CN113295367B - Electromagnetic balance device for high-precision measurement of wind tunnel test model resistance - Google Patents
Electromagnetic balance device for high-precision measurement of wind tunnel test model resistance Download PDFInfo
- Publication number
- CN113295367B CN113295367B CN202110473396.1A CN202110473396A CN113295367B CN 113295367 B CN113295367 B CN 113295367B CN 202110473396 A CN202110473396 A CN 202110473396A CN 113295367 B CN113295367 B CN 113295367B
- Authority
- CN
- China
- Prior art keywords
- resistance
- shell
- wind tunnel
- electromagnetic balance
- suspension assembly
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
- G01M9/04—Details
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
- G01M9/062—Wind tunnel balances; Holding devices combined with measuring arrangements
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses an electromagnetic balance device for high-precision measurement of wind tunnel test model resistance, which aims to solve the technical problems of low measurement precision caused by insufficient resolution and large nonlinear interference when a traditional internal strain balance is used for measuring the wind tunnel aircraft model resistance. The device comprises a wind tunnel aircraft model, a five-degree-of-freedom suppression device, a transfer flange, a resistance electromagnetic balance and a tail strut; the shell of the five-degree-of-freedom suppression device is connected with the first shell of the resistance electromagnetic balance through the adapter flange, the inner shaft of the five-degree-of-freedom suppression device is connected with the supporting shaft of the resistance electromagnetic balance, the wind tunnel aircraft model is installed on the shell, and finally the wind tunnel aircraft model is installed on the tail support rod through the supporting shaft of the electromagnetic balance to form the whole measuring device; during wind tunnel test, the aerodynamic load lift force Y, the pitching moment Mz, the lateral force Z, the yawing moment My and the rolling moment Mx of the wind tunnel aircraft model are inhibited by the five-degree-of-freedom inhibiting device, only the resistance X load is transmitted to the resistance electromagnetic balance without distortion, and then high-precision isolated measurement of the resistance is realized.
Description
Technical Field
The invention relates to a wind tunnel test force measuring device, in particular to an electromagnetic balance device for measuring the resistance of a wind tunnel test model with high precision, and belongs to the technical field of test aerodynamic measurement.
Background
With the continuous development of aerospace technology in China, the development of novel equipment types such as bullets, arrows, airplanes and the like is more and more diversified. The design of a novel aircraft often means a great innovation of the aerodynamic characteristics of the aircraft, and generally also puts more rigorous requirements on the field of wind tunnel aerodynamic test measurement, such as: the overall design has extremely high precision measurement requirements on certain key pneumatic parameters, high precision measurement requirements under the condition of strong mismatch of pneumatic loads and the like. Taking aircraft resistance measurement as an example, for strategic tactical missiles, airplanes and the like which pay more attention to the aerodynamic shape of resistance, in order to improve the range of voyage or strike, drag reduction design is carried out in the development process, but because the lift force/moment of the aircraft is not matched with the resistance, the difficulty of high-precision measurement of the resistance and the wind tunnel test for verifying the drag reduction is greatly improved. In addition, the current domestic and foreign wind tunnel force measurement tests mostly adopt an internal strain balance technology, and for a rod type strain balance, the resistance is the load component which is most difficult to measure, the main reason is that on one hand, the resistance is limited by the size of an inner cavity of a wind tunnel model, the diameter size of the balance is smaller relative to the length size, and in order to ensure a wider measuring range and higher sensitivity output, the contradiction between rigidity and sensitivity needs to be strictly coordinated; on the other hand, because the characteristics of the resistance load and the objective requirements of the setting of the measuring element are limited by the inherent measuring mechanism of the strain balance, the strain balance cannot be decoupled thoroughly in structural design and measurement, so that the loads of all components cannot be matched randomly, and when the balance deforms under the loading condition, all the components interfere with the resistance unit to different degrees and are mostly nonlinear, and the measuring difficulty of the resistance is increased.
