CN115165293A - Jaw type hood separation test device for hypersonic wind tunnel - Google Patents
Jaw type hood separation test device for hypersonic wind tunnel Download PDFInfo
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- CN115165293A CN115165293A CN202210770609.1A CN202210770609A CN115165293A CN 115165293 A CN115165293 A CN 115165293A CN 202210770609 A CN202210770609 A CN 202210770609A CN 115165293 A CN115165293 A CN 115165293A
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- 238000001612 separation test Methods 0.000 title claims abstract description 24
- 238000012360 testing method Methods 0.000 claims abstract description 109
- 230000007246 mechanism Effects 0.000 claims abstract description 49
- 238000000926 separation method Methods 0.000 claims abstract description 44
- 238000005259 measurement Methods 0.000 abstract description 7
- 230000009467 reduction Effects 0.000 abstract description 2
- 230000009471 action Effects 0.000 description 2
- 230000008859 change Effects 0.000 description 2
- 238000002474 experimental method Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007405 data analysis Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 239000003973 paint Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 238000009423 ventilation Methods 0.000 description 1
- 238000013022 venting Methods 0.000 description 1
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- 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
-
- 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
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- 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
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- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
A chin rest type hood separation test device for a hypersonic wind tunnel comprises a test piece, a separation mechanism, a chin rest type hood, a separation spring, a locking bolt, a balance, a straight support rod, a middle shaft, a locking nut, a bottom cover and a wind tunnel attack angle mechanism; firstly, a jaw type hood is fixedly connected with a test piece through a separating spring and a separating mechanism, secondly, the test piece is connected with a balance, a straight supporting rod and a middle shaft through a locking bolt, and then, the test piece is connected with a wind tunnel attack angle mechanism through a locking nut; finally, the control line of the antenna and the separating mechanism penetrates through the straight supporting rod and the inner hole of the middle shaft to be communicated with the measurement and control room for remote control. The test device of the invention can not only carry out the separation test of the chin type hood, but also can safely separate the chin type hood, and simultaneously the scale reduction ratio of the chin type hood can be improved to 1:5.
Description
Technical Field
The application relates to the technical field of hood separation experiment devices, in particular to a jaw type hood separation experiment device for a hypersonic wind tunnel.
Background
Generally, the suction type aircraft mainly adopts pneumatic layout forms such as an annular air inlet channel and a chin type air inlet channel, the invention mainly aims at the problem of separation of a nose cover of the suction type aircraft adopting the chin type air inlet channel, namely the height is 20km-30km, and the dynamic pressure is 144kpa-48kpa under the environmental conditions, on one hand, the invention discovers that under the environment of high dynamic pressure, the pressure resistance born by the chin type nose cover is too large, and the safe separation is difficult to realize; on the other hand, the jaw nose cap separation process can have a significant impact on aircraft stability.
At present, the applied clam-type hood separation dynamic test requirement testing mechanism of the hypersonic wind tunnel ventilation model has the following characteristics: 1. the test piece can be arranged on an attack angle mechanism of the wind tunnel, and the change of an attack angle or a sideslip angle within a certain range can be realized; 2. obtaining a dynamic separation process of the clam-type hood, and being capable of safely separating and not colliding with a test piece; 3. in the dynamic separation process of the clam type hood, the dynamic aerodynamic force change of the test piece is measured in real time; 4. under the test condition, the influence of the fastening and releasing mechanism on the dynamic aerodynamic force measurement of the test piece is reduced; 5. under the same test condition, adopting a large-size test piece as much as possible; 6. the test piece requirements are the venting pattern. However, the clam type hood (fairing) separation is usually at middle and high altitude, the height is more than 40Km, the dynamic pressure is less than 36kpa, the aerodynamic force is relatively small, and the test device is not suitable for a jaw type hood separation test.
Disclosure of Invention
The technical problem of the invention is solved: the device overcomes the defects of the prior art, provides a chin type hood separation test device for the hypersonic wind tunnel, and solves the problem that the chin type hood bears overlarge pressure resistance and is difficult to realize safe separation by combining a separation mechanism with separation force.
The technical scheme is as follows:
a chin formula hood separation test device for hypersonic wind tunnel which characterized in that includes: the device comprises a test piece, a separating mechanism, a jaw type hood, a separating spring, a locking bolt, a balance, a straight supporting rod, a middle shaft, a locking nut, a bottom cover and a wind tunnel attack angle mechanism;
the lower jaw type hood is fixedly connected with a test piece through a separation spring and a separation mechanism, the test piece is connected with the balance, the straight supporting rod and the middle shaft through a locking bolt, and then the lower jaw type hood is connected with the wind tunnel attack angle mechanism through a locking nut; finally, the control line of the antenna and the separating mechanism penetrates through the straight supporting rod and the inner hole of the middle shaft to be communicated with the measurement and control room for remote control.
