CAJ | 학술논문

考虑空气动力系数的不确定性与线性化后产生的模型不确定性，结合自适应与变结构方法，设计了一类自适应型滑模面，特别是其中针对南于空气动力学系数不定引起的舵系数未知情况，单独引入了自适应环节，补偿未知舵系数对系统的影响，同时通过构造Lyapunov函数证明其稳定性，并举例进行仿真研究。仿真结果表明了该方法的有效性。
고필공기동력계수적불학정성여선성화후산생적모형불학정성，결합자괄응여변결구방법，설계료일류자괄응형활모면，특별시기중침대남우공기동역학계수불정인기적타계수미지정황，단독인입료자괄응배절，보상미지타계수대계통적영향，동시통과구조Lyapunov함수증명기은정성，병거례진행방진연구。방진결과표명료해방법적유효성。
Considering the uncertainties caused by pneumatic parameters and model linearization of missile a kind of adaptive sliding mode control method was designed based on the combination of adaptive method and VSC method. Especially, the coefficient of the missile actuator was unknown because of the uncertain aero-coefficients, so a single adaptive item was adopted to compensate the unknown coefficient of actuator Finally, by constructing a Lyapunov function the stability of the system was proved. Some simulations were done to give examples, which showed the effectiveness of the proposed method