CN113188751B - Transonic wind tunnel optical test section - Google Patents
Transonic wind tunnel optical test section Download PDFInfo
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- CN113188751B CN113188751B CN202110531433.XA CN202110531433A CN113188751B CN 113188751 B CN113188751 B CN 113188751B CN 202110531433 A CN202110531433 A CN 202110531433A CN 113188751 B CN113188751 B CN 113188751B
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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
- G01M9/02—Wind tunnels
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Abstract
The invention discloses a transonic wind tunnel optical test section. The transonic wind tunnel optical test section comprises a test area, wherein an upper inner wall and a lower inner wall of the test area are provided with an array of vent holes; the device comprises an outer hole body sleeved outside a test area, wherein a cavity between the test area and the outer hole body is a standing chamber; the left and right sides in the test area, between the test area and the outer hole body, are provided with left separation sleeve and right separation sleeve respectively, and the inboard at left separation sleeve and right separation sleeve, be located the test area left and right both sides inner wall and be provided with the interior window, be provided with light path window and window of making a video recording on the interior window, left separation sleeve and right separation sleeve's outer window dress card is on the left and right lateral wall of the outer hole body that corresponds through respective outer window frame. The transonic wind tunnel optical test section reduces interference caused by a glass window and a parking chamber, improves the precision of pneumatic optical effect measurement, and is suitable for carrying out pneumatic optical effect measurement.
Description
Technical Field
The invention belongs to the technical field of high-speed wind tunnel tests, and particularly relates to a transonic wind tunnel optical test section.
Background
An aircraft flying at high speed in the atmospheric layer compresses surrounding air to cause high-frequency pulsation and even shock waves, so that an uneven flow field is formed. The light rays irregularly deflect when passing through the uneven flow field to form wave aberration, which can bring uncertain interference to laser measuring equipment and laser weapons. If the characteristic change of light passing through different flow fields can be mastered, the measurement result or the transmission process can be corrected, and the performance of the equipment is improved. The measurement of the aerodynamic optical effect in the wind tunnel is one of the effective methods for evaluating the characteristics of the laser uneven flow field.
The transonic wind tunnel test section consists of a test area and an outer hole body, and a room is arranged between the test area and the outer hole body. When the airflow is accelerated to be close to the sound velocity, a choking effect is generated, the acceleration cannot be continued, and a transonic velocity flow field cannot be formed.
At present, optical windows are generally arranged on two sides of an outer hole body of a transonic wind tunnel respectively to observe conditions in a test section, however, in this way, laser enters the test section from one side of the test section through two layers of optical glass, passes through a flow field, and irradiates a detection instrument through the two layers of optical glass. That is to say, when carrying out the laser transmission test, laser ray incides from outer hole body one side glass window, passes and resides the room space, incides the test area from the glass window of test section inner wall, and the laser characteristic changes after passing the test area, and the glass window that passes the other side inner wall again, resides the room, the glass window of outer hole body reaches receiving arrangement, has passed four layers of glass windows in the whole transmission process, and the secondary passes and resides the room space, and the reflection of laser and refraction have mixed into more interference factor, can introduce too much interference for the measurement of pneumatic optical effect. Therefore, the test section of the conventional transonic wind tunnel is not suitable for carrying out the measurement of the aerodynamic optical effect.
At present, it is urgently needed to improve a transonic speed test section, reduce the measurement error brought by reflection and refraction in the laser transmission process, and develop a transonic speed wind tunnel optical test section suitable for aerodynamic optical effect measurement.
Disclosure of Invention
The invention aims to solve the technical problem of providing a transonic wind tunnel optical test section.
The transonic wind tunnel optical test section is characterized in that wind tunnel incoming flow is taken as the front, the transonic wind tunnel optical test section comprises a cuboid test area which is formed by an upper inner wall, a lower inner wall, a left inner wall and a right inner wall and is provided with a front opening and a rear opening, and the upper inner wall and the lower inner wall are provided with vent holes in an array;
the testing device comprises a cuboid-shaped outer hole body which is sleeved outside a testing area and is provided with a front opening and a rear opening, wherein a cavity between the testing area and the outer hole body is a standing chamber;
the device comprises a left isolation sleeve penetrating through a parking chamber and arranged between the left inner wall of a test area and the left side wall of a corresponding outer hole body, and a right isolation sleeve penetrating through the parking chamber and arranged between the right inner wall of the test area and the right side wall of the corresponding outer hole body; the left inner wall corresponding to the left isolation sleeve and the right inner wall corresponding to the right isolation sleeve are respectively provided with an inner window, and the inner windows are provided with a light path window and a camera shooting window; and the outer window is arranged on the left side wall of the outer hole body corresponding to the left isolation sleeve and the right side wall of the outer hole body corresponding to the right isolation sleeve respectively, and the outer window is clamped on the outer hole body through an outer window frame.
Furthermore, optical glass is installed on the light path window, and infrared glass is installed on the camera shooting window.
Further, the vent hole is a circular through hole.
The transonic wind tunnel optical test section adopts the isolation sleeve to connect the inner window and the outer window frame, removes the glass window of the outer hole body, and improves the glass window of the inner wall. The inner window is provided with a light path window and a camera shooting window, the light path window is provided with optical glass and is beneficial to laser transmission, and the camera shooting window is provided with infrared glass and is beneficial to infrared light transmission.
The transonic wind tunnel optical test section meets the transonic flow field establishment condition, reduces the number of layers penetrating through glass during laser transmission from four layers to two layers, reduces the number of layers penetrating through glass during infrared light transmission from two layers to one layer, and transmits the laser and the infrared light in the isolation sleeve without penetrating through a resident room.
