CN108562396A - A kind of live calibration device suitable for piezoelectric type thrust vectoring frame - Google Patents
A kind of live calibration device suitable for piezoelectric type thrust vectoring frame Download PDFInfo
- Publication number
- CN108562396A CN108562396A CN201810705485.2A CN201810705485A CN108562396A CN 108562396 A CN108562396 A CN 108562396A CN 201810705485 A CN201810705485 A CN 201810705485A CN 108562396 A CN108562396 A CN 108562396A
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- China
- Prior art keywords
- thrust
- force snesor
- calibration
- draw ring
- frame
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Classifications
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01L—MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE
- G01L25/00—Testing or calibrating of apparatus for measuring force, torque, work, mechanical power, or mechanical efficiency
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- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
Abstract
The present invention proposes a kind of device for piezoelectric type thrust vectoring frame scene calibration, is applied in thrust measurement system, more particularly to rail control motor power vector measurement system.The invention is made of load cylinder, pillar standard force snesor, load bar, universal draw ring, female joint and thrust articulated bearing etc..Standard force snesor uses column structure form, standard to manage and connected using universal draw ring between sensor and load bar, and the transmission of power is using thrust articulated bearing on dynamometer.It is an advantage of the invention that entire calibration device effectively prevents additional moment when calibration, significantly improves the repeatability of thrust frame calibration to neutral number, and using flexible connection mode.
Description
Technical field
The present invention relates to a kind of piezoelectric type thrust vectoring frame scene calibration devices, belong to the survey of rail control engine test thrust
Measure technical field.
Background technology
Motor power vector is a space force vector, and size and Orientation is continually changing.In-orbit/attitude control is started
In machine altitude simulation test, thrust vectoring is that engine test process needs the important parameter obtained, is the weight of engine performance
Big criterion.Since rail/attitude control engine thrust vectoring measurement accuracy is more demanding, usually need to carry out before the test live in situ
Thrust calibration works.
Thrust vectoring frame is stationary engine and measures the main device of thrust vectoring, domestic at present generally to use piezoelectric type
Six square phase thrust vectoring frame carries out rail/attitude control engine thrust vectoring and measures, and uniformly divides according to ad hoc fashion on the same circumference
4 three-way piezoelectric sensors of cloth can measure size, direction and the work of active force according to the spatial position distribution relation of regulation
With point.
Thrust vectoring frame calibration principle is vertically to apply active force to dynamometer center, measures 4 uniformly distributed three-way piezoelectrics and passes
The output signal of sensor.The thrust calibration device in situ of scene used at present is mainly by oil cylinder, standard force snesor, load bar
With the compositions such as spheric washer.All parts are all made of threaded connection, and it is clearance fit to be threadedly coupled, before and after dismounting at the scene,
The position of loading force and direction change, and can not ensure center Vertical loading, lead to thrust calibration result repeatability error
It is larger.
Invention content
The technical problem to be solved in the present invention：It overcomes the deficiencies of the prior art and provide a kind of suitable for piezoelectric type thrust arrow
The live calibration device of frame is measured, the repeatability and precision of the calibration of vector frame are improved.
The technical scheme is that：A kind of live calibration device suitable for piezoelectric type thrust vectoring frame, mainly by adding
Carry the compositions such as oil cylinder, pillar standard force snesor, load bar, universal draw ring, female joint and thrust articulated bearing.
For load cylinder as power source, it is that plane coordinates plane to use thread connecting mode, the two with standard force snesor；
Standard force snesor strains force snesor using pillar, and both ends are respectively stud and threaded hole；Standard force snesor one end connects ten thousand
To draw ring, universal draw ring has space six degree of freedom；By short pin connection between universal draw ring and female joint, female joint and
Positioning method is connected using the shaft shoulder-seam allowance between load bar；The transferring element of dynamometer loading force selects thrust articulated bearing, axis
It is the fiberglass reinforced plastics that polytetrafluoroethylene (PTFE) is additive that bearing circle, which uses bearing steel, slidingsurface, and blowout patche is the axis that hardens
Steel is held, slidingsurface is hard chrome plating；Oscillating bearing and load bar one end are standby tight using nut.
Compared with the prior art, the invention has the advantages that：It is deformed along axis in stress using pillar standard force snesor
Line direction, it is ensured that the position of power does not shift when load；Increase universal drawing between standard force snesor and load bar
Original rigid connection is converted to flexible connection mode, it is possible to prevente effectively from the generation of additional moment by ring；Thrust articulated bearing exists
When bearing axial tension, has and good from centring property and not will produce lateral force square.It, can be with by this series of improvement
Significantly improve the repeatability of thrust frame calibration.
