CN102519643A - Six-component force measuring system of engine vector spray pipe - Google Patents
Six-component force measuring system of engine vector spray pipe Download PDFInfo
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- CN102519643A CN102519643A CN201110414253XA CN201110414253A CN102519643A CN 102519643 A CN102519643 A CN 102519643A CN 201110414253X A CN201110414253X A CN 201110414253XA CN 201110414253 A CN201110414253 A CN 201110414253A CN 102519643 A CN102519643 A CN 102519643A
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Abstract
The invention discloses a six-component force measuring system of an engine vector spray pipe, comprising a gas inlet pipeline, a corrugated pipe, a gas collecting chamber, a burning chamber, a stabilizing section, a connecting plate, a six-component scale and a scale base. The six-component force measuring system adopts the following working mode: high pressure gas enters the gas collecting chamber through the corrugated pipe from the gas inlet pipeline, and is ignited and burnt by the burning chamber, the generated high temperature gas flow is rectified by the stabilizing section and then is sprayed out from the vector spray pipe behind the stabilizing section, and the vectored thrust generated by the spray pipe is measured by the six-component scale, so that the performance of the vector spray pipe can be evaluated.
Description
Technical field
The present invention relates to aeromotor vector spray mechanical meaurement device, is a kind of engine vector spray six component force systems specifically.
Background technology
In the aeronautical technology development, Thrust Vectoring Technology makes aircraft have super maneuverability, high agility, STOL performance, stealthy performance and supersonic speed cruising ability.Domestic the vectored thrust Study on Technology is started from the later stage eighties 20th century, the engine vectored thrust testing table that builds up at present has four-component balance testing table and six component balance, testing table.But what all adopt is mechanical type force balance structure, adopts the diverse locations of many group sensor placements at platform, realizes the transmission and the decomposition of load through pull bar, physical construction such as hinged; System complex; Mechanism is many, install and debug all very difficulty, and system's first natural frequency is lower.Adopt the main flow bleed pipeline of comb toothing; The steel wire rubber tubular construction is as time stream bleed pipeline.Poor stability, the bleed pipeline is very big to the interference of measuring table, and measuring accuracy is not high.
For development thrust vectoring jet pipe technology, need a kind of six component force systems that are used to measure the experiment of thrust vectoring nozzle performance of development, so that thrust vectoring is measured accurately.
Summary of the invention
To the objective of the invention is in order addressing the above problem, to provide a cover can accurately assess the device for measuring force of engine vector spray performance.
Realize that technical scheme of the present invention is: a kind of engine vector spray six component force systems comprise admission line, corrugated tube, collection chamber, firing chamber, stable section, web joint, six COMPONENT BALANCE and day flat bed; Wherein:
1) admission line is made up of bend pipe and straight tube, and two symmetrical admission lines are introduced measuring system with the gases at high pressure of high-pressure air source;
2) corrugated tube, two corrugated tubes are arranged symmetrically in the collection chamber two ends, connect collection chamber and admission line;
3) collection chamber is fixed on the web joint, two side joint corrugated tubes, and front end is connected with the firing chamber; Connecing bellows end is inlet end, the similar gas tank, and two ends gas is joined at this, and the power that air pressure is produced is cancelled out each other and is reduced, and front end connects the place, firing chamber and is the outlet side;
4) firing chamber between collection chamber and stable section, connects firmly with both, external aviation kerosene pipeline, the high pressure draught of coming from collection chamber in the firing chamber effect down with the abundant mixing ignition of aviation kerosene, generation high-temperature high-pressure air flow;
5) stable section is fixed on the web joint, and the rear end is connected with the firing chamber, and during the jet pipe test, jet pipe is connected the stable section front end, and high temperature gas flow shrinks and current stabilization through stable section, through the jet pipe ejection, produces thrust again;
6) web joint is fixed on boxlike six COMPONENT BALANCE top, and upper surface connects stable section and collection chamber, and effect is that stable section and collection chamber directly are not connected on the unsteady frame of six COMPONENT BALANCE, and the metamorphosis that prevents to cause because of bolt is on balance;
7) six COMPONENT BALANCE comprise unsteady frame, fixed frame and three-dimensional force sensor, and said unsteady frame is positioned at the balance the top; Said fixed frame is positioned at below of balance; Said three-dimensional force sensor two ends up and down connects float frame and fixed frame respectively; The fixed frame of balance lower end is fixed on day flat bed, and upper end and web joint connect firmly, and is used to measure thrust and moment that jet pipe produces, and power and moment are thoroughly decomposed and exported;
8) day flat bed is used for fixing six COMPONENT BALANCE, adopts the cast steel ironware, and rigidity is big.