Aiming at wind tunnel test of aircraft resistance measurement, most of domestic and foreign aerodynamic test mechanisms adopt a test means based on a strain balance technology, and the wind tunnel test mainly comprises two types: 1) the high-precision six-component strain balance measuring technology comprises the following steps: the resistance measurement precision is improved by optimizing and designing the special high-precision resistance measurement balance. As mentioned above, the design core of the strain balance is to obtain the strain/deformation ratio as high as possible through reasonable structure design, machining, bridge design and the like, that is, on the premise that the rigidity of the balance is sufficiently large, the measurement resolution of each component is as high as possible, but the two are contradictory, and the compromise result is that the theoretically optimal design cannot be obtained. The strain balance is limited by an inherent measurement mechanism, cannot be completely decoupled structurally, and particularly has low decoupling degree for resistance components, so that interference errors can be caused, and the measurement accuracy cannot be substantially improved. 2) The wind tunnel test isolation measurement technology of the aircraft resistance comprises the following steps: the resistance of the aircraft is measured in an isolated way by adopting a special high-sensitivity strain balance by restraining the degrees of freedom of the aircraft in other five directions except the resistance. On one hand, the balance is in an over-constrained connection state, and the internal stress of the system can generate interference errors on the balance measurement, and even cause measurement failure in severe cases; on the other hand, other aerodynamic load information not filtered by the suppression mechanism is still transmitted to the balance, and then interference is generated. In addition, the high-sensitivity strain balance has poor adaptability and universality to aerodynamic loads, and has higher requirements on calibration of the balance and consistency of the use environment.
In conclusion, the strain balance technology has gradually presented the difficulty in meeting the requirements of developing advanced models in the aspect of improving the accuracy of measuring the resistance of the wind tunnel test model, and becomes a technical bottleneck in developing and pre-developing models.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the defects in the prior art are overcome, the isolated resistance measuring device based on the electromagnetic balance is provided for the high-precision measurement problem of the wind tunnel test aircraft model resistance, the technical problems that the traditional internal strain balance is insufficient in resolution and large in nonlinear interference when used for resistance measurement, so that the measurement precision is low are solved, and the high-precision measurement of the aircraft model resistance is realized.
The technical solution of the invention is as follows:
an electromagnetic balance device for measuring the resistance of a wind tunnel test model with high precision comprises: the device comprises a resistance electromagnetic balance, a five-degree-of-freedom suppression device, a wind tunnel aircraft model, a transfer flange and a tail strut;
the resistance electromagnetic balance comprises a first magnetic suspension assembly, a second magnetic suspension assembly, a resistance disc, a support shaft, a first shell, a second shell, a third shell, a displacement sensor, a silicon steel sheet group, a first limit nut, a second limit nut, an electric control system and a current measuring assembly; the resistance disc is arranged on the second shell and is axially positioned between the first magnetic suspension assembly and the second magnetic suspension assembly to jointly form a resistance measuring assembly, and the silicon steel sheet group is also arranged on the second shell and is axially positioned at the same position as the displacement sensor; when the resistance electromagnetic balance works, the electric control system controls the resistance measurement assembly to realize that the balance shell is axially suspended, after the resistance electromagnetic balance is loaded, the displacement sensor measures the axial displacement change of the balance shell, the electric control system realizes displacement return to zero by changing the control currents of the first magnetic suspension assembly and the second magnetic suspension assembly, then the current measurement assembly measures the current change of the system, and further the real-time resistance pneumatic load is obtained according to the current-resistance mapping relation;
the five-degree-of-freedom restraining device comprises a shell, an inner shaft and a restraining device, wherein the shell is connected with the inner shaft through the restraining device, so that the restraining of other five degrees of freedom except the resistance direction can be realized; the shell is connected with a first shell of the resistance electromagnetic balance through a transfer flange, and the inner shaft is connected with a supporting shaft of the resistance electromagnetic balance; the wind tunnel aircraft model is arranged on the shell, and finally the whole measuring device is arranged on the tail support rod through a support shaft of the electromagnetic balance; during a wind tunnel test, the pneumatic load of the wind tunnel aircraft model is transmitted to the resistance electromagnetic balance through the five-degree-of-freedom restraining device only without distortion, and then the high-precision measurement of the resistance is realized.
