RU94036121A - Method of measurement of rocket engine thrust by means of primary converter and stand for its realization - Google Patents

Method of measurement of rocket engine thrust by means of primary converter and stand for its realization

Info

Publication number
RU94036121A
RU94036121A RU94036121/28A RU94036121A RU94036121A RU 94036121 A RU94036121 A RU 94036121A RU 94036121/28 A RU94036121/28 A RU 94036121/28A RU 94036121 A RU94036121 A RU 94036121A RU 94036121 A RU94036121 A RU 94036121A
Authority
RU
Russia
Prior art keywords
friction clutch
primary converter
rocket engine
measurement
rocket
Prior art date
Application number
RU94036121/28A
Other languages
Russian (ru)
Other versions
RU2091736C1 (en
Inventor
А.Г. Завальнюк
В.И. Колотилин
Original Assignee
Конструкторское бюро приборостроения
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 Конструкторское бюро приборостроения filed Critical Конструкторское бюро приборостроения
Priority to RU94036121A priority Critical patent/RU2091736C1/en
Publication of RU94036121A publication Critical patent/RU94036121A/en
Application granted granted Critical
Publication of RU2091736C1 publication Critical patent/RU2091736C1/en

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  • Force Measurement Appropriate To Specific Purposes (AREA)
  • Testing Of Engines (AREA)

Abstract

FIELD: tests of rocket engines; methods and devices for measurement of rocket engine thrust pulse. SUBSTANCE: method consists in measurement of action of engine on primary converter and determination of pulse of this action; primary converter is acted on through longitudinal friction clutch which is shifted at moments when force of action exceeds nominal magnitude of primary converter; upon completion of rocket engine operation, displacement of friction clutch relative to initial position is measured and magnitude of pulse of rocket engine thrust is determined from relationship given in the Description. Stand for realization of this method consists of support, primary converter connected with recorder and fastenings for securing the engine under test; besides that stand is provided with double-acting longitudinal friction clutch connected in line: support - primary converter - engine under test and device for measuring longitudinal displacement of friction clutch. Friction clutch may be made in form of collet embracing the rod and engageable with this rod over external surface; device for measurement of longitudinal displacement of friction clutch has scale divisions applied on rod. Besides that, friction clutch may be made in form of piston engageable with cylindrical guide over external surface; zone of engagement is made of friction material. EFFECT: enhanced accuracy of measurement of pulse of rocket engine thrust.

Claims (1)

Изобретение относится к испытаниям ракетных двигателей, а конкретно к способам и устройствам для измерения импульса силы тяги ракетного двигателя. Целью изобретения является повышение точности измерения импульса силы тяги ракетного двигателя. Упомянутая цель достигается тем, что в способе измерения импульса силы тяги ракетного двигателя, включающем измерение воздействия двигателя на первичный преобразователь и определение импульса этого воздействия, на первичный преобразователь воздействуют через продольный фрикцион и в моменты превышения усилия воздействия номинального значения первичного преобразователя перемещают фрикцион, после окончания работы ракетного двигателя измеряют перемещение фрикциона относительно первоначального положения, а величину импульса силы тяги ракетного двигателя определяют соотношением, приведенным в описании. Для этого в стенд, включающий опору, первичный преобразователь, соединенный с регистратором и элементы крепления испытуемого двигателя, введены продольный фрикцион двухстороннего действия.The invention relates to tests of rocket engines, and specifically to methods and devices for measuring the momentum of the thrust of a rocket engine. The aim of the invention is to improve the accuracy of measuring the momentum of the thrust of a rocket engine. This goal is achieved by the fact that in the method of measuring the impulse of the thrust of a rocket engine, including measuring the impact of the engine on the primary converter and determining the impulse of this effect, the primary converter is exposed through a longitudinal friction clutch and when the impact force exceeds the nominal value of the primary converter, the friction clutch is moved after rocket engine operation measures the friction clutch relative to the initial position, and the magnitude of the impulse of the traction force gy of a rocket engine is determined by the ratio given in the description. For this purpose, a double-sided longitudinal friction clutch is introduced into a stand including a support, a primary transducer connected to a recorder and fastening elements of a test engine.
RU94036121A 1994-09-27 1994-09-27 Method of measurement of rocket engine thrust momentum and test bench for its realization RU2091736C1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
RU94036121A RU2091736C1 (en) 1994-09-27 1994-09-27 Method of measurement of rocket engine thrust momentum and test bench for its realization

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
RU94036121A RU2091736C1 (en) 1994-09-27 1994-09-27 Method of measurement of rocket engine thrust momentum and test bench for its realization

Publications (2)

Publication Number Publication Date
RU94036121A true RU94036121A (en) 1996-06-27
RU2091736C1 RU2091736C1 (en) 1997-09-27

Family

ID=20160917

Family Applications (1)

Application Number Title Priority Date Filing Date
RU94036121A RU2091736C1 (en) 1994-09-27 1994-09-27 Method of measurement of rocket engine thrust momentum and test bench for its realization

Country Status (1)

Country Link
RU (1) RU2091736C1 (en)

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101813537B (en) * 2010-03-18 2011-06-22 北京理工大学 Micro-thruster array testing table
RU2554668C1 (en) * 2014-01-29 2015-06-27 Публичное акционерное общество "Научно-производственное объединение "Искра" (ПАО "НПО "Искра") Rack for measurement of axial force of rocket engine traction
RU2607199C1 (en) * 2015-06-23 2017-01-10 Акционерное общество "Федеральный научно-производственный центр "Алтай" Method of solid fuel unit pulse determining
RU2624928C1 (en) * 2015-12-22 2017-07-11 Российская Федерация, от имени которой выступает Министерство обороны Российской Федерации Method of experimental determination of correction to engine thrust total impulse at stand test-firing
RU2659411C1 (en) * 2017-07-03 2018-07-02 Федеральное государственное унитарное предприятие "Центральный научно-исследовательский институт химии и механики" (ФГУП "ЦНИИХМ") Method of fire test of liquid propellant rocket engines
RU2730775C1 (en) * 2019-12-02 2020-08-25 Закрытое акционерное общество "СуперОкс" (ЗАО "СуперОкс") Electric rocket engine jet force measuring instrument

Also Published As

Publication number Publication date
RU2091736C1 (en) 1997-09-27

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