[특허]Ignition systems for hybrid and solid rocket motors

Hy-Pat Corporation

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특허 상세정보

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Ignition systems for hybrid and solid rocket motors

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	F02K-009/28 F02K-009/95
미국특허분류(USC)	060/251; 060/256
출원번호	US-0269366 (2002-10-11)
발명자 / 주소	Kline, Korey R. Deville, Derek Dee
출원인 / 주소	Hy-Pat Corporation
대리인 / 주소	Gordon &
인용정보	피인용 횟수 : 4 인용 특허 : 3

초록
▼

An ignition system for a rocket motor includes a soft plastic tube that extends up into the combustion chamber and is coupled to an oxidizer source. Ignition source wires extend through the tube and terminate at a first end at a location which is set back from the end of the tube, and have a second end coupled to an electric power supply. In operation, an oxidizer is introduced into the tube simultaneously with activation of the power supply. The set back portion of the plastic tube becomes fuel for the oxidizer and is consumed, introducing a fire plume into the combustion chamber. The tube introduces additional fuel distinct from the fuel grain or propellant which is in contact with the both the ignition source wires and oxidizer. In addition, the tube will not damage the nozzle as it is being blown of the rocket during the main propulsion phase.

대표
청구항
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1. An ignition system for a rocket motor, comprising:a) a plastic first tube having a first end and a second end; b) a pair of wires discrete from said first tube and having first and second ends, said pair of wires extending into said first tube and said first ends of said wires terminating near said first end of said first tube; c) a power supply coupled to said second ends of said wires; and d) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube. 2. An ignition system according to claim 1, wherein:said first ends of said wires are set back from said first end of said first tube and thereby define a set back portion of said first tube between said first ends of said wires and said first end of said first tube, wherein when said first tube is being supplied with said oxidizer and said power supply is activated, said oxidizer consumes at least some of said set back portion of said first tube as fuel. 3. An ignition system according to claim 1, wherein:said pair of wires extend into said tube through a hole in a sidewall of said first tube. 4. An ignition system according to claim 1, wherein:said power supply, when activated, causes an are to be produced across said first ends of said wires. 5. An ignition system according to claim 1, wherein:said first fluid oxidizer source includes i) a fluid oxidizer under relatively high pressure, ii) a pressure regulator adapted to lower said pressure of said fluid oxidizer, and iii) a valve which controls release of the relatively lower pressure fluid oxidizer into said second end of said first tube. 6. An ignition system according to claim 1, wherein:said first tube is relatively flexible. 7. An ignition system according to claim 1, wherein:said first tube is made of one of polyethylene, polypropylene, ABS, and nylon. 8. An ignition system according to claim 1, wherein:said fluid oxidizer is gaseous oxygen. 9. An ignition system for a rocket motor, comprising:a) a plastic first tube having an inner wall, a first end and a second end; b) a pair of wires having first and second ends, said first ends of said wires terminating near said first end of said first tube, wherein at least one of said first ends of said wires is in contact with said inner wall; c) a power supply coupled to said second ends of said wires; and d) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube. 10. An ignition system for a rocket motor, comprising:a) a plastic first tube having an inner wall, a first end and a second end; b) a pair of wires having first and second ends, said first ends of said wires terminating near said first end of said first tube, wherein said first tube and said wires are integrated in a plastic co-extrusion; c) a power supply coupled to said second ends of said wires; and d) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube. 11. An ignition system according to claim 10, wherein:said first ends of said wires are stripped of said plastic co-extrusion, and configured bent into said first tube through said first end of said first tube. 12. An ignition system for a rocket motor, comprising:a) a plastic first tube having a first end and a second end; b) a pair of wires having first and second ends, said first ends of said wires terminating near said first end of said first tube; c) a power supply coupled to said second ends of said wires; d) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube; e) a second tube having first and second ends; and f) a second fluid oxidizer source, wherein said first fluid oxidizer source supplies an oxidizer at a first flow rate into said second end of said first tube, and wherein said second fluid oxidizer source supplies an oxidizer at a second flow rate into said second end of said second tube, said second flow rate being greater than said first flow rate. 13. An ignition system according to claim 12, wherein:said second tube is provided concentrically about said first tube. 14. An ignition system according to claim 12, wherein:said first ends of said first and second tubes are longitudinally displaced. 