Control-oriented Modeling for Air-breathing Hypersonic Vehicle Using Parameterized Configuration Approach

Flight control technology of hypersonic vehicles is very difficult because hypersonic vehicles have many features, such as strong nonlinearity, variable coupling, parameter variation, and uncertainties. In this paper, based on the generic hypersonic vehicle longitudinal model, two flight control methods based on back-stepping and dynamic inversion control respectively are simulated and analyzed. For the back-stepping based control, the back-stepping method is introduced to design control inputs for subsystems of the flight model. For the dynamic inversion based control, an inversion system is obtained by using feed-back linearization, and then controllers are designed by using linear control methods. Simulation of the hypersonic vehicle longitudinal model and two control methods are carried out in this paper. The tracking control performances of velocity and altitude of the hypersonic vehicle are verified. Then the two control methods are analyzed and evaluated in terms of control performances and engineering practicability. The back-stepping based control has high response speed and precision, and it is very suitable for on-line control. The dynamic inversion based control has a stable dynamic performance and better portability.

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“…Proceedings of the 33rd Chinese Control Conference July 28-30, 2014, Nanjing, China [9] [4] . Wing-cone [11,12] . [13] cos sin sin cos…”

Section: Simulation Analysis Of Hypersonic Vehicle Flight Controlmentioning

confidence: 99%

Simulation analysis of hypersonic vehicle flight control based on back-stepping and dynamic inversion

Liu

Hong

Xiong

2014

Proceedings of the 33rd Chinese Control Conference

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“…The velocity coordinates are used to describe the aerodynamic forces and moments, determining the vehicle movement. Furthermore, we select the elevator deflection ( e ) and the throttle setting command ( c ) as the control inputs (U); so the nonlinear vehicle model is given as follows 11,12 …”

Section: Integrated Model Of Hypersonic Vehiclementioning

confidence: 99%

Research on advanced flight control methods based on actuator constraints for elastic model of hypersonic vehicle

Liu

Xiao

2013

Proceedings of the Institution of Mechanical Engineers, Part G:

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Powerful actuators are both indispensable and critical components for the flight control system of hypersonic vehicles. More importantly, the performance of actuators has substantial impact on the control ability; therefore, when designing the control system, one needs to fully take into account actuator restraints in order to meet the efficient and precise control demands under complex flight conditions. In this article, the advanced flight control methods concerned with actuator limitations are discussed for hypersonic vehicles. First, the longitudinal model of hypersonic vehicle is established with consideration of the nonlinear coupling dynamics. Second, the actuator constraints with the effect of elastic deformation are introduced to this built model and then the resulting unstable dynamics characteristic and the control limitation conditions are analyzed for hypersonic vehicle. Furthermore, the advanced flight control laws are designed by using the differential geometry principle and the total energy theory. Finally, simulation results verify the feasibility of the proposed methods for hypersonic vehicle.

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“…The flow out of internal nozzle directly affects the pressure distribution on the external nozzle, which have significant influence on the pitch moment. Lisa et al formulated the curve-fitted model by adding flexible states, but also ignored the effect of Mach number, 21 while the impact of Mach number on the aerodynamic coefficients have been taken into consideration by Li et al 22 Yet little attention has been drawn to the identification of the model structure.…”

Section: Introductionmentioning

confidence: 99%

Surrogate modeling of a 3D scramjet-powered hypersonic vehicle based on screening method IFFD

Chen

Liu

Shen

et al. 2016

Proceedings of the Institution of Mechanical Engineers, Part G:

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The emphasis of this paper lies in the development of an efficient approach to reproduce the behaviors of the scramjetpowered hypersonic system with high fidelity. The modeling of the dual-mode scramjet powered hypersonic vehicle dynamics with shock interaction, Ram-to-Scram transition, and finite rate chemistry reaction is firstly introduced. The structure of surrogate model is identified with the implement of iterative fractional factorial design (IFFD). In order to declare the reliability of the surrogate models, -gap metric is applied to distinguish the difference among these surrogate models in terms of closed-loop performance. The results show that the influence of Mach number on the aerodynamics should not be overlooked, and the effect of propulsion system to the aerodynamic pitch moment is dramatic. Further, the partial Kriging model appears to have the closest plants throughout the flight envelope compared with the full Kriging model and polynomials model. Nevertheless, considering the briefness of analytical expression, the polynomials model may be an alternative approach for design-oriented modeling.

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Control-oriented Modeling for Air-breathing Hypersonic Vehicle Using Parameterized Configuration Approach

Cited by 46 publications

References 12 publications

Simulation analysis of hypersonic vehicle flight control based on back-stepping and dynamic inversion

Simulation analysis of hypersonic vehicle flight control based on back-stepping and dynamic inversion

Research on advanced flight control methods based on actuator constraints for elastic model of hypersonic vehicle

Surrogate modeling of a 3D scramjet-powered hypersonic vehicle based on screening method IFFD

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