Furthermore, the first magnetic suspension assembly comprises an annular seat, a fixing ring, a magnetic core and windings, the annular seat is of an annular structure, the magnetic core is composed of N U-shaped silicon steel sheets and is divided into four parts which are arranged at equal angular intervals along the circumferential direction of the annular seat, the magnetic core is embedded into the annular seat and is fastened through the fixing ring to form a whole during installation, and the windings are uniformly wound in the U-shaped cavity of the magnetic core in the axial direction; the second magnetic suspension assembly and the first magnetic suspension assembly have the same composition and structure, and are axially and symmetrically arranged around the resistance disc.
Furthermore, the U-shaped silicon steel sheet is of a fan-shaped structure along the thickness direction, and the angle r of the U-shaped silicon steel sheet along the circumferential direction of the balance is 1-2 degrees.
Further, the resistance disc includes annular disc, first rectangle silicon steel sheet group and second rectangle silicon steel sheet group, the annular disc is the loop configuration, first rectangle silicon steel sheet group comprises a N rectangle silicon steel sheet, divide into the same four bibliographic categories and follow annular disc along axial one side along the equal angular interval embedding annular disc of annular disc circumference, second rectangle silicon steel sheet group has the same constitution with first rectangle silicon steel sheet group, follows annular disc circumference equal angular interval embedding annular disc along axial opposite side.
Furthermore, the rectangular silicon steel sheet is of a fan-shaped structure along the thickness direction, and the angle of the rectangular silicon steel sheet along the circumferential direction of the balance is 1-2 degrees.
Furthermore, the U-shaped silicon steel sheets of the first magnetic suspension assembly and the second magnetic suspension assembly and the rectangular silicon steel sheets of the resistance disc are arranged at the same relative positions along the circumference of the balance.
Further, the annular seat, the fixing ring and the annular disk are made of non-magnetic materials.
Further, the axial gap g between the first magnetic suspension assembly and the resistance disc and the axial gap g between the second magnetic suspension assembly and the resistance disc are 0.3-0.4 mm; an axial gap between the first limit nut and the first shell and an axial gap t between the second limit nut and the third shell are (g-0.1) mm; and a radial single-side gap h between the displacement sensor and the silicon steel sheet group is 0.5 mm.
Further, the electronic control system comprises a displacement measurement assembly, a signal amplifier and a controller.
Further, the restraining device is a mechanical linear ball spline or an electromagnetic five-degree-of-freedom restrainer. Compared with the prior art, the invention has the beneficial effects that:
(1) according to the electromagnetic balance device for high-precision measurement of the wind tunnel test model resistance, the measurement resolution of the resistance electromagnetic balance is high; the problem of interference of the five-freedom-degree restraining device on the installation internal stress of the balance is thoroughly solved by utilizing the non-contact advantage of electromagnetic suspension, and high-fidelity transmission and measurement of isolated measured loads are realized.
(2) According to the electromagnetic balance device for high-precision measurement of the wind tunnel test model resistance, the electromagnetic suspension assembly and the resistance disc of the resistance electromagnetic balance are in the silicon steel lamination mode, the nonlinear influence of magnetic hysteresis, eddy current and the like on an electromagnet is reduced, the force measurement linearity is high, the balance calibration difficulty can be reduced, and the measurement precision is improved.
(3) According to the electromagnetic balance device for high-precision measurement of the wind tunnel test model resistance, the resistance electromagnetic balance can realize self-adaptive matching of measuring ranges on the premise of not losing measurement resolution by adjusting the system bias current, the universality is high, modular development can be realized, design iteration is reduced, and the cost is saved.
(4) The electromagnetic balance device for high-precision measurement of the wind tunnel test model resistance provided by the invention has the advantages of high system rigidity and high frequency response, and can be widely applied to unsteady force measurement tests.
