CN115628874A - Hypersonic wind tunnel closed test section model supporting device - Google Patents
Hypersonic wind tunnel closed test section model supporting device Download PDFInfo
- Publication number
- CN115628874A CN115628874A CN202211636043.XA CN202211636043A CN115628874A CN 115628874 A CN115628874 A CN 115628874A CN 202211636043 A CN202211636043 A CN 202211636043A CN 115628874 A CN115628874 A CN 115628874A
- Authority
- CN
- China
- Prior art keywords
- model
- section
- wind tunnel
- model supporting
- hypersonic wind
- 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.)
- Granted
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
-
- 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 belongs to the technical field of hypersonic wind tunnel tests and discloses a model supporting device for a hypersonic wind tunnel closed test section. The model supporting device comprises a cylindrical supporting section fixed on a supporting seat, and the supporting section is fixedly connected behind a hypersonic wind tunnel closed test section; the inner wall of the supporting section is provided with three grooves parallel to the central axis of the supporting section, and the interval between every two adjacent grooves is 120 degrees; the three-fork model support frame is also included, the suspended end of each support arm is respectively provided with a circular arc-shaped support arm sliding plate, and the support arm sliding plates are clamped in the corresponding grooves; a sleeve is arranged in the center of the model supporting frame, the model supporting rod is fixed in the sleeve, and a test model is arranged at the front end of the model supporting rod; the model support frame slides, changes the position of test model, and after test model reached the position that sets up earlier, pack removable cover in the recess, the inner wall of guaranteeing the support section is level and smooth. The model supporting device is simple in structure, high in reliability, strong in adjusting capacity and easy to install.
Description
Technical Field
The invention belongs to the technical field of hypersonic wind tunnel tests, and particularly relates to a model supporting device for a hypersonic wind tunnel closed test section.
Background
The hypersonic wind tunnel is very important aerodynamic ground simulation test equipment in the field of aerospace. The hypersonic wind tunnel test is widely accepted by reliability, safety and economy as one of three technical means for researching the supersonic speed and the hypersonic aerodynamic characteristics.
At present, most of conventional hypersonic wind tunnel test sections adopt an open type, commonly used support modes comprise an abdominal support/back support, a tail support, a bracing wire support and the like, and main structures comprise a base, a support mechanism, a driving and transmission device, a support and the like.
However, for the ledwith tubular closed type hypersonic wind tunnel, the model supporting mode of the open type hypersonic wind tunnel cannot meet the test requirements, and the problems of large model supporting volume, non-compact structure, low reliability and the like are caused.
In order to ensure the authenticity and reliability of the closed hypersonic wind tunnel test data, a hypersonic wind tunnel closed test section model supporting device needs to be developed urgently at present.
Disclosure of Invention
The invention aims to solve the technical problem of providing a hypersonic wind tunnel closed test section model supporting device.
The model supporting device for the closed test section of the hypersonic wind tunnel is characterized by comprising a cylindrical supporting section fixed on a supporting seat, wherein end face flanges are respectively arranged at the front end and the rear end of the supporting section, and the supporting section is fixedly connected behind the closed test section of the hypersonic wind tunnel through a plurality of bolts penetrating through the end face flanges according to the flowing direction of airflow; three grooves parallel to the central axis of the supporting section are circumferentially arranged on the inner wall of the supporting section from a bus at the highest position on the inner wall, the interval between every two adjacent grooves is 120 degrees, the length of each groove is equal to that of the supporting section, and the front end and the rear end of each groove are provided with a limiting fixture block for plugging;
the model support frame is in a three-fork shape, the upper support arm is positioned in the vertical direction, the left support arm and the right support arm are positioned below the upper support arm and are symmetrically distributed in the left and right directions, a circular arc-shaped support arm sliding plate is arranged at the suspended end of each support arm, the support arm sliding plates are clamped in the corresponding grooves, and the model support frame slides back and forth along the central axis of the support section through the support arm sliding plates; a sleeve is arranged at the center of the model supporting frame, the model supporting rod is fixed in the sleeve, the model supporting rod is positioned on the central axis of the supporting section, and a test model is installed at the front end of the model supporting rod;
through the slip model support frame, change the position of test model, after test model reachd the position that sets up in advance in the hypersonic wind tunnel test section, pack removable cover in the recess, ensure that the inner wall of supporting the section levels smoothly.
