Abstract
The stability analysis method based on region of attraction is proposed for the hypersonic flight vehicles’ flight control verification in this article. Current practice for hypersonic flight vehicles’ flight control verification is largely dependent on linear theoretical analysis and nonlinear simulation research. This problem can be improved by the nonlinear stability analysis of flight control system. Firstly, the hypersonic flight vehicles’ flight dynamic model is simplified and fitted by polynomial equation. And then the region of attraction estimation method based on V–s iteration is presented to complete the stability analysis. Finally, with the controller law, the closed-loop system stability is analyzed to verify the effectiveness of the proposed method.
Highlights
A large number of flight tests have proved the feasibility of hypersonic flight vehicle (HFV)
With the high flight speed, wide flight envelope, complex flight environment, and the strong nonlinear relationship between system input and output, HFV’s control problem has always been a hot issue in recent years.[1]. It is well-known that the nonlinear model of HFV is unstable or even has some highly complex motion characteristics
The stability of aircraft has been greatly improved by the introduction of modern advanced control technology under normal condition, some undiscovered characteristics or unstable state points of aircraft could bring great threat to flight safety, which can even lead to significant accident
Summary
A large number of flight tests have proved the feasibility of hypersonic flight vehicle (HFV). Linear analysis approach is applied widely in this field, and the good effect has been gained, it assesses the closed-loop system’s stability and performance characteristics of aircraft at the trimming point. The commonly used method for ROA estimation in control field is numerical solution based on Lyapunov function. With the NASA’s winged-cone configuration hypersonic vehicle simulation model,[16] the polynomial fitting model is constructed firstly in this article to represent the HFV’s longitudinal dynamics, and the ROA analysis approach will be proposed to complete flight control law verification. In “Hypersonic vehicle models” section, the NASA’s winged-cone configuration hypersonic vehicle’s longitudinal aerodynamic equations are presented firstly, and the polynomial fitting model for longitudinal dynamics is obtained. S Mean aerodynamic chord, c Mass, m Pitch axis moment of inertia, Iyy Air density, Gravity constant, g
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