Drawings
FIG. 1 is a schematic diagram of an electromagnetic balance device for high-precision measurement of the resistance of a wind tunnel test model according to the invention;
FIG. 2 is a schematic view of an electromagnetic balance apparatus of the present invention;
FIG. 3 is a schematic diagram of the magnetic levitation assembly of the present invention;
FIG. 4 is a schematic diagram of the resistance disc of the present invention;
FIG. 5 is a view in the direction P of FIG. 3 and a view in the direction Q of FIG. 4;
Detailed Description
The following describes the embodiments of the present invention in detail with reference to the accompanying drawings 1 to 5.
The invention discloses an electromagnetic force measuring device for a wind tunnel test, which aims to solve the technical problems of low measurement precision caused by insufficient resolution and large nonlinear interference when a traditional internal strain balance is used for measuring the resistance of a wind tunnel aircraft model, and realize high-precision measurement of the resistance. Specifically, an electromagnetic balance device for high-precision measurement of the resistance of a wind tunnel test model is provided, as shown in fig. 1-2, and comprises a wind tunnel aircraft model 1, a five-degree-of-freedom suppression device, a transfer flange 3, a resistance electromagnetic balance and a tail strut 5;
the five-degree-of-freedom restraining device can restrain five-degree-of-freedom aerodynamic loads, namely lift force Y, pitching moment Mz, side force Z, yawing moment My and rolling moment Mx, except in the direction of resistance X, and comprises a shell 201, an inner shaft 202 and a restraining device 203, wherein the shell 201 is connected with the inner shaft 202 through the restraining device 203, and the restraining device 203 is a mechanical linear ball spline or an electromagnetic five-degree-of-freedom restraint with high rigidity;
the resistance electromagnetic balance comprises a first magnetic suspension assembly, a second magnetic suspension assembly, a resistance disc, a support shaft 401, a first shell 402, a second shell 415, a third shell 418, a displacement sensor 416, a silicon steel sheet group 417, a first limit nut 403, a second limit nut 419, an electric control system and a current measuring assembly 423, wherein the electric control system comprises a displacement measuring assembly 420, a signal amplifier 421 and a controller 422.
The first magnetic suspension assembly, the second magnetic suspension assembly and the displacement sensor 416 are sequentially arranged on the supporting shaft 401, the first shell 402, the second shell 415 and the third shell 418 are sequentially connected to form a balance shell, and the resistance disc is arranged on the second shell 415 and is axially positioned between the first magnetic suspension assembly and the second magnetic suspension assembly to jointly form a resistance measuring assembly based on the differential electromagnet principle and used for bearing, controlling and measuring resistance; a set of silicon steel sheets 417 is also mounted on the second housing 415 and is located axially in the same position as the displacement sensor 416 for axial displacement measurement of the balance housing;
the working principle of the resistance electromagnetic balance is as follows: when the pneumatic load testing device works, the electric control system controls the resistance measuring assembly to realize that the balance shell is axially suspended, after the pneumatic load is axially loaded, the displacement sensor 416 measures the axial displacement change of the balance shell, the electric control system realizes the displacement return to zero by changing the control currents of the first magnetic suspension assembly and the second magnetic suspension assembly, the current measuring assembly 423 measures the current change of the system, and then the real-time resistance pneumatic load is obtained according to the current-resistance mapping relation F (F) (i);
the shell 201 of the five-degree-of-freedom suppression device is connected with a first shell 402 of a resistance electromagnetic balance through an adapter flange 3, an inner shaft 202 is connected with a support shaft 401 of the resistance electromagnetic balance, a wind tunnel aircraft model 1 is installed on the shell 201, and finally the shell is installed on a tail support rod 5 through the support shaft 401 of the electromagnetic balance to form a whole measuring device; during wind tunnel test, the aerodynamic load lift force Y, the pitching moment Mz, the lateral force Z, the yawing moment My and the rolling moment Mx of the wind tunnel aircraft model 1 are inhibited by the five-degree-of-freedom inhibiting device, only the resistance X load is transmitted to the resistance electromagnetic balance without distortion, and then high-precision measurement of the resistance is realized.