In summary, the present application at least includes the following beneficial technical effects:
the prior art can not be used for carrying out a large dynamic pressure separation test on the jaw type hood; and the chin cup cannot be separated due to the excessively large pressure resistance. The test device of the invention can be used for carrying out the separation test of the chin type hood, the chin type hood can be safely separated, and the scale reduction ratio of the chin type hood can be improved to 1:5.
Drawings
FIG. 1 is a side view of a chin rest nose cap separation test device of a hypersonic wind tunnel with a test piece in an embodiment of the invention;
fig. 2 is a schematic diagram of a partially enlarged structure in an embodiment of the present invention.
Description of reference numerals: 1. a test piece; 2. a separating mechanism; 3. a chin cup; 4. a separation spring; 5. locking the bolt; 6. a balance; 7. a straight strut; 8. a middle shaft; 9. locking the nut; 10. a wind tunnel angle of attack mechanism; 11. a bottom cover;
21. fastening the wire; 22. a release device;
12. a bracket; 121. a pallet; 122. a connecting ring;
61. an inner shell of the test piece; 611. a taper hole;
62. a housing of the test piece; 621. an air inlet channel of the test piece;
31. a hood dovetail; 32. a dovetail second bevel.
Detailed Description
The present application will now be described in further detail with reference to the following figures and specific examples:
the embodiment of the application discloses a chin rest nose cap separation test device for a hypersonic wind tunnel, as shown in fig. 1 and 2, the device comprises a test piece 1, a separation mechanism 2, a chin rest nose cap 3, a separation spring 4, a locking bolt 5, a balance 6, a straight support rod 7, a middle shaft 8, a locking nut 9, a bottom cover 11 and a wind tunnel attack angle mechanism 10.
The straight supporting rod 7 is coaxially connected with the middle shaft 8, the balance 6 is connected to one end of the straight supporting rod, which is far away from the middle shaft 8, the test piece 1 is connected to the end part of the balance 6, which is far away from the straight supporting rod 7, the jaw type hood 3 is arranged on the outer side of the test piece 1, and the wind tunnel attack angle mechanism 10 is connected to the end part of the middle shaft 8, which is far away from the balance 6; a separation mechanism 2, wherein in a first use state, the separation mechanism is used for stably fixing the jaw type hood 3 on the outer side of the test piece 1, and in a second use state, the separation mechanism releases the fixation between the jaw type hood 3 and the test piece 1; the separation spring 4 penetrates through the test piece 1 and is connected between the lower jaw type hood 3 and the separation mechanism 2, a groove is formed in one side, facing the test piece 1, of the lower jaw type hood 3, the end portion of the separation spring 4 is clamped in the groove, and in the first using state, the separation spring 4 is in a compressed state. The jaw type hood 3 is fixedly connected with the test piece 1 through the separation spring 4 and the separation mechanism 2.
The separating mechanism 2 comprises a fastening line 21 and a releasing device 22, the fastening line 21 penetrates through the test piece 1, the fastening line 21 is connected between the jaw hood 3 and the separating mechanism 2, the fastening line 21 is used for enabling the jaw hood 3 to be stably attached to the outer side of the test piece 1, and the releasing device 22 is connected to the inner portion of the test piece 1 and used for cutting off the fastening line 21.
The bracket 12 is arranged in the test piece 1, the bracket 12 comprises a supporting plate 121 and at least two connecting rings 122, the connecting rings 122 are tightly attached to the inner wall of the test piece 1 and fixedly connected with the test piece 1, the supporting plate 121 is positioned in the connecting rings 122 and fixedly connected with the connecting rings 122, the supporting plate 121 and the connecting rings 122 are coaxially arranged, and the fastening line 21 is connected to the supporting plate 121.
