RU94029180A - Method of tightness testing of systems - Google Patents

Method of tightness testing of systems

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Publication number
RU94029180A
RU94029180A RU94029180/28A RU94029180A RU94029180A RU 94029180 A RU94029180 A RU 94029180A RU 94029180/28 A RU94029180/28 A RU 94029180/28A RU 94029180 A RU94029180 A RU 94029180A RU 94029180 A RU94029180 A RU 94029180A
Authority
RU
Russia
Prior art keywords
gas
testing
membrane
main line
line
Prior art date
Application number
RU94029180/28A
Other languages
Russian (ru)
Other versions
RU2082135C1 (en
Inventor
Н.Г. Панов
Original Assignee
Ракетно-космическая корпорация "Энергия" им.С.П.Королева
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Ракетно-космическая корпорация "Энергия" им.С.П.Королева filed Critical Ракетно-космическая корпорация "Энергия" им.С.П.Королева
Priority to RU94029180A priority Critical patent/RU2082135C1/en
Publication of RU94029180A publication Critical patent/RU94029180A/en
Application granted granted Critical
Publication of RU2082135C1 publication Critical patent/RU2082135C1/en

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  • Examining Or Testing Airtightness (AREA)

Abstract

FIELD: testing equipment. SUBSTANCE: method makes it possible to expand informativity of tightness testing of systems of flying vehicles having gas and hydraulic main lines separated by flexible membrane of compensator, of thermal control systems for example, thanks to determination of lack of tightness of compensator membrane. One of tested main lines is vacuumed and filled with testing gas up to atmospheric pressure. Excessive testing pressure is created in tested main line by way of vacuum treatment of another main line simultaneously with tested one which is followed by feed of ballast gas after tested main line is filled with testing gas of excessive pressure. Testing is started from test of hydraulic main line. After filling of gas main line with testing gas transfer of testing gas from gas main line through compensator membrane into hydraulic system is measured. Only after this if actual lack of tightness of membrane appears to be less than after this if actual lack of tightness of membrane appears to be less than permissible one specified excessive pressure of ballast gas is fed into hydraulic main line. EFFECT: expanded informativity of tightness testing. 1 cl

Claims (1)

Изобретение относится к испытательной технике и позволяет расширить информативность способа испытаний на герметичность систем летательных аппаратов, имеющих газовую и гидравлическую магистрали, разделенные гибкой мембраной компенсатора, например, систем терморегулирования за счет определения негерметичности мембраны компенсатора. Вакуумируют одну из проверяемых магистралей и заполняют ее контрольным газом до атмосферного давления, а избыточное испытательное давление в проверяемой магистрали создают путем вакуумирования одновременно с проверяемой магистралью другой магистрали системы с последующей подачей в нее после заполнения проверяемой магистрали контрольным газом заданного избыточного давления балластного газа, при этом испытания начинают с проверки гидравлической магистрали, а после заполнения газовой магистрали контрольным газом измеряют перетекание контрольного газа из газовой магистрали через мембрану компенсатора в гидравлическую магистраль и только затем, если тактическая негерметичность мембраны окажется меньше допустимой, подают в гидравлическую магистраль заданное избыточное давление балластного газа.The invention relates to test equipment and allows to expand the information content of the method of leak testing of aircraft systems having gas and hydraulic lines, separated by a flexible compensator membrane, for example, temperature control systems by determining leakage of the compensator membrane. One of the tested lines is evacuated and filled with control gas to atmospheric pressure, and an excess test pressure in the tested line is created by evacuating simultaneously with the tested line of the other line of the system with subsequent supply of the specified excess ballast gas pressure to it after filling the test line with the control gas, tests begin with checking the hydraulic line, and after filling the gas line with control gas, the overflow is measured s control gas from a gas pipeline through a membrane compensator in hydraulic line and only then if tactical leakage is less than the allowable membrane is fed into the hydraulic line predetermined overpressure ballast gas.
RU94029180A 1994-08-03 1994-08-03 Method of leak-proofness test of flight vehicle systems having gas and hydraulic lines separated by compensator flexible membrane RU2082135C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU94029180A RU2082135C1 (en) 1994-08-03 1994-08-03 Method of leak-proofness test of flight vehicle systems having gas and hydraulic lines separated by compensator flexible membrane

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU94029180A RU2082135C1 (en) 1994-08-03 1994-08-03 Method of leak-proofness test of flight vehicle systems having gas and hydraulic lines separated by compensator flexible membrane

Publications (2)

Publication Number Publication Date
RU94029180A true RU94029180A (en) 1996-06-20
RU2082135C1 RU2082135C1 (en) 1997-06-20

Family

ID=20159379

Family Applications (1)

Application Number Title Priority Date Filing Date
RU94029180A RU2082135C1 (en) 1994-08-03 1994-08-03 Method of leak-proofness test of flight vehicle systems having gas and hydraulic lines separated by compensator flexible membrane

Country Status (1)

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RU (1) RU2082135C1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2556283C2 (en) * 2013-11-12 2015-07-10 Открытое акционерное общество "Ракетно-космическая корпорация "Энергия" имени С.П. Королева" Leakage tests for spacecraft thermal control hydraulic system equipped with hydropneumatic compensator with fluid cavity limiting grate
RU2561786C1 (en) * 2014-04-29 2015-09-10 Федеральное государственное унитарное предприятие "Центральный аэрогидродинамический институт имени профессора Н.Е. Жуковского" (ФГУП "ЦАГИ") Method of protection of hollow articles from exceeding predetermined level of internal excess pressure of gas

Also Published As

Publication number Publication date
RU2082135C1 (en) 1997-06-20

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