Electrically controlled variable force deployment airbag and inflation

• US 9,457,761 B2
• Filed: 05/28/2014
• Issued: 10/04/2016
• Est. Priority Date: 05/28/2014
• Status: Active Grant

• Current Assignee: Raytheon Company (Rtx Corporation)
• Original Assignee: Raytheon Company (Rtx Corporation)
• Inventors: Villarreal, James K., Deppert, Thomas M., Langhenry, Mark T., Summers, Matt H.
• Primary Examiner(s): GOODEN JR, BARRY J
• Application Number:
  US14/289,513
• Publication Number:
  US 20150343988A1
• Time in Patent Office: 860 Days
• US Class Current: 1/1
• CPC Class Codes: B60R 21/00 Arrangements or fittings on vehicles for protecting or preventing injuries to occupants or pedestrians in case of accidents or other traffic risks safety belts or body harnesses in vehicles B60R22/00; devices, apparatus or methods for life-saving in general A62B; safety devices for propulsion unit control specially adapted for, or arranged in, vehicles B60K28/00; seats constructed to protect the occupant from the effect of abnormal g-forces, e.g. crash or safety seats, B60N2/42; energy-absorbing arrangements for hand wheels for steering vehicles B62D1/11; energy-absorbing arrangements for vehicle steering columns B62D1/19; harnessing in aircraft B64D25/00
• CPC Class Codes: B60R 21/264 using instantaneous generation of gas, e.g. pyrotechnic B60R21/268 takes precedence
• CPC Class Codes: B60R 21/2644 using only solid reacting substances, e.g. pellets, powder
• CPC Class Codes: C06B 33/06 the material being an inorganic oxygen-halogen salt
• CPC Class Codes: C06C 9/00 Chemical contact igniters; Chemical lighters
• CPC Class Codes: C06D 5/06 by reaction of two or more solids
• CPC Class Codes: F42B 3/04 for producing gas under pressure generators of inflation fluid especially adapted for vehicle air bags B60R21/26
• CPC Class Codes: F42B 3/128 characterised by the composition of the pyrotechnic material
• CPC Class Codes: F42B 3/14 Spark initiators F42B3/195 takes precedence
• CPC Class Codes: F42C 19/0823 Primers or igniters for the initiation or the propellant charge in a cartridged ammunition primers for caseless ammunition F42C19/085
• CPC Class Codes: F42C 19/12 electric

Abstract

The rate of combustion of an electrically operated propellant having self-sustaining threshold of at least 1,000 psi is controlled to produce chamber pressures that are sufficient to produce a desired pressure profile in the airbag to accommodate a range of human factors and crash conditions yet never exceeding the self-sustaining threshold. The combustion of the propellant is extinguished to control the total pressure impulse delivered to the airbag. Propellants formed with an ionic perchlorate-based oxidizer have demonstrated thresholds in excess of 1,500 psi and higher.

Claims

1. A method of deploying and inflating an airbag comprising:

providing a combustion chamber;

providing an amount of electrically operated propellant within the combustion chamber, said propellant comprising an ionic perchlorate-based oxidizer such that the propellant has a self-sustaining threshold pressure of at least 1,000 psi at which the propellant once ignited by an electrical input cannot be extinguished and below which the propellant can be extinguished by interruption of the electrical input;

coupling the airbag to the combustion chamber;

igniting the electrically operated propellant in the chamber by applying the electrical input to the electrically operated propellant; and

controlling the electrical input to the electrically operated propellant to vary a rate of combustion of the ignited electrically operated propellant, hence varying the pressure in the chamber at levels less than the self-sustaining threshold pressure, to control a pressure profile in the airbag and a total pressure impulse delivered to the airbag.

2. The method of claim 1, wherein said ionic perchlorate-based oxidizer comprises a liquid perchlorate-based oxidizer of approximately 50 to 90 percent of a mass of the electrically operated propellant, further comprising:

a binder of approximately 10 to 30 percent of the mass of the electrically operated propellant;

a metal-based fuel of approximately 5 to 30 percent of the mass of the electrically operated propellant.

3. The method of claim 1, wherein the electrical input is interrupted to extinguish the electrically operated propellant when the chamber pressure is greater than 500 psi.

