ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Integrated guidance and control design considering input saturation
Received date: 2016-10-28
Revised date: 2017-01-12
Online published: 2017-01-11
Supported by
National Natural Science Foundation of China (61403096);China Postdoctoral Science Foundation (2014M551242);the Fundamental Research Funds for the Central Universities (HIT.NSRIF.2014036,HIT.NSRIF.2015036);Heilongjiang Postdoctoral Fund (LBH-Z12112)
Hypersonic vehicle is fast varying in dive phase,so its actuator is easy to be saturated because of the physical constraint.Integrated guidance and control method considering input constraint is proposed.The longitudinal design model for integrated guidance and control is built.An extended state observer is taken to estimate the uncertainties and compensate them.A new integrated guidance and control method is built for the cascaded system based on the method of adding a power integrator and the method of nested anti-windup.Rigorous theoretic analysis proves that the control strategy can result in expected equilibrium of all system states in finite time.Because all the virtual control variables consider the saturation restraint,much more control capacity of the vehicle can be saved to realize accurate manipulation.A numerical simulation case is adopted to verify the effectiveness and robustness of the proposed method.
WANG Songyan , SUN Xiangyu , YANG Shengjiang , CHAO Tao . Integrated guidance and control design considering input saturation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2017 , 38(10) : 320897 -320897 . DOI: 10.7527/S1000-6893.2017.320897
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