A Disturbance Upper Bound Adaptive Fractional Order Global Terminal Sliding Mode Model-Free Control Method
A terminal sliding mode and control method technology, applied in adaptive control, general control system, control/regulation system, etc., can solve problems such as chattering, instability, terminal sliding mode control singularity, etc., to reduce steady-state error , increase the convergence speed and weaken the effect of chattering
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Embodiment 1
[0074] refer to Figure 1 to Figure 5 , which is the first embodiment of the present invention, provides a kind of disturbance upper bound adaptive fractional-order global terminal sliding mode model-free control method, the present invention is based on the super-local model of the model-free control of the hypersonic vehicle aerodynamic thermal ground simulation system, Combining iPD, time delay observer, fractional order global terminal sliding mode surface, equivalent control rate, approach rate, design controller u(t) to realize target tracking, refer to Figure 5 , is a disturbance upper bound adaptive fractional-order global terminal sliding mode model-free control block diagram of the hypersonic vehicle aerodynamic thermal ground simulation system of the present invention, specifically including:
[0075] S1: According to the law of energy conservation, establish the mathematical model of the aerothermal ground simulation system of the hypersonic vehicle and the hyperl...
Embodiment 2
[0139] refer to Figure 6 ~ Figure 9 , is the second embodiment of the present invention. This embodiment is different from the first embodiment in that it provides an experimental comparison of a disturbance upper bound adaptive fractional-order global interruption sliding mode model-free control method, specifically including:
[0140] In this embodiment, the hypersonic vehicle aerodynamic thermal ground simulation system will be used in the disturbance upper bound adaptive fractional-order global terminal sliding mode model-free control method (1), iPD traditional sliding mode control method (2), and traditional PID method (3) The output temperature and tracking error of the hypersonic vehicle aerothermal ground simulation system are measured and compared in real time.
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