IPC분류정보
국가/구분 |
United States(US) Patent
등록
|
국제특허분류(IPC7판) |
|
출원번호 |
US-0593727
(2008-03-28)
|
등록번호 |
US-8387359
(2013-03-05)
|
우선권정보 |
FR-07 54173 (2007-03-30) |
국제출원번호 |
PCT/FR2008/050543
(2008-03-28)
|
§371/§102 date |
20090929
(20090929)
|
국제공개번호 |
WO2008/135695
(2008-11-13)
|
발명자
/ 주소 |
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출원인 / 주소 |
|
인용정보 |
피인용 횟수 :
0 인용 특허 :
5 |
초록
▼
The electrolytic ignitor comprises an injector constituting a first electrode, a second electrode that is electrically insulated from the injector and that extends downstream beyond the injector, and a distribution channel to deliver a first mono-propellant to a first mono-propellant injector device
The electrolytic ignitor comprises an injector constituting a first electrode, a second electrode that is electrically insulated from the injector and that extends downstream beyond the injector, and a distribution channel to deliver a first mono-propellant to a first mono-propellant injector device constituted by at least one injection hole opening out in the vicinity of the second electrode, and an electrical power supply circuit adapted to raise the second electrode to a potential lying in the range 50 V to 1000 V relative to the potential of the first electrode. The electrical power dissipated by ionic conduction in the free jet of the first mono-propellant is suitable for giving rise to spontaneous decomposition of the first mono-propellant and for producing combustion gas that ensures ignition of jets of a second mono-propellant coming from a main injector situated in the vicinity of the second electrode.
대표청구항
▼
1. A mono-propellant rocket engine comprising: a main combustion chamber, an electrolytic ignitor, and a main injector, the electrolytic ignitor comprising an injector constituting a first electrode and including a first mono-propellant injector device for injecting a first liquid mono-propellant th
1. A mono-propellant rocket engine comprising: a main combustion chamber, an electrolytic ignitor, and a main injector, the electrolytic ignitor comprising an injector constituting a first electrode and including a first mono-propellant injector device for injecting a first liquid mono-propellant that is electrically conductive, a second electrode that is electrically insulated from the injector by an insulator, a tank for said first mono-propellant, a solenoid valve interposed between said tank and a distribution channel serving to dispense the first mono-propellant in said first mono-propellant injector device constituted by at least one injection hole opening out in a vicinity of the second electrode, and an electrical power supply circuit, the main injector being situated in the vicinity of the second electrode to inject jets of a second liquid mono-propellant into the main combustion chamber of the rocket engine, wherein the second electrode extends downstream beyond the injector, wherein the first liquid mono-propellant is injected via said at least one injection hole in a form of a free jet that strikes the second electrode in a zone situated outside a body of the injector, and wherein the electrical power supply circuit is adapted to raise the second electrode to a potential lying in a range of 50 volts to 1000 volts relative to a potential of the first electrode, in such a manner that a dissipation of electrical power by ionic conduction in the free jet of the first mono-propellant injected via said at least one injection hole is capable of causing temperature to rise sufficiently to lead to spontaneous decomposition of the first mono-propellant and to a production of combustion gas for ensuring ignition of the jets of the second mono-propellant coming from the main injector. 2. A rocket engine according to claim 1, wherein the dissipation of electrical power by ionic conduction in the free jet of the first mono-propellant injected via the at least one injection hole lies in a range of 100 to 1000 Watts per gram per second, and is capable of causing a temperature rise of 5000 to 20,000 degrees Celsius per second. 3. A rocket engine according to claim 1, wherein the second electrode is disposed centrally, and wherein a plurality of injection holes including the at least one injection hole for the first mono-propellant and outlets from the main injector are disposed around the central electrode. 4. A rocket engine according to claim 1, wherein the first mono-propellant injector device for injecting the first mono-propellant includes an annular channel. 5. A rocket engine according to claim 1, wherein the second electrode is made of a refractory metal comprising tungsten or tungsten/rhenium. 6. A rocket engine according to claim 1, wherein the first mono-propellant present in the tank is constituted by a same composition as the second mono-propellant delivered by the injector device for injecting the second mono-propellant. 7. A rocket engine according to claim 1, wherein the first mono-propellant comprises an aqueous solution of nitrate and a water-soluble fuel. 8. A rocket engine according to claim 7, wherein the aqueous solution of nitrate comprises hydroxylammonium nitrate, ammonium di-nitramide, or hydrazinium nitro-formate. 9. A rocket engine according to claim 7, wherein the water-soluble fuel comprises an alcohol or triethanolammonium nitrate. 