Rendezvous Trajectory Planning And Guidance Approach For Equatorial Elliptical Orbit

Orbit maneuver vehicle (OMV) has high maneuver ability. It is able to perform space missions using space rendezvous technology, including the space oberservation, capture, absorption, flyby and kinetic interception to some space spacecraft. The OMV studied in the paper is specified to that parking on the high eccentric orbit in equator plane. With the background of the rendezvous missions between the OMV and the target spacecraft on medium or high earth orbit, the dissertation studies the rendezvous process design, long-distance rendezvous orbital planning and guidance approaches, near-distance rendezvous orbital planning and guidance approaches, and the terminal guidance laws. The main results achieved in this dissertation are summarized as follows.The analytic formulae for the long-duration drift of inclination of the elliptical parking orbit in equator plane are deduced. (1) The rendezvous process between OMV and target spacecraft on un-limited orbit is analyzed. The rendezvous process is divided into several phases, and the dynamic model of each phase is established. (2) Aiming at the orbit with small inclination and high eccentricity, the analytic formulae for the long-duration drift of inclination are deduced and validated by simulation.The optimal planning approaches for the long-distance elliptical rendezvous trajectory in equator plane are proposed. (1) An optimal multiple-revolution Lambert rendezvous algorithm for elliptical trajectory is provided, and the optimal rendezvous trajectory can be obtained by solving only two Lambert orbits. (2) With the single-impulse multiple-revolution Lambert rendezvous trajectory, the optimal long-distance multiple-impulse rendezvous strategy is proposed by applying the non-optimal primer vector theory, the methods improving non-optimal trajectory and nonlinear programming approach. (3) The fixed-time rendezvous between the OMV and multiple target spacecraft is also studied, and the method to obtain the fuel-optimal visiting sequence of targets is provided.The optimal planning and guidance approaches with considering J2 perturbation for the long-distance elliptical rendezvous trajectory in equator plane are proposed. (1) Considering the J2 perturbation, the fuel-optimal fixed-time long-distance impulsive rendezvous strategy with high precision is proposed. (2) The optimal guidance plan of finite-thrust rendezvous is proposed by using Legendre Pseudospectral Method (LPM), and an initial guess generator is provided for a large number of design variables. The proposed guidance plan and the initial guess generator is validated by simulation. (3) Considering the J2 perturbation, the nonlinear error analysis for the long-distance rendezvous trajectory with initial state errors is performed by using covariance analysis description equation technique (CADET) and Monte Carlo simulation. (4) A guidance correct strategy based on state transfer matrix with considering J2 perturbation is proposed to reduce the effect of errors on the rendezvous trajectory.The optimal planning and guidance approaches for the near-distance elliptical rendezvous trajectory in equator plane are proposed. (1) The modeling errors of relative dynamic models are analyzed and compared, and the influences of navigation error and control error are analyzed. The linearized elliptical relative equations are chosen to describe the relative movement during the near-distance rendezvous phase. The nonlinear planning model for the elliptical linear rendezvous planning is provided. (2) The fixed-time near-distance rendezvous optimization approach is proposed by using the non-optimal primer vector theory, the methods improving non-optimal trajectory and nonlinear programming method. (3) Considering the mass variation and the constant thrust with adjustable direction, the hybrid optimization strategy for near-distance finite-thrust optimal rendezvous is proposed by hybrid optimal control method and multiple-shooting technique.The guidance laws for the rendzvous terminal phase of intelligent impactor carried by OMV are studied. (1) Considering environment disturbation, the neural network guidance (NNG) law is proposed and trained with data provided by LQG guidance, and the network structure, initial connect parameters and bias parameters are optimized by genetic algorithm. Simulation results show that the NNG guidance law satisfies miss-distance requirement and is roubust to the target's various kind of maneuver. (2) Replacing the sign function with fuzzy control logic, the fuzzy terminal variable structure guidance law is proposed. The stability of fuzzy controller is analyzed and proved by Lyapunov stability theory. Simulation results show that the provided guidance law doesn't only have strong robustness, but also eliminates the chattering phenomenon which is inherent of a sliding mode control.The dissertation studies optimal planning and guidance approaches for elliptical rendezvous trajectory, and expands the optimal rendezvous theory which have some theoretical significance. The proposed optimal rendezvous strategies both for long-distance elliptical rendezvous trajectory and near-distance elliptical rendezvous trajectory and terminal guidance laws will provide technique support for the space rendezvous scheme design and orbit control of OMV.