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By using light-weighted material in hypersonic flight vehicle, the vehicle body can be easily deformed. The mutual couplings in aerodynamics, flexible structure and control system will result in aeroservoelasticity problem. Based on the six-DOF geometry of a hypersonic flight vehicle, this paper uses assumed modes method, Shock-Expansion theory and Piston theory to develop the structural elastic model and the aerodynamic model, with actuator incorporated, the open-loop aeroservoelastic model of a six-DOF HFV is established. In open-loop analysis, the response of the elastic coordinates to the tail rudder deflection and the frequency characteristic of the transfer function of the tail rudder deflection to the first elastic coordinate are studied. A high gain feedback controller is designed for the aeroservoelastic model, and closed-loop analysis is conducted based on this model. The simulations show the influence of the elastic motion on the aerodynamic forces and moments.

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This paper considers the fault detection problem of distributed networked control systems (DNCS) with time delay. A sliding mode observer-based fault detection method for a two-level DNCS is presented and two different situations are considered. When all the states of the system are available for measurement, we convert the fault detection problem to a sliding motion stable and reachable problem. When some states of system are not available for measurement, we design a transformation matrix to separate the measurable states and the unknown states, and then different sliding mode observers for those unknown states are developed to achieve fault detection. Finally, a numerical example is provided to illustrate the effectiveness of the proposed method with simulation results.