CN105403335B - A kind of force snesor for testing rocket linkage load change - Google Patents
A kind of force snesor for testing rocket linkage load change Download PDFInfo
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- CN105403335B CN105403335B CN201410444548.5A CN201410444548A CN105403335B CN 105403335 B CN105403335 B CN 105403335B CN 201410444548 A CN201410444548 A CN 201410444548A CN 105403335 B CN105403335 B CN 105403335B
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- sensor
- rocket
- foil gauge
- connecting rod
- linkage
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Abstract
The present invention relates to rocket connecting rod load test technical fields, more particularly to a kind of force snesor for testing rocket linkage load change, the technical issues of purpose is solved in Major Ground Test and flight test is carried out, and existing sensor does not adapt to the labyrinth and hot environment of test connecting rod.It is characterized in that, it includes first sensor and second sensor.First sensor and second sensor are arranged in the connecting rod cylinder cylindrical end of rocket linkage, and first sensor and second sensor are located on same circumference.First sensor and second sensor are used to the load that measurement rocket linkage is born.The present invention demonstrates the sensor in connecting rod slow test has the advantages that accuracy is high, it can be monitored in boosting separation test and bundle point and a middle binding point connecting rod stressing conditions in the indeterminate binding device of three fulcrums in boosting, the control for certain model rocket connecting rod pretightning force provides reliable basis.
Description
Technical field
The present invention relates to rocket connecting rod load test technical fields, and in particular to a kind of test rocket linkage load becomes
The force snesor of change.
Background technology
Certain model rocket is the large rocket newly developed, and the connection of rocket core grade and boosting is bound by linkage.
Certain model rocket employs the new indeterminate bundling apparatus of three fulcrums, therefore is bundled a little in flight course is emitted for rocket
Each fulcrum stress and load change situation needs make understanding, to judge the indeterminate bundling apparatus load change rule of three fulcrums
Rule, the control for connecting rod pretightning force provide foundation.Meanwhile in large-scale grounds examinations such as whole rocket vibration test, Booster separation experiments
The variation tested and in flight test, also need to measure connecting rod load.
Bundle connecting rod connection mode：It bundlees connecting rod and bearing company is bundled with core grade and boost motor by both ends auricle and ball axis
It connects, can be rotated freely in certain angle scope inside connecting rod around two ball axis.Under load effect outside, connecting rod is subjected only to axial masterpiece
With.In ground experiment and flight test process (including the processes such as assembling and filling), it is desirable that a kind of sensor being capable of the company of measurement
The strain value of bar, and can strain data be converted into axial force suffered by connecting rod in real time.Existing sensor is mounted on connecting rod
Afterwards, can not be worked normally in Major Ground Test and flight test.
The content of the invention
Present invention aim to address in Major Ground Test and flight test is carried out, existing sensor does not adapt to
The technical issues of testing complicated connecting rod and hot environment provides a kind of adaptation connecting rod labyrinth, and range ability is big, accuracy
The force snesor of test rocket linkage load change high, stability is good, reliability is high.
What the present invention was realized in：
A kind of force snesor for testing rocket linkage load change, including first sensor and second sensor；The
One sensor and second sensor are arranged in the connecting rod cylinder cylindrical end of rocket linkage, and first sensor and second pass
Sensor is located on same circumference；First sensor and second sensor are used to the load that measurement rocket linkage is born.
First sensor as described above and second sensor are connected handing-over line with connecting rod cylinder cylindrical end with square end
Distance for 40mm, first sensor and the angle of the central axes of the connecting rod cylinder cylindrical end cross section of rocket linkage are
22.5 degree, the angle of second sensor and first sensor is 45 degree.
First sensor as described above is connected in a manner of full-bridge and formed by the first T-shaped strain gauge and the 3rd T-shaped strain gauge,
The central symmetry of first T-shaped strain gauge and the 3rd T-shaped strain gauge along the connecting rod cylinder cylindrical end cross section of rocket linkage.
