Method for calculating simulated leakage rate

A calculation method and leakage technology, applied in the calculation field of simulated leakage, can solve the problems of expensive aircraft equipment, lack of airtightness, large volume and other problems, and achieve the effect of reducing the test cost and test difficulty.

Inactive Publication Date: 2020-11-10
CHENGDU AIRCRAFT INDUSTRY GROUP
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Problems solved by technology

[0002] When the aircraft is flying at high altitude, there is a pressure difference between the inside and outside, and the pipeline or equipment that is not completely sealed will cause leakage, such as radar waveguide, etc. The radar waveguide is connected to the radar for the conduction of electromagnetic waves. Sealing, there is a small leakage (0.8~2g/h) in the radar waveguide, the air pressure in the waveguide will gradually decrease to the ambient pressure, the pressure drop will affect the transmission of electro

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  • Method for calculating simulated leakage rate
  • Method for calculating simulated leakage rate
  • Method for calculating simulated leakage rate

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Embodiment 1

[0037] Such as figure 1 As shown, a calculation method of simulated leakage includes the following steps:

[0038] a. Insert one end of the capillary 1 into the simulation chamber 2, and the other end extends outside the simulation chamber 2, and fill the simulation chamber 2 with pressure gas through the inlet 3;

[0039] b. Calculate the capillary length required for leakage according to the mass flow rate of the capillary, the formula is as follows:

[0040]

[0041] Among them, P1 and P2 are the pressures at the two ports of the capillary (pa); ρ is the flow density (kg / m 3 ); μ is the dynamic viscosity coefficient (pa s); l is the capillary length (m); r is the capillary radius (m), Q m is the set leakage rate;

[0042] c. Set dx as any length (m) on the capillary, and the pressure difference at both ends is dp=p1-p2, and the following formula can be obtained from formula (1):

[0043]

[0044] d. The following formula is obtained from the gas state formula P=ρR...

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Abstract

The invention discloses a method for calculating a simulated leakage rate, which comprises the following steps of: inserting one end of a capillary tube into a simulated cavity, extending the other end of the capillary tube to the outside of the simulated cavity, and filling pressure gas into the simulated cavity through an inlet; and b, calculating the length of the capillary tube required duringleakage according to the mass flow of the capillary tube. Leakage resistance is controlled through the capillary tube, the capillary tube is inserted after the cavity wall of the simulation piece ispunched, flow resistance is adjusted by adjusting the length of the capillary tube, control over local flow loss is converted into control over on-way loss, the tiny leakage amount is simulated and calculated, and the tiny leakage amount can be simulated with high precision. Test cost and test difficulty of the ground performance test of the micro-leakage equipment are effectively reduced.

Description

technical field [0001] The invention belongs to the technical field of aviation air pressure monitoring, in particular to a calculation method of simulated leakage. Background technique [0002] When the aircraft is flying at high altitude, there is a pressure difference between the inside and outside, and the pipeline or equipment that is not completely sealed will cause leakage, such as radar waveguide, etc. The radar waveguide is connected to the radar for the conduction of electromagnetic waves. Sealing, there is a small leakage (0.8~2g / h) in the radar waveguide, the air pressure in the waveguide will gradually decrease to the ambient pressure, the pressure drop will affect the transmission of electromagnetic waves in the waveguide, and may cause the waveguide to catch fire and damage the radar, so the design A pressurization system is used to pressurize the waveguide. In order to verify the performance of the pressurization system, a ground performance simulation test i...

Claims

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Application Information

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IPC IPC(8): G06F30/15G06F30/20B64F5/60G06F113/08G06F119/14
CPCG06F30/15G06F30/20B64F5/60G06F2113/08G06F2119/14
Inventor 吴佩佩晏涛陈维建何泳任杰马赛强陈齐林周君慧
Owner CHENGDU AIRCRAFT INDUSTRY GROUP
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