In this embodiment, with reference to fig. 2 and 3, the first magnetic suspension assembly includes an annular base 404, a fixing ring 405, a magnetic core 406 and windings 407, the annular base 404 is of an annular structure, the magnetic core 406 is composed of N U-shaped silicon steel sheets, and is divided into four identical parts that are arranged at equal angular intervals along the circumferential direction of the annular base 404, when the magnetic core 406 is installed, the magnetic core 406 is embedded into the annular base 404 and is fastened by the fixing ring 405 to form a whole, and the windings 407 are uniformly wound around the axial direction in the U-shaped cavity of the magnetic core 406; the second magnetic suspension assembly has the same composition and structure as the first magnetic suspension assembly, and the second magnetic suspension assembly and the first magnetic suspension assembly are axially symmetrically arranged around the resistance disc.
In this embodiment, with reference to fig. 2 and 4, the resistance disc includes an annular disc 409, a first rectangular silicon steel sheet group 408 and a second rectangular silicon steel sheet group 410, the annular disc 409 is of an annular structure, the first rectangular silicon steel sheet group 408 is composed of N rectangular silicon steel sheets, and is divided into four identical parts, which are embedded into one axial side of the annular disc 409 at equal angular intervals along the circumferential direction of the annular disc 409, and the second rectangular silicon steel sheet group 410 and the first rectangular silicon steel sheet group 408 have the same composition, and are embedded into the other axial side of the annular disc 409 at equal angular intervals along the circumferential direction of the annular disc 409.
In this embodiment, preferably, as shown in fig. 5, the U-shaped silicon steel sheet and the rectangular silicon steel sheet are both fan-shaped structures in the thickness direction, and the angle r is 1-2 ° in the circumferential direction of the balance; the relative positions of the U-shaped silicon steel sheets of the first magnetic suspension assembly and the second magnetic suspension assembly and the rectangular silicon steel sheets of the resistance disc are the same along the circumferential direction of the balance.
The electromagnetic suspension assembly and the resistance disc both adopt a silicon steel lamination mode, so that the nonlinear influence of magnetic hysteresis, eddy current and the like on the electromagnet can be reduced, and the measurement linearity is improved.
In this embodiment, the annular seat 404, the retaining ring 405, and the annular disk 409 are preferably made of non-magnetic materials.
In the present embodiment, preferably, as shown in fig. 2, the axial gap g between the first magnetic suspension assembly and the resistance disc and the axial gap g between the second magnetic suspension assembly and the resistance disc are 0.3mm to 0.4 mm; the axial clearance between the first limit nut 403 and the first housing 402 and the axial clearance t between the second limit nut 419 and the third housing 418 are (g-0.1) mm; the radial single-side gap h between the displacement sensor 416 and the silicon steel sheet group 417 is 0.5 mm; the distances are obtained through detailed theoretical calculation and finite element analysis so as to realize suspension measurement and limit protection of the resistance electromagnetic balance.
Those skilled in the art will appreciate that the invention may be practiced without these specific details. The above embodiments are exemplary, and the present invention can be extended to any specific and any novel combination disclosed in the present specification within the scope referred to in the claims, which also fall within the technical scope of the present invention.
The invention has not been described in detail in part of the common general knowledge of those skilled in the art.