The transonic wind tunnel optical test section reduces the interference caused by a glass window and a parking chamber, improves the precision of the pneumatic optical effect measurement, and is suitable for carrying out the pneumatic optical effect measurement.
Drawings
FIG. 1 is a schematic structural diagram of an optical test section of a transonic wind tunnel according to the present invention;
FIG. 2 is a schematic structural diagram of a left spacer sleeve in the transonic wind tunnel optical test section according to the present invention.
In the figure, 1, an outer hole body 2, an upper inner wall 3, a lower inner wall 4, a left inner wall 5, a right inner wall 6, a test area 7, a vent hole 8, a parking chamber 9, a left isolation sleeve 10, a right isolation sleeve 11, an inner window 12, an outer window frame 13, an optical path window 14 and a camera shooting window.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
As shown in fig. 1 and 2, the transonic wind tunnel optical test section of the invention comprises a front-back open cuboid test area 6 composed of an upper inner wall 2, a lower inner wall 3, a left inner wall 4 and a right inner wall 5, and the upper inner wall 2 and the lower inner wall 3 are provided with an array of vent holes 7;
the testing device comprises a cuboid outer hole body 1 which is sleeved outside a testing area 6 and is provided with a front opening and a rear opening, wherein a cavity between the testing area 6 and the outer hole body 1 is a standing chamber 8;
the device comprises a left isolation sleeve 9 which penetrates through a parking chamber 8 and is arranged between a left inner wall 4 of a test area 6 and the left side wall of a corresponding outer hole body 1, and a right isolation sleeve 10 which penetrates through the parking chamber 8 and is arranged between a right inner wall 5 of the test area 6 and the right side wall of the corresponding outer hole body 1; the left inner wall 4 corresponding to the left isolation sleeve 9 and the right inner wall 5 corresponding to the right isolation sleeve 10 are respectively provided with an inner window 11, and the inner window 11 is provided with a light path window 13 and a camera window 14; the left side wall of the outer hole body 1 corresponding to the left isolation sleeve 9 and the right side wall of the outer hole body 1 corresponding to the right isolation sleeve 10 are respectively provided with an outer window, and the outer windows are clamped on the outer hole body 1 through an outer window frame 12.
Furthermore, the optical path window 13 is provided with optical glass, and the camera window 14 is provided with infrared glass.
Further, the vent hole 7 is a circular through hole.
Example 1
The embodiment is a laser transmission test performed in the transonic wind tunnel optical test section, and the specific test process is as follows:
after the transonic wind tunnel is started, transonic airflow which flows uniformly at a certain speed is formed in the test area 6, the flow speed of the airflow in the dwelling chamber 8 is far lower than that of the test area, and the air pressure is lower than the atmospheric pressure. Laser passes through the optical glass of light path window 13 from left separation sleeve 9 and gets into the test section, and laser produces unknown refraction and reflection in test area 6, passes right inner wall 5, right separation sleeve 10 in proper order and jets out, and the laser characteristic of outgoing changes, and the external detecting instrument of accessible measures. Two layers of optical glass were passed through during the laser transmission test.
Example 2
The embodiment is an infrared light measurement test carried out in the transonic wind tunnel optical test section, and the specific test process is as follows:
after the transonic wind tunnel is started, the temperature of a test model in the test area 6 changes along with the change of the air flow speed, and infrared cameras are erected in the right isolation sleeve 10 and outside the camera window 14 to measure the temperature of the test model. The infrared light emitted by the test model passes through a layer of glass to reach the infrared camera.
Claims (3)
1. A transonic wind tunnel optical test section is characterized in that wind tunnel incoming flow is taken as the front, the transonic wind tunnel optical test section comprises a front-back-opening cuboid-shaped test area (6) composed of an upper inner wall (2), a lower inner wall (3), a left inner wall (4) and a right inner wall (5), and vent holes (7) in an array are formed in the upper inner wall (2) and the lower inner wall (3);
the testing device comprises a cuboid outer hole body (1) which is sleeved on the outer side of a testing area (6) and is provided with a front opening and a rear opening, wherein a cavity between the testing area (6) and the outer hole body (1) is a standing chamber (8);
the device comprises a left isolation sleeve (9) which penetrates through a parking chamber (8) and is arranged between a left inner wall (4) of a test area (6) and the left side wall of a corresponding outer hole body (1), and a right isolation sleeve (10) which penetrates through the parking chamber (8) and is arranged between a right inner wall (5) of the test area (6) and the right side wall of the corresponding outer hole body (1); the left inner wall (4) corresponding to the left isolation sleeve (9) and the right inner wall (5) corresponding to the right isolation sleeve (10) are respectively provided with an inner window (11), and the inner window (11) is provided with a light path window (13) and a camera window (14); the left side wall of the outer hole body (1) corresponding to the left isolation sleeve (9) and the right side wall of the outer hole body (1) corresponding to the right isolation sleeve (10) are respectively provided with an outer window, and the outer windows are clamped on the outer hole body (1) through an outer window frame (12).
2. The transonic wind tunnel optical test section according to claim 1, wherein optical glass is mounted on the light path window (13), and infrared glass is mounted on the camera window (14).
3. The transonic wind tunnel optical test section according to claim 1, characterized in that said vent holes (7) are circular through holes.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202110531433.XA CN113188751B (en) | 2021-05-17 | 2021-05-17 | Transonic wind tunnel optical test section |
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| CN202110531433.XA CN113188751B (en) | 2021-05-17 | 2021-05-17 | Transonic wind tunnel optical test section |
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| CN113188751B true CN113188751B (en) | 2022-08-26 |
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