CN105004475B - Dual force source thrust vectoring test adaptor demarcation frame - Google Patents
Dual force source thrust vectoring test adaptor demarcation frame Download PDFInfo
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- CN105004475B CN105004475B CN201510409302.9A CN201510409302A CN105004475B CN 105004475 B CN105004475 B CN 105004475B CN 201510409302 A CN201510409302 A CN 201510409302A CN 105004475 B CN105004475 B CN 105004475B
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- 230000009977 dual effect Effects 0.000 title claims abstract description 13
- 238000005259 measurement Methods 0.000 claims abstract description 11
- 210000003205 muscle Anatomy 0.000 claims abstract description 7
- 230000014509 gene expression Effects 0.000 claims description 2
- 238000010276 construction Methods 0.000 abstract description 3
- 238000009434 installation Methods 0.000 abstract description 3
- 208000007623 Lordosis Diseases 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 2
- 230000000694 effects Effects 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000005997 Calcium carbide Substances 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 210000000887 face Anatomy 0.000 description 1
- 210000003128 head Anatomy 0.000 description 1
- 238000009413 insulation Methods 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- CLZWAWBPWVRRGI-UHFFFAOYSA-N tert-butyl 2-[2-[2-[2-[bis[2-[(2-methylpropan-2-yl)oxy]-2-oxoethyl]amino]-5-bromophenoxy]ethoxy]-4-methyl-n-[2-[(2-methylpropan-2-yl)oxy]-2-oxoethyl]anilino]acetate Chemical compound CC1=CC=C(N(CC(=O)OC(C)(C)C)CC(=O)OC(C)(C)C)C(OCCOC=2C(=CC=C(Br)C=2)N(CC(=O)OC(C)(C)C)CC(=O)OC(C)(C)C)=C1 CLZWAWBPWVRRGI-UHFFFAOYSA-N 0.000 description 1
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- Force Measurement Appropriate To Specific Purposes (AREA)
Abstract
The invention discloses a kind of dual force source thrust vectoring test adaptor demarcation frame for attachment force generating means and dynamometer, applied in thrust measurement system, more particularly to rocket thrust test system.The invention is made up of change-over terminal, loading flange, demarcation flange and installation bolt etc..Two change-over terminals employ parallel structure, and two change-over terminals are linked together using circle ring, and circle ring is welded together with connecting plate with muscle, and a lifting eye is separately designed in two change-over terminals, can be used to dynamometry source span very big two points.It is an advantage of the invention that Change-over frame integrally uses monolithic construction, rigidity is higher, and intrinsic frequency is high, be conducive to improving dynamic measurement precision, and the overall spoke structure using hollow lordosis, reduce own wt, installation and debugging space is provided for caliberating device, it is simple in construction, debug conveniently.
Description
Technical field
Frame is demarcated the present invention relates to dual force source thrust vectoring test adaptor, it is in parallel using two single power sources switching caliberating devices
To realize to the switching between dual force source and sensor, the switching occasion more than one applied to power source number is more particularly to pressed
Application in the rocket thrust field of calcium carbide English sensor test dual force source.
Background technology
In rocket thrust test system, because motor head has propellant pipeline, heat insulation device etc., it is impossible to directly right
It is attached on dynamometer, it is necessary to transferred by Change-over frame.Reduce heat to be transmitted on dynamometer, larger is brought to measurement result
Influence.At present, compared many with the switching device of dynamometer for attachment force source generating means both at home and abroad.It is main to undertake power source and survey
Switching effect between force snesor, provides space for connection line, realizes and power is measured.
Existing attachment means are primarily directed to singular force-source., will be existing when the increase of power source is two or more
Single direction switching device fit together, be divided into two parts or more part as multi powers switching device, add structure
The number of part.Because component is relatively more, need to be connected between component and component, relative to dual force source in parallel switching device
Rigidity will decline for overall structure, and intrinsic frequency diminishes and increased the power interfered between component, serious situation
Distorted signals can be caused, dynamic measurement precision is influenceed；Also the flow of assembling can be increased more than component, process is cumbersome, and band therewith
The rigging error come, can also influence measurement accuracy.So although single power source switching device assembling makes as dual force source switching device
With convenient, but still limit the precision and accuracy of piezoelectric force structure.
