Flight-Propulsion Integration Dynamic Analysis and Adaptive Control of the Hypersonic Vehicle at Wide-Range Mach Numbers

Abstract

There are serious among various components of the hypersonic vehicle at wide-range Mach numbers, and the coupling among aerodynamic shape, propulsion system, structure, and control system is remarkable. For excellent performance, its components and functions are highly integrated, which brings serious challenges to traditional design examples, methods, and tools. To solve the integrated control problem of flight-propulsion coupling, a controller based on pole assignment is designed in this paper, and the control parameters can be adjusted according to real-time aerodynamic data. The parametric model of hypersonic vehicle at wide-range Mach numbers with coupling characteristics is established and the flight data under various working conditions are obtained. The flight dynamical model is established with a coupling relationship between the airframe and engine. Combined with the characteristic parameters of the aircraft attitude control closed-loop system, the control gain is designed based on expected poles and adjusted in real-time. The comparative simulations are carried out, and the results show that the control gain adjustment strategy based on aerodynamic parameter identification can improve the attitude angle command tracking quality and the robustness of the system.

Keywords

• Hypersonic vehicle
• wide-range Mach numbers
• aerodynamic parameter identification
• coupling control
• control gain adjustment strategy