Operating Characteristics of Low Power Arcjets for Space Propulsion
| Project/Area Number |
61460079
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| Research Category |
Grant-in-Aid for General Scientific Research (B)
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| Allocation Type | Single-year Grants |
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| Research Field |
Aerospace engineering
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| Research Institution | Osaka University |
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Principal Investigator |
YOSHIKAWA Takao Faculty of Engineering Science, Osaka University, 基礎工学部, 教授 (00029498)
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| Co-Investigator(Kenkyū-buntansha) |
ONOE Ken-ichi Faculty of Engineering Science, Osaka University, 基礎工学部, 助手 (70029429)
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| Project Period (FY) |
1986 – 1987
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| Project Status |
Completed (Fiscal Year 1987)
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| Budget Amount *help |
¥5,700,000 (Direct Cost: ¥5,700,000)
Fiscal Year 1987: ¥2,300,000 (Direct Cost: ¥2,300,000)
Fiscal Year 1986: ¥3,400,000 (Direct Cost: ¥3,400,000)
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| Keywords | Electric Propulsion / Arcjet / Station-Keeping / Frozen Flow Loss / Real Gas Effect / 実在気体効果 / 電離・解離を伴う流れ / 比推力 / 衛星の姿勢制御 / 解離,電離を伴う超音速流 |
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| Research Abstract |
This paper describes exploratory development of a low-power arcjet for space propulsion such as north-south station keeping for geosynchronous satellites. Three kinds of arcjets ( water cooled arcjet, two-dimensional visible arcjet and radiation cooled arcjet) has been designed and tested with N_2, H_2 and mixture of N_2+H_2 simulating hydrazine decomposion products at power levels from 0.5 to 3kW. The focus of the present research effort is to develop a stable arcjet thruster with high thrust performance at the low mass flow rate and low discharge current level. In the tests of arcjets, the following results were obtained.
(1) The large amount of electrode erosion occurs at the start-up. A double pulse trigger method is proposed as a softer starting procedure.
(2) The preferred operating conditions and thrust performance are as follows: Propellant N_2+2H_2, ( mixed gas ); arc current 16 A; mass flow rate 30 mg/s; total thrust 145 mN; specific impulse 494 sec; thrust efficiency 31.2 %.
(3) The heat input to the cathode is as high as 8 % of the input power and is removed by regenerative cooling of the propellant. In addition, the arc efficiency is 85 % .
(4) From the calculation, the frozen flow loss is 40-50 % of the input power. The preferred opening angle of the nozzle seems to be about 40゜ from the standpoint of the arc stability and thrust performance.
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Report
(2 results)
Research Products
(10 results)
