Research Of The Spacecraft’s Anti-tracking Control Method Based On The Theory Of Jump Systems

As the Earth’s outer space resources is continuing to be occupied, space attack-defense confrontation is inevitable in the future. The attacks aimed at spacecraftin orbit will become the focus of confrontation, so the spacecraft’s anti-trackingagainst the threat of weapons is extremely important. Based on the model of thespacecraft orbital dynamics, combined with jump systems theory, the anti-tracking problem is transformed into a jump model reference tracking controlinput. The corresponding mathematical description of the control problem andthe corresponding algorithm is proposed at the same time.First, this article gives basic knowledge of mathematics involved, includingthe spacecraft orbit model in inertial frames, jump systems theory and LMImethod used. The knowledge contains the models, corresponding definitions andLemmas used.Then for the system model without disturbance, the anti-tracking problem istransformed into a reference tracking problem for jump model and the problemwas described mathematically; for the control of the problem raised, theexistence of the tracking controller conditions is deduced, and combined withsufficient and necessary conditions for the stability of the jump system and thelinear matrix inequality approach, the solution steps is given, finishing as thealgorithm in the form; the simulation results of the system model withoutdisturbance in circular orbits and elliptical orbits demonstrate the effectiveness ofthe controller.Finally, for the system contains a type of It disturbance, for the same modelreference tracking control problem a mathematical description of the problem isgiven; for systems with It disturbance, tracking controller existence conditionsis analyzed and the form of tracking controller is analyzed in the perspective ofthe error augmented system, the result supports the validity of the proposedcontroller; according to jump systems containing random perturbations necessaryand sufficient conditions for stability, combined with linear matrix inequalityapproach, the control problem solving algorithm is given; taking the characteristics of It stochastic system simulation into account, using a discreteapproximation method for the numerical simulation, and for the circular orbitelliptical orbit, simulation results show that the proposed controller is effective.