Claims (10)
1. The utility model provides a wind tunnel test model resistance high accuracy measurement's electromagnetic balance device which characterized in that includes: the device comprises a resistance electromagnetic balance, a five-degree-of-freedom suppression device, a wind tunnel aircraft model (1), a transfer flange (3) and a tail support rod (5);
the resistance electromagnetic balance comprises a first magnetic suspension assembly, a second magnetic suspension assembly, a resistance disc, a supporting shaft (401), a first shell (402), a second shell (415), a third shell (418), a displacement sensor (416), a silicon steel sheet group (417), a first limit nut (403), a second limit nut (419), an electric control system and a current measuring assembly (423);
the resistance measuring device comprises a support shaft (401), a first magnetic suspension assembly, a second magnetic suspension assembly and a displacement sensor (416), wherein the first magnetic suspension assembly, the second magnetic suspension assembly and the displacement sensor (416) are sequentially arranged on the support shaft (401), a first shell (402), a second shell (415) and a third shell (418) are sequentially connected to form a resistance electromagnetic balance shell, a resistance disc is arranged on the second shell (415) and is axially positioned between the first magnetic suspension assembly and the second magnetic suspension assembly, and the first magnetic suspension assembly, the second magnetic suspension assembly, the displacement sensor (416), the electromagnetic balance shell and the resistance disc jointly form a resistance measuring assembly; the silicon steel sheet group (417) is also arranged on the second shell (415) and is positioned at the same position as the displacement sensor (416) along the axial direction; the first limiting nut (403) is axially installed on the outer side of the first shell (402), the second limiting nut (419) is axially installed on the outer side of the third shell (418), and the first limiting nut (403) and the second limiting nut (419) are used for axial limiting of the shell of the resistance electromagnetic balance;
when the resistance electromagnetic balance works, the electric control system controls the resistance measurement assembly to realize that the balance shell is axially suspended, after the resistance electromagnetic balance is loaded, the displacement sensor (416) measures the axial displacement change of the balance shell, the electric control system realizes the displacement return to zero by changing the control currents of the first magnetic suspension assembly and the second magnetic suspension assembly, the current measurement assembly (423) measures the current change, and then the real-time resistance pneumatic load is obtained according to the current-resistance mapping relation;
the five-degree-of-freedom suppression device comprises a shell (201), an inner shaft (202) and a suppression device (203); the shell (201) is connected with the inner shaft (202) through a restraining device (203), and other five degrees of freedom except the resistance direction are restrained; the shell (201) is connected with a first shell (402) of the resistance electromagnetic balance through an adapter flange (3), and the inner shaft (202) is connected with a support shaft (401) of the resistance electromagnetic balance; the wind tunnel aircraft model (1) is installed on the shell (201), and finally the whole measuring device is installed on the tail support rod (5) through a support shaft (401) of the electromagnetic balance; during wind tunnel test, the pneumatic load of the wind tunnel aircraft model (1) is transmitted to the resistance electromagnetic balance through the five-degree-of-freedom restraining device only without distortion, and then high-precision measurement of resistance is achieved.
2. The electromagnetic balance device for high-precision measurement of the resistance of the wind tunnel test model according to claim 1, characterized in that: the first magnetic suspension assembly comprises an annular base (404), a fixed ring (405), a magnetic core (406) and a winding (407); the annular seat (404) is of an annular structure, the magnetic core (406) is divided into four identical parts which are arranged at equal angular intervals along the circumferential direction of the annular seat (404), and the four identical parts of the magnetic core (406) are composed of N U-shaped silicon steel sheets in total; when the winding is installed, the magnetic core (406) is embedded into the annular seat (404) and is fastened by the fixing ring (405) to form a whole, and the winding (407) is uniformly wound around the axial direction in the U-shaped cavity of the magnetic core (406); the second magnetic suspension assembly and the first magnetic suspension assembly have the same composition and structure, and are axially and symmetrically arranged around the resistance disc.
3. The electromagnetic balance device for high-precision measurement of the resistance of the wind tunnel test model according to claim 2, wherein: the U-shaped silicon steel sheet is of a fan-shaped structure along the thickness direction, and the angle r of the U-shaped silicon steel sheet along the circumferential direction of the balance is 1-2 degrees.
