Results of satellite raising and orbit transfer studies for low power electrothermal arc-jet propulsion systems
The satellite raising (or orbit transfer) applications of low power electrothermal arc-jet engines are considered. Advantages and disadvantages of using solar panelelectrothermal propulsion for satellite raising are briefly discussed, and parametric mission study methods and results are reported for a specific mission of raising a satellite from an inclined parking orbit to a synchronous equatorial orbit. Effects of independently varying the following parameters were investigated: propellant type, engine power level, power supply specific weight, thruster specific impulse, and payload. Ascent time and parking orbit altitude were the dependent variables. Arc-jet engine design and development goals, in terms of propellant type, power level, and specific impulse, are optimized for the specified mission. Results indicate an optireum power level between 1.5 and 3 kw, based on projected power supply specific weights, and further indicate potential advantages of ammonia over hydrogen as the propellant, provided required engine life can be obtained. Principal potential advantage of ammonia over hydrogen is the much shorter ascent time required, while principal disadvantage involves the more severe thruster development problems. Criteria are suggested for selecting design and development goals for engine specific impulse. (auth)
- Research Organization:
- Plasmadyne Corp., Santa Ana, CA (United States)
- Sponsoring Organization:
- Sponsor not identified
- NSA Number:
- NSA-17-032219
- OSTI ID:
- 4875390
- Report Number(s):
- CONF-10--38; Preprint--63010
- Country of Publication:
- United States
- Language:
- English
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