CAJ | 학술논문

非线性严反馈系统的控制中，由于迭代和系统的设计过程，反步法成为研究热点之一。然而，由于需要推导虚拟控制的解析导数，传统反步法存在“计算膨胀”问题，当被控对象的系统阶数较高或模型较复杂时，“计算膨胀”问题更为严重，这限制了反步法在实际工程中的应用。因此，提出一类新型的指令滤波反步法，避免传统反步法中“计算膨胀”问题。该方法采用输入状态稳定性(Input-to-State Stability, ISS)和小增益定理保证闭环系统的稳定性，为严反馈系统的控制器设计提供了简洁有效的方式。针对高超声速飞行器巡航段纵向的速度和高度跟踪问题，综合指令滤波反步法和动态逆方法设计有效的状态反馈控制器，最后在数值仿真中验证了所设计的控制器能实现高超声速飞行器在爬升机动中对速度和高度的稳定跟踪。
비선성엄반궤계통적공제중，유우질대화계통적설계과정，반보법성위연구열점지일。연이，유우수요추도허의공제적해석도수，전통반보법존재“계산팽창”문제，당피공대상적계통계수교고혹모형교복잡시，“계산팽창”문제경위엄중，저한제료반보법재실제공정중적응용。인차，제출일류신형적지령려파반보법，피면전통반보법중“계산팽창”문제。해방법채용수입상태은정성(Input-to-State Stability, ISS)화소증익정리보증폐배계통적은정성，위엄반궤계통적공제기설계제공료간길유효적방식。침대고초성속비행기순항단종향적속도화고도근종문제，종합지령려파반보법화동태역방법설계유효적상태반궤공제기，최후재수치방진중험증료소설계적공제기능실현고초성속비행기재파승궤동중대속도화고도적은정근종。
Controlling non-linear strict-feedback systems adopting back-stepping method is a focused research, due to the iteration and systematic process. However, traditional back-stepping design suffers form the problem of“explosion of complexity”, owing to the analytic derivatives of virtual control. The problem of“explosion of complexity”in back-stepping technology restricts the practical engineering applications, as the object is in a high order or in a complicate mathematical model. In this paper, a novel command filtered back-stepping control is investigated to solve such a problem, which provides a simple and effective way for controlling strict-feedback systems, by combining input-to-state stability with small-gain theorem. A combination of command filtered back-stepping control and dynamic inversion technology is adopted for designing a dynamic state-feedback controller that provides stable tracking of the velocity and altitude reference trajectories for a flexible Hypersonic Flight Vehicle cruise longitudinal model . The proposed methodology is verified in numerical simulations in a climbing maneuver case of separate velocity and altitude reference commands.