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This paper presents a novel control design strategy for the hypersonic vehicle using the elastic surrogate model. First, the parametric model is established for the rigid mode of the hypersonic vehicle based on the engineering estimation and panel methods. Then, the beam surrogate model is applied to identify the elastic mode of the hypersonic vehi...
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Citations
... Zong put forward a hypersonic model that took elasticity into account [8]. Liu developed a more accurate elastic replacement model [9]. In the modeling, comprehensive algorithm [10], quantitative echo [11], two-stage orbit [12] and other new methods based on the BGK scheme of gas dynamics were adopted. ...
This paper investigates the fault tolerance control of hypersonic aircrafts with L1 adaptive control method in the presence of loss of actuator effectiveness fault. The hypersonic model considers the uncertainties caused by the features of nonlinearities and couplings. Elasticity is taken into account in hypersonic vehicle modeling which makes the model more accurate. A velocity L1 adaptive controller and an altitude L1 adaptive controller are designed to control flexible hypersonic vehicle model with actuator loss fault. A PID controller is designed as well for comparison. Finally, the simulation results are used to analyze the effectiveness of the controller. Compared to the results of PID controller, L1 controllers have better performance.
... The hypersonic flow contains high energy and the boundary layers become high-temperature regions; therefore, thermal analysis is essential to consider with aerodynamic behavior [3]. The elastic disturbance is another concern for highspeed flight, hence, Liu et al. [4] created a control-relevant model to suppress elastic disturbances and outlined the performance limitation analysis. Complex environment and flight requirements of the hypersonic vehicles are leading the researchers to focus on several design considerations. ...
Hypersonic vehicles are receiving great attention in recent years due to their high speed and long-range capabilities. The shock waves come into consideration as a propagating disturbance for any aircraft when it exceeds the speed of sound. Complex environment and flight requirements of the hypersonic vehicles are leading the researchers to focus on several design considerations. Adaptive shape deformation is one of the prospective areas among them which has an impact on thermal loading, global and local load factors, vehicle acceleration, total energy dissipation, and fuel consumption. The wings play a key role in the aerodynamic performances of a flying machine; therefore, the overall performance of the hypersonic vehicle can be improved by applying morphing technologies on the wing. Morphing can help with reducing wave drag, increasing lift-to-drag ratio as well as enhancing flight endurance, and extending the range for a hypersonic vehicle. In this study, the telescopic wing morphing profile is considered for the aerodynamics and vibration analysis. The experimental validations of the aerodynamics and vibration characteristics are conducted by a wind-tunnel experiment and a vibration-testing arrangement, respectively, using a small-scale model of the wing. The computational analysis of the aerodynamics and vibration characteristics of the morphing wings are conducted and compared. Thus, a comprehensive study including the comparison between morphing modes can establish a standard to choose the appropriate morphing technique for the hypersonic vehicles.
