CN212658412U - Wind tunnel model supports interference force measurement test constructional device - Google Patents
Wind tunnel model supports interference force measurement test constructional device Download PDFInfo
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- CN212658412U CN212658412U CN202021044017.4U CN202021044017U CN212658412U CN 212658412 U CN212658412 U CN 212658412U CN 202021044017 U CN202021044017 U CN 202021044017U CN 212658412 U CN212658412 U CN 212658412U
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Abstract
The utility model discloses a wind-tunnel model supports interference force cell test constructional device relates to wind-tunnel model test technical field, and its technical scheme main points are: the wing tip supporting device structure comprises a double-supporting support, a left supporting rod, a right supporting rod, a balance wing connecting cover, an attack angle sensor cover, a supporting rod fairing, a left force measuring balance, a right force measuring balance, a wing tip supporting fairing, a false tail supporting force measuring balance, a false tail support, a concentrated mass adjusting block, a pressure measuring sensor and an attack angle sensor. The device can be used for correcting the wind tunnel model tail support interference test, and can accurately simulate the tail appearance and the flow of a flow field of the wind tunnel model when the wind tunnel model is not in a false tail support state; when the wind tunnel model is provided with the false tail support structure, the false tail support is fixed on the machine body, the pneumatic load acting on the false tail support is small, the false tail support is not easy to contact with the wind tunnel model, the pressure in the cavity of the wind tunnel model is stable, and the fluctuation amplitude is small; meanwhile, the device is simple to realize and easy to operate.
Description
Technical Field
The utility model relates to a wind-tunnel model test technical field, more specifically say, it relates to a wind-tunnel model supports interference force measurement test constructional device.
Background
The conventional wind tunnel force measurement test usually uses a tail support mode to support an aircraft model for wind tunnel test, the shape of the tail part of the model is changed due to the installation of a balance and a support device thereof, and because the interference of the tail support on the model must be accounted for by viscous near-field disturbance, accurate support interference data is difficult to obtain by adopting a calculation method, so the tail support interference is generally corrected by a test method by means of false tail support at present. The wing tip supporting device is a main supporting form for carrying out a wind tunnel model tail support interference correction test, two working conditions of whether a false tail supporting structure exists or not are tested through a left balance and a right balance 2, and model tail support interference test correction is obtained by comparing the difference of whether false tail supporting exists or not.
At present, the false tail support is installed on a support connected to the middle part of a wind tunnel, the front end of the false tail support is inserted into a model cavity but is not in contact with the model, and 2 balances can directly measure the difference of the support with or without the tail support. The layout has the defects that the wind tunnel model wings are easy to elastically deform in the test process of the wind tunnel test and generate translation and rotation; meanwhile, the false tail support is easy to contact with the model, so that the balance has incorrect force measurement; in addition, the space positions of the false tail support and the model are easy to change, so that the pressure in the cavity of the wind tunnel model is unstable, the fluctuation range is large, and the data precision of the wind tunnel test is easy to reduce. The advanced foreign false tail support is adjusted in the test process through the pose adjusting mechanism connected to the support in the middle of the model, the defect is that the adjusting time is long, most of the false tail support is suitable for a continuous wind tunnel, the adjusting range is limited, and if the rigidity of the aircraft model and the wing tip dual support is weak, the false tail support still has the possibility of contacting with the model.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a wind tunnel model supporting interference force measurement test structure device, which can be used for correcting a wind tunnel model tail supporting interference test and can accurately simulate the tail appearance and the flow field of a wind tunnel model when the wind tunnel model does not have a false tail supporting state; when the wind tunnel model is provided with the false tail support structure, the false tail support is fixed on the machine body, the pneumatic load acting on the false tail support is small, the false tail support is not easy to contact with the wind tunnel model, the pressure in the cavity of the wind tunnel model is stable, and the fluctuation amplitude is small; meanwhile, the device is simple to realize and easy to operate.
The above technical purpose of the present invention can be achieved by the following technical solutions: a wind tunnel model supporting interference force measurement test structure device comprises a wing tip supporting device structure and a wind tunnel model, wherein the wing tip supporting device structure comprises a double-supporting support with two supporting ends, and the two supporting ends of the double-supporting support are both connected with a supporting rod; the front end of the supporting rod is provided with a force measuring balance; the force measuring balance is provided with a balance wing connecting cover and an attack angle sensor cover close to the balance wing connecting cover; a strut fairing is arranged at the end part of the strut, which is far away from the double supporting seats; the left wing and the right wing of the wind tunnel model are connected with the balance wing connecting cover through corresponding wing tip supporting fairings; a false tail support force measuring balance is arranged in a cavity in the wind tunnel model; the cantilever of the pseudo-tail support force-measuring balance is supported by a pseudo-tail support; a centralized mass adjusting block is arranged in the cavity of the wind tunnel model; a pressure sensor is arranged in the balance wing connecting cover; and an attack angle sensor is arranged in the attack angle sensor cover.
