Aerospace vehicle large envelope switching control method adopting protection mapping theory

Abstract

The invention discloses an aerospace vehicle large envelope switching control method adopting a protection mapping theory. The method is characterized by averaging network division flight envelopes, selecting a balance point and establishing a linear model; then based on a gap metric, selecting a nominal point in a flight large envelope; designing an aerospace vehicle control structure; according to a flight attitude, controlling a target and determining a stability range; according to the protection mapping theory, determining an inner ring attitude controller parameter for a linear system of each balance point; and then calculating and acquiring a transfer function of the linear system; establishing an equivalent low order model of an inner ring system and an equivalent low order model of an outer ring system; extracting a state matrix of each linear system; using a Jacobian linearization method to establish an LPV model; according to a flight locus, controlling the target and determining the stability range; based on a protection mapping parameter, setting an algorithm and calculating an outer ring height controller parameter; and finally, acquiring an analytical expression of a controller.

Description

technical field [0001] The invention relates to a design strategy of a large-envelope adaptive control law of an aerospace vehicle. In particular, the invention discloses a large-envelope switching control method of an aerospace vehicle using a protection mapping theory. Background technique [0002] Aerospace Vehicle (ASV) is a new type of reusable aircraft that integrates aircraft, spacecraft and vehicle. It can not only perform hypersonic cruise flight in the atmosphere, but also enter the orbit through the atmosphere. Therefore, it has high military and civilian value. Different from traditional aircraft, ASV exhibits the characteristics of multi-task, multi-working mode and large-scale high-speed maneuvering. In order to complete the established mission, the entire flight process includes four stages of subsonic speed, transonic speed, supersonic speed and hypersonic speed. Therefore, a large number of technical problems need to be solved urgently. solve. [0003] As ...

AI Technical Summary

Problems solved by technology

First of all, due to the ASV's multi-task, multi-working mode and large-scale maneuvering flight, the ASV presents strong nonlinear dynamic characteristics. The traditional method can no longer meet the requirements of its control performance and control accuracy. Therefore, the new control system should have more excellent Excellent performance and better versatility, thus effectively reducing design complexity

Secondly, the entire flight environment and aerodynamic characteristics of ASV have fast time-varying characteristics, and the rapid consumption of fuel will also cause changes in the center of mass and moment of inertia of the aircraft, which leads to the ASV control problem is a fast time-varying parameter system stability problem

Firstly, the gain-scheduled controller switches continuously within the large flight envelope according to the flight state, and the sudden change of fast time-varying parameters will affect the response of the system; secondly, the controller structure is not fixed during the design process, which leads to different operating points Designing a controller is a time-consuming and inefficient process

In addition, the gain preset control lacks perfect theoretical analysis. Although it can have better feedback performance at local points and meet the expected index requirements, it cannot guarantee to meet the stability and robustness performance index requirements of the entire flight envelope.

Therefore, this method has certain limitations in the design ideas and design process, and cannot well meet the control design requirements of modern high-performance aircraft.

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