4. A method of deploying and inflating an airbag comprising:

providing a combustion chamber with an electrode structure configured for coupling with an electrical power source;

providing an amount of electrically operated propellant within the combustion chamber, said propellant comprising an ionic perchlorate-based oxidizer such that the propellant has a self-sustaining threshold pressure of at least 1,000 psi at which the propellant once ignited by an electrical input cannot be extinguished and below which the propellant can be extinguished by interruption of the electrical input;

coupling the airbag to the combustion chamber;

igniting the electrically operated propellant in the chamber by applying the electrical input to the electrically operated propellant via the electrode structure;

generating pressurized gas within the chamber from combustion of the ignited electrically operated propellant, pressures in the chamber reaching more than 500 psi but never more than the self-sustaining threshold pressure of the propellant;

exhausting the pressurized gas from the chamber to inflate the airbag;

varying the electrical input to the electrically operated propellant to vary a rate of combustion of the ignited electrically operated propellant, hence varying the pressure in the chamber at levels less than the self-sustaining threshold pressure, to control a pressure profile in the airbag; and

extinguishing the electrically operated propellant with the interruption of the electrical input to burn less than all of said propellant to control a total pressure impulse delivered to the airbag.

5. The method of claim 4, wherein there is only a single amount of the electrically operated propellant.

6. The method of claim 4, wherein the self-sustaining threshold pressure is at least 1,500 psi and wherein pressures within the chamber reach more than 1,000 psi.

7. The method of claim 4, wherein the pressure in the chamber reaches a peak pressure of more than 500 psi, and wherein the electrical input is varied to modulate the chamber pressure either before or after the peak pressure.

8. The method of claim 4, wherein the electrical input is interrupted to extinguish the electrically operated propellant at a chamber pressure greater than 500 psi.

9. The method of claim 4, wherein the electrical input is varied such that the pressure profile in the airbag estimates a desired pressure profile.

10. The method of claim 9, further comprising:

computing the desired pressure profile based on at least one human factor input and at least one measured crash input.

11. The method of claim 10, further comprising:

computing a propellant burn rate profile to provide the desired pressure profile in the airbag;

computing an electrical input profile and chamber pressure profile to provide the propellant burn rate profile; and

varying the electrical input according to the electrical input profile.

12. The method of claim 4, wherein said ionic perchlorate-based oxidizer comprises a liquid perchlorate-based oxidizer of approximately 50 to 90 percent of a mass of the electrically operated propellant, further comprising:

a binder of approximately 10 to 30 percent of the mass of the electrically operated propellant;

a metal-based fuel of approximately 5 to 30 percent of the mass of the electrically operated propellant.

13. The method of claim 12, wherein the metal-based fuel in cooperation with the liquid perchlorate-based oxidizer provides the electrically operated propellant with a specific energy of around 600 to 1100 joules per gram at ambient pressure.

14. The electrically operated propellant of claim 12, wherein the electrically operated propellant has an initial total pressure impulse value at an initial time, and a mature pressure impulse value at a second time after storage for at least 30 days at a temperature of around 140 degrees Fahrenheit, and the mature total pressure impulse value is substantially the same as the initial total pressure impulse value.

15. A method of deploying and inflating an airbag comprising:

providing a combustion chamber;

providing an amount of electrically operated propellant within the combustion chamber, said propellant comprising an ionic-based oxidizer such that the propellant has a self-sustaining threshold pressure of at least 1,000 psi at which the propellant once ignited by an electrical input cannot be extinguished and below which the propellant can be extinguished by interruption of the electrical input;

coupling the airbag to the combustion chamber;

igniting the electrically operated propellant in the chamber by applying the electrical input to the electrically operated propellant; and

controlling the electrical input to the electrically operated propellant to vary a rate of combustion of the ignited electrically operated propellant, hence varying the pressure in the chamber at levels less than the self-sustaining threshold pressure, to control a pressure profile in the airbag and a total pressure impulse delivered to the airbag.

