CAJ | 학술논문

针对攻击型临近空间飞行器的跳跃机动突防对常规拦截导弹提出的挑战, 本文首先建立了视线坐标系下的三维弹-目相对运动方程,引入目标跳跃幅度变化率估计目标跳跃机动的能力,基于滑模变结构控制理论,设计了随弹-目距离和目标跳跃幅度变化率自适应调节的滑模趋近律,推导了视线坐标系下导弹的三维制导律. 其次, 采用轨控直接力控制技术, 设计了直接力/气动力复合控制的分配方案.仿真结果表明: 采用该制导律与控制策略的拦截弹能够精确拦截高速、大机动目标,同时拦截弹弹道平缓,需用过载和能量消耗均较小.
침대공격형림근공간비행기적도약궤동돌방대상규란절도탄제출적도전, 본문수선건립료시선좌표계하적삼유탄-목상대운동방정,인입목표도약폭도변화솔고계목표도약궤동적능력,기우활모변결구공제이론,설계료수탄-목거리화목표도약폭도변화솔자괄응조절적활모추근률,추도료시선좌표계하도탄적삼유제도률. 기차, 채용궤공직접력공제기술, 설계료직접력/기동력복합공제적분배방안.방진결과표명: 채용해제도률여공제책략적란절탄능구정학란절고속、대궤동목표,동시란절탄탄도평완,수용과재화능량소모균교소.
A nonlinear guidance law is proposed to confront the challenge of offensive near-space ve-hicles.Firstly, 3-D relative motion equations of missile and target are built in sight coordinate system. The gradient of target jump range is introduced to estimate its maneuverable capability.An adaptive slid-ing mode reaching law varying with the gradient of target jump range and the distance between missile and target is designed.3-D guidance law in sight coordinate system is got based on sliding mode control theo-ry.Secondly, the allocation strategy of reaction-jet/aerodynamic multi-control is designed and trajectory-control lateral-jets control technology is used in the terminal phase.Simulation results show that intercep-tor using this guidance law and control strategy can hit hypersonic and high maneuvering target accurately. Meanwhile the flight ballistics is smoother and required overload is lesser as well as energy consumption.