Control method for cabin temperature control system during switching aircraft engine state

Abstract

The invention belongs to the technical field of aircraft cabin temperature control and relates to a control method for a cabin temperature control system during switching an aircraft engine state. When an engine is switched from a slow state to a normal state, a cold air duct regulating valve is opened at a full speed, a temperature control valve is closed at a certain speed, and the temperature of a cabin is adjusted by using a PID algorithm after the cold air duct regulating valve is fully opened and the temperature control valve is closed; and when the engine is switched from the normal state to the slow state, the control quantity received by the cold air duct regulating valve is 2-4 times larger than the normal control quantity calculated and output by the PID algorithm, the control quantity received by the temperature control valve is 2-5 times larger than the normal control quantity calculated and output by the PID algorithm, and the temperature of the cabin is adjusted by using the PID algorithm after the cold air duct regulating valve is fully closed and the temperature control valve is fully opened or the temperature of a cabin air supply pipeline reaches a target value. Problems that the temperature control of the cabin is overshot and the the temperature of the cabin air supply pipeline exceeds the target value during switching the engine state are solved; and the system control stability is enhanced.

Description

technical field [0001] The invention belongs to the technical field of aircraft cockpit temperature control, and relates to a control method for a cockpit temperature control system in an aircraft engine switching state. Background technique [0002] With the development of engines at home and abroad, the engine performance has been greatly improved. The engine can switch from idle to normal state in an instant, resulting in a transient change in the outlet temperature of the environmental control bleed air system. Because the environmental control cockpit temperature control system is In the large inertia control system, in order to ensure the stability of the system, the adjustment speed of each actuator is relatively slow. However, when the engine state is changed, the system is adjusted according to the normal state, and the system response must not keep up with the change of the engine state, which will inevitably cause system control overshoot, overheating of the air s...

AI Technical Summary

Problems solved by technology

[0002] With the development of engines at home and abroad, the engine performance has been greatly improved. The engine can switch from idle to normal state in an instant, resulting in a transient change in the outlet temperature of the environmental control bleed air system. Because the environmental control cockpit temperature control system is Large inertia control system, in order to ensure system stability, the adjustment speed of each actuator is relatively slow

However, when the engine state changes, the system is adjusted according to the normal state, and the system response must not keep up with the change of the engine state, which will inevitably cause system control overshoot, air supply pipeline overtemperature, and even system temperature control instability.

Most of the solutions to this problem at home and abroad are to mix the air drawn by the fan with the gas of the environmental control air conditioning system when the engine state is changed. This method will bring about the problems of increased system weight and high noise.