Yuxiao Wang , Tao Chao  , Songyan Wang  , Ming Yang

DOI Number XXX-YYY-ZZZ

Conference Number HiSST 2018_1800991

The development of hypersonic flight control system is a challenging task, because of the tightly coupled, highly nonlinear and notoriously uncertain nature of hypersonic vehicle(HV) dynamics. Differential flatness method is applied to the linearization of the longitudinal model of HV. A finite time convergent controller is designed for the nominal linearized model. Then an integral sliding mode controller is added to deal with the uncertainty of the system. In addition, a discrete linear tracking differentiator(TD) is used to extract high order differential signal of the system, which can avoid the high order differential signal polluted in the numerical calculation. A case study is presented to illustrate the capability of the proposed control method.

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In Categories: Guidance & Control Systems, High-Speed Aerodynamics and Aerothermodynamics, HiSST 2018, Hypersonic Flight Dynamics, Supersonic and Hypersonic Aircraft Design
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