Furthermore, the model supporting rod is a pipe body, and a central cavity used for protecting and leading out the measurement and control cable is arranged.
Furthermore, a taper hole is formed in the inner cavity of the sleeve, a key groove I is formed in the wall of the taper hole, a conical section matched with the taper hole is arranged on the model supporting rod, and a key groove II corresponding to the key groove I is formed in the wall surface of the conical section; the model bracing piece passes the sleeve from the past to the back, through flat key position sleeve and the model bracing piece that runs through keyway I and keyway II, draws tight fixed sleeve and model bracing piece through the bolt of model bracing piece front end.
Furthermore, the model supporting rod is matched with an extension section, the extension section is in a circular tube shape, the front end of the extension section is provided with front end threads, the rear end of the extension section is provided with rear end threads, the extension section is fixedly connected with the test model through the front end threads, and the extension section is fixedly connected with the model supporting rod through the rear end threads.
Further, the central angle of the arm sliding plate is 20 degrees.
Furthermore, a wire slot is formed in the leeward side of the upper supporting arm.
Furthermore, the movable cover plate comprises an upper support arm cover plate, a left support arm cover plate and a right support arm cover plate, the upper support arm cover plate is clamped in a groove corresponding to the upper support arm, the left support arm cover plate is clamped in a groove corresponding to the left support arm, and the right support arm cover plate is clamped in a groove corresponding to the right support arm; an upper support arm cover plate wire groove is formed in an upper support arm cover plate positioned behind the model support frame, and the upper support arm cover plate wire groove and the wire groove are used for protecting and leading out a measurement and control cable.
Further, the movable cover plate is a series of movable cover plates with step length change.
Furthermore, the limiting clamping block is provided with a countersunk screw hole which is fixed through the countersunk screw.
The hypersonic wind tunnel closed test section model supporting device adopts an end face flange bolt fastening connection mode, and can ensure that the supporting section is stably and reliably fixed, so that the test model is stable and reliable. By adopting the fixing modes of conical surface matching, flat key positioning and bolt tensioning, the accurate positioning and reliable connection between the sleeve and the model supporting rod can be ensured, the model supporting rod is ensured to only have the freedom of movement along the central axis, and the other five degrees of freedom are limited. The triangular support frame can ensure the stability of the support arm by using the stability of the triangle. The measurement and control cable is protected and led out along the way by adopting the hollow model supporting rod, the wire groove and the support arm cover plate wire groove, and the measurement and control cable can be prevented from being damaged by the high-temperature state of the hypersonic wind tunnel test environment. The lengthened section can flexibly adapt to test models with different interfaces, the processing amount is small, and the matching test model assembling work can be completed on a test site conveniently. A series of movable cover plates with variable step lengths can flexibly adapt to the position requirement of the test model, and the position of the test model can be changed conveniently on the test site.
The model supporting device for the closed test section of the hypersonic wind tunnel is suitable for a test environment with high closed flow velocity and small space of the Ludwigshi tubular hypersonic wind tunnel, solves the technical problems of difficult installation of a test model, low position fixing reliability and the like, has the advantages of simple structure, high reliability, strong regulating capability, easy installation and engineering popularization value.