An inner shell 61 of the test piece is arranged at one end of the balance 6 far away from the straight supporting rod 7, the end part of the balance 6 close to the straight supporting rod 7 has 10-degree taper, and the straight supporting rod 7 is matched with the 10-degree taper at the end part of the balance 6; taper holes 611 are formed in one end, far away from the straight supporting rod 7, of the inner shell 61 of the test piece, the taper of the taper holes 611 is 5 degrees, the balance 6 is located in the taper holes 611 of 5 degrees, the locking bolt 5 penetrates through the inner shell 61 of the test piece and is in threaded connection with the balance 6, and connection between the balance 6 and the test piece 1 is achieved. The outer wall of the end part of the balance 6 is far away from to the inner shell 61 of the test piece 1 which is sleeved with the test piece, the test piece 1 is connected with the inner shell 61 of the test piece through a bolt, and the bottom of the taper hole 611 is provided with a taper matched with the taper of the balance 6. The inner shell 61 of the test piece is connected with the outer shell 62 of the test piece through fastening screws, and the test piece 1, the outer shell 62 of the test piece and the balance 6 are connected together through the locking bolts 5 and the inner shell 61 of the test piece.
As shown in fig. 2, the outer wall of the housing 62 of the test piece is provided with an inlet channel 621 of the test piece, the inlet channel 621 of the test piece extends along the direction towards the test piece 1, the front end of the chin bar hood 3 close to the housing 62 of the test piece is provided with a hood dovetail 31, and the end of the inlet channel 621 of the test piece is clamped on the hood dovetail 31. Specifically, the air inlet 621 of the test piece has a size of 30-50mm along the circumferential direction of the housing 62 of the test piece. Hood forked tail 31 includes first inclined plane and blocks the inclined plane, the tip of the intake duct 621 of test piece is provided with the guide inclined plane, along the direction that is close to 1 axis of test piece, the guide inclined plane is gradually to the direction slope that is close to straight branch 7, first inclined plane cooperatees with the guide inclined plane, it is located one side that test piece 1 was kept away from on first inclined plane to block the inclined plane, first inclined plane is the V type with the hood forked tail 31 that blocks the inclined plane and form, it is less than the size of first inclined plane along 1 axis direction of test piece to block the size of inclined plane along 1 axis direction of test piece. The end part of the lower jaw type hood 3 close to the shell 62 of the test piece is provided with a dovetail second inclined surface 32, the dovetail second inclined surface 32 is positioned on one side of the inner wall of the test piece 1 facing the hood dovetail 31, and the dovetail second inclined surface 32 is gradually inclined towards the direction close to the straight supporting rod 7 along the direction far away from the axis of the test piece 1. So that one end of the test piece 1 close to the straight supporting rod 7 is not attached to the test piece any more, and the jaw type hood 3 is separated from the test piece 1 more easily. When the release device 22 cuts the fastening line 21, the separation spring 4 pushes the chin cup 3, and the chin cup 3 rotates around the end of the inlet 621 of the specimen, thereby completing the separation of the chin cup 3.
The wind tunnel attack angle mechanism 10 is sleeved outside the middle shaft 8 and is positioned at the end part of the middle shaft 8 far away from the straight strut 7; the end part of the middle shaft 8 far away from the straight supporting rod 7 is in threaded connection with a locking nut 9, and the locking nut 9 is abutted with the end part of the wind tunnel attack angle mechanism 10 far away from the straight supporting rod 7; the end part of the wind tunnel attack angle mechanism 10 far away from the straight supporting rod 7 is connected with a bottom cover 11 in a threaded mode, and the bottom cover 11 covers the locking nut 9.
And the connecting wire of the balance and the control wire of the separating mechanism penetrate through the straight supporting rod 7 and the inner hole of the middle shaft 8 to lead to the measurement and control room.
The test device is mainly used for carrying out a separation test of the jaw type hood of the hypersonic wind tunnel, the test needs to be carried out in a 1-meter-level hypersonic wind tunnel, the jaw type hood 3 is fastened on a test piece 1 through a separation spring 4 and a separation mechanism 2, the test piece 1 is connected with a balance 6, a straight strut 7 and a middle shaft 8 through a locking bolt 5, and then is connected with a wind tunnel attack angle mechanism 11 through a locking nut 9; the wind tunnel establishes a uniform flow field, the wind tunnel attack angle mechanism 11 moves upwards to deliver the whole test device to the uniform flow field, the separation mechanism 2 is unlocked, the chin-type hood 3 is separated under the action of aerodynamic force and the separation spring 4, and the measurement is carried out in real time by the high-speed camera and the dynamic force measuring system. The invention can provide service for the separation test of the jaw type hood of other hypersonic wind tunnels.
