Solar thermal propulsion for planetary spacecraft
Previous studies have shown that many desirable planetary exploration missions require large injection delta-V. Solar Thermal Rocket (STR) propulsion, under study for orbit-raising applications may enhance or enable such high-energy missions. The required technology of thermal control for liquid hydrogen propellant is available for the required storage duration. Self-deploying, inflatable solar concentrators are under study. The mass penalty for passive cryogenic thermal control, liquid hydrogen tanks and solar concentrators does not compromise the specific impulse advantage afforded by the STR as compared to chemical propulsion systems. An STR injection module is characterized and performance is evaluated by comparison to electric propulsion options for the Saturn Orbiter Titan Probe (SOTP) and Uranus Flyby Uranus Probe (UFUP) missions.
- OSTI ID:
- 5766197
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
PROPULSION SYSTEMS
COMPARATIVE EVALUATIONS
DESIGN
SOLAR THERMAL POWER PLANTS
SPACECRAFT POWER SUPPLIES
ION PROPULSION
ROCKET ENGINES
SOLAR CONCENTRATORS
TEMPERATURE CONTROL
WEIGHT
CONTROL
ELECTRONIC EQUIPMENT
ENGINES
EQUIPMENT
POWER PLANTS
POWER SUPPLIES
PROPULSION
SOLAR EQUIPMENT
SOLAR POWER PLANTS
THERMAL POWER PLANTS
140703* - Solar Thermal Power Systems- Distributed Collector