A trajectory generation and system characterization model for cislunar low-thrust spacecraft. Volume 1: User's manual

Details A trajectory generation and system characterization model for cislunar low-thrust spacecraft. Volume 1: User's manual A trajectory generation and system characterization model for cislunar low-thrust spacecraft. Volume 1: User's manual

May 1990

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1990stin...9324536k&link_type=abstract

Final Report (Diskette Supplement) Large Scale Programs Inst., Austin, TX.

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Applications

Applications Programs (Computers), Cislunar Space, Earth-Moon Trajectories, Low Thrust, Mathematical Models, Midcourse Trajectories, Spacecraft Guidance, Spacecraft Trajectories, Trajectory Analysis, User Manuals (Computer Programs), Algorithms, Nuclear Electric Propulsion, Spacecraft Propulsion

Scientific paper

The documentation of the Trajectory Generation and System Characterization Model for the Cislunar Low-Thrust Spacecraft is presented in Technical and User's Manuals. The system characteristics and trajectories of low-thrust nuclear electric propulsion spacecraft can be generated through the use of multiple system technology models coupled with a high-fidelity trajectory generation routine. The Earth to Moon trajectories utilize near Earth orbital plane alignment, midcourse control dependent upon the spacecraft's Jacobian constant, and capture to target orbit utilizing velocity matching algorithms. The trajectory generation is performed in a perturbed two-body equinoctial formulation and the restricted three-body formulation. A single control is determined by the user for the interactive midcourse portion of the trajectory. The full spacecraft system characteristics and trajectory are provided as output. The software is included on two floppy disks.

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