Nonlinear control of terminal guided mortar projectile

The terminal guided mortar projectile aerodynamic layout type and characteristic is elaborated in this article. To increase the flying distance, it was combined with the actual situation of mortars aerodynamic layout. “-+” type configurations is selected. A pair of “a” triangle-shaped foldable wing is arrange in missile body. The method of A is used to calculate the air of drag coefficient and lift coefficient. Analysis show the differences between the algorithm of feedback linearization and the linearization algorithm under the assumption of small perturbations. A input-output feedback linearization algorithm is proposed to decouple and sub-channel control the nonlinear system terminal guided mortar projectile. On the pitch and yaw channels, the model reference adaptive control algorithm is adopted to guarantee the reliability and stability of the system. The simulation results showed that the accuracy has greatly improved in the terminal guided mortar projectile control system.