By adopting the technical scheme, when a wind tunnel force measurement test is carried out, a measurement system of a wind tunnel model is formed by 2+1 wind tunnel balances (a left measurement balance and a right measurement balance 2 and a false tail support force measurement balance 1), when the wind tunnel model is in a state without false tail support, the pneumatic load of the wind tunnel model is measured together in a wing tip support mode through the left measurement balance and the right measurement balance 2, and the pneumatic load positioned in a wind tunnel model moment reference center is obtained through force system translation according to the pneumatic load measured respectively; when the wind tunnel model is in a state with a false tail support, all pneumatic loads of the wind tunnel model and the false tail support are obtained by measuring in a wingtip support mode through 2 measuring balances, and 1 false tail support force measuring balance in a cavity of the wind tunnel model measures the pneumatic load acting on the false tail support in a cantilever support mode; the method comprises the steps that the pneumatic load of a wind tunnel model with a false tail support state can be obtained through translation conversion of a pneumatic load force system measured by 2 measuring balance and 1 false tail support force measuring balance, and then the tail support interference correction quantity of the wind tunnel model is obtained through comparing the pneumatic load difference of the wind tunnel model without the false tail support state and the wind tunnel model with the false tail support state; the device can be used for correcting the wind tunnel model tail support interference test, and can accurately simulate the tail appearance and the flow of a flow field of the wind tunnel model when the wind tunnel model is not in a false tail support state; when the wind tunnel model is provided with the false tail support structure, the false tail support is fixed on the machine body, the pneumatic load acting on the false tail support is small, the false tail support is not easy to contact with the wind tunnel model, the pressure in the cavity of the wind tunnel model is stable, and the fluctuation amplitude is small; meanwhile, the device is simple to realize and easy to operate.
The utility model discloses further set up to: the number of the force measuring balances is 2, the number of the false tail supporting force measuring balances is 1, and the force measuring balance and the false tail supporting force measuring balances form a force measuring system of the wind tunnel model.
By adopting the technical scheme, the measuring balance is supported by the 2 measuring balance and the 1 false tail, so that a force measuring system of the wind tunnel model is conveniently formed, and the measurement of the pneumatic load of the wind tunnel model is realized.
The utility model discloses further set up to: the number of the attack angle sensors is 3, and the 3 attack angle sensors respectively and correspondingly measure 2 measurement days and the space pose of the false tail support force-measuring balance.
By adopting the technical scheme, the sensor is used for measuring the force measuring scale and processing and using the pose wind-supply hole test data of the false tail support force measuring scale through the attack angle sensor.
The utility model discloses further set up to: the false tail support is consistent with the shape of the real tail support, and the false tail support is made of light composite materials.
By adopting the technical scheme, the false tail support and the real tail support are consistent in appearance, and the false tail support is made of the light composite material, so that the required test state and the trim adjustment of the wind tunnel model posture are convenient to guarantee, and the test error is reduced.
The utility model discloses further set up to: the false tail support force-measuring balance in the cavity of the wind tunnel model is fixedly connected with the wind tunnel model, and the measuring end of the false tail support force-measuring balance is connected with the false tail support.
By adopting the technical scheme, the false tail support force-measuring balance in the cavity of the wind tunnel model is fixedly connected with the wind tunnel model, and the measuring end of the false tail support force-measuring balance is connected with the false tail support, so that the false tail support force-measuring balance can measure the pneumatic load acting on the false tail support conveniently.
