RU1772638C - Fluid-tightness testing device - Google Patents

Abstract

The invention relates to spacecraft (SC). used in lengthy leak tests in the vacuum chamber of spacecraft systems. having a wide range of allowable leaks. The aim of the invention is to improve the quality of control of the amount of leakage of the product. This is achieved by that. that in the leakproofness test apparatus comprising a vacuum chamber and a leak detector and valve mounted on it, the leakage control unit is made in the form of a measuring tank with an adjustable control flow and a pressure sensor placed on it. 1 ill.

Description

The invention relates to the creation of spacecraft, and is used in lengthy leak tests in a vacuum chamber of spacecraft systems having a wide range of permissible leaks.

A leakproofness testing apparatus is known comprising a vacuum chamber, a valve and a control leak.

Closest to this technical solution is a leak testing device comprising a vacuum chamber with a valve and a control leak.

In this device in a vacuum chamber according to the method of comparison with the flow from the control leak, according to OST 92-1527-73 KA SYSTEMS, which have a wide range of permissible leaks (from 0.01 to 18.0 μm Hg / s), it is required during lengthy leak tests, the use of a number of control leaks with various

types of control gas flows.

The aim of the invention is to improve the quality of monitoring the amount of leakage of the product.

This is achieved by the fact that in the proposed device, the leakage monitoring unit is made in the form of a measured capacitance of an adjustable control leak (RCT) placed on it and a pressure sensor.

The drawing shows a General view of the proposed device.

It contains a vacuum chamber 1 with a valve 2, including a measured vacuum container 3 with a pressure sensor 4 and an RCT 5, connected by a pipe 6 to an air console 7. The test spacecraft 8 is installed in a vacuum chamber, whose systems are connected by pipelines 9 and 10 to an air console 7. Vacuum chamber 1 vacuum is pumped 11. The tightness of spacecraft 8 systems is measured by leak detector 12. Speed

with

6

VI

VI

u o so

00

pressure increases in the measured vacuum container 3 are measured with a stopwatch 13 over pressure sensor 4.

The device operates as follows.

Opening the valve 2, vacuum the vacuum chamber 1 and the measured vacuum tank 3 by the pump 11 to the working vacuum. Close valve 2 and measure the increase in pressure A p0 by pressure sensor 4 during the time L0 by stopwatch 13 in the measured vacuum container 3 due to gas separation and leakage.

After that, the amount of gas separation and leakage into the measured vacuum container 3 is determined by the formula Q0 l ° V,

1lTo

where V is the volume of the measured vacuum container 3. By opening valve 2, control gas is supplied from the console 7 through a pipe 6 to the RCT 5 and the opening of the RCT 5 is opened. Close valve 2 and measure the increase in pressure Ap by pressure sensor 4 for time A g by stopwatch 13 in a measured vacuum tank 3. The total value of gas separation, leakage and the flow of control gas from the RKT 5 is determined by the formula

QЈ dR V, and the magnitude of the flow of the control gas from the RCT 5 as follows Approx. 0Ј Qo. Open valve 2 and record readings “to the leak detector 12 for the measured flow of control gas from the RCT 5, then close valve 2. Charge the first KA system 8 and record readings Oizd of the leak detector 12 for the flow of control gas from leaks of the first KA system.

The value of the control gas flow from the leak in the first spacecraft system is determined by the formula Further

"Ct

retune RCT 5 to the next control gas stream by changing its opening or pressure of the control gas supplied to it. By determining the amount of control gas flow from the RCT 5, a second spacecraft system is charged. the readings of the leak detector 12 are recorded and the leakage rate of the second spacecraft system is determined as above.

Using this unit for

leak test of spacecraft systems eliminates the need for a set of different control leaks in connection with the use of a single RCT; measurement of the amount of control gas flow from the RCT is carried out directly during the leak test; increases the accuracy of measuring the actual value of leakage of the tested spacecraft system and thereby increases the reliability

work item.

Claims (1)

The claims A leakproofness testing apparatus comprising a vacuum chamber, a leak detector installed thereon, a valve and a leakage control unit connected to the valve, characterized in that. in order to improve quality control, the leakage control unit is made in the form of a measuring tank and an adjustable control leak and a pressure sensor placed on it. 8 / s