Said stable section has three layers of interior China and foreign countries in a tubular form, and internal layer is used for through high temperature gas flow, and there is the space in internal layer and middle level, and sealing, are used for being used for cooling device through chilled water, and skin plays a supportive role, and whole stable section is supported on the web joint.
The invention has the beneficial effects as follows:
1, whole six component force system stiffnesses are big, under loading distortion little, little by the interference that distortion produces;
2, air intake duct adopts symmetrical general layout, effectively offsets the perturbed force that produces because of gases at high pressure;
3, utilize corrugated tube as the inlet pipe connection road, bellows stiffness is little, can ignore with respect to boxlike six COMPONENT BALANCE rigidity, has both solved the air inlet problem, again the not measurement of influence power and moment;
4, adopt boxlike six COMPONENT BALANCE as the mechanical meaurement instrument, this balance is a kind of outer formula balance, and its rigidity is big, and measuring accuracy is high, satisfies the measurement needs fully;
5, specialized designs web joint, be used to solve the interference that causes be installed.In the installation process; Processing always has the existence of error, and surface of contact can not be accomplished to fit fully, and bolt will produce distortion when connecting; Distortion is delivered on the three-dimension sensor through the unsteady frame of six component box type balances; Cause the three-dimension sensor distortion, cause whole dynamometry system zero point excessive, influence is measured; Web joint processing itself is simple, can obtain higher precision, and effect is to separate stable section and six COMPONENT BALANCE, reduces distortion and transmits;
6, stable section and collection chamber all are fixed on the web joint of six COMPONENT BALANCE top, and additional moment is little;
7, stable section is designed with interlayer, and chilled water therefrom passes through during work, and the generation heat that will burn is taken away, and equipment is lowered the temperature.
Description of drawings
Fig. 1 is engine vector spray six component force system schematic of the present invention
Fig. 2 is the present invention's six COMPONENT BALANCE synoptic diagram
Label among the figure: 1-admission line, 2-corrugated tube, 3-collection chamber, 4-firing chamber, 5-stable section, 6-web joint, 7-six COMPONENT BALANCE, 8-day flat bed, 9-jet pipe, the 10-frame that floats, 11-fixed frame, 12-three-dimensional force sensor.
Embodiment
Like Fig. 1, shown in Figure 2: this engine vector spray six component force systems comprise admission line 1, corrugated tube 2, collection chamber 3, firing chamber 4, stable section 5, web joint 6, six COMPONENT BALANCE 7 and day flat bed 8; Wherein: admission line 1, constitute by bend pipe and straight tube, the admission line 1 of two symmetries is introduced measuring system with the gases at high pressure of high-pressure air source; 2, two corrugated tubes 2 of corrugated tube are arranged symmetrically in collection chamber 3 two ends, connect collection chamber 3 and admission line 1; Collection chamber 3 is fixed on the web joint 6, and front end is connected with firing chamber 4, two side joint corrugated tubes 2, and the similar gas tank, both sides are inlet end, and it is the outlet side that front end connects 4 places, firing chamber, and two ends gas is joined at this, and the power that air pressure is produced is cancelled out each other and is reduced; Firing chamber 4 between collection chamber 3 and stable section 5, connects firmly with both, external aviation kerosene pipeline, the high pressure draught of coming from collection chamber 3 in the firing chamber 4 effects down with the abundant mixing ignition of aviation kerosene, generation high-temperature high-pressure air flow; Stable section 5 is fixed on the web joint 6, and the rear end is connected with firing chamber 4; Stable section 5 has three layers of interior China and foreign countries in a tubular form, and internal layer is used for through high temperature gas flow; There is the space in internal layer and middle level, and sealing, are used for through chilled water; Be used for cooling device, skin plays a supportive role, and whole stable section 5 is supported on the web joint 6.During the jet pipe test, jet pipe 9 is connected stable section 5 front ends, and high temperature gas flow shrinks and current stabilization through stable section 5, through the jet pipe ejection, produces thrust again; Web joint 6; Through being bolted to boxlike six COMPONENT BALANCE 7 tops; Upper surface connects stable section 5 and collection chamber 3, and effect is that stable section 5 and collection chamber 