The content of the invention
The technical problem to be solved in the present invention is based on singular force-source switching device and is different from singular force-source switching dress
The exchanging structure in parallel put, designs a kind of technological performance, reliable operation, it is easy to install, easy to use, compact conformation, energy gram
Take switching device of the single switching device assembling as multi powers switching device drawback.The device has effectively widened dynamometer pair
The measurement of multi powers, improves the measurement accuracy of test system.
The technical solution adopted by the present invention is：
A kind of dual force source thrust vectoring test adaptor demarcates frame, including two change-over terminals, annulus frame, two lifting eyes, two
Individual loading flange, connecting plate, demarcation flange and muscle；Change-over terminal is respectively equipped with the cylindrical structure of ring flange for upper and lower side, and two turn
The both sides that end symmetrical expression is welded on annulus frame are connect, two change-over terminal upper surfaces connect in actually measurement with by dynamometry source；Two
Outside sets a lifting hole(eyelet) respectively in the middle part of change-over terminal；Two change-over terminal lower surfaces match with two loading flange upper surfaces respectively
Close, two loading flanges and two change-over terminal lower surfaces are rigidly connected respectively by bolt and loaded to simulate actual measurement power source, it is complete
Into the staking-out work of dynamometer；Welded between annulus frame and connecting plate by eight muscle being evenly arranged, connection board diameter is less than circle
Ring stand diameter；Demarcation flange upper surface is engaged with the lower surface of connecting plate, by bolt that connecting plate and demarcation flange is rigid
Connection.
The loading flange face of described change-over terminal lower end is parallel with the guarantee of connecting plate lower surface；Load flange and change-over terminal it
Between ensure position degree and axiality；Ensure position degree and axiality between connecting plate and demarcation flange.
The remarkable result of the present invention：The dual force source switching demarcation frame of design invention, by using two change-over terminals and annulus
Frame welds to form parallel-connection structure, realizes the switching of dual force source and force cell.It can be applied to Aero-Space, defence and military etc.
In power test event.The device technique is good, good stability, it is simple in construction, debug conveniently.
Brief description of the drawings
Fig. 1 is the principle schematic of structure of the present invention.
Fig. 2 is demarcation flange structural representation.
Fig. 3 is loading flange structural representation.
Fig. 4 demarcates the 3-D effect schematic diagram of frame for switching.
Fig. 5 is switching demarcation frame, loading flange, the installation diagram for demarcating flange.
In figure：1 change-over terminal, 2 annulus framves, 3 lifting eyes, 4 bolts, 5 loading flanges, 6 connecting plates, 7 demarcation flanges, 8 muscle；a
Load flange upper surface, b loading flanges lower surface；C demarcation flanges upper surface, d connecting plates lower surface；E change-over terminals upper end, f turns
Connect end lower end.
Embodiment
Describe the specific implementation of the present invention in detail with reference to accompanying drawing and technical scheme：As shown in figure 1, loading flange 5 upper surface a
It is engaged, is rigidly connected by bolt 4 by flange 5 is loaded with change-over terminal 1 with the lower surface f of change-over terminal 1；Annulus frame 2 and connecting plate 6
Welded by eight muscle being evenly arranged 8；The demarcation upper surface c of flange 7 is engaged with the lower surface d of connecting plate 6, passes through spiral shell
Connecting plate 6 and demarcation flange 7 are rigidly connected by bolt 4.Flange 5 is loaded during assembling will ensure one with the assembling between change-over terminal 1
Fixed position degree and axiality；Similarly, the assembling of connecting plate 6 and demarcation flange 7 will ensure certain position degree and axiality；Plus
The lower end f of man-hour change-over terminal 1 connecting flange faces will ensure certain depth of parallelism requirement with connecting plate lower surface d.In addition, annulus frame
2 use hollow structure to mitigate the weight of structure in itself.
In use, be connected by the mounting hole on two loading flanges with power source generating means, the peace on demarcation flange
Dress hole is connected with sensor, it is achieved thereby that the switching of power source span very big two point of applications and force cell.
