Designing Backstepping Control System for Hypersonic Vehicle Based on Feedback Linearization

Abstract EN

A hypersonic vehicle uses the airbreathing scramjet engine and the airframe and engine integrated design.

Therefore, there is a strong cross-coupling effect among its aerodynamic force, thrust, structure, and control.

The nonlinearity and uncertainty of the model cause difficulties in control system design.

Considering the nonlinearity, coupling characteristics, and aerodynamic parametric uncertainty of its longitudinal dynamic model, we design the control law for its altitude system and velocity system based on the adaptive backstepping control method.

Because of the feedback linearization method, we introduce the constraints of the flight vehicle’s actuator into the design, obtaining the robust adaptive control system constrained by the actuator of the flight vehicle.

To avoid the high-order derivation problem of the feedback linearization method and the derivation of the virtual control volume in adaptive backstepping control method, we use the arbitrary-order robust exact differentiator to solve the high-order derivatives in feedback linearization and utilize the command filter to obtain the virtual control volume and its derivatives.

The simulation results show that the robust adaptive control system we designed can achieve the error-free tracking of altitude and velocity command.

It can well overcome the influence of structural parameters, aerodynamic parametric uncertainty, and disturbances; meanwhile, the control command can satisfy the constraints of the actuator.