4. The electromagnetic balance device for high-precision measurement of the resistance of the wind tunnel test model according to claim 2, wherein: the resistance disc comprises an annular disc (409), a first rectangular silicon steel sheet group (408) and a second rectangular silicon steel sheet group (410); the annular disc (409) is of an annular structure, mounting grooves are formed in the two sides of the annular disc (409) along the axial direction, the first rectangular silicon steel sheet group (408) is composed of N rectangular silicon steel sheets and is divided into four parts which are identical, and the four parts are embedded into the mounting grooves in one side of the annular disc (409) at equal angular intervals along the circumferential direction of the annular disc (409); the second rectangular silicon steel sheet group (410) and the first rectangular silicon steel sheet group (408) have the same composition, and are embedded into the mounting groove in the other side of the annular disc (409) at equal angular intervals along the circumferential direction of the annular disc (409).
5. The electromagnetic balance device for high-precision measurement of the wind tunnel test model resistance according to claim 4, characterized in that: the rectangular silicon steel sheet is of a fan-shaped structure along the thickness direction, and the angle r of the rectangular silicon steel sheet is 1-2 degrees along the circumferential direction of the balance.
6. The electromagnetic balance device for high-precision measurement of the resistance of the wind tunnel test model according to claim 4 or 5, wherein: the U-shaped silicon steel sheets of the first magnetic suspension assembly and the second magnetic suspension assembly and the rectangular silicon steel sheets of the resistance disc are arranged at the same relative positions along the circumferential direction of the balance.
7. The electromagnetic balance device for high-precision measurement of the resistance of the wind tunnel test model according to claim 4 or 5, wherein: the annular seat (404), the fixing ring (405) and the annular disk (409) are made of non-magnetic materials.
8. The electromagnetic balance device for high-precision measurement of the resistance of the wind tunnel test model according to claim 1, characterized in that: axial gaps g between the first magnetic suspension assembly and the resistance disc and between the second magnetic suspension assembly and the resistance disc are 0.3mm-0.4 mm; an axial clearance between the first limit nut (403) and the first housing (402) and an axial clearance t between the second limit nut (419) and the third housing (418) is (g-0.1) mm; and a radial single-side gap h between the displacement sensor (416) and the silicon steel sheet group (417) is 0.5 mm.
9. The electromagnetic balance device for high-precision measurement of the resistance of the wind tunnel test model according to claim 1, characterized in that: the electronic control system comprises a displacement measurement component (420), a signal amplifier (421) and a controller (422).
10. The electromagnetic balance device for high-precision measurement of the resistance of the wind tunnel test model according to claim 1, characterized in that: the restraining device (203) is a mechanical linear ball spline or an electromagnetic five-degree-of-freedom restrainer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110473396.1A CN113295367B (en) | 2021-04-29 | 2021-04-29 | Electromagnetic balance device for high-precision measurement of wind tunnel test model resistance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202110473396.1A CN113295367B (en) | 2021-04-29 | 2021-04-29 | Electromagnetic balance device for high-precision measurement of wind tunnel test model resistance |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN113295367A CN113295367A (en) | 2021-08-24 |
| CN113295367B true CN113295367B (en) | 2022-08-12 |
Family
ID=77320494
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202110473396.1A Active CN113295367B (en) | 2021-04-29 | 2021-04-29 | Electromagnetic balance device for high-precision measurement of wind tunnel test model resistance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN113295367B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113899432B (en) * | 2021-09-30 | 2023-11-21 | 武汉大学 | Magnetic suspension balance and mass measurement method |
| CN114001909B (en) * | 2021-11-09 | 2023-04-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Design method of displacement element for wind tunnel roll dynamic derivative test |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004309357A (en) * | 2003-04-08 | 2004-11-04 | National Aerospace Laboratory Of Japan | Drag calibration method in magnetic suspension and balance system |