Drawings
FIG. 1 is a schematic structural diagram of a model supporting device for a closed test section of a hypersonic wind tunnel according to the invention;
FIG. 2a is a schematic structural view (front view) of a support frame in the model support device for the hypersonic wind tunnel closed test section of the invention;
FIG. 2b is a schematic structural diagram (side view) of a support frame in the model support device for the hypersonic wind tunnel closed test section according to the invention;
FIG. 3a is a schematic structural view (front view) of a model support rod in the hypersonic wind tunnel closed test section model support device of the invention;
FIG. 3b is a schematic structural diagram (sectional view) of a model support rod in the hypersonic wind tunnel closed test section model support device according to the present invention;
FIG. 4a is a schematic structural diagram (front view) of a flat key in a model supporting device of a hypersonic wind tunnel closed test section according to the invention;
fig. 4b is a schematic diagram (top view) of a flat key structure in the model supporting device of the hypersonic wind tunnel closed test section according to the invention;
fig. 5a is a schematic structural diagram (front view) of an elongated section in the model supporting device for the closed test section of the hypersonic wind tunnel according to the present invention;
fig. 5b is a schematic structural diagram (top view) of an elongated section in the model supporting device for the closed test section of the hypersonic wind tunnel according to the present invention;
FIG. 5c is a schematic structural diagram (cross-sectional view) of an elongated section in the model supporting device for the closed test section of the hypersonic wind tunnel according to the present invention;
FIG. 6a is a schematic structural diagram (front view) of a left arm cover plate in a model supporting device for a hypersonic wind tunnel closed test section according to the present invention;
FIG. 6b is a schematic structural diagram (sectional view) of a left arm cover plate in the hypersonic wind tunnel closed test section model supporting device according to the present invention;
FIG. 7a is a schematic structural diagram (front view) of an upper support cover plate in a hypersonic wind tunnel closed test section model supporting device according to the present invention;
FIG. 7b is a schematic structural diagram (sectional view) of an upper support cover plate in the hypersonic wind tunnel closed test section model supporting device according to the present invention;
FIG. 8a is a schematic structural diagram (front view) of a right arm cover plate in a hypersonic wind tunnel closed test section model supporting device according to the present invention;
FIG. 8b is a schematic structural diagram (sectional view) of a right arm cover plate in the hypersonic wind tunnel closed test section model supporting device according to the present invention;
FIG. 9a is a schematic structural diagram (a perspective view) of a limiting fixture block of a left support arm in the hypersonic wind tunnel closed test section model supporting device according to the present invention;
fig. 9b is a schematic structural diagram (bottom view) of a limiting clamping block of a left support arm in the hypersonic wind tunnel closed test section model supporting device according to the present invention;
FIG. 10a is a schematic diagram (perspective view) of a limiting structure of an upper arm in a model supporting device for a hypersonic wind tunnel closed test section according to the present invention;
FIG. 10b is a schematic diagram (bottom view) of a limiting structure of an upper arm in the model supporting device for the hypersonic wind tunnel closed test section according to the present invention;
FIG. 11a is a schematic diagram (a perspective view) of a limiting structure of a right arm in a model supporting device for a hypersonic wind tunnel closed test section according to the present invention;
fig. 11b is a schematic diagram (bottom view) of a limiting structure of a right support arm in the hypersonic wind tunnel closed test section model supporting device according to the invention.