Description of the drawings
Fig. 1 is the principle schematic of structure of the invention.
Fig. 2 is universal draw ring bearing arrangement schematic diagram.
Fig. 3 is female joint structure principle chart.
Fig. 4 is thrust articulated bearing structure principle chart.
Specific implementation mode
The present invention is described in further detail with technical solution below in conjunction with the accompanying drawings.
As shown in Figure 1, live calibration device includes 1 load cylinder, 2 pillar standard force snesors, 3 universal draw rings, 4 spills
Connector, 5 load bars, 6 thrust articulated bearings, 7 calibration flanges etc..
Load cylinder 1 is connected through a screw thread with pillar standard force snesor 2, needs to ensure that the two is Pre strained state after connection；
It is similarly thread connecting mode between standard force snesor 2 and universal draw ring 3, installation is standby female first on standard force snesor 2,
Later preload is connect with universal draw ring 3；Short pin connection, 4 rear end of female joint is used to connect between universal draw ring 3 and female joint 4
Load bar 5 is connect, load bar 5 passes through thrust articulated bearing 6, acted on by the blowout patche of locking nut and thrust frame oscillating bearing 6
The center of flange is demarcated in front end.
In conclusion the above is merely preferred embodiments of the present invention, being not intended to limit the scope of the present invention.
All within the spirits and principles of the present invention, any modification, equivalent replacement, improvement and so on should be included in the present invention's
Within protection domain.
Claims (1)
1. a kind of live calibration device suitable for piezoelectric type thrust vectoring frame, which is characterized in that by load cylinder (1), pillar
Standard force snesor (2), universal draw ring (3), female joint (4), load bar (5), thrust articulated bearing (6) and calibration flange
(7) it forms.Load cylinder (1) is used as power source, and with standard force snesor (2) using thread connecting mode, the two is oil cylinder axis
Cooperation face-to-face；It is respectively stud and threaded hole that pillar, which strains force snesor (2) both ends,；Standard force snesor one end connects universal drawing
Ring (3), universal draw ring (3) have space six degree of freedom；It is recessed by short pin connection between universal draw ring (3) and female joint (4)
Positioning method is connected using the shaft shoulder-seam allowance between shape connector (4) and load bar (5)；The transferring element of dynamometer loading force is selected
Thrust articulated bearing (6), thrust articulated bearing (6) seat ring use bearing steel, and blowout patche is hardened bearing steel；Thrust articulated bearing
(6) and load bar (5) one end is standby tight using nut.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810705485.2A CN108562396A (en) | 2018-07-02 | 2018-07-02 | A kind of live calibration device suitable for piezoelectric type thrust vectoring frame |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810705485.2A CN108562396A (en) | 2018-07-02 | 2018-07-02 | A kind of live calibration device suitable for piezoelectric type thrust vectoring frame |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108562396A true CN108562396A (en) | 2018-09-21 |
Family
ID=63555594
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810705485.2A Pending CN108562396A (en) | 2018-07-02 | 2018-07-02 | A kind of live calibration device suitable for piezoelectric type thrust vectoring frame |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108562396A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109163836A (en) * | 2018-10-01 | 2019-01-08 | 北京航天三发高科技有限公司 | A kind of Universal flexible dynamometry component |
| CN110057493A (en) * | 2019-03-29 | 2019-07-26 | 北京航天试验技术研究所 | A kind of rocket engine thrust-measuring device dynamic calibration system |
| CN111174970A (en) * | 2020-03-11 | 2020-05-19 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Dynamic calibration platform suitable for propeller pushing torque force measuring instrument |
| CN111721127A (en) * | 2019-03-18 | 2020-09-29 | 北京三兴汽车有限公司 | Improved oil cylinder joint pin shaft of steel pusher |
