Nonlinear PID control method for rear cabin pressure system of high-altitude platform

Abstract

The invention belongs to the technical field of aero-engine high-altitude simulation, and particularly relates to a high-altitude platform rear cabin pressure system nonlinear PID control method. Themethod comprises the steps: determining a pressure deviation e according to a pressure expected value and a pressure feedback value; establishing an optimization objective function J(theta) formed bythe pressure deviation, wherein theta is a controller parameter vector, theta=[Kp, Ki, Kd], Kp is a proportionality coefficient, Ki is an integral coefficient, Kd is a differential coefficient, J* isa target minimum value, J'' is a second-order differential of J(theta), and [theta]* is the optimal value of the controller parameter; utilizing an extreme value search algorithm to enable the optimization objective function J(theta) to reach a minimum value to determine a control parameter optimal value of the PID control algorithm; and forming a control quantity control pressure feedback value according to the optimal value of the control parameter of the PID control algorithm. According to the method, online self-tuning and self-optimizing can be achieved, the method does not depend on a mathematical model of a controlled object, the good set value tracking effect and anti-jamming capability are achieved, and the dynamic adjustment quality in the engine rapid transition state test can be effectively improved.

Description

technical field [0001] The invention belongs to the technical field of high-altitude simulation of aero-engines, and in particular relates to a nonlinear PID control method for a rear cabin pressure system of a high-altitude platform. Background technique [0002] The aero-engine high-altitude simulation test bench is a large-scale ground equipment for testing and evaluating the high-altitude working performance of aero-engines. It undertakes the test tasks of aero-engines from design to finalization under various flight environmental conditions, and plays a vital role in the technical development of aero-engines. role. The flight altitude simulation system (that is, the aft cabin pressure adjustment system that simulates the engine flight altitude) is the key equipment for the engine flight altitude simulation, and its adjustment quality is directly related to the accuracy and reliability of the engine air working condition simulation. Compared with other control subsystem...

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Problems solved by technology

[0004] Purpose of the invention: The present invention provides a non-linear PID control method for the aft cabin pressure system of the high-altitude platform to solve the problem that the controller cannot dynamically adjust the PID parameter value to actively adapt to the change of the nonlinear characteristics of the system, which seriously affects the dynamic adjustment of the aft cabin pressure Problems with characteristics and control accuracy

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