Research On Guidance And Attitude Control Of Missile With Side-window Detection For Terminal Guidance

The side-window detection technology can be adopted to solve the problem ofaerodynamic heat induced by high speed and active infrared seeker can operationnormally. This paper is studied to solve the problems of guidance and attitude controlproblems of aerodynamic missile with side-window detection. The study mainlyincludes side-window constraint modeling, terminal guidance law design and attitudecontrol system design.Firstly, mathematical description of missile-and-target, missile center-of-massmotion and attitude motion is established, side-window constrain is described byangle of attack and sideslip angle constrain according to field of view of side-window,attitude angle and LOS, based on which the nonlinear model of aerodynamic missilewith side-window detection is derived, then the model is analyzed.Secondly, the combat progress of terminal guidance for aerodynamic missilewith side-window detection is analyzed. The analysis mainly includes seekermeasurement principle analysis, target-tracking analysis, attitude control modeanalysis and terminal guidance analysis, based on which terminal guidance law isdesigned and estimation method of target maneuvering acceleration is derived basedon extended state observer. The simulation is carried out to verify the designedterminal guidance law and estimation method of target maneuvering acceleration.Thirdly, based on predictive control theory, the attitude control system isdesigned for constrained and unconstrained. The simulation is carried out to verifythe designed method.Finally, based on the design of the terminal guidance law and attitude control,the simulation of integrated detection, guidance and attitude control is carried out toverify the research.