| CN112525538A (en) * | 2020-11-10 | 2021-03-19 | 西安航天动力测控技术研究所 | Solid rocket engine test frame thrust in-situ calibration device and use method |
| CN114509206A (en) * | 2022-02-14 | 2022-05-17 | 武汉理工大学 | Calibration device and calibration method for strain S-deformation six-component sensor |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4112839C1 (en) * | 1991-04-19 | 1992-03-05 | A.M. Erichsen Gmbh, 5600 Wuppertal, De | |
| JP3316491B2 (en) * | 2000-04-11 | 2002-08-19 | 昭 前川 | Hydraulic control valve for measurement that offsets small errors due to oil flow rate |
| CN105486441A (en) * | 2015-12-31 | 2016-04-13 | 西安航天动力试验技术研究所 | Attitude-control engine vector thrust measurement and calibration integrated device and measurement method |
| CN105547585A (en) * | 2015-12-31 | 2016-05-04 | 西安航天动力试验技术研究所 | Attitude control engine vector thrust original position calibration apparatus |
| CN105675205A (en) * | 2015-12-31 | 2016-06-15 | 西安航天动力试验技术研究所 | Vacuum thrust in situ automatic calibrating device |
| CN106546380A (en) * | 2016-09-28 | 2017-03-29 | 中国航空规划设计研究总院有限公司 | A kind of stepless space criteria vectorial force calibrating installation |
| CN107202660A (en) * | 2017-06-06 | 2017-09-26 | 西安航天动力试验技术研究所 | 4 25N attitude control engine thermal vacuum environment stable state thrust calibration measurement apparatus |
| CN107860504A (en) * | 2017-10-10 | 2018-03-30 | 西安航天动力试验技术研究所 | The Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine |
-
2018
- 2018-07-02 CN CN201810705485.2A patent/CN108562396A/en active Pending
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE4112839C1 (en) * | 1991-04-19 | 1992-03-05 | A.M. Erichsen Gmbh, 5600 Wuppertal, De | |
| JP3316491B2 (en) * | 2000-04-11 | 2002-08-19 | 昭 前川 | Hydraulic control valve for measurement that offsets small errors due to oil flow rate |
| CN105486441A (en) * | 2015-12-31 | 2016-04-13 | 西安航天动力试验技术研究所 | Attitude-control engine vector thrust measurement and calibration integrated device and measurement method |
| CN105547585A (en) * | 2015-12-31 | 2016-05-04 | 西安航天动力试验技术研究所 | Attitude control engine vector thrust original position calibration apparatus |
| CN105675205A (en) * | 2015-12-31 | 2016-06-15 | 西安航天动力试验技术研究所 | Vacuum thrust in situ automatic calibrating device |
| CN106546380A (en) * | 2016-09-28 | 2017-03-29 | 中国航空规划设计研究总院有限公司 | A kind of stepless space criteria vectorial force calibrating installation |
| CN107202660A (en) * | 2017-06-06 | 2017-09-26 | 西安航天动力试验技术研究所 | 4 25N attitude control engine thermal vacuum environment stable state thrust calibration measurement apparatus |
| CN107860504A (en) * | 2017-10-10 | 2018-03-30 | 西安航天动力试验技术研究所 | The Quasi dynamic thrust measurement calibration integrated apparatus of attitude control engine |
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109163836A (en) * | 2018-10-01 | 2019-01-08 | 北京航天三发高科技有限公司 | A kind of Universal flexible dynamometry component |
| CN111721127A (en) * | 2019-03-18 | 2020-09-29 | 北京三兴汽车有限公司 | Improved oil cylinder joint pin shaft of steel pusher |
| CN110057493A (en) * | 2019-03-29 | 2019-07-26 | 北京航天试验技术研究所 | A kind of rocket engine thrust-measuring device dynamic calibration system |
| CN111174970A (en) * | 2020-03-11 | 2020-05-19 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Dynamic calibration platform suitable for propeller pushing torque force measuring instrument |
| CN111174970B (en) * | 2020-03-11 | 2021-04-06 | 中国船舶科学研究中心（中国船舶重工集团公司第七0二研究所） | Dynamic calibration platform suitable for propeller pushing torque force measuring instrument |
| CN112525538A (en) * | 2020-11-10 | 2021-03-19 | 西安航天动力测控技术研究所 | Solid rocket engine test frame thrust in-situ calibration device and use method |
| CN112525538B (en) * | 2020-11-10 | 2023-08-08 | 西安航天动力测控技术研究所 | Solid rocket engine test frame thrust in-situ calibration device and use method |
| CN114509206A (en) * | 2022-02-14 | 2022-05-17 | 武汉理工大学 | Calibration device and calibration method for strain S-deformation six-component sensor |
| CN114509206B (en) * | 2022-02-14 | 2023-02-28 | 武汉理工大学 | Calibration device and calibration method for strain S-deformation six-component sensor |
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Application publication date: 20180921 |
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