In the drawings, 1. A support section; 2. a support frame; 3. a model support bar; 4. a sleeve; 5. a limiting clamping block; 6. a removable cover plate; 7. an end face flange; 8. a supporting seat; 9. a lengthening section; 10. a support arm sliding plate 11, an upper support arm; 12. a wire slot; 13. a key groove I; 14. a flat bond; 15. a conical section; 16. a key groove II; 17. front end threads; 18. rear end threads; 19. a left support arm cover plate; 20. an upper arm cover plate; 21. the upper support arm cover plate wire groove; 22. a right arm cover plate; 23. a left support arm; 24. and a right support arm.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
As shown in fig. 1, the model supporting device for the closed test section of the hypersonic wind tunnel in the embodiment includes a cylindrical supporting section 1 fixed on a supporting seat 8, end face flanges 7 are respectively arranged at the front end and the rear end of the supporting section 1, and according to the flowing direction of airflow, the supporting section 1 is fixedly connected to the rear of the closed test section of the hypersonic wind tunnel through a plurality of bolts penetrating through the end face flanges 7; three grooves parallel to the central axis of the support section 1 are circumferentially arranged on the inner wall of the support section 1 from the bus at the highest position on the inner wall, the interval between the adjacent grooves is 120 degrees, the length of the groove is equal to that of the support section 1, and the front end and the rear end of the groove are provided with limiting fixture blocks 5 for plugging;
as shown in fig. 2a and 2b, the three-fork model support frame 2 is further included, the upper support arm 11 is located in the vertical direction, the left support arm 23 and the right support arm 24 are located below the upper support arm 11 and are symmetrically distributed in the left and right directions, the suspended end of each support arm is respectively provided with a circular arc-shaped support arm sliding plate 10, the support arm sliding plates 10 are clamped in corresponding grooves, and the model support frame 2 slides back and forth along the central axis of the support section 1 through the support arm sliding plates 10; a sleeve 4 is arranged at the center of the model supporting frame 2, the model supporting rod 3 is fixed in the sleeve 4, the model supporting rod 3 is positioned on the central axis of the supporting section 1, and a test model is arranged at the front end of the model supporting rod 3;
through sliding the model support frame 2, change the position of test model, after test model reachd the position that sets up in advance in the hypersonic wind tunnel test section, pack removable cover 6 in the recess, ensure that the inner wall of support section 1 levels smoothly.
Further, the model supporting rod 3 is a pipe body and is provided with a central cavity for protecting and leading out a measurement and control cable.
Further, as shown in fig. 3a, 3b, 4a, and 4b, a tapered hole is formed in the inner cavity of the sleeve 4, a key slot i 13 is formed in the hole wall of the tapered hole, a conical section 15 matched with the tapered hole is arranged on the model supporting rod 3, and a key slot ii 16 corresponding to the key slot i 13 is formed in the wall surface of the conical section 15; the model supporting rod 3 passes through the sleeve 4 from front to back, and through the flat key 14 locating sleeve 4 and the model supporting rod 3 of running through keyway I13 and keyway II 16, the bolt through the model supporting rod 3 front end draws tight fixed sleeve 4 and model supporting rod 3.
Further, as shown in fig. 5a, 5b, and 5c, the model supporting rod 3 is matched with an extension section 9, the extension section 9 is in a circular tube shape, a front end thread 17 is arranged at the front end of the extension section 9, a rear end thread 18 is arranged at the rear end of the extension section 9, the extension section 9 and the test model are fixedly connected through the front end thread 17, and the extension section 9 and the model supporting rod 3 are fixedly connected through the rear end thread 18.
Further, the arm sliding plate 10 has a central angle of 20 °.
Furthermore, a line slot 12 is formed on the leeward side of the upper arm 11.
Further, as shown in fig. 6a, fig. 6b, fig. 7a, fig. 7b, fig. 8a, and fig. 8b, the removable cover 6 includes an upper arm cover 20, a left arm cover 19, and a right arm cover 22, the upper arm cover 20 is mounted in a corresponding groove of the upper arm 11, the left arm cover 19 is mounted in a corresponding groove of the left arm 23, and the right arm cover 22 is mounted in a corresponding groove of the right arm 24; an upper support arm cover plate wire casing 21 is arranged on an upper support arm cover plate 20 positioned behind the model support frame 2, and the upper support arm cover plate wire casing 21 and the wire casing 12 are used for protecting and leading out measurement and control cables.
Further, the movable cover plate 6 is a series of movable cover plates 6 with step length changes.
Furthermore, as shown in fig. 9a, 9b, 10a, 10b, 11a, and 11b, the limiting fixture block 5 is provided with a countersunk screw hole, and is fixed by the countersunk screw.
