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An iterative guidance algorithm using orbital elements as terminal constraints for spacecraft orbit transfer
Received date: 2014-12-02
Revised date: 2014-12-24
Online published: 2015-03-04
An adapted iterative guidance algorithm is researched for the orbit transfer mission of spacecraft. Based on the traditional iterative guidance method, we directly found the optimal control model on the geocentric inertial frame, use the orient vector of the thrust as the control variable to adapt for the significantly change of attitude angel, found the boundary conditions by using the target orbital elements directly as the terminal constraints, obtain the relationship between the accuracy of the solutions of the constraint equations and the injection accuracy, and then present a concise and effective iterative guidance algorithm using orbital elements as terminal constraints for spacecraft orbit transfer. Numerical simulations have demonstrated the effectiveness and better adaptability than the traditional method.
DENG Yifan , LI Chaobing , WANG Zhigang . An iterative guidance algorithm using orbital elements as terminal constraints for spacecraft orbit transfer[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2015 , 36(6) : 1975 -1982 . DOI: 10.7527/S1000-6893.2015.0046
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