3 directly are not connected on six COMPONENT BALANCE, the 7 unsteady frames, and the metamorphosis that prevents to cause because of bolt is on six COMPONENT BALANCE 7; Six COMPONENT BALANCE 7 comprise that said unsteady frame 10 is positioned at balance 7 the tops by unsteady frame 10, fixed frame 11 and three-dimensional force sensor 12; Said fixed frame 11 is positioned at below of balance 7; Said three-dimensional force sensor connects float frame 10 and fixed frame 11 respectively in two ends about in the of 12; The fixed frame 11 of balance 7 lower ends is fixed on day flat bed 8, and upper end and web joint 6 connect firmly, and is used to measure thrust and moment that jet pipe 9 produces, and power and moment are thoroughly decomposed and exported; It flat bed 8 is used for fixing six component box type balances 7, adopts ironcasting, and the cross section is I shape, and rigidity is big, and can make sky flat bed 8 distortion of submitting the bolt generation can not be delivered to the upper surface of day flat bed 8, does not influence balance and uses.
Engine vector spray of the present invention six component force systems are the six component force platforms that are used for the test vector jet pipe.During dynamometer check, the tested vector spray model that is is connected stable section 5 front ends through bolt, and high-pressure air source is through admission line 1 entering system; Corrugated tube 2 symmetric arrangement are that two bursts of opposite air-flow symmetries of pressure equidirectional get into collection chamber 3, have offset the additional thrust that is produced by high pressure draught; Gas flows out from the collection chamber outlet after collection chamber is collected, and gets into firing chamber 4; The external aviation kerosene in firing chamber, aviation kerosene mix and fully burning with gases at high pressure under the effect of firing chamber, produce high-temperature high-pressure air flow; Get into stable section 5 and shrink current stabilization, spray at a high speed through vector spray then, the thrust of generation is delivered to stable section 5; Be reacted on six COMPONENT BALANCE 7 through web joint 6, the power that vector spray produces accurately measured out by six COMPONENT BALANCE 7.
Claims (2)
1. engine vector spray six component force systems is characterized in that: comprise admission line, corrugated tube, collection chamber, firing chamber, stable section, web joint, six COMPONENT BALANCE and day flat bed; Wherein:
1) admission line is made up of bend pipe and straight tube, and two symmetrical admission lines are introduced measuring system with the gases at high pressure of high-pressure air source;
2) corrugated tube, two corrugated tubes are arranged symmetrically in the collection chamber two ends, connect collection chamber and admission line;
3) collection chamber is fixed on the web joint, two side joint corrugated tubes, and front end is connected with the firing chamber; Connecing bellows end is inlet end, the similar gas tank, and two ends gas is joined at this, and the power that air pressure is produced is cancelled out each other and is reduced, and front end connects the place, firing chamber and is the outlet side;
4) firing chamber between collection chamber and stable section, connects firmly with both, external aviation kerosene pipeline, the high pressure draught of coming from collection chamber in the firing chamber effect down with the abundant mixing ignition of aviation kerosene, generation high-temperature high-pressure air flow;
5) stable section is fixed on the web joint, and the rear end is connected with the firing chamber, and during the jet pipe test, jet pipe is connected the stable section front end, and high temperature gas flow shrinks and current stabilization through stable section, through the jet pipe ejection, produces thrust again;
6) web joint is fixed on boxlike six COMPONENT BALANCE top, and upper surface connects stable section and collection chamber, and effect is that stable section and collection chamber directly are not connected on the unsteady frame of six COMPONENT BALANCE, and the metamorphosis that prevents to cause because of bolt is on balance;
7) six COMPONENT BALANCE comprise unsteady frame, fixed frame and three-dimensional force sensor, and said unsteady frame is positioned at the balance the top; Said fixed frame is positioned at below of balance; Said three-dimensional force sensor two ends up and down connects float frame and fixed frame respectively; The fixed frame of balance lower end is fixed on day flat bed, and upper end and web joint connect firmly, and is used to measure thrust and moment that jet pipe produces, and power and moment are thoroughly decomposed and exported;
8) day flat bed is used for fixing six COMPONENT BALANCE, adopts the cast steel ironware, and rigidity is big.
