Semi-physical simulation system for hovering control with multi-mode hybrid propulsion

As the complexity of space missions increases, the design of the ground verification system of relative motion control becomes increasingly difficult, especially for geostationary satellites, whose relative motion configuration involves various flight forms such as accompanying flight, circling flight, and hovering, etc. Aiming at the new requirement of hovering control of geostationary orbit satellites, the formation of the "drip" hovering configuration in the plane is studied by using the parameters of semi-long axis difference and eccentricity difference based on relative orbital parameters description method. A two-parameter design method of in-plane hovering in multi-mode hybrid propulsion mode is proposed, and a general space motion simulation verification system is designed with the positional accuracy being in the order of millimeter. Semi-physical tests for the configuration guidance control law are carried out, which show that the semi-physical simulation posi-tion estimation error is about 20 m (3σ), the guidance control law is correct, and the proposed verification method can also be applied to the ground of other relative motion control techniques. © 2019, Editorial Department of Journal of Chinese Inertial Technology. All right reserved.