CAJ | 학술논문

通过建立相对于终端弹目连线的导弹运动方程，将time-to-go的负n次幂函数引入到目标函数中，推导得到不考虑制导动力学的扩展比例导引和扩展的带落角约束的最优制导律。提出了广义最优制导律的概念，阐述了其在两种不同坐标系下的表现形式和意义。针对终端弹目连线坐标系下的广义最优制导律，利用幂级数解法对闭环弹道微分方程进行了解析求解，得到了导弹相对终端弹目连线的位置、速度和加速度指令的解析表达式，并利用仿真的方法对解析结果进行了验证。
통과건립상대우종단탄목련선적도탄운동방정，장time-to-go적부n차멱함수인입도목표함수중，추도득도불고필제도동역학적확전비례도인화확전적대락각약속적최우제도률。제출료엄의최우제도률적개념，천술료기재량충불동좌표계하적표현형식화의의。침대종단탄목련선좌표계하적엄의최우제도률，이용멱급수해법대폐배탄도미분방정진행료해석구해，득도료도탄상대종단탄목련선적위치、속도화가속도지령적해석표체식，병이용방진적방법대해석결과진행료험증。
Based on the equations of missile motion with respect to the desired terminal line of sight (DTLOS), the extended proportional navigation and extended optimal guidance law with impact angle constraint was deduced for lag-free system when - n power of time-to-go was introduced into the object function. The concept of the generalized optimal guidance law (GOPL) was proposed and the expressions and meaning of which in two different frames of reference were demonstrated. For the GOPL in the DTLOS frame, the analytical solutions of the closed-form trajectory were derived according to the method of power series and the analytical position, velocity and acceleration command were obtained. Finally, the analytical solutions were validated by the simulation results.