SU427255A1 - DEVICE FOR MEASURING THE FORCE OF A TURBO-REACTIVE ENGINE - Google Patents
DEVICE FOR MEASURING THE FORCE OF A TURBO-REACTIVE ENGINEInfo
- Publication number
- SU427255A1 SU427255A1 SU1719762A SU1719762A SU427255A1 SU 427255 A1 SU427255 A1 SU 427255A1 SU 1719762 A SU1719762 A SU 1719762A SU 1719762 A SU1719762 A SU 1719762A SU 427255 A1 SU427255 A1 SU 427255A1
- Authority
- SU
- USSR - Soviet Union
- Prior art keywords
- measuring
- force
- turbo
- reactive engine
- string
- Prior art date
Links
Landscapes
- Force Measurement Appropriate To Specific Purposes (AREA)
Description
Изобретение относитс к силоизмерительной технике и может быть использовано дл измерени силы т ги турбореактивного двигател самолета.The invention relates to load measurement technology and can be used to measure the thrust force of an airplane turbojet.
Известное силоизмерительное устройство, содержащее струну с датчиком и регистрирующий прибор, не позвол ет производить измерение силы т ги турбореактивного двигател самолета с требуемой точностью.The known force-measuring device, which contains a string with a sensor and a recording instrument, does not allow measuring the thrust force of an airplane's turbojet with the required accuracy.
РЬобретение устран ет указанный недостаток .This invention eliminates this drawback.
Дл этого один конец индикатора жестко закреплен на хвостовой части самолета, а другой через систему роликов соединен с подвижным подпружиненным штоком индукционного датчика.To do this, one end of the indicator is rigidly fixed to the tail of the aircraft, and the other is connected to a movable spring-loaded rod of the induction sensor through a system of rollers.
На фиг. 1 и 2 изображено предложенное устройство в двух проекци х.FIG. Figures 1 and 2 show the proposed device in two projections.
Устройство содержит струну /, котора перекинута через ролики 2 и 3.The device contains a string /, which is thrown over the rollers 2 and 3.
Струна одним концом крепитс к фюзел жу летательиого аппарата, другим - к штоку 4 индукционного датчика. На шток 4 одета пружина 5.One end of the string is attached to the fuselage of the flying apparatus, the other to the rod 4 of the induction sensor. On the stem 4 is wearing a spring 5.
Передний конец 6 щтока 4 имеет возможность перемещатьс в зазоре между двум индукционными катушками 7. Регистрирующий прибор 8 присоединен ко вторичной облотке катушки. В корпусе прибора 9 установ2The front end 6 of the stem 4 has the ability to move in the gap between the two induction coils 7. The recording device 8 is connected to the secondary coil winding. In the instrument case 9 set2
лена втулка 10. Устройство дл измерени силы т ги турбореактивного двигател установлено на хвостовой части самолета И (фиг. 2).A sleeve 10 is installed. A device for measuring the thrust force of a turbojet engine is installed at the tail end of the aircraft AND (FIG. 2).
Струиа / под действием выхлопных газов испытывает нат жение, в результате чего, струна перемещает подпружиненный шток 4.The jet / is subjected to tension under the action of exhaust gases, as a result of which the string displaces the spring-loaded rod 4.
Передний конец 6 штока 4 будет перемещатьс в правое положение. Измеиение положени переднего конца 6 штока 4 в зазоре между двум иидукционными катушками 7 будет наводить сигнал во вторичиой обмотке катушки, св занной с регистрирующим ирибором 8. Регистрирующий нрибор 8 будет фиксировать силу т ги турбореактивиого двигател .The front end 6 of the stem 4 will move to the right position. Measuring the position of the front end 6 of the stem 4 in the gap between the two imitation coils 7 will direct a signal in the secondary coil winding associated with the recording and selection device 8. The recording device 8 will record the pulling force of the turbojet engine.
Предмет изобретени Subject invention
Устройство дл измерени силы т ги турбореактивного двигател , содержащее индикатор в виде иат нутой струны с датчиком и регистрирующий прибор, отличающеес тем, что, с целью увеличени точности измерени , в нем один конец индикатора жестко закреплен на хвостовой части самолета, а другой через систему роликов соединен с подвижным подпружиненным штоком индукционного датчика . Ю Ц / // / /////Jy/A ///////////A device for measuring the thrust power of a turbojet engine, comprising an indicator in the form of an iathe string with a sensor and a recording device, characterized in that, in order to increase the measurement accuracy, one end of the indicator is rigidly fixed on the tail section of the aircraft connected to a movable spring-loaded rod induction sensor. Yu C / // / // /// Jy / A ///////////
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU1719762A SU427255A1 (en) | 1971-12-01 | 1971-12-01 | DEVICE FOR MEASURING THE FORCE OF A TURBO-REACTIVE ENGINE |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| SU1719762A SU427255A1 (en) | 1971-12-01 | 1971-12-01 | DEVICE FOR MEASURING THE FORCE OF A TURBO-REACTIVE ENGINE |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| SU427255A1 true SU427255A1 (en) | 1974-05-05 |
Family
ID=20494653
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| SU1719762A SU427255A1 (en) | 1971-12-01 | 1971-12-01 | DEVICE FOR MEASURING THE FORCE OF A TURBO-REACTIVE ENGINE |
Country Status (1)
| Country | Link |
|---|---|
| SU (1) | SU427255A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104535240A (en) * | 2014-12-24 | 2015-04-22 | 北京航空航天大学 | Micro-thrust measurement device with thermal protection system |
-
1971
- 1971-12-01 SU SU1719762A patent/SU427255A1/en active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104535240A (en) * | 2014-12-24 | 2015-04-22 | 北京航空航天大学 | Micro-thrust measurement device with thermal protection system |
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