2. according to the said engine vector spray of claim 1 six component force systems, it is characterized in that: said stable section has three layers of interior China and foreign countries in a tubular form; Internal layer is used for through high temperature gas flow, and there is the space in internal layer and middle level, and sealing; Be used for through chilled water; Be used for cooling device, skin plays a supportive role, and whole stable section is supported on the web joint.
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| CN201110414253XA CN102519643A (en) | 2011-12-13 | 2011-12-13 | Six-component force measuring system of engine vector spray pipe |
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| CN201110414253XA CN102519643A (en) | 2011-12-13 | 2011-12-13 | Six-component force measuring system of engine vector spray pipe |
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Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104111138A (en) * | 2014-04-30 | 2014-10-22 | 中国航天空气动力技术研究院 | Large-scale missile engine six-component dynamometry and calibrating device |
| CN104315956A (en) * | 2014-11-07 | 2015-01-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Device and method for measuring height of vector nozzle of aeroengine in force bearing state |
| CN105203291A (en) * | 2015-10-28 | 2015-12-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Wind tunnel experiment system used for vector-boosting airplane model |
| CN106441794A (en) * | 2016-11-28 | 2017-02-22 | 中国科学院力学研究所 | Six-component aerodynamic force measurement device of high-speed train model |
| CN106840591A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of experimental rig of direct measurement jet flow thrust |
| CN106898236A (en) * | 2017-03-19 | 2017-06-27 | 佛山市三水区希望火炬教育科技有限公司 | A kind of floating-island type aircraft carrier it is special be vertically moved up or down large-scale early warning plane model |
| CN108225776A (en) * | 2018-04-08 | 2018-06-29 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of small-size turbojet engine vector spray testboard |
| CN109580070A (en) * | 2018-11-23 | 2019-04-05 | 北京航天试验技术研究所 | A kind of vectored thrust measuring device not influencing engine axial admission |
| CN110487507A (en) * | 2019-09-06 | 2019-11-22 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of five component strain balances for nacelle internal resistance dynamometer check |
| CN112945443A (en) * | 2021-02-05 | 2021-06-11 | 中国航发沈阳发动机研究所 | Thrust measuring platform for spray pipe |
| CN113063538A (en) * | 2021-03-22 | 2021-07-02 | 马洪文 | Distributed multi-dimensional force sensor |
| CN113091979A (en) * | 2019-12-23 | 2021-07-09 | 马洪文 | Distributed multi-dimensional force measuring system and force measuring method |
| CN113218661A (en) * | 2021-04-07 | 2021-08-06 | 上海新力动力设备研究所 | Cold air thrust testing device for attitude and orbit control engine |
| CN117073969A (en) * | 2023-10-12 | 2023-11-17 | 中国航空工业集团公司沈阳空气动力研究所 | Accurate measurement device and measurement method for static thrust of radial disturbance injection jet pipe |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4328703A (en) * | 1980-02-14 | 1982-05-11 | Avco Corporation | Thrust measuring test stand |
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
| CN102183353A (en) * | 2011-02-21 | 2011-09-14 | 中国海洋石油总公司 | A single-column measuring device of wind force and hydraulic force |
-
2011
- 2011-12-13 CN CN201110414253XA patent/CN102519643A/en active Pending
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4328703A (en) * | 1980-02-14 | 1982-05-11 | Avco Corporation | Thrust measuring test stand |
| CN101464215A (en) * | 2009-01-15 | 2009-06-24 | 大连理工大学 | Propulsion test device of piezo-electricity type rocket motor |
