Fuel efficient periodic gain control strategies for spacecraft relative motion in elliptic chief orbits

摘要: Periodic gain continuous control strategies are applied to the nonlinear time periodic equations of spacecraft relative motion when chief orbit is elliptic. Specifically, based on time-varying linear quadratic regulator (LQR), Lyapunov–Floquet transformation (LFT) with time-invariant LQR, LFT backstepping, and feedback linearization implemented shown be much more fuel efficient than constant control. Both natural constrained leader-follower two-spacecraft formations studied. Furthermore, a dead-band added for formation reduce amount used. The closed-loop response effort required investigated compared same settling envelopes all strategies.