First T-shaped strain gauge as described above includes the 11st foil gauge and the 12nd foil gauge, and the 3rd T-shaped strain gauge includes the
31 foil gauges and the 32nd foil gauge；First sensor B2 ports respectively with the 1a2 ends of the 11st foil gauge and the 1b1 of the 12nd foil gauge
End connection, 3a1 end of the first sensor A2 ports respectively with the 1b2 ends of the 12nd foil gauge and the 31st foil gauge are connected, and first passes
3b2 end of the sensor C2 ports respectively with the 1a1 ends of the 11st foil gauge and the 32nd foil gauge is connected, first sensor D2 ports difference
It is connected with the 3a2 ends of the 31st foil gauge and the 3b1 ends of the 32nd foil gauge.
Second sensor as described above is connected in a manner of full-bridge and formed by the second T-shaped strain gauge and the 4th T-shaped strain gauge,
The central symmetry of second T-shaped strain gauge and the 4th T-shaped strain gauge along the connecting rod cylinder cylindrical end cross section of rocket linkage.
Second T-shaped strain gauge as described above includes the 21st foil gauge and the 22nd foil gauge, and the 4th T-shaped strain gauge includes the
41 foil gauges and the 42nd foil gauge；Second sensor B1 ports respectively with the 2a2 ends of the 21st foil gauge and the 2b1 of the 22nd foil gauge
End connection, 4a1 end of the second sensor A1 ports respectively with the 2b2 ends of the 22nd foil gauge and the 41st foil gauge are connected, and second passes
4b2 end of the sensor C1 ports respectively with the 2a1 ends of the 21st foil gauge and the 42nd foil gauge is connected, second sensor D1 ports difference
It is connected with the 4a2 ends of the 41st foil gauge and the 4b1 ends of the 42nd foil gauge.
The beneficial effects of the invention are as follows：
The present invention includes first sensor and second sensor.The present invention is now carried applied to the binding connecting rod of the model rocket
Lotus monitors.Straight-bar and the drawing operating mode of brace and pressure operating mode in connecting rod slow test is bundled；Large-scale ground boosting separation test
Middle use.The sensor is demonstrated in connecting rod slow test has the advantages that accuracy is high, can be supervised in boosting separation test
It surveys in the indeterminate binding device of three fulcrums and point and a middle binding point connecting rod stressing conditions is bundled in boosting, it is pre- for certain model rocket connecting rod
The control of clamp force provides reliable basis.
Description of the drawings
Fig. 1 is a kind of strain gauge adhesion position of the force snesor of test rocket linkage load change of the present invention
Front view；
Fig. 2 is a kind of strain gauge adhesion position of the force snesor of test rocket linkage load change of the present invention
A is to structure chart；
Fig. 3 is a kind of group bridge of the first sensor of the force snesor of test rocket linkage load change of the present invention
Structure；
Fig. 4 is a kind of group bridge knot of the second sensor of the force snesor of test rocket linkage load change of the present invention
Structure.
Specific embodiment
The present invention is described further with reference to the accompanying drawings and examples.
As shown in Figure 1, a kind of force snesor for testing rocket linkage load change, including first sensor and second
Sensor.First sensor and second sensor are arranged in the connecting rod cylinder cylindrical end of rocket linkage, the first sensing
Device and second sensor are located on same circumference.First sensor and second sensor are used to measurement rocket linkage and are held
The load received.
As depicted in figs. 1 and 2, first sensor and second sensor are connected friendship with square end with connecting rod cylinder cylindrical end
The distance of wiring is 40mm, first sensor and the folder of the central axes of the connecting rod cylinder cylindrical end cross section of rocket linkage
Angle is 22.5 degree, and the angle of second sensor and first sensor is 45 degree.
As shown in figure 3, first sensor connects group with the 3rd T-shaped strain gauge 3 by the first T-shaped strain gauge 1 in a manner of full-bridge
Into center of first T-shaped 1 and the 3rd T-shaped strain gauge 3 of strain gauge along the connecting rod cylinder cylindrical end cross section of rocket linkage
Symmetrically.First T-shaped strain gauge 1 includes the 11st foil gauge 1a and the 12nd foil gauge 1b, and the 3rd T-shaped strain gauge 3 includes the 31st strain
Piece 3a and the 32nd foil gauge 3b.First sensor B2 ports respectively with the 1a2 ends of the 11st foil gauge 1a and the 12nd foil gauge 1b
1b1 ends connect, and 3a1 end of the first sensor A2 ports respectively with the 1b2 ends of the 12nd foil gauge 1b and the 31st foil gauge 3a is connected,
3b2 end of the first sensor C2 ports respectively with the 1a1 ends of the 11st foil gauge 1a and the 32nd foil gauge 3b is connected, first sensor
3b1 end of the D2 ports respectively with the 3a2 ends of the 31st foil gauge 3a and the 32nd foil gauge 3b is connected.