The hypersonic wind tunnel lower jaw type hood separation test device is used in the following process:
firstly, a test piece 1 is connected with a balance 6, a straight support rod 7 and the front end of a middle shaft 8 through a locking bolt 5, and then the rear end of the middle shaft 8 is connected with a wind tunnel attack angle mechanism 11 through a locking nut 9 and a bottom cover 10; and the balance 3 data line and the separating mechanism 2 control line pass through the straight supporting rod 7 and the inner hole of the middle shaft 8 to be communicated with the measurement and control room for remote control.
Secondly, spraying anti-reflection paint on the test piece 1, and pasting a mark point on the lower jaw type head cover 3; the lower jaw type hood 3 is fixedly connected with the separation mechanism 2 on the test piece 1 through a separation spring 4;
thirdly, reasonably selecting dynamic pressure of the wind tunnel test; after the wind tunnel establishes a uniform flow field, the wind tunnel attack angle mechanism 11 moves upwards to deliver the whole test device to the uniform flow field, and simultaneously sends instructions to the separation mechanism 2, the balance 6 data acquisition device and the three high-speed cameras through remote control; the separating mechanism 2 is unlocked, the chin head cover 3 is separated under the action of the pneumatic force and the separating spring 4, and the high-speed camera and the balance 6 measure the separation in real time.
Finally, data analysis, namely, as a synchronization technology is adopted, the shooting speed of the high-speed camera is consistent with the data acquisition frequency of the balance 6, and the characteristic characteristics of the separation process of the chin head cover 3 correspond to the force measurement of the balance 6 one by one; the test results may be converted to flight conditions according to similar criteria.
The above embodiments are preferred embodiments of the present application, and the protection scope of the present application is not limited by the above embodiments, so: all equivalent changes made according to the structure, shape and principle of the present application shall be covered by the protection scope of the present application.
Claims (10)
1. The utility model provides a chin formula hood separation test device for hypersonic wind tunnel which characterized in that: comprises a straight supporting rod (7);
the balance (6) is connected to one end of the straight supporting rod (7);
the test piece (1) is connected to the end part, far away from the straight supporting rod (7), of the balance (6);
the lower jaw type head cover (3) is arranged on the outer side of the test piece (1);
the separation mechanism (2) is used for enabling the jaw type head cover (3) to be stably fixed on the outer side of the test piece (1) in a first use state, and is used for releasing the fixing between the jaw type head cover (3) and the test piece (1) in a second use state;
the separation spring (4) penetrates through the test piece (1) and is arranged between the lower jaw type hood (3) and the separation mechanism (2), and in a first use state, the separation spring (4) is in a compressed state;
and the wind tunnel attack angle mechanism (10) is connected to the end part of the straight supporting rod (7) far away from the balance (6).
2. The chin bar hood separation test device for hypersonic wind tunnel according to claim 1, wherein: one side of the lower jaw type hood (3) facing the test piece (1) is provided with a groove, and the end part of the separation spring (4) is clamped in the groove.
3. The chin bar hood separation test device for hypersonic wind tunnels according to claim 1, characterized in that: the separating mechanism (2) comprises a fastening line (21) and a releasing device (22), the fastening line (21) penetrates through the test piece (1), the fastening line (21) is connected between the lower jaw type hood (3) and the separating mechanism (2), the fastening line (21) is used for enabling the lower jaw type hood (3) to be stably attached to the outer side of the test piece (1), and the releasing device (22) is connected inside the test piece (1) and used for cutting off the fastening line (21).
4. The chin bar hood separation test device for hypersonic wind tunnel according to claim 1, wherein: be provided with bracket (12) in test piece (1), bracket (12) include layer board (121) and two at least go-between (122), go-between (122) hug closely test piece (1) inner wall and with test piece (1) fixed connection, layer board (121) are located go-between (122) and with go-between (122) fixed connection, fastening line (21) are connected in layer board (121).
5. The chin bar hood separation test device for hypersonic wind tunnel according to claim 1, wherein: one end of the balance (6) far away from the straight supporting rod (7) is provided with an inner shell (61) of the connecting piece test piece, one end of the inner shell (61) of the connecting piece test piece is provided with a taper hole (611), the balance (6) is located in the taper hole (611), the locking bolt (5) penetrates through the inner shell (61) of the connecting piece test piece and is in threaded connection with the balance (6), and the test piece (1) is connected to the end of the inner shell (61) of the test piece.
6. The chin cup separation test device for hypersonic wind tunnel according to claim 5, wherein: the end part of the balance (6) far away from the straight supporting rod (7) is provided with a taper, and the bottom of the taper hole (611) is provided with a taper matched with the taper of the end part of the balance (6).