| CN104198154A (en) * | 2014-09-18 | 2014-12-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-end force measurement device and double-end measurement method |
| CN108181083A (en) * | 2018-01-16 | 2018-06-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Small-range high lift-drag ratio force balance applied to low density wind tunnel |
| CN110207944A (en) * | 2019-06-26 | 2019-09-06 | 中国航天空气动力技术研究院 | A kind of wind tunnel experiment high-precision resistance measurement method and device |
| CN112362294A (en) * | 2020-11-27 | 2021-02-12 | 中国航天空气动力技术研究院 | Coaxial parallel axial load measuring high-precision wind tunnel force measuring balance |
-
2021
- 2021-04-29 CN CN202110473396.1A patent/CN113295367B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004309357A (en) * | 2003-04-08 | 2004-11-04 | National Aerospace Laboratory Of Japan | Drag calibration method in magnetic suspension and balance system |
| CN104198154A (en) * | 2014-09-18 | 2014-12-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Double-end force measurement device and double-end measurement method |
| CN108181083A (en) * | 2018-01-16 | 2018-06-19 | 中国空气动力研究与发展中心超高速空气动力研究所 | Small-range high lift-drag ratio force balance applied to low density wind tunnel |
| CN110207944A (en) * | 2019-06-26 | 2019-09-06 | 中国航天空气动力技术研究院 | A kind of wind tunnel experiment high-precision resistance measurement method and device |
| CN112362294A (en) * | 2020-11-27 | 2021-02-12 | 中国航天空气动力技术研究院 | Coaxial parallel axial load measuring high-precision wind tunnel force measuring balance |
Non-Patent Citations (2)
| Title |
|---|
| 2.4m×2.4m跨声速风洞虚拟飞行试验天平研制;向光伟 等;《实验流体力学》;20140228;第28卷(第01期);第65-69页 * |
| 基于减小轴向力测量干扰的高精度测力天平研制;闫万方 等;《实验流体力学》;20181231;第32卷(第06期);第61-67页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN113295367A (en) | 2021-08-24 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN113295367B (en) | Electromagnetic balance device for high-precision measurement of wind tunnel test model resistance | |
| US8415947B2 (en) | Method for stress assessment that removes temperature effects and hysteresis on the material property measurements | |
| JP2545365B2 (en) | Torque measuring device | |
| CN108181083B (en) | Small-range high lift-drag ratio force balance applied to low-density wind tunnel | |
| CN105588669B (en) | Axle pin type three-way force cell sensor | |
| CN113375888B (en) | Electromagnetic suspension force measuring device and method for dynamic and static pneumatic load separation measurement | |
| CN101419118B (en) | Support reaction type wind-tunnel balance shafting static calibration method | |
| CN100383488C (en) | Method and sensor for measuring radial and axial displacement of synchronouslly rotation axis | |
| CN111175014B (en) | Balance system and method for accurately measuring rotor wing pneumatic load | |
| CN101858800B (en) | Load cell for detecting supporting force on load-bearing support element | |
| CN107683404B (en) | Method and device for measuring forces or torques by means of at least two spaced-apart magnetic field sensors | |
| CN100554887C (en) | Radial direction magnetic bearing integrated type differential electric inductance sensing device | |
| CN108106812A (en) | A kind of dynamometric system for thrust calibration | |
| CN111238711B (en) | Rotor axial force testing method | |
| CN110207944B (en) | High-precision resistance measuring method and device for wind tunnel experiment | |
| CN112362294B (en) | Coaxial parallel axial load measuring high-precision wind tunnel force measuring balance | |
| CN108507753B (en) | Output signal combination method of three-component optical fiber balance | |
| CN106885662A (en) | Footpath axial composite-rotor Non-contact loader and machine tool chief axis rigidity testing system | |
| CN113567897A (en) | Self-adaptive measuring method of annular TMR array sensor | |
| CN103411733B (en) | A kind of high-speed main shaft electromagnetic type spot dynamic balance device and method | |
| JP2000258109A (en) | Amount-of-displacement measuring instrument | |
| CN110487507A (en) | A kind of five component strain balances for nacelle internal resistance dynamometer check | |
| CN103527644B (en) | A kind of magnet fluid sealing axle of energy Measurement accuracy hot vacuum environment lower angle | |
| CN103527643A (en) | Magnetic fluid sealing shaft with torque measurement | |
| CN114577434B (en) | High-precision six-component balance and method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |