CAJ | 학술논문

对于目标任意机动的三维拦截情况，空空导弹一体化制导控制系统模型呈现非线性、耦合和不确定特性，使控制器设计困难。为此，首先对导弹非线性耦合控制系统模型进行简化，得到三通道近似线性化模型，同时认为通道间的耦合项未知有界。在此基础上，推导俯仰和偏航通道的一体化制导控制系统模型。之后考虑干扰的不确定性，利用滑模控制响应快速、对参数变化及扰动不敏感等优点，设计了空空导弹一体化滑模自适应制导控制律，并基于Lyapunov理论证明了其稳定性。数值仿真结果表明，目标任意机动情况下，该一体化制导控制律不仅能够保证导弹命中精度，而且可同时保证弹体姿态的稳定，相对于传统方法，该方法有更好的拦截效果。
대우목표임의궤동적삼유란절정황，공공도탄일체화제도공제계통모형정현비선성、우합화불학정특성，사공제기설계곤난。위차，수선대도탄비선성우합공제계통모형진행간화，득도삼통도근사선성화모형，동시인위통도간적우합항미지유계。재차기출상，추도부앙화편항통도적일체화제도공제계통모형。지후고필간우적불학정성，이용활모공제향응쾌속、대삼수변화급우동불민감등우점，설계료공공도탄일체화활모자괄응제도공제률，병기우Lyapunov이론증명료기은정성。수치방진결과표명，목표임의궤동정황하，해일체화제도공제률불부능구보증도탄명중정도，이차가동시보증탄체자태적은정，상대우전통방법，해방법유경호적란절효과。
For the 3D interception of an arbitrarily maneuvering target, it is difficult to design the controller of an air to air missile’ s integrated guidance and control system because its model is nonlinear, coupling and uncertain. Therefore, we simplify the model of the nonlinear and coupling control system and obtain the approximately linear model with three channels. On these bases, we establish the pitch and yaw channel integrated guidance and control model. Taking into account the uncertainty of disturbance, we use the sliding mode control, which has rapid re-sponse and is not sensitive to parameter change and disturbance, to design the air to air missile’ s adaptive and in-tegrated guidance and control law and then prove its stability with the Lyapunov method. To verify the effectiveness of the integrated guidance and control law, we carry out its simulation;the results, given in Figs.2 through 5 and Tables 2 and 3, and their analysis show preliminarily that the integrated guidance and control law can guarantee the accuracy of the air to air missile hitting an arbitrarily maneuvering target and guarantee the stability of its attitude;thus it is more effective for interception.