CN209910943U - Wind tunnel balance terminal attitude measuring device - Google Patents
Wind tunnel balance terminal attitude measuring device Download PDFInfo
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- CN209910943U CN209910943U CN201920665141.3U CN201920665141U CN209910943U CN 209910943 U CN209910943 U CN 209910943U CN 201920665141 U CN201920665141 U CN 201920665141U CN 209910943 U CN209910943 U CN 209910943U
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- tunnel balance
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- 238000005259 measurement Methods 0.000 claims abstract description 17
- 238000005096 rolling process Methods 0.000 claims description 41
- 238000009434 installation Methods 0.000 claims description 13
- 239000010453 quartz Substances 0.000 claims description 5
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 5
- 238000000034 method Methods 0.000 description 5
- 230000005484 gravity Effects 0.000 description 4
- 238000010586 diagram Methods 0.000 description 3
- 239000011159 matrix material Substances 0.000 description 3
- 230000036544 posture Effects 0.000 description 2
- 230000000694 effects Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model relates to a wind-tunnel balance calibration technical field specifically discloses a wind-tunnel balance terminal attitude measurement device. The device comprises a mounting seat and an accelerometer, wherein the accelerometer comprises a roll angle accelerometer I, a pitch angle accelerometer and a roll angle accelerometer II, and the three accelerometers are respectively mounted on a roll reference surface I, a pitch reference surface and a roll reference surface II of the mounting seat. The utility model discloses a wind-tunnel balance terminal attitude measuring device realizes wind-tunnel balance terminal every single move angle and roll angle's accurate measurement at a wide range scope when wind-tunnel balance single vector multi-element calibration, every move angle measurement range 45, roll angle measurement range 180, and measurement accuracy is superior to 1', when satisfying wind-tunnel balance terminal attitude measurement accuracy, has that the structure is simpler, advantage that the cost is lower.
Description
Technical Field
The invention belongs to the technical field of wind tunnel balance calibration, and particularly relates to a wind tunnel balance terminal attitude measuring device.
Background
The calibration of the wind tunnel balance is one of the main links of the wind tunnel balance application, and aims to obtain a relation matrix between input and output of the wind tunnel balance through the calibration of the wind tunnel balance. When the wind tunnel balance is actually used, the input of the wind tunnel balance, namely the effective aerodynamic load, can be obtained through back calculation according to the relationship matrix between the input and the output of the wind tunnel balance, which are obtained through calibration. The calibration process of the wind tunnel balance is a process for simulating the use state of the wind tunnel balance, and during calibration of the wind tunnel balance, the calibration equipment applies accurate design load to the wind tunnel balance, and the output of the wind tunnel balance is acquired through the data acquisition instrument, so that the calculation of the input and output relation matrix of the wind tunnel balance is carried out. The calibration equipment of the wind tunnel balance has various types, and different types have advantages, wherein the single-vector multi-element calibration equipment is concerned about due to the characteristics of simple equipment structure and control, high reliability, low development cost and the like.
The wind tunnel balance single vector multi-element calibration means that the multi-element calibration of the wind tunnel balance is completed only by using a single force vector. In single vector calibration, the direction and the acting point of a force vector on a wind tunnel balance body axis coordinate system are changed, so that the force vector is projected on the wind tunnel balance body axis coordinate system, force components in three coordinate axis directions are generated, namely axial force, normal force and lateral force, and moment components in the three coordinate axis directions are generated simultaneously, namely pitching moment, yawing moment and rolling moment. The single-vector multi-element calibration method can be divided into two types, one type is that a wind tunnel balance is fixed, and a force vector with a variable and controllable direction action point is generated by equipment to act on the wind tunnel balance; the other type adopts the gravity of the weight as a force vector, and changes the posture and the position of the wind tunnel balance through equipment, thereby realizing the state that the direction and the acting point of the gravity of the weight and the wind tunnel balance reach the calibration requirement. Because the gravity direction is always along the vertical direction, the single-vector multi-element calibration method for changing the attitude and the position of the wind tunnel balance by using the gravity of the weight as a force vector through equipment is generally applied. In specific application, the postures of the wind tunnel balance are more measured by adopting a laser system, so that the wind tunnel balance has high precision, but the cost is high, and the problem of small measurement range exists.
Disclosure of Invention
The invention aims to provide a wind tunnel balance terminal attitude measuring device, which solves the problems of accurate measurement of the wind tunnel balance terminal attitude and calibration of a wind tunnel balance.
