CAJ | 학술논문

考虑拦截器使用耗尽关机固体推进系统的情况,提出需用速度增益曲面概念,设计了基于该概念的大气层外超远程拦截导引方法.根据Lambert导引,给定拦截时间就有唯一的指令推力方向与之对应,导引过程分为两个阶段:零控拦截到达阶段,选择最优拦截时间,需用速度增益曲面迅速与助推时间-拦截时间平面相切;零控拦截保持阶段,拦截时间不断减小,保持需用速度增益曲面在助推时间-拦截时间平面上滑动,消耗多余的推进剂.利用拟零控拦截概念使两个导引阶段平缓过渡,避免了导引方法切换时推力方向的跳变.导引律计及了J_2,z项摄动对滑行段弹道的影响,导引精度对推进系统参数偏差的鲁棒性强.仿真结果表明本文制导方法用于大气层外超远程目标拦截,脱靶量仅为km量级,推进系统参数偏差对导引精度的影响很小.
고필란절기사용모진관궤고체추진계통적정황,제출수용속도증익곡면개념,설계료기우해개념적대기층외초원정란절도인방법.근거Lambert도인,급정란절시간취유유일적지령추력방향여지대응,도인과정분위량개계단:령공란절도체계단,선택최우란절시간,수용속도증익곡면신속여조추시간-란절시간평면상절;령공란절보지계단,란절시간불단감소,보지수용속도증익곡면재조추시간-란절시간평면상활동,소모다여적추진제.이용의령공란절개념사량개도인계단평완과도,피면료도인방법절환시추력방향적도변.도인률계급료J_2,z항섭동대활행단탄도적영향,도인정도대추진계통삼수편차적로봉성강.방진결과표명본문제도방법용우대기층외초원정목표란절,탈파량부위km량급,추진계통삼수편차대도인정도적영향흔소.
The concept of a velocity-to-be-gained surface and a guidance law based on it for super-range exoatmospheric intercept is proposed for an interceptor with a fuel-exhaustion-shutoff solid rocket motor.Time-tointercept determines the exclusive command thrust orientation in Lambert guidance,and the presented guidante process is composed of two stages:the optimal time-to-intercept is chosen to make the velocity-to-begained surface osculate the boost-time VS time-to-intercept plane during the zero-effort-intercept-achieving stage;then the velocity-to-be-gained surface slides on the boost-time vs time-to-intercept plane by decreasing the time-to-intercept durative to exhaust the redundant fuel.The concept of pseudo-zero-effort-intercept is used in the proposed guidance tO avoid thrust orientation break at the shift of the two guidance processes.The J2 item perturbation is considered in the guidance law,whose guidance precision is robust to motor parameter uncertainties.Simulation results demonstrate that the order of zero elfort miss magnitude is kilometer and the guidance precision is robust to motor parameter uncertainties when using the proposed guidance law for superrange exoatmospheric intercept.