Although the present invention is made that detailed description with above-mentioned preferred embodiment to the present invention, above-mentioned implementation is not used
Example limits the present invention.Those skilled in the art is not it should be recognized that departing from technical characteristic given by the present invention and scope
In the case of, the increase made to technology, with this area some same contents replacement, protection scope of the present invention all should be belonged to.
Claims (1)
1. a kind of dual force source thrust vectoring test adaptor demarcates frame, it is characterised in that the dual force source thrust vectoring test adaptor mark
Determining frame includes two change-over terminals, annulus frame, two lifting eyes, two loading flanges, connecting plate, demarcation flange and muscle；Change-over terminal
The cylindrical structure of ring flange is respectively equipped with for upper and lower side, two change-over terminal symmetrical expressions are welded on the both sides of annulus frame, two switchings
End upper surface connects in actually measurement with by dynamometry source；Outside sets a lifting eye respectively in the middle part of two change-over terminals；Switching
End lower surface should ensure that certain depth of parallelism when being processed with loading flange upper surface, two change-over terminal lower surfaces add with two respectively
Carry flange upper surface to be engaged, certain position degree and axiality will be ensured by during assembling coordinating between change-over terminal and loading flange,
Two loading flanges are rigidly connected with two change-over terminal lower surfaces respectively respectively by bolt and loaded to simulate actual measurement power source, it is complete
Into the staking-out work of dynamometer；Welded between annulus frame and connecting plate by eight muscle being evenly arranged, connection board diameter is less than circle
Ring stand diameter；Demarcation flange upper and lower end face should ensure that certain depth of parallelism, demarcation flange upper end when being processed with connecting plate lower surface
Face is engaged with the lower surface of connecting plate, and certain position degree will be ensured and same by demarcating between flange and connecting plate to coordinate during assembling
Connecting plate and demarcation flange, are rigidly connected by axle degree by bolt.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510409302.9A CN105004475B (en) | 2015-07-13 | 2015-07-13 | Dual force source thrust vectoring test adaptor demarcation frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510409302.9A CN105004475B (en) | 2015-07-13 | 2015-07-13 | Dual force source thrust vectoring test adaptor demarcation frame |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105004475A CN105004475A (en) | 2015-10-28 |
| CN105004475B true CN105004475B (en) | 2017-07-11 |
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| CN201510409302.9A Active CN105004475B (en) | 2015-07-13 | 2015-07-13 | Dual force source thrust vectoring test adaptor demarcation frame |
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Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108168774B (en) * | 2017-12-27 | 2020-01-14 | 中国航发四川燃气涡轮研究院 | Space vector force calibration method |
| CN109269718B (en) * | 2018-11-23 | 2020-12-29 | 北京航天试验技术研究所 | Stepless regulation engine vector thrust calibration device |
Family Cites Families (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101435728B (en) * | 2008-12-18 | 2011-01-26 | 中国科学院力学研究所 | Apparatus and method for measuring small rocket engine thrust force vector in vacuum |
| KR101059777B1 (en) * | 2008-12-29 | 2011-08-26 | 한국과학기술원 | Thrust measurement and correction device of rocket engine and its method |
| KR101054734B1 (en) * | 2008-12-31 | 2011-08-08 | 한국항공우주연구원 | Thrust measuring device and method |
| CN101614606B (en) * | 2009-07-30 | 2011-02-16 | 中国科学院力学研究所 | Measuring device and method of thrust vector of detection space plasma thruster |
| CN202836851U (en) * | 2012-08-07 | 2013-03-27 | 北京航天试验技术研究所 | Thrust vector measurement system |
| CN102818676B (en) * | 2012-08-16 | 2014-07-02 | 北京航空航天大学 | Thrust rack in-situ calibration system |
| CN103759885B (en) * | 2013-12-26 | 2015-11-11 | 长春轨道客车股份有限公司 | A kind of calibration test platform for force-measuring wheel set |
| 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 |
| CN104374519A (en) * | 2014-10-17 | 2015-02-25 | 北京航天益森风洞工程技术有限公司 | Force generator for in-situ calibration of thrust rack |
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