As shown in figure 4, second sensor connects group with the 4th T-shaped strain gauge 4 by the second T-shaped strain gauge 2 in a manner of full-bridge
Into center of second T-shaped 2 and the 4th T-shaped strain gauge 4 of strain gauge along the connecting rod cylinder cylindrical end cross section of rocket linkage
Symmetrically.Second T-shaped strain gauge 2 includes the 21st foil gauge 2a and the 22nd foil gauge 2b, and the 4th T-shaped strain gauge 4 includes the 41st strain
Piece 4a and the 42nd foil gauge 4b.Second sensor B1 ports respectively with the 2a2 ends of the 21st foil gauge 2a and the 22nd foil gauge 2b
2b1 ends connect, and 4a1 end of the second sensor A1 ports respectively with the 2b2 ends of the 22nd foil gauge 2b and the 41st foil gauge 4a is connected,
4b2 end of the second sensor C1 ports respectively with the 2a1 ends of the 21st foil gauge 2a and the 42nd foil gauge 4b is connected, second sensor
4b1 end of the D1 ports respectively with the 4a2 ends of the 41st foil gauge 4a and the 42nd foil gauge 4b is connected.
In use, for example in first sensor ,+5V a driving voltage, rocket connecting rod dress are added in B2 ports, D2 ports
It puts and is not deformed in the case that not stressing, the T-shaped strain gauge of first be pasted onto on rocket linkage and the 3rd T-shaped strain gauge
Also without deformation, strain gauge resistance value does not change, and electric bridge keeps balance, and A1 ports, the output of C1 port signals are zero；Work as rocket battery
Lever apparatus is deformed under stressing conditions, and the T-shaped strain gauge of first be pasted onto on connecting rod and the 3rd T-shaped strain gauge also deform,
Strain gauge resistance value changes, and bridge balance is broken, and A1 ports, C1 port signals export a signal.According to signal magnitude and
Transducer calibration sensitivity can calculate load suffered by rocket linkage.
The present invention includes first sensor and second sensor.Since first sensor and second sensor are arranged in rocket
The designated position of connecting rod is bundled, therefore can accurately measure the load change of rocket binding connecting rod.The present invention is now applied to the type
The binding connecting rod load monitoring of number rocket.Straight-bar and the drawing operating mode of brace and pressure operating mode in connecting rod slow test is bundled；Greatly
It is used in the boosting separation test of type ground.The sensor is demonstrated in connecting rod slow test has the advantages that accuracy is high, can
It is monitored in boosting separation test and bundlees point and a middle binding point connecting rod stressing conditions in the indeterminate binding device of three fulcrums in boosting,
Control for certain model rocket connecting rod pretightning force provides reliable basis.
Claims (5)
1. a kind of force snesor for testing rocket linkage load change, it is characterised in that：It includes first sensor and the
Two sensors；First sensor and second sensor are arranged in the connecting rod cylinder cylindrical end of rocket linkage, and first passes
Sensor and second sensor are located on same circumference；First sensor and second sensor are used to measurement rocket linkage institute
The load born；
The first sensor and second sensor be connected with connecting rod cylinder cylindrical end with square end handing-over line distance be
40mm, first sensor and the angle of the central axes of the connecting rod cylinder cylindrical end cross section of rocket linkage are 22.5 degree,
The angle of second sensor and first sensor is 45 degree.
2. the force snesor of test rocket linkage load change according to claim 1, it is characterised in that：Described
First sensor is connected in a manner of full-bridge and formed by the first T-shaped strain gauge and the 3rd T-shaped strain gauge, the first T-shaped strain gauge and
Central symmetry of the three T-shaped strain gauges along the connecting rod cylinder cylindrical end cross section of rocket linkage.
