CAJ | 학술논문

针对高性能飞航导弹过载控制系统,从便于工程实现的角度出发,应用滑模观测/区分器(SMOD),通过角速度对角加速度进行估计,然后利用角速度和角加速度与过载的一阶、二阶导数问的近似关系,设计了一种滑模变结构控制律,滑模面由过载误差及误差的一阶、二阶导数组成.仿真结果验证了方法的正确性和有效性.
침대고성능비항도탄과재공제계통,종편우공정실현적각도출발,응용활모관측/구분기(SMOD),통과각속도대각가속도진행고계,연후이용각속도화각가속도여과재적일계、이계도수문적근사관계,설계료일충활모변결구공제률,활모면유과재오차급오차적일계、이계도수조성.방진결과험증료방법적정학성화유효성.
For an agile winged missile control system,using the sliding mode observer/differentiator(SMOD)to estimate the pitch acceleration by pitch rate,a variable structure control law is designed in the point of view of engineering application,and the sliding mode surface consists of overload signals elTor and its first-order and second-order derivatives,which are further replaced by pitch rate and pitch acceleration respectively.Simulation resuits show the validity and effectiveness of the proposed method.