To sum up, the utility model discloses following beneficial effect has: the method comprises the following steps that 2+1 wind tunnel balances (a left measuring balance and a right measuring balance and a 1 false tail supporting force measuring balance) are adopted to form a measuring system of a wind tunnel model, when the wind tunnel model is in a state without false tail support, the pneumatic load of the wind tunnel model is measured together in a wing tip supporting mode through the left measuring balance and the right measuring balance, and the pneumatic load located in a moment reference center of the wind tunnel model is obtained through force system translation according to the pneumatic load measured respectively; when the wind tunnel model is in a state with a false tail support, all pneumatic loads of the wind tunnel model and the false tail support are obtained by measuring in a wingtip support mode through 2 measuring balances, and 1 false tail support force measuring balance in a cavity of the wind tunnel model measures the pneumatic load acting on the false tail support in a cantilever support mode; the method comprises the steps that the pneumatic load of a wind tunnel model with a false tail support state can be obtained through translation conversion of a pneumatic load force system measured by 2 measuring balance and 1 false tail support force measuring balance, and then the tail support interference correction quantity of the wind tunnel model is obtained through comparing the pneumatic load difference of the wind tunnel model without the false tail support state and the wind tunnel model with the false tail support state; the device can be used for correcting the wind tunnel model tail support interference test, and can accurately simulate the tail appearance and the flow of a flow field of the wind tunnel model when the wind tunnel model is not in a false tail support state; when the wind tunnel model is provided with the false tail support structure, the false tail support is fixed on the machine body, the pneumatic load acting on the false tail support is small, the false tail support is not easy to contact with the wind tunnel model, the pressure in the cavity of the wind tunnel model is stable, and the fluctuation amplitude is small; meanwhile, the device is simple to realize and easy to operate.
Drawings
Fig. 1 is a schematic view of a wing tip support device according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a wind tunnel model without a false tail support and a wingtip support device in an embodiment of the present invention;
fig. 3 is a schematic structural diagram of a wind tunnel model with a false tail support and a wing tip support device in an embodiment of the present invention;
fig. 4 is a schematic diagram of mass balance and attitude balancing of a wind tunnel model in an embodiment of the present invention.
In the figure: 1. a double-support; 2. a strut; 3. a balance wing connecting cover; 4. an angle of attack sensor cover; 5. a strut fairing; 6. a force measuring balance; 7. a wind tunnel model; 8. the wing tip supports the fairing; 9. supporting a false tail; 10. the false tail supports a force measuring balance; 11. mass tuning blocks are aggregated.
Detailed Description
The present invention will be described in further detail with reference to the accompanying fig. 1-4.
Example (b): a wind tunnel model 7 supporting interference force measurement test structure device is shown in figures 1 to 4 and comprises a wing tip supporting device structure and a wind tunnel model 7, wherein the wing tip supporting device structure comprises a double-supporting support 1 with two supporting ends, and the two supporting ends of the double-supporting support 1 are both connected with a support rod 2; the front end of the supporting rod 2 is provided with a force measuring balance 6; the force measuring balance 6 is provided with a balance wing connecting cover 3 and an attack angle sensor cover 4 close to the balance wing connecting cover 3; the end part of the strut 2 far away from the double supporting seats is provided with a strut 2 fairing; the left wing and the right wing of the wind tunnel model 7 are connected with the balance wing connecting cover 3 through the corresponding wing tip supporting fairings 8; a false tail support force measuring balance 10 is arranged in a cavity inside the wind tunnel model 7; a false tail support 9 is supported by a false tail support force measuring balance 10 in a cantilever way; a centralized mass adjusting block 11 is arranged in the cavity of the wind tunnel model 7. A load cell (not shown in the figure) is arranged in the balance wing connecting cover 3. An angle of attack sensor (not shown) is mounted in the angle of attack sensor cover 4.
In this embodiment, wiring grooves (not shown in the figure) are provided inside the left and right wings of the wind tunnel model 7, the double-support 1 and the strut 2 (two, which are arranged in bilateral symmetry) for the lines of the sensors at the first stage of the lines of the load cell balance 6 and the pseudo-tail support load cell balance 10 to pass through. When a wind tunnel force test is carried out, a measuring system of a wind tunnel model 7 is formed by 2+1 wind tunnel balances (a left measuring balance and a right measuring balance and a 1 false tail supporting force measuring balance 10), when the wind tunnel model 7 is in a state without a false tail support 9, the pneumatic load of the wind tunnel model 7 is measured jointly in a wing tip supporting mode through the left measuring balance and the right measuring balance, and the pneumatic load located in a moment reference center of the wind tunnel model 7 is obtained through force system translation according to the pneumatic load measured respectively. When the wind tunnel model 7 is in a state with the false tail support 9, all the aerodynamic loads of the wind tunnel model 7 and the false tail support 9 are obtained through measurement of 2 measuring balances in a wingtip support mode, and the aerodynamic loads acting on the false tail support 9 are measured through measurement of 1 false tail support force measuring balance 10 in a cantilever support mode, wherein the 1 false tail support force measuring balance is positioned in a cavity of the wind tunnel model 7. The pneumatic load of the wind tunnel model 7 with the state of the false tail support 9 can be obtained by translation conversion of the pneumatic load force system measured by 2 measuring balance platforms and 1 false tail support force measuring balance 10, and then the interference correction quantity of the tail support of the wind tunnel model 7 is obtained by comparing the pneumatic load difference of the wind tunnel model 7 without the state of the false tail support 9 and the state with the false tail support 9.
