CAJ | 학술논문

为解决高超声速飞行器俯冲段精确制导与机动突防问题，研究了机动突防最优制导方法。针对零化视线角速率降低突防性能的问题，在俯冲平面及转弯平面内分别设计了正弦形式的视线角参考运动，同时为进一步实现俯冲精确制导，以落速最大为性能指标，利用最优控制对其进行跟踪，引入了伪控制量，以简化最优制导问题的求解，最后分析了该方法的稳定性及制导性能。以 CAV -H 为例进行仿真分析，仿真结果表明，该方法能够实现机动飞行，且能够高精度地满足终端落角及落点约束，可为高超声速飞行器俯冲段精确制导及机动突防提供参考。
위해결고초성속비행기부충단정학제도여궤동돌방문제，연구료궤동돌방최우제도방법。침대령화시선각속솔강저돌방성능적문제，재부충평면급전만평면내분별설계료정현형식적시선각삼고운동，동시위진일보실현부충정학제도，이락속최대위성능지표，이용최우공제대기진행근종，인입료위공제량，이간화최우제도문제적구해，최후분석료해방법적은정성급제도성능。이 CAV -H 위례진행방진분석，방진결과표명，해방법능구실현궤동비행，차능구고정도지만족종단락각급낙점약속，가위고초성속비행기부충단정학제도급궤동돌방제공삼고。
To solve precise guidance and maneuver penetration problems for hypersonic vehicle in dive phase,the optimal guidance method with maneuver was proposed.Considering that the traditional guidance law based on zero-LOS angle rate can debase penetrative ability,it designed reference motion for the rate in diving-plane and turning-plane.Besides,in order to enhance penetrative ability farther and realize precise guidance,it took advantage of optimal control with the optimal index of maximum terminal velocity to track the LOS angle rate,and pseudo control variable was introduced to simplify the resolution of optimal control problem.Finally,it analyzed the guidance capability and stability of this method.The results of CAV-H vehicle test show that the algorithm can realize maneuvering flight,and can satisfy terminal impact point and falling angle constraints.Therefore,the method can offer reference for high precision guidance and maneuver penetration for hypersonic vehicle in dive phase.