10. A rocket engine according to claim 1, wherein the electrical power supply circuit comprises a DC power supply, at least one capacitor, and a switch, and wherein the injector constituting the first electrode presents a potential close to electrical ground. 11. A rocket engine according to claim 10, wherein the switch comprises a power transistor or a thyristor. 12. A rocket engine according to claim 10, wherein the capacitor and the switch are housed in a housing secured to the body of the electrolytic ignitor. 13. A rocket engine according to claim 1, wherein the electrical power supply circuit comprises a DC power source, at least one capacitor, a chopper circuit, and a voltage-raising transformer including a primary winding and a secondary winding being electrically isolated from each other, the primary winding being connected to the chopper circuit and the secondary winding being connected between the second electrode and the injector constituting the first electrode. 14. A rocket engine according to claim 1, wherein the insulator comprises a first insulator portion mounted to be able to expand freely, and a second insulator portion providing sealing between the second electrode and an insulator support. 15. A rocket engine according to claim 14, wherein the first insulator portion comprises at least one ceramic block made of boron nitride or of alumina. 16. A rocket engine according to claim 14, wherein the second insulator portion is made of alumina and is brazed firstly to the second electrode and secondly to the insulator support. 17. A rocket engine according to claim 14, wherein the second insulator portion is made of a flexible material comprising one of polytetrafluoroethylene, polytrifluorochloroethylene, Vespel, and fiberglass-filled polytetrafluoroethylene. 18. A rocket engine according to claim 14, wherein the second insulator portion is combined with a coaxial cable socket receiving a connector for a coaxial cable. 19. A rocket engine according to claim 1, wherein the electrical power supply circuit is adapted to raise the second electrode to a potential lying in the range 100 volts to 500 volts relative to the potential of the first electrode constituted by the injector. 20. A rocket engine according to claim 1, wherein: the dissipation of electrical power by ionic conduction in the free jet of the first mono-propellant injected via the at least one injection hole lies in a range of 100 to 1000 Watts per gram per second, and is capable of causing a temperature rise of 5000 to 20,000 degrees Celsius per second;the second electrode is disposed centrally, and a plurality of injection holes including the at least one injection hole for the first mono-propellant and outlets from the main injector are disposed around the central electrode;the second electrode is made of a refractory metal comprising tungsten or tungsten/rhenium;the first mono-propellant present in the tank is constituted by a same composition as the second mono-propellant delivered by the injector device for injecting the second mono-propellantthe first mono-propellant comprises an aqueous solution of nitrate and a water-soluble fuel;the aqueous solution of nitrate comprises hydroxylammonium nitrate, ammonium di-nitramide, or hydrazinium nitro-formate;the water-soluble fuel comprises an alcohol or triethanolammonium nitrate;the insulator comprises a first insulator portion mounted to be able to expand freely, and a second insulator portion providing sealing between the second electrode and an insulator support;the first insulator portion comprises at least one ceramic block made of boron nitride or of alumina; andthe electrical power supply circuit is adapted to raise the second electrode to a potential lying in the range 100 volts to 500 volts relative to the potential of the first electrode constituted by the injector. 21. A rocket engine according to claim 20, wherein: the electrical power supply circuit comprises a DC power supply, at least one capacitor, and a switch, and the injector constituting the first electrode presents a potential close to electrical ground;the switch comprises a power transistor or a thyristor; andthe capacitor and the switch are housed in a housing secured to the body of the ignitor. 22. A rocket engine according to claim 20, wherein the electrical power supply circuit comprises a DC power source, at least one capacitor, a chopper circuit, and a voltage-raising transformer including a primary winding and a secondary winding being electrically isolated from each other, the primary winding being connected to the chopper circuit and the secondary winding being connected between the second electrode and the injector constituting the first electrode. 23. A rocket engine according to claim 20, wherein the second insulator portion is made of alumina and is brazed firstly to the second electrode and secondly to the insulator support. 24. A rocket engine according to claim 20, wherein the second insulator portion is made of a flexible material comprising one of polytetrafluoroethylene, polytrifluorochloroethylene, Vespel, and fiberglass-filled polytetrafluoroethylene. 25. A rocket engine according to claim 20, wherein the second insulator portion is combined with a coaxial cable socket receiving a connector for a coaxial cable. 26. A rocket engine according to claim 20, wherein the first mono-propellant injector device includes an annular channel.
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