Integrated design method for guidance and control of hypersonic aerocraft

Abstract

The invention discloses an integrated design method for guidance and control of a hypersonic aerocraft. The method comprises steps that firstly, a nonlinear dynamic model of the hypersonic aerocraft is established, based on the singular perturbation theory, the nonlinear dynamic model is divided into a slow time-varying guidance loop and a fast time-varying control loop, secondly, a nominal controller and a linear time-varying feedback controller of the two loops are designed separately, actual control input of the two loops is calculated, and lastly, control output of the two loops is calculated based on the mapping relationship. The method is advantaged in that aiming at the complex flight mission profile of the hypersonic aerocraft and a flight control problem along the trajectory, thecharacteristics of the hypersonic vehicle with strong coupling, strong nonlinearity and fast time-varying are considered, in the case of large system perturbation and external disturbance in the model, based on the trajectory linearization control method, integrated strategy design of guidance control is completed, the method is simple for realization and easy for engineering application in the hypersonic aircraft, and the method has better control performance and robust performance.

Description

technical field [0001] The invention belongs to the technical field of aircraft control, in particular to an integrated design method for guidance and control of a hypersonic aircraft based on a trajectory linearization method. Background technique [0002] Different from traditional aircraft, hypersonic aircraft has the characteristics of flight trajectory across large airspace and large speed range, which makes its flight state parameters and dynamic characteristics change rapidly, and is more sensitive to changes in environmental parameters; the body / engine integration technology makes the body of hypersonic aircraft. , the coupling between the propulsion systems is stronger, which makes the matching between the force systems show strong nonlinear characteristics; in addition, the flight environment of hypersonic aircraft is complex, and the aircraft is affected by large disturbances and disturbances during flight, and It is difficult to accurately simulate the complex fl...

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to overcome the deficiencies of the prior art, and propose a hypersonic aircraft guidance and control integrated design method based on the trajectory linearization method, which can solve the problems of the guidance loop and control of the hypersonic aircraft when the external disturbance and interference are large. loop mismatch problem

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