3. the force snesor of test rocket linkage load change according to claim 2, it is characterised in that：Described
First T-shaped strain gauge includes the 11st foil gauge and the 12nd foil gauge, and the 3rd T-shaped strain gauge includes the 31st foil gauge and the 32nd strain
Piece；1b1 end of the first sensor B2 ports respectively with the 1a2 ends of the 11st foil gauge and the 12nd foil gauge is connected, first sensor
3a1 end of the A2 ports respectively with the 1b2 ends of the 12nd foil gauge and the 31st foil gauge is connected, and first sensor C2 ports are respectively with
The 1a1 ends of 11 foil gauges are connected with the 3b2 ends of the 32nd foil gauge, the first sensor D2 ports 3a2 with the 31st foil gauge respectively
End is connected with the 3b1 ends of the 32nd foil gauge.
4. the force snesor of test rocket linkage load change according to claim 1, it is characterised in that：Described
Second sensor is connected in a manner of full-bridge and formed by the second T-shaped strain gauge and the 4th T-shaped strain gauge, the second T-shaped strain gauge and
Central symmetry of the four T-shaped strain gauges along the connecting rod cylinder cylindrical end cross section of rocket linkage.
5. the force snesor of test rocket linkage load change according to claim 4, it is characterised in that：Described
Second T-shaped strain gauge includes the 21st foil gauge and the 22nd foil gauge, and the 4th T-shaped strain gauge includes the 41st foil gauge and the 42nd strain
Piece；2b1 end of the second sensor B1 ports respectively with the 2a2 ends of the 21st foil gauge and the 22nd foil gauge is connected, second sensor
4a1 end of the A1 ports respectively with the 2b2 ends of the 22nd foil gauge and the 41st foil gauge is connected, and second sensor C1 ports are respectively with
The 2a1 ends of 21 foil gauges are connected with the 4b2 ends of the 42nd foil gauge, the second sensor D1 ports 4a2 with the 41st foil gauge respectively
End is connected with the 4b1 ends of the 42nd foil gauge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410444548.5A CN105403335B (en) | 2014-09-03 | 2014-09-03 | A kind of force snesor for testing rocket linkage load change |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410444548.5A CN105403335B (en) | 2014-09-03 | 2014-09-03 | A kind of force snesor for testing rocket linkage load change |
Publications (2)
| Publication Number | Publication Date |
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| CN105403335A CN105403335A (en) | 2016-03-16 |
| CN105403335B true CN105403335B (en) | 2018-05-18 |
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| CN201410444548.5A Active CN105403335B (en) | 2014-09-03 | 2014-09-03 | A kind of force snesor for testing rocket linkage load change |
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Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS56102338A (en) * | 1980-01-14 | 1981-08-15 | Sakamura Kikai Seisakusho:Kk | Punching pressure abnormality detector in continuous multistage former |
| CN2619249Y (en) * | 2003-05-15 | 2004-06-02 | 同济大学 | Detector for tyre earth pressure and road surface structureinner stress change under tyre function |
| CN100412521C (en) * | 2006-08-07 | 2008-08-20 | 南京航空航天大学 | Three-D small range force sensor |
| FR2913949B1 (en) * | 2007-03-23 | 2009-10-02 | Goodrich Actuation Systems Sas | IMPROVEMENTS IN THE DETECTION OF THE RETRIEVAL OF EFFORT OF THE SECONDARY PATH OF A FLIGHT CONTROL ACTUATOR. |
| CN101368817B (en) * | 2008-10-13 | 2010-06-09 | 上海大学 | Dynamic measurement method and system for elastic link lever deflection of miniature rotor aircraft pitch-changing mechanism |
| CN101655402B (en) * | 2009-08-31 | 2011-03-23 | 重庆长安汽车股份有限公司 | Method for testing preload of engine connecting rod bolt and special tool thereof |
| FR2964737B1 (en) * | 2010-09-14 | 2013-05-31 | Airbus Operations Sas | METHOD OF MEASURING EFFORTS IN JUNCTIONS IN HIGH TEMPERATURE ENVIRONMENT AND INSTRUMENTAL AXIS OF IMPLEMENTATION, PARTICULARLY FOR REAR AIRCRAFT TURBOELECTOR ATTACHMENT |
| CN103454025A (en) * | 2013-08-28 | 2013-12-18 | 中国商用飞机有限责任公司 | Load cell and large load measuring method capable of carrying out calibration in multiple angles for air craft |
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