航空兵器
航空兵器
항공병기
HANGKONG BINGQI
2014年
4期
8-11
,共4页
临近空间拦截弹%H∞制导律%Lyapunov方法
臨近空間攔截彈%H∞製導律%Lyapunov方法
림근공간란절탄%H∞제도률%Lyapunov방법
near-space interceptor%H∞ guidance%Lyapunov methods
为了对以X-51 A为代表的临近空间高超声速飞行器实施有效拦截，提出一种新的具有强鲁棒性的非线性H∞制导律。首先，将目标机动作为系统扰动，建立拦截弹-目标相对运动学数学模型；根据几何方法拦截策略分析，提出以离心加速度的均方根为扰动输出；引入Hamil-ton函数并基于最优控制理论，得到非线性H∞制导律。该方法利用Lyapunov稳定性理论严格证明了制导系统的全局渐近稳定性，且无需求解Hamilton-Jacobi-Issacs（HJI）偏微分方程。仿真结果表明，该制导律不仅具有很强的鲁棒性也能获得良好的制导精度。
為瞭對以X-51 A為代錶的臨近空間高超聲速飛行器實施有效攔截，提齣一種新的具有彊魯棒性的非線性H∞製導律。首先，將目標機動作為繫統擾動，建立攔截彈-目標相對運動學數學模型；根據幾何方法攔截策略分析，提齣以離心加速度的均方根為擾動輸齣；引入Hamil-ton函數併基于最優控製理論，得到非線性H∞製導律。該方法利用Lyapunov穩定性理論嚴格證明瞭製導繫統的全跼漸近穩定性，且無需求解Hamilton-Jacobi-Issacs（HJI）偏微分方程。倣真結果錶明，該製導律不僅具有很彊的魯棒性也能穫得良好的製導精度。
위료대이X-51 A위대표적림근공간고초성속비행기실시유효란절，제출일충신적구유강로봉성적비선성H∞제도률。수선，장목표궤동작위계통우동，건립란절탄-목표상대운동학수학모형；근거궤하방법란절책략분석，제출이리심가속도적균방근위우동수출；인입Hamil-ton함수병기우최우공제이론，득도비선성H∞제도률。해방법이용Lyapunov은정성이론엄격증명료제도계통적전국점근은정성，차무수구해Hamilton-Jacobi-Issacs（HJI）편미분방정。방진결과표명，해제도률불부구유흔강적로봉성야능획득량호적제도정도。
In order to implement effective intercept of the near space hypersonic vehicle such as X -51A, a new continuous nonlinear H∞ guidance law with robustness is proposed .First, the mathematic mode is built according to the relationship between the missile and the target whose acceleration is intro -duced as disturbance .The root mean square of the centrifugal acceleration as the disturbance output is proposed based on the intercept strategic analysis by the geometric relationship .The nonlinear H∞ guid-ance law are obtained by Hamilton function and the optimal control theory .The asymptotic stability of the guidance system is strictly proved by Lyapunov stability theory , and applying this method , it is unnecessa-ry to solve the Hamilton-Jacobi-Iasscs( HJI) partial differential equation .The simulation results show that the guidance law not only has strong robustness but also get good guidance accuracy .
