基于可变弹翼迫击炮弹的制导方法研究

The Research of Guidance Method based on Variable Wings Mortars

针对常规迫击炮弹飞行距离短、精度差的缺点,对迫击炮弹进行气动设计,在弹身增设"一"字形可变弹翼,通过控制弹翼前缘后掠角来改变弹翼面积,进而调控射程,实现制导.采用最小二乘法拟合控制关系,以PID算法设计控制系统,并将四元数快速处理技术应用于Matlab下的仿真.结果表明,变弹翼制导迫击炮弹在打击6 000m距离的目标时,圆概率误差为4m,射击精度有很大提高.

For the shortcomings of short flying distance and poor accuracy of mortars, the research in aerodynamic design of mortars is put forward. Variable missile wings of ＂--＂ glyph are extra designed on the missile. By the means of controlling the leading edge sweep angle of the missile wings, the wing area is changed, and then regulate and control the gunshot and implement the guidance. Least square method is used to fit the control relationship and PID algo rithm is used to design the control system and quaternion fast-processing technique will be employed to the simulation in MATI.AB. The simulation effect indicates that shooting accuracy has greatly increased when the variable missile wings of guided mortars rounds hit the target at the distance of 6000 m with 1the circular error of 4 m.