航空兵器
航空兵器
항공병기
HANGKONG BINGQI
2012年
1期
18-24
,共7页
导弹%末制导%协同控制%扩张状态观测器
導彈%末製導%協同控製%擴張狀態觀測器
도탄%말제도%협동공제%확장상태관측기
missile%terminal guidance%synergetic control%extend state observer（ESO）
针对导弹制导系统中存在的模型不确定性和外部扰动,研究了末制导规律的设计与实现问题。首先,建立了导弹三维制导的运动学模型,描述了俯仰通道和偏航通道之间的耦合关系。其次,针对无终端约束和有终端约束情况,基于协同控制理论分别设计了非线性制导规律。然后,将制导模型中的目标机动加速度、通道耦合项及量测误差视为系统总扰动,利用扩张状态观测器对其进行估计,并分析了闭环系统的稳定性。所得制导律不依赖于系统精确的数学模型,不需要太多的观测信息。仿真结果表明,该制导律既能用于目标机动的制导,也能用于有终端约束的制导,且具有良好的制导精度,鲁棒性较强。
針對導彈製導繫統中存在的模型不確定性和外部擾動,研究瞭末製導規律的設計與實現問題。首先,建立瞭導彈三維製導的運動學模型,描述瞭俯仰通道和偏航通道之間的耦閤關繫。其次,針對無終耑約束和有終耑約束情況,基于協同控製理論分彆設計瞭非線性製導規律。然後,將製導模型中的目標機動加速度、通道耦閤項及量測誤差視為繫統總擾動,利用擴張狀態觀測器對其進行估計,併分析瞭閉環繫統的穩定性。所得製導律不依賴于繫統精確的數學模型,不需要太多的觀測信息。倣真結果錶明,該製導律既能用于目標機動的製導,也能用于有終耑約束的製導,且具有良好的製導精度,魯棒性較彊。
침대도탄제도계통중존재적모형불학정성화외부우동,연구료말제도규률적설계여실현문제。수선,건립료도탄삼유제도적운동학모형,묘술료부앙통도화편항통도지간적우합관계。기차,침대무종단약속화유종단약속정황,기우협동공제이론분별설계료비선성제도규률。연후,장제도모형중적목표궤동가속도、통도우합항급량측오차시위계통총우동,이용확장상태관측기대기진행고계,병분석료폐배계통적은정성。소득제도률불의뢰우계통정학적수학모형,불수요태다적관측신식。방진결과표명,해제도률기능용우목표궤동적제도,야능용우유종단약속적제도,차구유량호적제도정도,로봉성교강。
Considering the model uncertainty and external disturbance in guidance system, the design and implementation method of terminal guidance law for a missile is investigated. Firstly, the three- dimensional（3D） guidance model is established in spherical coordinate, and the coupling between pitch channel and yaw channel is described. Secondly, the nonlinear guidance laws are designed respectively based on synergetic control theory, corresponding to no ending constraints and ending constraints. Final- observe error along with cross-coupling and target acceleration are regarded as the total system disturb- ances, which could be estimated by the extended state observer （ESO）, and also the stability of closed loop system is analyzed. The resulting guidance laws are independent of explicit mathematical model, and require little guidance information. The simulation results show that the proposed guidance laws are suitable for both given impact direction requirements and maneuvering targets with excellent guidance performance.
