IPC분류정보
국가/구분 |
United States(US) Patent
등록
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국제특허분류(IPC7판) |
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출원번호 |
US-0837821
(2001-04-17)
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발명자
/ 주소 |
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출원인 / 주소 |
- The United States of America, as represented by the Administrator of the National Aeronautics and Space Administration
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대리인 / 주소 |
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인용정보 |
피인용 횟수 :
1 인용 특허 :
11 |
초록
▼
A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the reduced toxicity propellant to the ACS decom
A reduced toxicity fuel satellite propulsion system including a reduced toxicity propellant supply (10) for consumption in an axial class thruster (14) and an ACS class thruster (16). The system includes suitable valves and conduits (22) for supplying the reduced toxicity propellant to the ACS decomposing element (26) of an ACS thruster. The ACS decomposing element is operative to decompose the reduced toxicity propellant into hot propulsive gases. In addition the system includes suitable valves and conduits (18) for supplying the reduced toxicity propellant to an axial decomposing element (24) of the axial thruster. The axial decomposing element is operative to decompose the reduced toxicity propellant into hot gases. The system further includes suitable valves and conduits (20) for supplying a second propellant (12) to a combustion chamber (28) of the axial thruster, whereby the hot gases and the second propellant auto-ignite and begin the combustion process for producing thrust.
대표청구항
▼
1. A reduced toxicity fuel satellite propulsion system comprising: a first reduced toxicity liquid propellant supply, wherein the first propellant includes a reduced toxicity satellite fuel; a thruster, wherein the thruster includes a decomposing element, wherein the decomposing element is opera
1. A reduced toxicity fuel satellite propulsion system comprising: a first reduced toxicity liquid propellant supply, wherein the first propellant includes a reduced toxicity satellite fuel; a thruster, wherein the thruster includes a decomposing element, wherein the decomposing element is operative to decompose the propellant; and wherein the decomposing element includes a plasmatron; means for selectively supplying the propellant to the decomposing element, whereby the propellant is decomposed into hot gases; a second liquid propellant supply, wherein the second propellant includes an oxidizer; a second supplying means for selectively supplying the second propellant to the thruster, and wherein the second supplying means is operative to selectively supplying the second propellant to the thruster. 2. The reduced toxicity fuel satellite propulsion system as recited in claim 1, wherein the second supplying means is operative to selectively supply oxidizer to the plasmatron; wherein the plasmatron includes: a cathode, wherein the cathode is electrically charged; an anode, wherein the anode encircles the cathode, wherein the anode has the opposite polarity of the cathode, wherein the satellite fuel and oxidizer are input into the plasmatron between the anode and the cathode wherein an electrical discharge arc between the anode and the cathode is produced whereby the electrical arc is operative to decompose the satellite fuel into hot gases. 3. The reduced toxicity fuel satellite propulsion system as recited in claim 2, wherein the plasmatron includes means for imparting the input of the satellite fuel and oxidizer with tangential velocity around the anode, whereby the electrical discharge arc between the anode and the cathode sweeps around the anode to prevent overheating and erosion in one location. 4. The reduced toxicity fuel satellite propulsion system as recited in claim 1 wherein the satellite fuel includes a reduced toxicity satellite fuel selected from the group consisting of alcohols, ethers, amines, nitroparaffins, saturated hydrocarbon, unsaturated hydrocarbons, ring compounds, and strained ring compounds. 5. The reduced toxicity fuel satellite propulsion system as recited in claim 1 wherein the satellite fuel includes a reduced toxicity satellite fuel selected from the group consisting of methanol, ethanol, methylamine, ethylamine, methane, ethane, pentane, propane, 1-pentene, acetylene, ethylene, JP-10 and cyclopropane, and quadricyclane. 6. The reduced toxicity fuel satellite propulsion system as recited in claim 5 wherein: the thruster further includes a combustion chamber; the decomposing element is operative to output the hot gas into the combustion chamber; the second supplying means is operative to selectively supply the second propellant to the combustion chamber of the thruster, whereby the second propellant and the hot gases auto-ignite and produce thrust for maneuvering the satellite. 7. A method for propelling a satellite comprising the steps of: supplying a thruster with a first reduced toxicity propellant; decomposing the first propellant into hot gases with a plasmatron; supplying the thruster with a second propellant; combining the hot gases with the second propellant inside a combustion chamber of the thruster, whereby the second propellant and hot gases auto-ignite and produce thrust for maneuvering the satellite. 8. A method for propelling a satellite as recited in claim 7, wherein the first propellant includes methylamine, and wherein the second propellant includes liquid oxygen.
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