Because torsional rigidity of the wing of the wind tunnel model 7 is weak, after the pseudo-tail support force-measuring balance 10 and the pseudo-tail support 9 are installed in the cavity of the wind tunnel model 7, the center of the pseudo-tail support 9 is generally inconsistent with the wing tip support center position of the wind tunnel model 7, and torsion of the wing of the wind tunnel model 7 easily causes the wing appearance of the wind tunnel model 7 to change before and after the wind tunnel model 7 is installed with the pseudo-tail support 9, and influences the distribution of aerodynamic force, therefore, mass balancing and attitude balancing need to be carried out on the wind tunnel model 7. The balance weight of the wind tunnel model 7 can be realized by replacing the mass of the concentrated mass adjusting block 11, and the attitude balancing of the wind tunnel model 7 is realized by adjusting the center of the concentrated mass adjusting block 11 relative to the wing tip supporting position of the wind tunnel model 7. The attitude adjustment of the wind tunnel model 7 based on the lumped mass adjusting blocks 11 is actually carried out by processing and manufacturing the false tail support 9 by using a light composite material in order to reduce the weight of the lumped mass adjusting blocks 11. For a wind tunnel model 7 with or without a false tail support 9, a false tail support load cell balance 10 may be held in the wind tunnel model 7.
The device can be used for correcting the tail support interference test of the wind tunnel model 7, and can accurately simulate the tail appearance and the flow of a flow field of the wind tunnel model 7 when the wind tunnel model 7 is in a state without the false tail support 9. When the wind tunnel model 7 is provided with the false tail support 9, the false tail support 9 is fixed on the machine body, the pneumatic load acting on the false tail support 9 is small, the contact with the wind tunnel model 7 is not easy to occur, the pressure in the cavity of the wind tunnel model 7 is stable, and the fluctuation range is small. Meanwhile, the device is simple to realize and easy to operate.
The number of the force-measuring balances 6 is 2, the number of the false tail supporting force-measuring balances 10 is 1, and the force-measuring balances 6 and the false tail supporting force-measuring balances 10 form a force-measuring system of the wind tunnel model 7.
In this embodiment, 2 measurement balance and 1 false tail support 9 measurement balance are used to form a force measurement system of the wind tunnel model 7, so as to measure the pneumatic load of the wind tunnel model.
The number of the attack angle sensors is 3, and the 3 attack angle sensors respectively and correspondingly measure 2 measurement days and the space pose of the false tail support force-measuring balance 10.
In this embodiment, the attitude for measuring the load cell balance 6 and the pseudo-tail supported load cell balance 10 is used for processing the wind tunnel test data by the angle of attack sensor.
The false tail support 9 is in accordance with the shape of the real tail support, and the false tail support 9 is made of light composite material.
In this embodiment, the shape of the false tail support 9 is the same as that of the real tail support, and the false tail support 9 is made of a light composite material, so that the attitude of the wind tunnel model 7 can be adjusted conveniently.
The pseudo-tail support force-measuring balance 10 in the cavity of the wind tunnel model 7 is fixedly connected with the wind tunnel model 7, and the measuring end of the pseudo-tail support force-measuring balance 10 is connected with the pseudo-tail support 9.
In this embodiment, the pseudo-tail support force-measuring balance 10 in the cavity of the wind tunnel model 7 is fixedly connected with the wind tunnel model 7, and the measuring end of the pseudo-tail support force-measuring balance 10 is connected with the pseudo-tail support 9, so that the pseudo-tail support 9 can measure the pneumatic load acting on the pseudo-tail support 9 by the balance.
