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In this paper, an attitude control strategy is proposed for a class of tail-sitter aerial vehicles, which is required to achieve the desired tracking control performance during the mode transition. The resulted controller is constructed by a nominal controller and a robust compensator to reduce the effects of nonlinear dynamics and uncertainties. Theoretical analysis and numerical simulation results...
This paper presents a robust controller design approach for the longitudinal dynamics of hypersonic vehicles. The proposed linear and time-invariant controller includes a state feedback H∞ controller and a robust compensator. The robust compensator is introduced to restrain the effects of nonlinear dynamics and unstructured uncertainties in the whole frequency range. It is proven that the velocity...
The reusable launch vehicle (RLV) has strongly nonlinear, fast time-varying characters and multiple control modes, which challenge attitude control in task-adaptability greatly. A nonlinear RCS/aerosurfaces compound controller control scheme was presented. First a RLV model equipped with reaction control system (RCS) and aerosurfaces is developed. Then fast and slow loops control system is designed...
A direct method is discussed for multistage launch vehicle ascent trajectory optimization. First the optimal control problem is modeled with the performance index as maximum terminal mass. A modified Gauss Pseudospectral method is used to design a rapid optimal algorithm for multistage launch vehicle ascent trajectory. The nonlinear terminal state constraints are converted into linear terminal state...
The guidance system of terminal flight is to guide the vehicle flies into the target precisely in a specific direction while satisfy all the constraints. A new adaptive proportion navigation guidance method is proposed. First the constraints are analyzed. To provide enough time for the lateral and longitudinal adjustments, a convergence strategy is designed and it improves the performance of proportion...
A composite control treatment based on sliding mode is presented to a hypersonic nonlinear longitudinal dynamics. The aircraft model is developed with a unique integrated airframe-propulsion configuration which arise couplings between propulsion and aerodynamics and it is also a non-minimum phase systems with zero-dynamics. All of these result in intractable nonlinear system for control design. In...
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