| CN102183353A (en) * | 2011-02-21 | 2011-09-14 | 中国海洋石油总公司 | A single-column measuring device of wind force and hydraulic force |
Non-Patent Citations (2)
| Title |
|---|
| 姚裕等: "大膨胀比喷管试验台的六分量天平研究", 《南京理工大学学报》, vol. 35, no. 4, 31 August 2011 (2011-08-31), pages 547 - 551 * |
| 湛华海: "航空发动机矢量喷管六分量测力系统研制", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》, no. 6, 15 June 2009 (2009-06-15) * |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104111138B (en) * | 2014-04-30 | 2016-03-02 | 中国航天空气动力技术研究院 | A kind of large-scale missile propulsive plant six component force and calibrating installation |
| CN104111138A (en) * | 2014-04-30 | 2014-10-22 | 中国航天空气动力技术研究院 | Large-scale missile engine six-component dynamometry and calibrating device |
| CN104315956A (en) * | 2014-11-07 | 2015-01-28 | 沈阳黎明航空发动机(集团)有限责任公司 | Device and method for measuring height of vector nozzle of aeroengine in force bearing state |
| CN104315956B (en) * | 2014-11-07 | 2016-09-07 | 沈阳黎明航空发动机(集团)有限责任公司 | Aero-engine vector spout load state height measuring device and measuring method |
| CN105203291A (en) * | 2015-10-28 | 2015-12-30 | 中国航空工业集团公司沈阳飞机设计研究所 | Wind tunnel experiment system used for vector-boosting airplane model |
| CN106441794A (en) * | 2016-11-28 | 2017-02-22 | 中国科学院力学研究所 | Six-component aerodynamic force measurement device of high-speed train model |
| CN106441794B (en) * | 2016-11-28 | 2019-01-04 | 中国科学院力学研究所 | A kind of six component aerodynamics force measurement device of high-speed rain movable model type |
| CN106840591B (en) * | 2016-12-29 | 2019-04-30 | 中国航天空气动力技术研究院 | A kind of experimental rig directly measuring jet flow thrust |
| CN106840591A (en) * | 2016-12-29 | 2017-06-13 | 中国航天空气动力技术研究院 | A kind of experimental rig of direct measurement jet flow thrust |
| CN106898236A (en) * | 2017-03-19 | 2017-06-27 | 佛山市三水区希望火炬教育科技有限公司 | A kind of floating-island type aircraft carrier it is special be vertically moved up or down large-scale early warning plane model |
| CN108225776A (en) * | 2018-04-08 | 2018-06-29 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of small-size turbojet engine vector spray testboard |
| CN109580070A (en) * | 2018-11-23 | 2019-04-05 | 北京航天试验技术研究所 | A kind of vectored thrust measuring device not influencing engine axial admission |
| CN110487507A (en) * | 2019-09-06 | 2019-11-22 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of five component strain balances for nacelle internal resistance dynamometer check |
| CN110487507B (en) * | 2019-09-06 | 2024-02-23 | 中国航空工业集团公司沈阳空气动力研究所 | Five-component strain balance for nacelle internal resistance force measurement test |
| CN113091979A (en) * | 2019-12-23 | 2021-07-09 | 马洪文 | Distributed multi-dimensional force measuring system and force measuring method |
| CN112945443A (en) * | 2021-02-05 | 2021-06-11 | 中国航发沈阳发动机研究所 | Thrust measuring platform for spray pipe |
| CN113063538A (en) * | 2021-03-22 | 2021-07-02 | 马洪文 | Distributed multi-dimensional force sensor |
| CN113063538B (en) * | 2021-03-22 | 2023-01-20 | 马洪文 | Distributed multi-dimensional force sensor |
| CN113218661A (en) * | 2021-04-07 | 2021-08-06 | 上海新力动力设备研究所 | Cold air thrust testing device for attitude and orbit control engine |
| CN117073969A (en) * | 2023-10-12 | 2023-11-17 | 中国航空工业集团公司沈阳空气动力研究所 | Accurate measurement device and measurement method for static thrust of radial disturbance injection jet pipe |
| CN117073969B (en) * | 2023-10-12 | 2024-01-23 | 中国航空工业集团公司沈阳空气动力研究所 | Accurate measurement device and measurement method for static thrust of radial disturbance injection jet pipe |
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Application publication date: 20120627 |