The working principle is as follows: when a wind tunnel force test is carried out, a measuring system of a wind tunnel model 7 is formed by 2+1 wind tunnel balances (a left measuring balance and a right measuring balance and a 1 false tail supporting force measuring balance 10), when the wind tunnel model 7 is in a state without a false tail support 9, the pneumatic load of the wind tunnel model 7 is measured jointly in a wing tip supporting mode through the left measuring balance and the right measuring balance 2, and the pneumatic load located in a moment reference center of the wind tunnel model 7 is obtained through force system translation according to the measured pneumatic load. When the wind tunnel model 7 is in a state with the false tail support 9, all the aerodynamic loads of the wind tunnel model 7 and the false tail support 9 are obtained through measurement of 2 measuring balances in a wingtip support mode, and the aerodynamic loads acting on the false tail support 9 are measured through measurement of 1 false tail support force measuring balance 10 in a cantilever support mode, wherein the 1 false tail support force measuring balance is positioned in a cavity of the wind tunnel model 7. The pneumatic load of the wind tunnel model 7 with the state of the false tail support 9 can be obtained through translation conversion of the pneumatic load force system measured by 2 measuring balance platforms and 1 false tail support force measuring balance 10, and then the interference correction quantity of the wind tunnel model 7 tail support is obtained by comparing the pneumatic load difference of the wind tunnel model 7 without the state of the false tail support 9 and the state with the false tail support 9. The device can be used for correcting the tail support interference test of the wind tunnel model 7, and can accurately simulate the tail appearance and the flow of a flow field of the wind tunnel model 7 when the wind tunnel model 7 is in a state without the false tail support 9. When the wind tunnel model 7 is provided with the false tail support 9, the false tail support 9 is fixed on the machine body, the pneumatic load acting on the false tail support 9 is small, the contact with the wind tunnel model 7 is not easy to occur, the pressure in the cavity of the wind tunnel model 7 is stable, and the fluctuation range is small. Meanwhile, the device is simple to realize and easy to operate.
The present embodiment is only for explaining the present invention, and it is not limited to the present invention, and those skilled in the art can make modifications to the present embodiment without inventive contribution as required after reading the present specification, but all of them are protected by patent laws within the scope of the claims of the present invention.
Claims (5)
1. The utility model provides a wind-tunnel model supports interference dynamometry test constructional device, includes wingtip strutting arrangement structure and wind-tunnel model (7), characterized by: the wing tip supporting device structure comprises a double-supporting support (1) with two supporting ends, wherein the two supporting ends of the double-supporting support (1) are connected with supporting rods (2); the front end of the supporting rod (2) is provided with a force measuring balance (6); the force measuring balance (6) is provided with a balance wing connecting cover (3) and an attack angle sensor cover (4) close to the balance wing connecting cover (3); the end part of the support rod (2) far away from the double supporting seats is provided with a support rod (2) fairing; the left wing and the right wing of the wind tunnel model (7) are connected with the balance wing connecting cover (3) through the corresponding wing tip supporting fairing (8); a false tail support force-measuring balance (10) is arranged in a cavity in the wind tunnel model (7); a pseudo-tail support (9) is supported by a cantilever of the pseudo-tail support force-measuring balance (10); a centralized mass adjusting block (11) is arranged in the cavity of the wind tunnel model (7); a pressure sensor is arranged in the balance wing connecting cover (3); an attack angle sensor is arranged in the attack angle sensor cover (4).
2. The wind tunnel model supporting interference force measurement test structure device according to claim 1, wherein: the number of the force measuring balances (6) is 2, the number of the false tail supporting force measuring balances (10) is 1, and the force measuring balances (6) and the false tail supporting force measuring balances (10) form a force measuring system of the wind tunnel model (7).
3. The wind tunnel model supporting interference force measurement test structure device according to claim 2, wherein: the number of the attack angle sensors is 3, and the 3 attack angle sensors respectively and correspondingly measure the space poses of the 2 measurement heaven levels and the false tail support force-measuring balance (10).
4. The wind tunnel model supporting interference force measurement test structure device according to claim 1, wherein: the false tail support (9) is consistent with the shape of the real tail support, and the false tail support (9) is made of light composite materials.
5. The wind tunnel model supporting interference force measurement test structure device according to claim 1, wherein: the false tail support force-measuring balance (10) in the cavity of the wind tunnel model (7) is fixedly connected with the wind tunnel model (7), and the measuring end of the false tail support force-measuring balance (10) is connected with the false tail support (9).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021044017.4U CN212658412U (en) | 2020-06-09 | 2020-06-09 | Wind tunnel model supports interference force measurement test constructional device |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202021044017.4U CN212658412U (en) | 2020-06-09 | 2020-06-09 | Wind tunnel model supports interference force measurement test constructional device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111638033A (en) * | 2020-06-09 | 2020-09-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel model supports interference force measurement test constructional device |
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2020
- 2020-06-09 CN CN202021044017.4U patent/CN212658412U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111638033A (en) * | 2020-06-09 | 2020-09-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel model supports interference force measurement test constructional device |
| CN111638033B (en) * | 2020-06-09 | 2024-11-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel model support interference force measurement test structure device |
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