Although embodiments of the invention have been described above, it is not intended to be limited to the specific details set forth in the description or the embodiments, but rather, to one skilled in the art, that all of the features of the invention disclosed, or all of the steps of any method or process disclosed, may be combined in any suitable manner, except for mutually exclusive features and/or steps, without departing from the principles of the invention, and that the invention is not limited to the specific details set forth and illustrated in the drawings described herein.
Claims (9)
1. A model supporting device for a hypersonic wind tunnel closure test section is characterized by comprising a cylindrical supporting section (1) fixed on a supporting seat (8), wherein end face flanges (7) are respectively arranged at the front end and the rear end of the supporting section (1), and the supporting section (1) is fixedly connected behind the hypersonic wind tunnel closure test section through a plurality of bolts penetrating through the end face flanges (7) according to the flowing direction of airflow; three grooves parallel to the central axis of the supporting section (1) are arranged on the inner wall of the supporting section (1) along the circumferential direction of the inner wall from a bus at the highest position on the inner wall, the interval between the adjacent grooves is 120 degrees, the length of the groove is equal to that of the supporting section (1), and the front end and the rear end of the groove are provided with limiting clamping blocks (5) for plugging;
the support structure is characterized by further comprising a three-fork-shaped model support frame (2), wherein the upper support arm (11) is located in the vertical direction, the left support arm (23) and the right support arm (24) are located below the upper support arm (11) and are distributed in bilateral symmetry, a circular arc-shaped support arm sliding plate (10) is arranged at the suspended end of each support arm, the support arm sliding plates (10) are clamped in corresponding grooves, and the model support frame (2) slides back and forth along the central axis of the support section (1) through the support arm sliding plates (10); a sleeve (4) is arranged at the center of the model supporting frame (2), the model supporting rod (3) is fixed in the sleeve (4), the model supporting rod (3) is positioned on the central axis of the supporting section (1), and a test model is installed at the front end of the model supporting rod (3);
through sliding the model support frame (2), change the position of test model, after test model reachd the position that sets up in advance in the hypersonic wind tunnel test section, pack removable cover (6) in the recess, ensure that the inner wall of support section (1) levels smoothly.
2. The hypersonic wind tunnel closed test section model supporting device according to claim 1, wherein the model supporting rod (3) is a pipe body and is provided with a central cavity for protecting and leading out a measurement and control cable.
3. The hypersonic wind tunnel closed test section model supporting device according to claim 1, characterized in that a tapered hole is arranged in the inner cavity of the sleeve (4), a key groove I (13) is formed in the hole wall of the tapered hole, a conical section (15) matched with the tapered hole is arranged on the model supporting rod (3), and a key groove II (16) corresponding to the key groove I (13) is arranged on the wall surface of the conical section (15); the model supporting rod (3) passes through the sleeve (4) from the front to the back, and through a flat key (14) positioning sleeve (4) and the model supporting rod (3) which run through the key groove I (13) and the key groove II (16), the bolt at the front end of the model supporting rod (3) is used for pulling and fastening the sleeve (4) and the model supporting rod (3).
4. The hypersonic wind tunnel closed test section model supporting device according to claim 1, characterized in that the model supporting rod (3) is matched with the lengthened section (9), the lengthened section (9) is in a circular tube shape, a front end thread (17) is arranged at the front end of the lengthened section (9), a rear end thread (18) is arranged at the rear end of the lengthened section (9), the lengthened section (9) and the test model are fixedly connected through the front end thread (17), and the lengthened section (9) and the model supporting rod (3) are fixedly connected through the rear end thread (18).
5. The hypersonic wind tunnel closed test section model supporting device according to claim 1, characterized in that the central angle of the arm sliding plate (10) is 20 degrees.
6. The hypersonic wind tunnel closed test section model supporting device according to claim 1, characterized in that a line groove (12) is formed in the leeward side of the upper supporting arm (11).
