Covariance-Based Multiple-Impulse Rendezvous Design

Abstract

A novel trajectory design methodology is proposed in the current work to minimize the state uncertainty in the crucial mission of spacecraft rendezvous. The trajectory is shaped under constraints utilizing a multiple-impulse approach. State uncertainty is characterized in terms of covariance, and the impulse time as the only affective parameter in uncertainty propagation is selected to minimize the trace of the covariance matrix. Further, the impulse location is also adopted as the other design parameter to satisfy various translational constraints of the space mission. Efficiency and viability of the proposed idea have been investigated through some scenarios that include constraints on final time, control effort, and maximum thruster limit addition to considering safe corridors. The obtained results show that proper selection of the impulse time and impulse position fulfils a successful feasible rendezvous mission with minimum uncertainty.

Simulation Framework for Orbit Propagation and Space Trajectory Visualization

“…The presented framework is capable of linking with various optimization algorithms for solving spacecraft trajectory optimization problems such as interplanetary transfers [36] and space rendezvous [37]. In this section, a multi-impulse trajectory optimization problem is optimized and simulated to illustrate the capability of this tool.…”

On the Impulsive Formation Control of Spacecraft Under Path Constraints

“…The global stabilization of CW system by saturated linear feedback is discussed in [19]. A covariance-based rendezvous design method is developed in [20] by Shakouri et al at which several constraints on the control effort, maximum impulse value, flight time, and safe zones are taken into account.…”