An analytic approximation to very high specific impulse and specific power interplanetary space mission analysis

Details An analytic approximation to very high specific impulse and specific power interplanetary space mission analysis An analytic approximation to very high specific impulse and specific power interplanetary space mission analysis

Sep 1995

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1995stin...9613400w&link_type=abstract

Presented at the 6th Space Flight Mechanics Meeting, Austin, TX, 11-15 1996; sponsored by AAS and AIAA

Computer Science

Performance

Flight Time, High Impulse, High Thrust, Interplanetary Flight, Interplanetary Trajectories, Space Missions, Specific Impulse, Trajectory Analysis, Trajectory Optimization, Equations Of Motion, Jupiter (Planet), Manned Space Flight, Nuclear Propulsion, Propellant Mass Ratio, Propulsion System Performance, Rendezvous Trajectories, Round Trip Trajectories

Scientific paper

A simple, analytic approximation is derived to calculate trip time and performance for propulsion systems of very high specific impulse (50,000 to 200,000 seconds) and very high specific power (10 to 1000 kW/kg) for human interplanetary space missions. The approach assumed field-free space, constant thrust/constant specific power, and near straight line (radial) trajectories between the planets. Closed form, one dimensional equations of motion for two-burn rendezvous and four-burn round trip missions are derived as a function of specific impulse, specific power, and propellant mass ratio. The equations are coupled to an optimizing parameter that maximizes performance and minimizes trip time. Data generated for hypothetical one-way and round trip human missions to Jupiter were found to be within 1% and 6% accuracy of integrated solutions respectively, verifying that for these systems, credible analysis does not require computationally intensive numerical techniques.

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