The Rotating Missile’s Research Of Control And Guidance System Based On Inertia Measurements

Among active missiles,the rotating missile plays an important role. Manycountries in the world are still putting significant resources into its research becauseof its low price and good properties in attack. The guidance and control method oftraditinoal rotating missiles is based on coupled model between the pitch channeland the yaw channel. However,with the development of science and theimprovement of production technology,it has been a trend to research decoupledrotating missiles by using the combination of various inertial components.Based on the combination of2pendulous gyroscopes、2linear accelerometersand one optical fibre gyro,this thesis will give one method in decoupling the coupledmissile model. Then the decoupled model will be reduced order by using Rouththeory and be adjusted artificially. After correction,the new modern,working from2Ma to2.5Ma,will be used to design a LPV switching controller. Then this thesiswill present the sliding-mode variable structure guidance. At last,an emulation inSimulink software will be given,combining the LPV switching control method andthe sliding-mode variable structure guidance,to test the missile’s dynamic charact-eristics and tracks of both the missile and the target.