16. The method of claim 15, further comprising:

computing a specified pressure profile for the airbag based on at least one human factor input and at least one measured crash input;

computing a propellant burn rate profile to provide the specified pressure profile in the airbag;

computing an electrical input profile and chamber pressure profile to provide the propellant burn rate profile; and

varying the electrical input according to the electrical input profile.

17. The method of claim 15, further comprising interrupting the electrical input to extinguish the electrically operated propellant at a chamber pressure greater than 500 psi.

18. An airbag assembly, comprising:

a combustion chamber with an electrode structure configured for coupling with an electrical power source;

an amount of electrically operated propellant within the combustion chamber, said propellant comprising an ionic-based oxidizer such that the propellant has a self-sustaining threshold pressure of at least 1,000 psi at which the propellant once ignited by an electrical input cannot be extinguished and below which the propellant can be extinguished by interruption of the electrical input;

an airbag coupled to the combustion chamber; and

a controller configured to

apply the electrical input to the electrically operated propellant via the electrode structure to ignite the electrically operated propellant in the chamber, generate pressurized gas within the chamber from the combustion of the ignited electrically operated propellant to pressures in the chamber reaching more than 500 psi but never more than the self-sustaining threshold pressure of the propellant and exhaust pressurized gas from the chamber to inflate the airbag;

vary the electrical input to vary a rate of combustion of the ignited electrically operated propellant, hence varying the pressure in the chamber at levels less than the self-sustaining threshold pressure, to control a pressure profile in the airbag; and

interrupt the electrical input to extinguish the electrically operated propellant to burn less than all of said propellant to control a total pressure impulse delivered to the airbag.

19. The airbag assembly of claim 18, wherein there is only a single amount of the electrically operated propellant.

20. The airbag assembly of claim 18, wherein the controller is configured to

compute a specified pressure profile for the airbag based on at least one human factor input and at least one measured crash input;

compute a propellant burn rate profile to provide the specified pressure profile in the airbag;

compute an electrical input profile and chamber pressure profile to provide the propellant burn rate profile; and

vary the electrical input according to the electrical input profile.

21. The airbag assembly of claim 18, wherein the controller is configured to interrupt the electrical input to extinguish the electrically operated propellant at a chamber pressure greater than 500 psi to control the total pressure impulse.

22. The airbag assembly of claim 18, wherein the ionic-based oxidizer comprises an ionic perchlorate-based oxidizer.

23. The airbag assembly of claim 22, wherein said ionic perchlorate-based oxidizer comprises a liquid perchlorate-based oxidizer of approximately 50 to 90 percent of a mass of the electrically operated propellant, further comprising:

a binder of approximately 10 to 30 percent of the mass of the electrically operated propellant; and

a metal-based fuel of approximately 5 to 30 percent of the mass of the electrically operated propellant.

24. An airbag assembly, comprising:

a combustion chamber;

an amount of electrically operated propellant within the combustion chamber, said propellant comprising an ionic-based oxidizer such that the propellant has a self-sustaining threshold pressure of at least 1,000 psi at which the propellant once ignited by an electrical input cannot be extinguished and below which the propellant can be extinguished by interruption of the electrical input;

an airbag coupled to the combustion chamber; and

a controller configured to apply the electrical input to the electrically operated propellant to ignite the electrically operated propellant in the chamber and to vary a rate of combustion of the ignited electrically operated propellant, hence varying the pressure in the chamber at levels less than the self-sustaining threshold pressure, to control a pressure profile in the airbag and a total pressure impulse delivered to the airbag.

25. The airbag assembly of claim 24, wherein the ionic-based oxidizer comprises an ionic perchlorate-based oxidizer.

26. The airbag assembly of claim 25, wherein said ionic perchlorate-based oxidizer comprises a liquid perchlorate-based oxidizer of approximately 50 to 90 percent of a mass of the electrically operated propellant, further comprising:

a binder of approximately 10 to 30 percent of the mass of the electrically operated propellant; and

a metal-based fuel of approximately 5 to 30 percent of the mass of the electrically operated propellant.

27. The airbag assembly of claim 25, wherein the controller is configured to interrupt the electrical input to extinguish the electrically operated propellant at chamber pressures greater than 500 psi to control the total pressure impulse delivered to the airbag.