高技术通讯
高技術通訊
고기술통신
HIGH TECHNOLOGY LETTERS
2014年
10期
116-124
,共9页
制导律%微分对策%剩余飞行时间加权%碰撞角度约束%机动目标拦截
製導律%微分對策%剩餘飛行時間加權%踫撞角度約束%機動目標攔截
제도률%미분대책%잉여비행시간가권%팽당각도약속%궤동목표란절
guidance law%differential game%time to go weighting%impact angle constraint%maneuvering target interception
为提高拦截导弹的毁伤效果和机动性能，基于微分对策理论，提出了一种具有碰撞角度约束和剩余飞行时间加权的微分对策制导律。该制导律的推导基于最坏目标机动情形，并不受限于目标是否机动及其具体的机动形式，同时由于采用了剩余飞行时间对控制命令加权，使得拦截导弹峰值加速度提前，从而具有足够的弹道调整时间以降低制导末端的机动性要求。基于非线性系统仿真进行了制导律的验证，结果表明该制导律可以实现近于零值的脱靶量和碰撞角误差，且拦截导弹制导末端的加速度也被大大降低。
為提高攔截導彈的燬傷效果和機動性能，基于微分對策理論，提齣瞭一種具有踫撞角度約束和剩餘飛行時間加權的微分對策製導律。該製導律的推導基于最壞目標機動情形，併不受限于目標是否機動及其具體的機動形式，同時由于採用瞭剩餘飛行時間對控製命令加權，使得攔截導彈峰值加速度提前，從而具有足夠的彈道調整時間以降低製導末耑的機動性要求。基于非線性繫統倣真進行瞭製導律的驗證，結果錶明該製導律可以實現近于零值的脫靶量和踫撞角誤差，且攔截導彈製導末耑的加速度也被大大降低。
위제고란절도탄적훼상효과화궤동성능，기우미분대책이론，제출료일충구유팽당각도약속화잉여비행시간가권적미분대책제도률。해제도률적추도기우최배목표궤동정형，병불수한우목표시부궤동급기구체적궤동형식，동시유우채용료잉여비행시간대공제명령가권，사득란절도탄봉치가속도제전，종이구유족구적탄도조정시간이강저제도말단적궤동성요구。기우비선성계통방진진행료제도률적험증，결과표명해제도률가이실현근우령치적탈파량화팽당각오차，차란절도탄제도말단적가속도야피대대강저。
Based on the differential game theory, a time to go weighted differential game guidance law with impact angle constraints is presented for improvement of the warhead lethality and maneuvering performance of interception missiles. The derivation of this guidance law considers the worst case target maneuver, so it is not limited to a specific target’s maneuvering form. It makes an interception missile have enough time to adjust its trajectory to reduce the guidance terminal’s need for the maneuverability because it uses the time to go weighting for the controlling command to advance the peak acceleration of the interception missile. The nonlinear system simulations were carried out and the results showed that the guidance law exhibited its excellent performance by providing a near zero miss distance and an impact angle error, and reduced the terminal accelerations of the missile greatly.
