A small parameter method in problems of maneuvering space vehicles with aerodynamic efficiency |
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Authors: | VP Plokhikh VV Sonin |
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Institution: | Central Aerohydrodynamics Institute and Intercosmos Council, Leninsky Prospect, 14, 117901 Moscow V71, U.S.S.R. |
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Abstract: | The motion of a satellite with aerodynamic efficiency along a low near-circular orbit is considered in the paper. The controls of bank angle γ and lift coefficient Cy are used as control functions. The introduction of a small parameter () makes it possible to integrate an adjoint system of equations and to obtain an approximate solution to the complete problem in the class of piecewise-constant control functions. Maximum values for the coordinates of heading angle η and lateral derivation from the plane of a reference orbit ?, which are connected with orbit plane angle by the relation cos i = cos ? · cos h, are used as criteria of maneuvering capability for a satellite with aerodynamic efficiency. Optimal programs for bank angle and incidence variation are derived and the influence of lift-to-drag ratio on the vehicle maneuvering capabilities has been estimated.It is shown that the process of the optimal motion is a special kind of gravitational skipping similar to the Keplerian motion but with continuous descent. |
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