Adaptive winglet switching control system and working method for near-space variable-wing aircraft

Abstract

The invention discloses a near space variable wing aircraft adaptive winglet switching control system and a working method thereof, and belongs to the technical field of aviation aerospace propulsion control. For the problem of stable tracking control of speed and attitude of a near space variable wing aircraft and with the influence of a variable wing structure on modeling and the problem of switching control in the winglet telescoping process being considered, the method is characterized by obtaining a state equation expression based on a nonlinear model of an aircraft; and according to relative order of velocity and pitch angle, establishing reference models of an adaptive control system. A designed adaptive controller comprises a nominal controller and an adaptive update module, wherein the adaptive update module is used for automatically updating controller parameters to realize smooth transition before and after winglet switching. The system and method can ensure global stability of a closed-loop system, and the system is allowed to have good tracking performance and robust performance.

Description

technical field [0001] The invention belongs to the technical field of aerospace propulsion control, and specifically refers to an adaptive winglet switching control system and working method for a near-space variable-wing aircraft. Background technique [0002] The propulsion power used by the near-space vehicle is a supersonic combustion ramjet engine that does not need its own oxidant, and the aerodynamic layout is an integrated body / engine design. There is a strong coupling between the elastic body of the near-space vehicle and the flight propulsion system, the nonlinear characteristics of the vehicle model are very serious, the flight process has rapid time-varying characteristics, the aerodynamic characteristics of the near-space vehicle change drastically, and various uncertainties are serious , the traditional classical control methods cannot well meet the performance requirements of flight control system stability and strong robustness. Therefore, to ensure the rea...

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Problems solved by technology

Factors such as large-span flight envelope, severe external disturbance, elastic deformation, high temperature and low-density flow effects will seriously affect the stability of the system

Second, the flight control system must meet robustness requirements

However, the dynamic inverse method is sensitive to modeling errors, and under normal circumstances, it is very difficult to accurately model nonlinear systems. Once the modeling is different from the actual system, the cancellation of nonlinear coupling characteristics will have an impact, resulting in deterioration of control performance. , the robustness cannot be guaranteed

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