Navigation And Control Of Space Control Technology Verification System

Space control technology verification system is a set of large-scale flotation platformsupport, using two sets of aircraft simulators, ground control to monitor the operation oflarge-scale flotation physical simulation system. Space control technology verificationsystem can achieve remote control of the aircraft space important key technologiessemi-physical simulation, an important principle of the process demonstration flight, aswell as scalable orbital transfer vehicle subsequent feasibility of new technologies such asthree levels of verification technology validation, the formation of a flotation physicalverification simulation system.The preliminary system design function is to achieve orbital transfer vehicle spacecontrol technology validation, and its main function is to follow the expansion offormation flight, autonomous docking in orbit servicing technologies such verification.Verification system based on space control technology development needs, physicalsimulation system on the ground for the overall design, physical simulation system todetermine the composition of the ground and the linkages between subsystems;parameters on air bearings, pneumatic circuits, and other aspects of the center of massbalance argument and focuses on aircraft simulators and ground control systems detaileddesign.The aircraft simulator dynamics and kinematics modeling, based on satellitesimulator operating modes and operating environment on the satellite simulator controlstrategies and allocation strategies actuator design, combined with the results of modelingand design of the aircraft simulator results the control algorithm simulation, verificationcontrol strategy performance; analysis of experimental environment generated by theinterference force and disturbing torque.Design and simulation of aircraft actuator allocation strategy, and the actuatorcontroller design for simulation, and then build the aircraft tracking error equation, on thebasis of the design state error feedback control laws, namely simulated aircraft positioncontrol system. Design of the spacecraft attitude control method, first deduced attitudekinematics and dynamics equations, based on the entire system tasks, the Euler anglesconversion Rodrigues parameters, design parameters based on linear feedback Rodriguesattitude control method.