CAJ | 학술논문

利用非线性模型预测控制的思想建立了战斗机末端规避导弹的机动策略求解方法。根据导弹与战机的空战态势，建立了导弹与战机的相对运动微分方程；将导弹的导引律引入到导弹运动模型中，与飞机模型一起构建了系统预测模型，并对飞机和导弹的运动约束进行了分析。通过对导弹结构限制和战术特性的分析，给出了飞机机动规避导弹的性能指标，进而建立了机动规避导弹的最优控制模型。利用高斯伪谱法对模型进行求解，采用滚动优化策略实现了对机动规避策略的闭环求解。针对导弹气动参数和导航比未知以及相对测量量具有噪声的问题，利用极大似然法对导弹的气动参数和导航比进行估计，实现了对系统预测模型的反馈校正。仿真结果表明，此方法能够实现对导弹的机动规避。
이용비선성모형예측공제적사상건립료전두궤말단규피도탄적궤동책략구해방법。근거도탄여전궤적공전태세，건립료도탄여전궤적상대운동미분방정；장도탄적도인률인입도도탄운동모형중，여비궤모형일기구건료계통예측모형，병대비궤화도탄적운동약속진행료분석。통과대도탄결구한제화전술특성적분석，급출료비궤궤동규피도탄적성능지표，진이건립료궤동규피도탄적최우공제모형。이용고사위보법대모형진행구해，채용곤동우화책략실현료대궤동규피책략적폐배구해。침대도탄기동삼수화도항비미지이급상대측량량구유조성적문제，이용겁대사연법대도탄적기동삼수화도항비진행고계，실현료대계통예측모형적반궤교정。방진결과표명，차방법능구실현대도탄적궤동규피。
The maneuver strategy solving method for fighter avoiding the attack from missile in the endgame is developed by using the theory of nonlinear model predictive control.According to the situation of the engagement of missile and fighter,the motion differential equation was established.The guidance law was introduced into the missile kinematic model,and the system predictive model was set up together with the fighter’s model.Then,the kinematic constraint of the fighter and missile was analyzed.The performance indices of the fighter avoiding missile attack were proposed based on the analysis of the structure limitation and tactical characteristics of missile and the optimal control model was built. The Gauss Pseudospectral Method was used to solve the model,and the close-loop solution is realistic by using the RHC strategy.The Maximum Likelihood Estimation method was used to estimate the aerodynamic parameter and navigation ratio aiming at the problem of the uncertain and measurement noise,and the feedback correction of the system predictive model is realistic.The numerical simulation result shows that the maneuvering strategy can help the fighter avoid the missile attack.