Solar bimodal mission and operational analysis
- Rockwell Aerospace, Rocketdyne Division, Canoga Park, California (United States)
- The Aerospace Corporation, El Segundo, California (United States)
Recent interest by both government and industry has prompted evaluation of a solar bimodal upper stage for propulsion/power applications in Earth orbit. The solar bimodal system provides an integral propulsion and power system for the orbit transfer and on-orbit phases of a satellite mission. This paper presents an initial systems evaluation of a solar bimodal system used to place satellite payloads for Geosynchronous Earth Orbit (GEO), High Earth Orbit (HEO-Molniya class), and Mid Earth Orbit (GPS class) missions with emphasis on the GEO mission. The analysis was performed as part of the Operational Effectiveness and Cost Comparison Study (OECS) sponsored by Phillips Laboratory (PL). The solar bimodal concept was investigated on a mission operational and performance basis for on-orbit power levels ranging from less than 1 kWe to 20 kWe. Atlas IIAS, Delta 7920, and Titan IV launch vehicles were considered for injecting the solar bimodal upper stage and payload into initial orbits ranging from Low Earth Orbit (LEO) (185{times}185 km circular) to higher apogee altitudes (185{times}18,500 km elliptical). The influences of engine thrust, power level, trip time, staging altitude, and thermal storage charge-discharge characteristics on the mission payload capability were developed. {copyright} {ital 1996 American Institute of Physics.}
- DOE Contract Number:
- AC03-92SF19138
- OSTI ID:
- 385523
- Report Number(s):
- CONF-960109--
- Journal Information:
- AIP Conference Proceedings, Journal Name: AIP Conference Proceedings Journal Issue: 1 Vol. 361; ISSN 0094-243X; ISSN APCPCS
- Country of Publication:
- United States
- Language:
- English
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