The technical scheme of the invention is as follows: a wind tunnel balance terminal attitude measuring device comprises a mounting base and an accelerometer, wherein the accelerometer comprises a roll angle accelerometer I, a pitch angle accelerometer and a roll angle accelerometer II; the mounting seat is of a shell structure and comprises a mounting reference surface, a pitching reference surface, a rolling reference surface I and a rolling reference surface II, wherein the mounting reference surface is of a planar plate-shaped structure; two sides of the installation reference surface are vertically connected with the installation reference surface to form a rolling reference surface II of a triangular flat plate structure, and a rolling angle accelerometer II is arranged on the rolling reference surface II; forming a rolling reference surface I on a flat plate structure vertically connected with the installation reference surface and the rolling reference surface II, wherein a rolling angle accelerometer I is arranged on the rolling reference surface I; the pitching reference surface is of a flat plate structure, is vertically connected with the rolling reference surface I and is vertical to the installation reference surface, and a pitching angle accelerometer is arranged on the pitching reference surface.
The mounting reference surface is provided with a plurality of mounting screw holes which are uniformly distributed.
The rolling angle accelerometer I, the pitch angle accelerometer and the rolling angle accelerometer II are flexible quartz accelerometers.
The pitching reference surface is provided with a connector, and the connector is connected with the input and output of the roll angle accelerometer I, the pitch angle accelerometer and the roll angle accelerometer II through internal wiring.
The mounting reference surface is provided with at least 2 positioning pin holes.
The invention has the following remarkable effects: the wind tunnel balance terminal attitude measuring device and the method thereof for calibrating the balance realize the application of the wind tunnel balance terminal attitude measuring device in the balance calibration through the three flexible quartz accelerometers and the specially designed mutual position relationship of the three flexible quartz accelerometers. The wind tunnel balance terminal attitude measuring device provided by the invention can realize accurate measurement of the pitch angle and the roll angle of the wind tunnel balance terminal in a wide range when the wind tunnel balance is subjected to single vector multi-element calibration, the pitch angle measuring range is +/-45 degrees, the roll angle measuring range is +/-180 degrees, the measuring accuracy is better than 1', the wind tunnel balance terminal attitude measuring accuracy is met, and the wind tunnel balance terminal attitude measuring device has the advantages of simpler structure and lower cost.
Drawings
FIG. 1 is a schematic structural diagram of a wind tunnel balance terminal attitude measurement device according to the present invention;
FIG. 2 is a schematic diagram of a position relationship of a sensitive shaft of the wind tunnel balance terminal attitude measurement device according to the present invention;
FIG. 3 is a schematic diagram of the installation and use of a wind tunnel balance terminal attitude measurement device according to the present invention;
in the figure: 1. a mounting seat; 2. a roll angle accelerometer I; 3. a pitch angle accelerometer; 4. a roll angle accelerometer II; 5. a connector assembly; 6. loading a sleeve; 7. a strut; 8. a weight hanging point; 9. a sensitive axis of a rolling angle accelerometer I; 10. a pitch angle accelerometer sensitive axis; 11. a sensitive axis of a rolling angle accelerometer II; 12. mounting screw holes; 13. and positioning the pin hole.
Detailed Description
The invention is described in further detail below with reference to the figures and the embodiments.
As shown in fig. 1, the wind tunnel balance terminal attitude measurement device comprises a mounting base 1, accelerometers and a connector 5, wherein the accelerometers comprise three accelerometers, namely a roll angle accelerometer I2, a pitch angle accelerometer 3 and a roll angle accelerometer II4, which are all flexible quartz accelerometers; the mounting seat 1 is of a shell structure and comprises a mounting reference surface, a pitching reference surface, a rolling reference surface I and a rolling reference surface II, wherein the mounting reference surface is of a planar plate-shaped structure, a plurality of uniformly distributed mounting screw holes 12 and positioning pin holes 13 are formed in the mounting reference surface, the number of the positioning pin holes 13 is more than or equal to 2, and the mounting reference surface is positioned in an XYZ space coordinate system and is parallel to an XZ plane; two rolling reference surfaces II parallel to the YZ plane are arranged on two sides of the installation reference surface, wherein the rolling reference surfaces II are of triangular flat plate structures, and rolling angle accelerometers II4 are arranged on the rolling reference surfaces II; the rolling reference surface I is vertically connected with the installation reference surface and the rolling reference surface II at the same time to form a rolling reference surface I parallel to the XY plane, wherein the rolling reference surface I is of a rectangular flat plate structure, and a rolling angle accelerometer I2 is installed on the rolling reference surface I; the pitch reference plane is of a rectangular flat plate structure, a pitch angle accelerometer 3 and a connector 5 are mounted on the pitch reference plane, and the input and output of a roll angle accelerometer I2, the pitch angle accelerometer 3 and a roll angle accelerometer II4 are gathered on the connector 5 through internal wiring by the connector 5;
as shown in fig. 2, a sensitive axis 9 of a roll angle accelerometer i 2 and a sensitive axis 11 of a roll angle accelerometer ii4 are perpendicular to each other and parallel to the XZ plane; a pitch angle accelerometer sensitive axis 10 of the pitch angle accelerometer 3 is parallel to the Y axis;
as shown in fig. 3, the wind tunnel balance terminal attitude measuring device of the present invention is installed on a support rod 7, a balance is installed on the support rod 7, a balance loading sleeve 6 is installed on the balance, and the wind tunnel balance terminal attitude measuring device is positioned and installed at the front end of the balance loading sleeve through an installation screw hole 12 and a positioning pin hole 13 on an installation reference surface; and weights are mounted on weight mounting points 8 on the balance loading sleeve 6 through a strong force maleic wire, and output voltages of the roll angular velocity meter I (2), the pitch angle accelerometer (3) and the roll angular accelerometer II (4) are respectively measured by opening a voltmeter of the wind tunnel balance terminal attitude measuring device after the weights are static.
