Induced L2 norm control for Missile Early-Warning Satellite Attitude maneuver

In this paper, the Missile Early Warning Satellite Attitude Control problem is introduced, A two step incorporated and systematic method for modeling and control of missile early warning satellite is formulated. Firstly, the nonlinear dynamic and kinematics equation of the missile early warning satellite are reformulated to linear parameter variation (LPV) system. Secondly, based on the LPV model, an induced L₂ norm controller is introduced to eliminate the affect caused by the rotation of onboard mobile facilities, the designed LPV controller can guarantee that the induced L₂ norm from disturbance to attitude tracking error is less than a pre-given number. The LPV controller design problem is solved by Sum of Squares (SOS) programming techniques. The effectiveness of the proposed control technique is shown in simulations.