Direct interplanetary trajectory design with a precise V-infinity targeting technique

摘要

An interplanetary trajectory design requires a good initial guess which is obtained by precisely fixing the departure V-infinity/excess velocity vector. A small deviation in the V-infinity vector causes large deviation in the arrival target parameters. The departure hyperbolic orbit characteristics are synchronized such that the V-infinity vector is obtained at the planet sphere of influence. The current paper focuses on an analytical technique to target the V-infinity vector and to obtain the corresponding departure orbit characteristics under three-body force model. The proposed multiconic-differential evolution (MCDE) method refines the iterative pseudostate design and provides improved design which results in minimal deviations in the arrival target parameters. The arrival parking orbit inclination achieved upon numerical propagation of the iterative pseudostate design has large deviation from the desired value. This is corrected using the proposed method. In this method, the departure hyperbola is propagated using pseudostate technique in multiple steps, termed as the multiconic propagation technique, accounting for the gravity fields of both the planet and Sun. The differential evolution technique is used to refine the initial departure hyperbolic orbit characteristics under the three-body force model.