实际工程中,低成本导航系统的性能特点决定其不能在全姿态下工作,当空地导弹高空发射打击近程目标时,广义弹道成型中制导律(GTSGL)会导致下滑段弹体俯仰姿态角超出陀螺的测量范围。针对这一问题,文中在GTSGL的基础上通过增加姿态角约束修正项提出了带多约束条件的弹道成型中制导律。仿真表明,所提中制导律在满足中制导末端位置和角度约束的同时能够有效的限制弹体俯仰姿态角,在工程约束条件下具有更理想的中制导性能。

In practical engineering, the properties of low-cost navigation system determine that it can't work at all attitudes. When air-to-ground missile launched in high-altitude to attack short-range targets, the prominent characteristic of generalized trajectory-shaping guidance law (GTSGL) could result in pitching angle beyond the measurement range of gyro sensor in glide trajectory. Concerning this problem, a new trajectory-shaping guidance law with multi-constraint was proposed in this paper. This new guidance law can limit pitching angle by adding pitching angle restriction item on the basis of GTSGL. Simulation result shows that the proposed midcourse guidance law can effectively limit the pitching angle and meet impact position and angle constraints, which has more ideal midcourse performance under engineering constraints.