Approach Guidance with Double-Line-of-Sight Measuring Navigation Constraint for Autonomous Rendezvous

摘要

Based on double-line-of-sightmeasuring relative navigationmethod, an approach guidance law with the triangle-nmeasuring constraint is presented for autonomous rendezvous. The observability of double-line-of-sight measuringnrelative navigation system is analyzed using the state estimation error covariance matrix. The triangle-measuringnnavigation constraint is described as a keep-out cone. The approach guidance law is designed via artificial potentialnfunctionmethod. It is ensured that there is a high region of potential in the keep-out cone and the potential still has anunique minimum at the goal position. Numerical simulations are undertaken to verify the guidance methodnproposed. The results indicate that the control impulses of the potential function guidance ensure convergence of thenchase spacecraft to reach the goal position without violating the navigation keep-out zone.