15. An ignition system according to claim 12, further comprising:g) a distribution means for distributing a common source of fluid oxidizer to said first and second fluid oxidizer sources. 16. An ignition system according to claim 12, wherein;said first tube, said second tube, and said wires are integrated in a co-extrusion. 17. An ignition system according to claim 12, wherein:said first and second tubes are defined by two lumens of a single plastic extrusion. 18. An ignition system for a rocket motor, comprising:a) a first tube having a first end and a second end; b) a second tube having first and second ends; c) a pair of wires having first and second ends, said first ends of said wires terminating near said first end of said first tube; d) a power supply coupled to said second ends of said wires; e) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube; and f) a second fluid oxidizer source which supplies an oxidizer to said second end of said second tube, wherein said first fluid oxidizer source supplies said oxidizer at a first flow rate into said second end of said first tube, and wherein said second fluid oxidizer source supplies said oxidizer at a second flow rate into said second end of said second tube, said second flow rate being greater than said first flow rate. 19. A rocket, comprising:a) a rocket motor having a combustion chamber; and b) an ignition system for said rocket motor, said ignition system including, i) a plastic first tube having a first end and a second end, said first end extending into said combustion chamber, ii) a pair of wires discrete from said first tube and extending into said first tube, said pair of wires having first and second ends, said first ends of said wires terminating near said first end of said first tube, iii) a power supply coupled to said second ends of said wires and adapted to create an ignition spark across said first ends of said wires, and iv) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube. 20. A rocket according to claim 19, wherein:said rocket motor is a hybrid rocket motor. 21. A rocket according to claim 19, wherein:said rocket motor is a solid rocket motor. 22. A rocket according to claim 19, wherein:said first ends of said wires are set back from said first end of said first tube and thereby define a set back portion of said first tube between said first ends of said wires and said first end of said first tube, wherein when said first tube is being supplied with said oxidizer and said power supply is activated, said oxidizer consumes at least some of said set back portion of said first tube as fuel. 23. A rocket, comprising:a) a rocket motor having a combustion chamber; and b) an ignition system for said rocket motor, said ignition system including, i) a plastic first tube having a first end and a second end, said first end extending into said combustion chamber, ii) a pair of wires having first and second ends, said first ends of said wires terminating near said first end of said first tube, wherein said first tube and said wires are integrated in a plastic co-extrusion, iii) a power supply coupled to said second ends of said wires and adapted to create an ignition spark across said first ends of said wires, and iv) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube. 24. A rocket, comprising:a) a rocket motor having a combustion chamber; and b) an ignition system for said rocket motor, said ignition system including, a plastic first tube having a first end and a second end, said first end extending into said combustion chamber, ii) a pair of wires having first and second ends, said first ends of said wires terminating near said first end of said first tube, iii) a power supply coupled to said second ends of said wires and adapted to create an ignition spark across said first ends of said wires, iv) a first fluid oxidizer source which supplies an oxidizer to said second end of said first tube, v) a second tube having first and second ends, said first end extending into said combustion chamber, and vi) a second fluid oxidizer source, wherein said first fluid oxidizer source supplies an oxidizer at a first flow rate into said second end of said first tube, and wherein said second fluid oxidizer source supplies an oxidizer at a second flow rate into said second end of said second tube, said second flow rate being greater than said first flow rate such that said oxidizer supplied into said second tube relatively rapidly fills said combustion chamber and said oxidizer supplied into said first tube is adapted to consume said plastic of said first tube when said power source creates an ignition spark across said first ends of said wires.

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이 특허를 인용한 특허 피인용횟수: 4

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Ignition systems for hybrid and solid rocket motors

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