7. The chin bar hood separation test device for hypersonic wind tunnel according to claim 1, wherein: the outer shell (62) that is provided with the test piece of inner shell (61) of test piece, shell (62) surface of test piece is provided with intake duct (621) of test piece, and intake duct (621) of test piece extend along the direction towards test piece (1), and the front end of intake duct (621) of test piece and hood forked tail (31) looks joint.
8. The chin bar hood separation test device for hypersonic wind tunnel according to claim 7, wherein: the end part of the lower jaw type hood (3) close to the shell (62) of the test piece is provided with a second inclined surface (32), the dovetail second inclined surface (32) is located on one side of the inner wall of the test piece (1) facing the dovetail cover (31), and the dovetail second inclined surface (32) is gradually inclined towards the direction close to the straight supporting rod (7) along the direction far away from the axis of the test piece (1).
9. The chin bar hood separation test device for hypersonic wind tunnels according to claim 1, characterized in that: one end, far away from the balance (6), of the straight supporting rod (7) is connected with a middle shaft (8), and the wind tunnel attack angle mechanism (10) is sleeved outside the middle shaft (8) and is positioned at the end part, far away from the straight supporting rod (7), of the middle shaft (8);
the end part of the middle shaft (8) far away from the straight supporting rod (7) is in threaded connection with a locking nut (9), and the locking nut (9) is abutted with the end part of the wind tunnel attack angle mechanism (10) far away from the straight supporting rod (7);
the end part of the wind tunnel attack angle mechanism (10) far away from the straight supporting rod (7) is in threaded connection with a bottom cover (11), and the bottom cover (11) covers the locking nut (9).
10. The chin bar hood separation test device for hypersonic wind tunnel according to claim 9, wherein: the axis position of the straight supporting rod (7) and the middle shaft (8) is provided with a threading hole, and a connecting line of the balance (6) and a control line of the separating mechanism (2) penetrate through the threading hole to be connected to an industrial personal computer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210770609.1A CN115165293A (en) | 2022-06-30 | 2022-06-30 | Jaw type hood separation test device for hypersonic wind tunnel |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210770609.1A CN115165293A (en) | 2022-06-30 | 2022-06-30 | Jaw type hood separation test device for hypersonic wind tunnel |
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| Publication Number | Publication Date |
|---|---|
| CN115165293A true CN115165293A (en) | 2022-10-11 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210770609.1A Pending CN115165293A (en) | 2022-06-30 | 2022-06-30 | Jaw type hood separation test device for hypersonic wind tunnel |
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05273061A (en) * | 1992-03-30 | 1993-10-22 | Mitsubishi Heavy Ind Ltd | Load-measuring device |
| KR20120068183A (en) * | 2010-12-17 | 2012-06-27 | 한국항공우주연구원 | Apparatus for assembling and disassembling wind tunnel balance and wind tunnel testing system |
| CN111006837A (en) * | 2019-11-22 | 2020-04-14 | 中国航天空气动力技术研究院 | Hood separation wind tunnel test device applied to large dynamic pressure continuous adjustment |
| CN111122104A (en) * | 2020-01-13 | 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 | Separation wind tunnel test device for plane-symmetric hypersonic aircraft hood |
| CN112577695A (en) * | 2020-12-24 | 2021-03-30 | 中国航天空气动力技术研究院 | Device for hypersonic wind tunnel ventilation model hood separation dynamic test |
-
2022
- 2022-06-30 CN CN202210770609.1A patent/CN115165293A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH05273061A (en) * | 1992-03-30 | 1993-10-22 | Mitsubishi Heavy Ind Ltd | Load-measuring device |
| KR20120068183A (en) * | 2010-12-17 | 2012-06-27 | 한국항공우주연구원 | Apparatus for assembling and disassembling wind tunnel balance and wind tunnel testing system |
| CN111006837A (en) * | 2019-11-22 | 2020-04-14 | 中国航天空气动力技术研究院 | Hood separation wind tunnel test device applied to large dynamic pressure continuous adjustment |
| CN111122104A (en) * | 2020-01-13 | 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 | Separation wind tunnel test device for plane-symmetric hypersonic aircraft hood |
| CN112577695A (en) * | 2020-12-24 | 2021-03-30 | 中国航天空气动力技术研究院 | Device for hypersonic wind tunnel ventilation model hood separation dynamic test |
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