1, wherein the shock transducer is an electromagnetic transducer comprising a magnetic core able to slide in a tubular body in opposition to a calibrated spring when subject to a shock, as well as a detector coil positioned coaxially around the body.

5. Shock detector according to claim 4, wherein an intermediate, amagnetic material pellet is placed between the magnetic core and the spring.

6. Shock detector according to claim 4, wherein the ends of the tubular body are sealed and it has a calibrated orifice issuing at its end adjacent to the calibrated spring.

7. Shock detector according to claim 4, wherein a setscrew makes it possible to apply the magnetic core to the calibrated spring.

8. Shock detector according to claim 1, also incorporating an autonomous energy source.

9. Shock detector according to claim 8, wherein the autonomous energy source comprises at least one rechargeable battery, which can be connected to an electric supply circuit of the vehicle.

10. Shock detector according to claim 2, wherein the detection and control means incorporate means for regulating said predetermined threshold.

11. Aircraft distress beacon, incorporating a shock detector and emitter means controlled by said shock detector, wherein the shock detector comprises a shock transducer able to emit, in the case of a shock, a pulse signal having an amplitude and a duration respectively proportional to the amplitude and duration of said shock, integration means sensitive to said pulse signal for supplying an integrated signal having an amplitude, which increases with the amplitude and with the duration of the shock and detection and control means sensitive to said integrated signal for triggering the safety system when the amplitude of said integrated signal exceeds a predetermined threshold, wherein said shock detector further comprises amplification means and shading means for the pulse signal, interposed between the shock transducer and the integration means, and the pulse signal shaping means incorporate a non-linear amplifier and inverted clipping diodes having calibrated thresholds.

12. Distress beacon according to claim 11, wherein the shock detector forms an interchangeable part of the beacon.

13. Distress beacon according to claim 11, wherein the shock detector incorporates a first autonomous energy source and the emitter means incorporate a second autonomous energy source.

14. Distress beacon according to claim 11 comprising a control circuit for the emitter means, independent of the shock detector, able to control the automatic putting into operation of the emitter means in the case of a breakage of a cable of said control circuit forming a loop travelling within the aircraft.

15. Distress beacon according to claim 11 comprising a remote control, which can be placed on the aircraft control panel.

16. Shock detector which can be carried on a vehicle for automatically triggering, in the case of a shock or impact, at least one safety system, said detector comprising a shock transducer able to emit, in the case of a shock,a pulse signal having an amplitude and a duration respectively proportional to the amplitude and duration of the shock, integration means, sensitive to said pulse signal, for supplying an integrated signal having an amplitude which increases with the amplitude and duration of the shock and detection and control means sensitive to said integrated signal for triggering the safety system when the amplitude of said integrated signal exceeds a predetermined threshold;

said shock detector further comprising amplification means and shaping means for the pulse signal, interposed between the shock transducer and the integration means; and

wherein the pulse signal shaping means incorporate a non-linear amplifier and inverted clipping means having calibrated thresholds.

17. Aircraft distress beacon, incorporating a shock detector and emitter means controlled by said shock detector, wherein the shock detector comprises a shock transducer able to emit, in the case of a shock, a pulse signal having an amplitude and a duration respectively proportional to the amplitude and duration of said shock, integration means sensitive to said pulse signal for supplying an integrated signal having an amplitude, which increases with the amplitude and with the duration of the shock and detection and control means sensitive to said integrated signal for triggering the safety system when the amplitude of said integrated signal exceeds a predetermined threshold, wherein said shock detector further comprises amplification means and shaping means for the pulse signal, interposed between the shock transducer and the integration means, and the pulse signal shaping means incorporate a non-linear amplifier and inverted clipping means having calibrated thresholds.