7. The hypersonic wind tunnel closed test section model supporting device according to claim 6, characterized in that the movable cover plate (6) comprises an upper arm cover plate (20), a left arm cover plate (19) and a right arm cover plate (22), wherein the upper arm cover plate (20) is clamped in a corresponding groove of the upper arm (11), the left arm cover plate (19) is clamped in a corresponding groove of the left arm (23), and the right arm cover plate (22) is clamped in a corresponding groove of the right arm (24); an upper support arm cover plate wire groove (21) is formed in an upper support arm cover plate (20) located behind the model support frame (2), and the upper support arm cover plate wire groove (21) and the wire groove (12) are used for protecting and leading out a measurement and control cable.
8. The hypersonic wind tunnel closed test section model supporting device according to claim 1, characterized in that the movable cover plates (6) are a series of movable cover plates (6) with step length changes.
9. The hypersonic wind tunnel closed test section model supporting device according to claim 1, wherein a countersunk screw hole is formed in the limiting clamping block (5) and is fixed through the countersunk screw.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211636043.XA CN115628874B (en) | 2022-12-20 | 2022-12-20 | Hypersonic wind tunnel closed test section model supporting device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211636043.XA CN115628874B (en) | 2022-12-20 | 2022-12-20 | Hypersonic wind tunnel closed test section model supporting device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN115628874A true CN115628874A (en) | 2023-01-20 |
| CN115628874B CN115628874B (en) | 2023-03-10 |
Family
ID=84910695
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202211636043.XA Active CN115628874B (en) | 2022-12-20 | 2022-12-20 | Hypersonic wind tunnel closed test section model supporting device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN115628874B (en) |
Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004354290A (en) * | 2003-05-30 | 2004-12-16 | Kawasaki Heavy Ind Ltd | Wind tunnel model support device |
| CN104729826A (en) * | 2015-04-13 | 2015-06-24 | 中国航天空气动力技术研究院 | Supersonic wind tunnel velocity field calibration and measurement total pressure tube vibration suppression device |
| CN204666331U (en) * | 2015-06-08 | 2015-09-23 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of supersonic wind tunnel flutter test model inserts mechanism |
| CN208579903U (en) * | 2018-08-14 | 2019-03-05 | 中国航天空气动力技术研究院 | A kind of high intensity air intake duct wind tunnel test supporting mechanism |
| CN110132528A (en) * | 2019-06-27 | 2019-08-16 | 中国空气动力研究与发展中心高速空气动力研究所 | It is a kind of temporarily to rush formula supersonic wind tunnel sonic boom measurement experimental rig and measuring method |
| CN110595729A (en) * | 2019-09-10 | 2019-12-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-jet flow interference test device for hypersonic wind tunnel surface symmetry model |
| CN111122101A (en) * | 2020-01-08 | 2020-05-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel double-cover static cast cover back-support force measurement test device |
| CN111397838A (en) * | 2020-04-03 | 2020-07-10 | 中国空气动力研究与发展中心超高速空气动力研究所 | Axial symmetry ventilation model aerodynamic force measurement test device and use method |
| CN112284674A (en) * | 2020-10-21 | 2021-01-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Electromagnet hanging and throwing device for hypersonic wind tunnel model free flight test |
| CN114838903A (en) * | 2022-03-28 | 2022-08-02 | 中国航天空气动力技术研究院 | Wind tunnel air inlet channel test support with throttling and injection functions |
-
2022
- 2022-12-20 CN CN202211636043.XA patent/CN115628874B/en active Active
Patent Citations (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004354290A (en) * | 2003-05-30 | 2004-12-16 | Kawasaki Heavy Ind Ltd | Wind tunnel model support device |
| CN104729826A (en) * | 2015-04-13 | 2015-06-24 | 中国航天空气动力技术研究院 | Supersonic wind tunnel velocity field calibration and measurement total pressure tube vibration suppression device |
