RU2013138626A - METHOD FOR MEASURING FLOW PARAMETERS AT THE EXIT OF FLOWS OF LA MODELS - Google Patents

METHOD FOR MEASURING FLOW PARAMETERS AT THE EXIT OF FLOWS OF LA MODELS Download PDF

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RU2013138626A
RU2013138626A RU2013138626/28A RU2013138626A RU2013138626A RU 2013138626 A RU2013138626 A RU 2013138626A RU 2013138626/28 A RU2013138626/28 A RU 2013138626/28A RU 2013138626 A RU2013138626 A RU 2013138626A RU 2013138626 A RU2013138626 A RU 2013138626A
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model
pressure
transducers
ducts
transmitted
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RU2013138626/28A
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Russian (ru)
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RU2539769C1 (en
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Виктор Иванович Бирюков
Геннадий Андреевич Федоренко
Александр Алексеевич Павленко
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Российская Федерация, от имени которой выступает Министерство промышленности и торговли Российской Федерации (Минпромторг России)
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  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)

Abstract

Способ измерения параметров потока на выходе из протоков моделей летательных аппаратов, в котором модель с протоками, имитирующими каналы силовой установки, устанавливают в аэродинамической трубе с гребенкой приемников полных и статических давлений, передают измеряемые давления к преобразователям давления, электрические выходы которых присоединяют к измерительной аппаратуре, отличающийся тем, что приемники давлений подсоединяют встык к преобразователям давления, которые монтируют в одном корпусе с электронным коммутатором в хвостовой части модели, электрические выходы преобразователей подключают к электронному коммутатору, электрический сигнал, от которого передают на измерительную аппаратуру по кабелю, расположенному внутри державки модели (не снимая обтекателя державки) и проводят измерения давлений в одном эксперименте с весовыми измерениями аэродинамических сил и моментов, действующих на модель.A method for measuring flow parameters at the exit from the ducts of aircraft models, in which a model with ducts simulating the power plant channels is installed in a wind tunnel with a comb of full and static pressure receivers, the measured pressures are transmitted to pressure transducers, the electrical outputs of which are connected to the measuring equipment, characterized in that the pressure receivers are connected end-to-end to pressure transducers, which are mounted in one housing with an electronic switch in the tail part of the model, the electrical outputs of the transducers are connected to an electronic switch, the electrical signal from which is transmitted to the measuring equipment via a cable located inside the model holder (without removing the fairing of the holder) and pressure measurements are carried out in one experiment with weight measurements of aerodynamic forces and moments acting on the model.

Claims (1)

Способ измерения параметров потока на выходе из протоков моделей летательных аппаратов, в котором модель с протоками, имитирующими каналы силовой установки, устанавливают в аэродинамической трубе с гребенкой приемников полных и статических давлений, передают измеряемые давления к преобразователям давления, электрические выходы которых присоединяют к измерительной аппаратуре, отличающийся тем, что приемники давлений подсоединяют встык к преобразователям давления, которые монтируют в одном корпусе с электронным коммутатором в хвостовой части модели, электрические выходы преобразователей подключают к электронному коммутатору, электрический сигнал, от которого передают на измерительную аппаратуру по кабелю, расположенному внутри державки модели (не снимая обтекателя державки) и проводят измерения давлений в одном эксперименте с весовыми измерениями аэродинамических сил и моментов, действующих на модель. A method for measuring flow parameters at the exit from the ducts of aircraft models, in which a model with ducts simulating the power plant channels is installed in a wind tunnel with a comb of full and static pressure receivers, the measured pressures are transmitted to pressure transducers, the electrical outputs of which are connected to the measuring equipment, characterized in that the pressure receivers are connected end-to-end to pressure transducers, which are mounted in one housing with an electronic switch in the tail part of the model, the electrical outputs of the transducers are connected to an electronic switch, the electrical signal from which is transmitted to the measuring equipment via a cable located inside the model holder (without removing the fairing of the holder) and pressure measurements are carried out in one experiment with weight measurements of aerodynamic forces and moments acting on the model.
RU2013138626/28A 2013-08-21 2013-08-21 Determination of flow parameters at outlet of aircraft model ducts RU2539769C1 (en)

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115575080A (en) * 2022-12-09 2023-01-06 中国空气动力研究与发展中心高速空气动力研究所 Method for accurately measuring internal resistance of high-speed wind tunnel ventilation model
CN115575074A (en) * 2022-12-09 2023-01-06 中国空气动力研究与发展中心高速空气动力研究所 High-speed wind tunnel ventilation model internal resistance measurement uncertainty analysis method

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* Cited by examiner, † Cited by third party
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RU2730428C1 (en) * 2020-01-13 2020-08-21 Российская Федерация, от имени которой выступает Государственная корпорация по атомной энергии "Росатом" (Госкорпорация "Росатом") Small pressure receiver
CN114486308B (en) * 2021-12-30 2024-05-10 北京动力机械研究所 Heat exchange characteristic experimental method for micro tube bundle

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2339928C1 (en) * 2007-03-19 2008-11-27 Институт теоретической и прикладной механики им. С.А. Христиановича СО РАН (ИТПМ СО РАН) Calibration aerodynamic model for determining systematic errors and method of determining systematic errors
RU2381471C1 (en) * 2008-07-16 2010-02-10 Институт теоретической и прикладной механики им. С.А. Христиановича СО РАН (ИТПМ СО РАН) Device for identification of traction characteristics in imitators of air-feed jet engines (afje), method for detection of traction characteristics of afje imitators and method for control of validity in detection of traction characteristics of afje imitators
RU2491512C2 (en) * 2011-11-22 2013-08-27 Открытое акционерное общество "Лётно-исследовательский институт имени М.М. Громова" (ОАО "ЛИИ имени М.М. Громова") Method of determining flow rate of air through air inlet during flight tests of propulsive jet engine of hypersonic aircraft

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN115575080A (en) * 2022-12-09 2023-01-06 中国空气动力研究与发展中心高速空气动力研究所 Method for accurately measuring internal resistance of high-speed wind tunnel ventilation model
CN115575074A (en) * 2022-12-09 2023-01-06 中国空气动力研究与发展中心高速空气动力研究所 High-speed wind tunnel ventilation model internal resistance measurement uncertainty analysis method
CN115575074B (en) * 2022-12-09 2023-03-10 中国空气动力研究与发展中心高速空气动力研究所 High-speed wind tunnel ventilation model internal resistance measurement uncertainty analysis method
CN115575080B (en) * 2022-12-09 2023-03-24 中国空气动力研究与发展中心高速空气动力研究所 Method for accurately measuring internal resistance of high-speed wind tunnel ventilation model

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Effective date: 20150822