初始段大离轴制导律研究

Guidance Law for High Off-Bore-Sight Angle Launching Condition

研究了一种空空导弹大离轴发射制导律问题,首先建立制导系统平面拦截数学模型,从理论上分析大离轴发射的制导约束需求;在其基础上利用李雅普洛夫分析方法,以零化离轴角进行制导律的推导,并考虑导引头和惯性测量单元所能得到的信息源形成实用性强的简化制导律;最后在大离轴情况下应用大离轴制导律和比例导引律进行了数字仿真计算,仿真结果表明:给出的大离轴制导律较比例导引律性能更佳。

A new guidance law was studied for high off-bore-sight angle launching condition. At first, a planar interception model was set up and the requirement of guidance was analyzed in the theory. Then, the simplified guidance law was introduced at the condition of zero line-of-sight angular rate and zero off- axis angle on the basis of Lyapunov analyze method, which was applied by considering the information sources of seeker and inertia-measure-unit. Finally, computer simulation was processed and the results in- dicated that the guidance which was studied can improve the performance of missile at the high off-bore- sight angle launching comparing with proportional navigation law.