An equivalent sliding mode fault-tolerant control method with continuous switching is proposed for vertical tail damage.First,the nonlinear damage model of aircraft and the estimation of stability and control derivati...An equivalent sliding mode fault-tolerant control method with continuous switching is proposed for vertical tail damage.First,the nonlinear damage model of aircraft and the estimation of stability and control derivatives are introduced.Secondly,the linear sliding surface and the equivalent sliding mode controller are constructed,and the sufficient conditions for the stability of the damaged aircraft motion model are given by using the Lyapunov technique.The damage-tolerant controller is designed based on an adaptive sliding mode control for analyzing damaged aircraft systems.Furthermore,the hyperbolic tangent function is utilized to replace the symbolic function in the controller.The feasibility of the hyperbolic tangent function as the switching function is analyzed theoretically.Finally,the Boeing-747100/200 model is taken as an example to demonstrate the efficiency of theoretical results by recognizing the structural fault of aircraft.Numerical results show that the control law has a positive impact on the performance of the closed-loop system,and it also has a better fault tolerance and robustness towards external disturbance compared with traditional methods of damaged aircraft stabilization control.展开更多
By establishing the finite element models and corresponding calculation methods for the target board and rod-shaped fragment, the penetration effect of the high-velocity rod-shaped fragments＇ impact on the LY- 12cz t...By establishing the finite element models and corresponding calculation methods for the target board and rod-shaped fragment, the penetration effect of the high-velocity rod-shaped fragments＇ impact on the LY- 12cz thin sheet is analyzed by analog calculation. The variation rules of the residual velocity and residual mass of fragments, chock mass and crevasse shape are obtained when the fragment penetrates target board with different incidence velocities and attack angles. Corresponding fitting computation formulas are concluded from the above calculating data. The conclusions are helpful to analyzing the destructivity of fragment and protective ability of aircraft structure. In addition, they can guide the research for battle damage mode and assessment effectively.展开更多
基金The National Natural Science Foundation of China(No.61973172,61973175)the Key Technologies R&D Program of Tianjin(No.19JCZDJC32800).
文摘An equivalent sliding mode fault-tolerant control method with continuous switching is proposed for vertical tail damage.First,the nonlinear damage model of aircraft and the estimation of stability and control derivatives are introduced.Secondly,the linear sliding surface and the equivalent sliding mode controller are constructed,and the sufficient conditions for the stability of the damaged aircraft motion model are given by using the Lyapunov technique.The damage-tolerant controller is designed based on an adaptive sliding mode control for analyzing damaged aircraft systems.Furthermore,the hyperbolic tangent function is utilized to replace the symbolic function in the controller.The feasibility of the hyperbolic tangent function as the switching function is analyzed theoretically.Finally,the Boeing-747100/200 model is taken as an example to demonstrate the efficiency of theoretical results by recognizing the structural fault of aircraft.Numerical results show that the control law has a positive impact on the performance of the closed-loop system,and it also has a better fault tolerance and robustness towards external disturbance compared with traditional methods of damaged aircraft stabilization control.
基金Sponsored by the Ministerial Level Advanced Research Foundation(2164K)
文摘By establishing the finite element models and corresponding calculation methods for the target board and rod-shaped fragment, the penetration effect of the high-velocity rod-shaped fragments＇ impact on the LY- 12cz thin sheet is analyzed by analog calculation. The variation rules of the residual velocity and residual mass of fragments, chock mass and crevasse shape are obtained when the fragment penetrates target board with different incidence velocities and attack angles. Corresponding fitting computation formulas are concluded from the above calculating data. The conclusions are helpful to analyzing the destructivity of fragment and protective ability of aircraft structure. In addition, they can guide the research for battle damage mode and assessment effectively.