| CN204666331U (en) * | 2015-06-08 | 2015-09-23 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of supersonic wind tunnel flutter test model inserts mechanism |
| CN208579903U (en) * | 2018-08-14 | 2019-03-05 | 中国航天空气动力技术研究院 | A kind of high intensity air intake duct wind tunnel test supporting mechanism |
| CN110132528A (en) * | 2019-06-27 | 2019-08-16 | 中国空气动力研究与发展中心高速空气动力研究所 | It is a kind of temporarily to rush formula supersonic wind tunnel sonic boom measurement experimental rig and measuring method |
| CN110595729A (en) * | 2019-09-10 | 2019-12-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-jet flow interference test device for hypersonic wind tunnel surface symmetry model |
| CN111122101A (en) * | 2020-01-08 | 2020-05-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Hypersonic wind tunnel double-cover static cast cover back-support force measurement test device |
| CN111397838A (en) * | 2020-04-03 | 2020-07-10 | 中国空气动力研究与发展中心超高速空气动力研究所 | Axial symmetry ventilation model aerodynamic force measurement test device and use method |
| CN112284674A (en) * | 2020-10-21 | 2021-01-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Electromagnet hanging and throwing device for hypersonic wind tunnel model free flight test |
| CN114838903A (en) * | 2022-03-28 | 2022-08-02 | 中国航天空气动力技术研究院 | Wind tunnel air inlet channel test support with throttling and injection functions |
Non-Patent Citations (3)
| Title |
|---|
| 薛全兴: "高超声速飞行器模型送进支撑***设计与研究" * |
| 郝东: "飞行器跨超声速风洞试验模型中尾支撑结构的力学特性研究" * |
| 陈德华;刘大伟;尹陆平;师建元;彭超;饶正周;: "2.4m跨声速风洞多功能支撑***试验技术研究" * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN115628874B (en) | 2023-03-10 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN210884900U (en) | Pile foundation steel reinforcement cage hoisting accessory with locate function | |
| CN109632238B (en) | 90-degree large attack angle device for sub-span supersonic wind tunnel | |
| CN202119434U (en) | Positioning device for cableway pipe of cable-stayed bridge | |
| CN104359649A (en) | Movable correcting device for common hypersonic-velocity wind tunnel | |
| CN115628874B (en) | Hypersonic wind tunnel closed test section model supporting device | |
| WO2022257830A1 (en) | Riser vortex-induced vibration response testing device and method for using same | |
| CN213090703U (en) | Laser centering measuring device | |
| CN111156224A (en) | Support device for vibration test of hydraulic pipeline of aircraft engine | |
| CN108844714B (en) | Variable-curvature bionic non-smooth surface drag reduction testing device and simulation device | |
| CN215726703U (en) | Three-degree-of-freedom motion adjusting device | |
| CN106706949B (en) | A wind cup installing support for tunnel ventilation wind speed or when amount of wind test | |
| CN206905722U (en) | A kind of measurement sensor supporting structure for being used to measure Hydropower Unit guide bearing throw | |
| CN114046142B (en) | Efficient measuring device for tunnel blasting drilling angle | |
| CN113029505B (en) | Wind tunnel flow field mobile measurement device | |
| CN1252442C (en) | Three dimensional collinear measuring ring for drillhole inclination survey and axial deformation | |
| CN109946037B (en) | Blocking moving device for simulating bracket interference quantity change and application | |
| CN220058848U (en) | Integrated device for positioning and anti-collision of embedded wire pipe | |
| CN219200320U (en) | Telescopic device for measuring center of ship shaft rudder system | |
| CN212254194U (en) | Detachable is sounding speed sensor for bridge | |
| CN219367077U (en) | Combined pipeline joint module | |
| CN215491874U (en) | A hang dress plumb line current surveying system for open channel | |
| CN213809220U (en) | Ventilating duct support | |
| CN214640448U (en) | Flange side opening positioning fixture | |
| CN218443591U (en) | Span-middle distribution detection device for bolt holes of flange pipe fittings | |
| CN219589606U (en) | Get type and measure frock |
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 |