Controlling the trajectory of a low-thrust spacecraft along the heliocentric portion of the flight from the earth to Mars

Details Controlling the trajectory of a low-thrust spacecraft along the heliocentric portion of the flight from the earth to Mars Controlling the trajectory of a low-thrust spacecraft along the heliocentric portion of the flight from the earth to Mars

Dec 1974

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1974kosis..12..819b&link_type=abstract

Kosmicheskie Issledovaniia, vol. 12, Nov.-Dec. 1974, p. 819-833. In Russian.

Computer Science

Earth-Mars Trajectories, Error Correcting Codes, Low Thrust Propulsion, Time Optimal Control, Trajectory Control, Trajectory Optimization, Airborne/Spaceborne Computers, Algorithms, Error Analysis, Monte Carlo Method, Numerical Control, Random Errors, Spacecraft Control, Spacecraft Trajectories, Thrust Programming

Scientific paper

The two-dimensional problem of controlling a low-thrust spacecraft along a heliocentric flight trajectory between the gravitational fields of the earth and Mars is examined. The control is based on periodic prediction of the phase coordinates by integrating the equations of motion on the onboard digital computer. An algorithm is proposed for the optimal correction of the trajectory of a low-thrust spacecraft, using the predicted phase coordinates and determining the control parameters that ensure time-optimal two-way flight to Mars for a given stay on the planet and for a given engine operation time. The influence of correlated thrust errors with respect to magnitude and direction, and of measurement errors on the accuracy of trajectory-parameter estimates is analyzed. The operation of the control system in the presence of disturbances is studied by a Monte Carlo technique.

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