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.

Control design using PID with state feedback for Air-breathing Hypersonic Vehicle

“…The developed linear 6DOF AHV model given by (22)(23) is used for the simulation to understand the open loop dynamic behavior and the model's response. The simulation incorporates the aerodynamic coefficient model, the engine model with the propulsion engine, and with the standard atmospheric conditions from Section 2.…”

“…A controller with full-state feedback creates the input vector u(t), and accordingly, the control law is designed with state-space representation. Considering the control law design using the state feedback method, the LTI system state model expressed with (22)(23), indicating open-loop dynamics representation needs controller design. For the state feedback-based design control law using the state model is expressed using (28),…”

Constraints Maintaining Mesh Refinement Method for Solving Whole Trajectory of Discontinuous Aerodynamics

“…As shown in Fig. 1, the propulsion systems of the advanced vehicles mentioned in the first paragraph, whether rocket engines or scramjet engines, are integrated design with the body [28,29]. There are at least two engine modes during the vehicle's entire flight, such as the ascent of the poweron mode switching to the descent of the power-off mode, the turbine engine changing to a scramjet engine, etc.…”