Circuitry for testing inflatable personal restraint systems

• US 10,364,034 B2
• Filed: 08/31/2015
• Issued: 07/30/2019
• Est. Priority Date: 04/05/2011
• Status: Active Grant

• Current Assignee: AmSafe, Inc. (Transdigm Group Incorporated)
• Original Assignee: AmSafe, Inc. (Transdigm Group Incorporated)
• Inventors: Shields, Ronald A., Settles, Peter Anthony, Hagan, Willard F., Gullotto, Giuseppe
• Primary Examiner(s): Edwards, Jerrah
• Application Number:
  US14/840,916
• Publication Number:
  US 20160096625A1
• Time in Patent Office: 1,429 Days
• CPC Class Codes: B60R 2021/0093 Aircraft
• CPC Class Codes: B60R 2021/01156 Current or voltage overload
• CPC Class Codes: B60R 2021/01184 Fault detection or diagnostic circuits in power circuits B60R2021/01129
• CPC Class Codes: B60R 2021/01286 Electronic control units
• CPC Class Codes: B60R 21/01 Electrical circuits for triggering passive safety arrangements, e.g. airbags, safety belt tighteners, in case of vehicle accidents or impending vehicle accidents electrical circuits for transmission of signals between steering wheel and the vehicle itself B60R16/027; for electrically actuating belt retractor locking means B60R22/343
• CPC Class Codes: B60R 21/0132 responsive to vehicle motion parameters , e.g. to vehicle longitudinal or transversal deceleration or speed value
• CPC Class Codes: B60R 21/01546 using belt buckle sensors
• CPC Class Codes: B60R 21/0173 Diagnostic or recording means therefor
• CPC Class Codes: B64D 11/062 Belts or other passenger restraint means for passenger seats
• CPC Class Codes: B64D 11/06205 Arrangements of airbags
• CPC Class Codes: B64D 11/0621 Airbag initiation or activation means
• 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
• CPC Class Codes: B64D 25/02 Supports or holding means for living bodies
• CPC Class Codes: G01R 31/54 Testing for continuity
• CPC Class Codes: G07C 5/0808 Diagnosing performance data testing of vehicles G01M17/00; testing of electrical installation on vehicles G01R31/005
• CPC Class Codes: G07C 5/0841 Registering performance data recording measured values G01D; information storage G11B

Abstract

An electronic module assembly (EMA) for use in controlling one or more personal restraint systems. A programmed processor within the EMA is configured to determine when a personal restraint system associated with each seat in a vehicle should be deployed. In addition, the programmed processor is configured to perform a diagnostic self-test to determine if the EMA and the personal restraint systems are operational. In one embodiment, results of the diagnostic self-test routine are displayed on a display included on the electronic module assembly. In an alternative embodiment, the results of the diagnostic self-test routine are transmitted via a wireless transceiver to a remote device. The remote device can include a wireless interrogator or can be a remote computer system such as a cabin management computer system.

Claims

1. An electronics module assembly configured to control the inflation of an airbag in an aircraft, comprising:

a battery;

a crash sensor;

a control circuit for selectively completing a first current path from the battery through an ignitor upon receipt of a signal from the crash sensor, wherein current in the first current path activates the ignitor and causes the airbag to inflate;

a test circuit for selectively completing a second current path that is different from the first current path, wherein the second current path conducts current from the battery through the ignitor to test an electrical connection between the battery and the ignitor, wherein the second current path includes a resistor in the second current with a resistance selected to limit the current in the second current path to a level that prevents the ignitor from activating when the second current path is completed; and

one or more visual indicators that are selectively enabled to provide a visual status of the ability of the electronics module assembly to inflate the airbag.

2. The electronics module assembly of claim 1, wherein the test circuit is configured to detect a voltage at the resistance in the second current path, wherein the voltage is indicative of whether the electronics module assembly has the ability to inflate the airbag.

3. The electronics module assembly of claim 1, wherein the test circuit includes a transistor that is selectively enabled to complete the second current path.

4. The electronics module assembly of claim 1, wherein the one or more visual indicators are light emitting diodes.

5. The electronics module assembly of 2, wherein the test circuit includes a processor with an analog to digital converter that is configured to:

read the voltage at the resistance in the second current path;

compare the voltage read at the resistance with a predetermined voltage; and

enable a visual indicator based on the comparison.

6. A personal restraint system for use in an aircraft, comprising:

an airbag;

an ignitor that is configured to inflate the airbag when activated;

an electronics module assembly that is configured to control the inflation of the airbag that includes;

a battery;

a crash sensor;

a control circuit for selectively completing a first current path from the battery through the ignitor upon receipt of a signal from the crash sensor that causes the ignitor to activate;

a test circuit for selectively completing a second current path that is different from the first current path, wherein the second path conducts current from the battery through the ignitor to test the ability of the electronics module assembly to activate the ignitor, wherein the second current path includes a resistor in the second current path with a resistance selected to limit the current in the second current path to a level that prevents the ignitor from activating when the second current path is completed; and

one or more visual indicators that are selectively enabled to provide a visual status of the ability of the electronics module assembly to inflate the airbag.

7. The personal restraint system of claim 6, wherein the first current path includes a switch in series with the ignitor that is closed when the crash sensor is activated.

8. The personal restraint system of claim 6, wherein the test circuit is activated manually.

9. The personal restraint system of claim 6, wherein the test circuit is activated wirelessly.

10. The personal restraint system of claim 6, wherein the control circuit includes a first transistor that is selectively enabled to complete the first current path through the ignitor.

11. The personal restraint system of claim 6, wherein the test circuit includes a second transistor that is selectively enabled to complete the second current path through the ignitor.

12. An electronics module assembly configured to control the inflation of an airbag in an aircraft, comprising:

a battery;

a crash sensor;

a first transistor electrically connected to the ignitor and configured to complete a first current path from the battery through an ignitor upon activation of the crash sensor, wherein a current in the first current path activates the ignitor and causes the airbag to inflate;

a second transistor electrically connected to the ignitor and configured to complete a second current path that is different from the first current path and that is selectively completed from the battery through the ignitor to test if the electronics module assembly can activate the ignitor to inflate the airbag;

wherein the second current path includes a resistor with a resistance that is selected to limit the current in the second current path to a level that prevents the ignitor from activating when the second current path is completed; and

one or more visual indicators that are selectively enabled to provide a visual status of the ability of the electronics module assembly to inflate the airbag.

13. The electronics module assembly of claim 12, wherein the first current path includes a switch that is activated by the crash sensor to pass a current through the ignitor.

14. An electronics module assembly configured to control the inflation of an airbag in an aircraft, comprising:

a battery;

a crash sensor;

a first transistor electrically connected to an ignitor and configured to complete a first current path from the battery through the ignitor upon activation of the crash sensor, wherein a current in the first current path activates the ignitor and causes the airbag to inflate;

a second transistor electrically connected to the ignitor and configured to complete a second current path that is different than the first current path and that is selectively completed from the battery through the ignitor to test if the battery can deliver sufficient current to activate the ignitor and inflate the airbag;

wherein the second current path includes a resistor with a resistance that is selected to limit the current in the second current path to a level that prevents the ignitor from activating when the second current path is completed; and

one or more visual indicators that are selectively enabled to provide a visual status of the ability of the battery to inflate the airbag.