Optimal launching of an earth satellite using aerodynamic forces

Details Optimal launching of an earth satellite using aerodynamic forces Optimal launching of an earth satellite using aerodynamic forces

Mar 1991

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1991kosis..29..255f&link_type=abstract

Kosmicheskie Issledovaniia (ISSN 0023-4206), vol. 29, Mar.-Apr. 1991, p. 255-271. In Russian.

Computer Science

1

Aerodynamic Forces, Ascent Trajectories, Pontryagin Principle, Spacecraft Launching, Boundary Value Problems, Computer Techniques, Equations Of Motion, Gravitational Fields

Scientific paper

This paper examines the problem of optimizing trajectories for injecting a satellite into an earth orbit by means of aerodynamic forces. A fast-convergence simulation procedure of optimization is developed on the basis of the Pontriagin's maximum principle (Pontriagin et al., 1969), which includes a solution of two-point boundary-value problem by a modified Newton's method with an automatic choice of an adequate initial solution estimate. Conditions for qualitative changes (including bifurcations) in optimal launch conditions and orbital injection trajectories are investigated.

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