CAJ | 학술논문

针对拦截高速机动目标的需求，研究了一种完全制导控制一体化有限时间收敛控制算法。首先，根据传统完全制导控制一体化模型，推导了导弹完全制导控制一体化视线角速率有限时间收敛模型；其次，构造了带补偿函数的非线性滑模切换函数，根据有限时间收敛终端滑模控制理论，设计了基于完全制导控制一体化的有限时间收敛控制算法，并通过自适应方法对系统不确定性的最大值进行了估计、运用高阶滑模微分器对视线角速率和弹目相对距离的高阶导数进行了解算；最后，仿真结果表明，与一般的控制算法相比，论文所设计的有限时间收敛控制算法能够达到视线角速率有限时间收敛，且具有更小的脱靶量和更短的飞行时间。
침대란절고속궤동목표적수구，연구료일충완전제도공제일체화유한시간수렴공제산법。수선，근거전통완전제도공제일체화모형，추도료도탄완전제도공제일체화시선각속솔유한시간수렴모형；기차，구조료대보상함수적비선성활모절환함수，근거유한시간수렴종단활모공제이론，설계료기우완전제도공제일체화적유한시간수렴공제산법，병통과자괄응방법대계통불학정성적최대치진행료고계、운용고계활모미분기대시선각속솔화탄목상대거리적고계도수진행료해산；최후，방진결과표명，여일반적공제산법상비，논문소설계적유한시간수렴공제산법능구체도시선각속솔유한시간수렴，차구유경소적탈파량화경단적비행시간。
A finite time convergent control algorithm on integrated missile guidance and control is proposed to meet the needs of intercepting maneuvering targets at high speed.Firstly,a finite??time convergent line??of??sight rate model is derived based on total integrated missile guidance and control according to the tradi-tional total integrated missile guidance and control model.Secondly,a nonlinear sliding mode switching function with compensating factor is construct,and a finite time convergent control algorithm of integrated missile guidance and control is designed based on finite??time convergent theory.Besides,an adaptive meth-od is adopted to estimate the maximum value of the system's uncertainty,and the higher??order sliding mode differentiators are adopted to solve the higher??order derivatives of line??of??sight rate and the distance between the missile and the target.Finally,the simulation results show that the proposed finite time con-vergent control algorithm can achieve the finite time convergence of the line??of??sight rate,and has less miss distance and shorter intercepting time,compared to the general control algorithms.