Claims (5)
1. A wind-tunnel balance terminal attitude measuring device is characterized in that: the device comprises a mounting base (1) and accelerometers, wherein the accelerometers comprise a rolling angle accelerometer I (2), a pitching angle accelerometer (3) and a rolling angle accelerometer II (4); the mounting seat (1) is of a shell structure and comprises a mounting reference surface, a pitching reference surface, a rolling reference surface I and a rolling reference surface II, wherein the mounting reference surface is of a planar plate-shaped structure; two sides of the installation reference surface are vertically connected with the installation reference surface to form a rolling reference surface II of a triangular flat plate structure, and a rolling angle accelerometer II (4) is arranged on the rolling reference surface II; forming a rolling reference surface I on a flat plate structure vertically connected with the installation reference surface and the rolling reference surface II, wherein a rolling angle accelerometer I (2) is arranged on the rolling reference surface I; the pitching reference surface is of a flat plate structure, is vertically connected with the rolling reference surface I and is vertical to the installation reference surface, and a pitching angle accelerometer (3) is arranged on the pitching reference surface.
2. The wind tunnel balance terminal attitude measurement device of claim 1, wherein: the mounting reference surface is provided with a plurality of uniformly distributed mounting screw holes (12).
3. The wind tunnel balance terminal attitude measurement device of claim 1, wherein: the rolling angle accelerometer I (2), the pitching angle accelerometer (3) and the rolling angle accelerometer II (4) are flexible quartz accelerometers.
4. The wind tunnel balance terminal attitude measurement device of claim 1, wherein: every single move reference surface on be equipped with connector (5), connector (5) through inside walk the line with roll angle accelerometer I (2), pitch angle accelerometer (3) and roll angle accelerometer II (4) the input/output be connected.
5. The wind tunnel balance terminal attitude measurement device of claim 1 or 2, wherein: the mounting reference surface is provided with positioning pin holes (13), and the number of the positioning pin holes (13) is at least 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920665141.3U CN209910943U (en) | 2019-05-10 | 2019-05-10 | Wind tunnel balance terminal attitude measuring device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920665141.3U CN209910943U (en) | 2019-05-10 | 2019-05-10 | Wind tunnel balance terminal attitude measuring device |
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| Publication Number | Publication Date |
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| CN209910943U true CN209910943U (en) | 2020-01-07 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201920665141.3U Expired - Fee Related CN209910943U (en) | 2019-05-10 | 2019-05-10 | Wind tunnel balance terminal attitude measuring device |
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| CN (1) | CN209910943U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110108442A (en) * | 2019-05-10 | 2019-08-09 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind-tunnel balance terminal attitude measuring and its method in balance calibration |
| CN117705091A (en) * | 2024-02-05 | 2024-03-15 | 中国空气动力研究与发展中心高速空气动力研究所 | High-precision attitude measurement method based on wide-range quartz flexible accelerometer |
-
2019
- 2019-05-10 CN CN201920665141.3U patent/CN209910943U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110108442A (en) * | 2019-05-10 | 2019-08-09 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind-tunnel balance terminal attitude measuring and its method in balance calibration |
| CN117705091A (en) * | 2024-02-05 | 2024-03-15 | 中国空气动力研究与发展中心高速空气动力研究所 | High-precision attitude measurement method based on wide-range quartz flexible accelerometer |
| CN117705091B (en) * | 2024-02-05 | 2024-04-16 | 中国空气动力研究与发展中心高速空气动力研究所 | High-precision attitude measurement method based on wide-range quartz flexible accelerometer |
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20200107 |
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| CF01 | Termination of patent right due to non-payment of annual fee |