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Dynamic aviation thermal power testing system and rapid temperature and pressure control method

A test system, thermodynamic technology, applied in non-electric variable control, control/regulation system, simultaneous control of multiple variables, etc., to reduce workload, avoid coupling effects, and stabilize air flow

Active Publication Date: 2015-03-25
BEIHANG UNIV
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  • Abstract
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AI Technical Summary

Problems solved by technology

[0003] Most of the existing aeronautical thermodynamic test benches can only conduct steady-state tests on specimens, and state parameters such as temperature, pressure, and flow are constant

Method used

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  • Dynamic aviation thermal power testing system and rapid temperature and pressure control method

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Embodiment Construction

[0045] The operation of the dynamic aviation thermodynamic test system will be described in detail below in conjunction with the accompanying drawings.

[0046] The dynamic aviation thermodynamic test system according to an embodiment of the present invention is as figure 1 as shown, figure 1 The system shown can be roughly divided into two parts: the test air supply system and the heating system, and the heat exchanger 8 connects these two parts; specifically: the air source (not shown) supplies normal temperature air, through the intake pipe 1 and the first quick adjustment After valve 2, it is divided into upper and lower paths. The upper road is the normal temperature road, and the lower road is the hot road. The lower air passes through the second quick regulating valve 3 and then enters the heat exchanger 8, and the heat exchanger 8 heats the lower air; the upper air passes through the third quick regulating valve 4 and is mixed with the heated lower air. The first te...

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Abstract

The invention belongs to the field of environment simulation and control, and relates to a dynamic aviation thermal power testing system and a rapid temperature and pressure control method which are mainly used for the airplane environment control system ground simulation test and are capable of achieving rapid temperature, pressure and flow adjustment and carrying out rapid temperature increasing and reducing and pressure increasing and reducing of an environment control system and the full-flight envelope dynamic simulation test. According to the dynamic aviation thermal power testing system, the project achieving difficulty of a heater is lowered through an indirect heating mode, and the possible problem of dried burning due to direct heating can be avoided. The temperature and pressure are independently controlled, and the temperature and pressure coupling effect is eliminated. A rapid adjusting mechanism is arranged in front of a heat exchanger, the project achieving difficulty of the adjusting mechanism is lowered, accordingly, the reliability of the system is improved, and the manufacturing cost of the system is reduced. The system is further provided with a heat regenerator, part of waste heat can be recycled, the system efficiency is improved, and the consumed energy of the system is reduced.

Description

technical field [0001] The invention relates to a dynamic aviation thermodynamic test system and a rapid control method of temperature and pressure, belonging to the technical field of environment simulation and control. Background technique [0002] The aviation thermodynamic test bench is an important support system for the research and development of the aircraft environmental control system, and its main function is to carry out the air environment simulation test of the aircraft environmental control system. By adjusting the pressure, flow, temperature and other parameters of the dry air from the air source system, simulate the bleed air, cockpit air supply, ram air and other air supply states of the aircraft engine under various flight states of the aircraft on the ground, and evaluate the aircraft System component performance and operational reliability. [0003] Most of the existing aeronautical thermodynamic test benches can only conduct steady-state tests on speci...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D27/02
Inventor 刘猛吴豪阿嵘庞丽萍王浚
Owner BEIHANG UNIV
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