Optimal Guidance of Low-Thrust Interplanetary Space Vehicles

Optimal Control;Optimization;Space vehicle guidance;Ion Engine;Low Thrust Guidance

Ash, Gerald Richard ; Sridhar, Rangasami

University:California Institute of Technology

Department:Engineering and Applied Science

关键词: Optimal Control;    Optimization;    Space vehicle guidance;    Ion Engine;    Low Thrust Guidance;   

Others  :  https://thesis.library.caltech.edu/8085/1/Ash_gr_1969.pdf

美国|英语

来源: Caltech THESIS

【 摘 要 】

The low-thrust guidance problem is defined as the minimum terminal variance (MTV) control of a space vehicle subjected to random perturbations of its trajectory. To accomplish this control task, only bounded thrust level and thrust angle deviations are allowed, and these must be calculated based solely on the information gained from noisy, partial observations of the state. In order to establish the validity of various approximations, the problem is first investigated under the idealized conditions of perfect state information and negligible dynamic errors. To check each approximate model, an algorithm is developed to facilitate the computation of the open loop trajectories for the nonlinear bang-bang system. Using the results of this phase in conjunction with the Ornstein-Uhlenbeck process as a model for the random inputs to the system, the MTV guidance problem is reformulated as a stochastic, bang-bang, optimal control problem. Since a complete analytic solution seems to be unattainable, asymptotic solutions are developed by numerical methods. However, it is shown analytically that a Kalman filter in cascade with an appropriate nonlinear MTV controller is an optimal configuration. The resulting system is simulated using the Monte Carlo technique and is compared to other guidance schemes of current interest.