A Review of High Thrust, High Delta-V Options for Microsatellite Missions

Microsatellites have been suggested as a means of enhancing a variety of proposed space missions, ranging from low-Earth-orbit to solar-system exploration. With improvements in propulsion technology geared toward microsatellites, the ultimate delta-V (deltaV) capabilities of some microsatellite syst...

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Bibliographic Details
Main Authors: Scharfe, David B, Ketsdever, Andrew
Format: Report
Language:English
Subjects:
Astronautics
BIPROPELLANTS
EARTH ORBITS
MICROROCKETS
MICROSATELLITES
MINIATURIZED ELECTROSTATIC THRUSTERS
PROPULSION SYSTEMS
PROPULSION TECHNOLOGIES
REACTION TIME
RENDEZVOUS SPACECRAFT
SCENARIOS
SOLAR SYSTEM
SOLAR THERMAL PROPULSION
SPACE EXPLORATION
SPACE MISSIONS
SPECIFIC IMPULSE
SYMPOSIA
THRUST
WUAFRL50260542
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Summary:Microsatellites have been suggested as a means of enhancing a variety of proposed space missions, ranging from low-Earth-orbit to solar-system exploration. With improvements in propulsion technology geared toward microsatellites, the ultimate delta-V (deltaV) capabilities of some microsatellite systems are now in the range of several km/s, opening the doors to a variety of high deltaV, fast response scenarios. This paper provides a brief overview of propulsion technologies currently available for microsatellites, and an evaluation of each technology for potential use in a demanding mission. The sample mission is that of a microsatellite inspector which, starting in a 200 km parking orbit, must be diverted to rendezvous with another satellite in orbit at a different altitude and inclination. It is found that existing bipropellant microrocket designs provide a high thrust value, combined with a 300 s specific impulse, allowing for response times of only a few hours for such an inspector mission with deltaV requirements over 1 km/s. Miniaturized electrostatic thrusters provide the largest ultimate deltaV capability, approaching 10 km/s, but with a very low thrust level and therefore a response time capability of several months. Newly developed micro-solar thermal systems fill in the middle ground for these two options, providing the moderate thrust levels and specific impulse values necessary for a response time on the order of one day and a deltaV of several km/s. For presentation at the AIAA Joint Propulsion Conference and Exhibit (45th) held in Denver, CO on 2-5 August 2009.