CN213748993U - Infrared pneumatic optical distortion wind tunnel test system - Google Patents
Infrared pneumatic optical distortion wind tunnel test system Download PDFInfo
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- CN213748993U CN213748993U CN202023181997.5U CN202023181997U CN213748993U CN 213748993 U CN213748993 U CN 213748993U CN 202023181997 U CN202023181997 U CN 202023181997U CN 213748993 U CN213748993 U CN 213748993U
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Abstract
The utility model belongs to the technical field of aerospace experiment technique and specifically relates to an infrared pneumatic optical distortion wind tunnel test system is related to. The infrared pneumatic optical distortion wind tunnel test system comprises: the infrared laser device is used for emitting an infrared beam which sequentially passes through the collimator, the target, the first optical window, the test model, the second optical window and the receiver; the infrared beam data received by the receiver is stored in a data processor; and a visible light laser is arranged between the target and the first optical window, and the emission direction of the working end of the visible light laser is the same as that of the working end of the infrared laser. The utility model relates to an infrared pneumatic optical distortion wind-tunnel test system has adopted infrared laser instrument, and is truer to the simulation of high-speed aircraft seeker (experimental model) pneumatic optical effect, presses close to true actual combat environment more. The infrared light path system is arranged to meet the wind tunnel conditions, which is beneficial to the development of the test and the acquisition of the test data.
Description
Technical Field
The utility model belongs to the technical field of aerospace experiment technique and specifically relates to an infrared pneumatic optical distortion wind tunnel test system is related to.
Background
The infrared seeker gradually becomes the best choice for terminal guidance of various high-speed aircrafts due to the characteristics of strong anti-interference capability and high guidance precision. However, when the missile flies at high speed in the atmosphere, the high-speed airflow can generate a serious pneumatic heating effect, so that the head of the missile generates a severe high-temperature environment. When the detection light passes through the high-temperature flow field, due to the nonuniformity of the density field distribution, the detection light generates pneumatic optical effects such as deflection attenuation and the like, a large sight error occurs on a detection target, and the position of the target detected by the seeker greatly deviates from the actual position of the target, so that the detection precision is reduced, and the hit rate of the missile is reduced.
The aerooptical problem is always a key problem which puzzles the improvement of the detection capability of the aircraft, and the wind tunnel test is an important way for solving the aerooptical problem of the aircraft. A large amount of manpower, financial resources and material resources are input into developed countries such as the United states to carry out pneumatic optical test research, and a major breakthrough is made, so that the pneumatic optical test device is successfully applied to weaponry. In China, the research on the pneumatic optical problem is also emphasized in recent years, a plurality of pneumatic optical research topics are successively developed, and research results provide powerful support for the development of model equipment. However, the conventional pneumatic optical test is mostly carried out by adopting a visible light wave band under test conditions, but in practice, a seeker mostly adopts an infrared wave band, although a pneumatic optical rule of the visible light wave band is in certain correlation with the infrared wave band and can be similar to an analog, the relationship between the pneumatic optical rule of the infrared wave band and the visible light wave band is not clear along with the more complex test simulation environment, and the infrared wave band cannot be calculated from the rule of the visible light wave band alone. Therefore, an effective infrared pneumatic optical distortion wind tunnel testing method and system are lacked at present, the pneumatic optical problem of the infrared band can be tested and researched, and the requirements of actual weapon models are met better.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide an infrared pneumatic optics distortion wind-tunnel test system, this infrared pneumatic optics distortion wind-tunnel test system can solve the pneumatic optics effect problem to the infrared seeker of high-speed aircraft, provides an infrared pneumatic optics distortion wind-tunnel test system, through infrared laser instrument, target, optical window and receiver etc. realizes the infrared pneumatic optics distortion measurement in wind-tunnel test model flow field.
The utility model provides an infrared pneumatic optical distortion wind-tunnel test system, include: the infrared laser device is used for emitting an infrared beam which sequentially passes through the collimator, the target, the first optical window, the test model, the second optical window and the receiver; the infrared beam data received by the receiver is stored in a data processor; and a visible light laser is arranged between the target and the first optical window, and the emission direction of the working end of the visible light laser is the same as that of the working end of the infrared laser.
Wherein the collimator is an infrared collimator; the infrared beams pass through the collimator tube to form infrared parallel beams with equal phases.
Wherein the target is a hollowed flat plate; the hollowed-out patterns are clear in edges and corners.
After the infrared parallel light beams pass through the target, the infrared parallel light beams form infrared light beams in hollow pattern shapes on the target.
The two sides of the test model are respectively provided with a first optical window and a second optical window; the first optical window and the second optical window are both infrared optical windows.
The transmission waveband of the infrared optical window is 8-12 microns, and the infrared waveband transmittance is not less than 85%.
Wherein, the end part of the test model is an arc-shaped test model; and the arc-shaped end of the test model is provided with a flow field blowing to the arc-shaped end.
Wherein the receiver is an infrared light receiver; the data processor is a data processing computer.
An active vibration reduction platform is arranged below the infrared laser, the collimator, the target, the visible light laser, the first optical window, the test model, the second optical window and the receiver; the active damping platform comprises: the system comprises an optical flat plate, a displacement detection system and an active vibration reduction module; the infrared laser, the collimator, the target, the visible laser, the first optical window, the test model, the second optical window and the receiver are arranged on the optical flat plate; an active vibration reduction module is arranged below the optical flat plate; and a vibration frequency and amplitude displacement detection system for monitoring the ground in real time is arranged below the active vibration reduction module.
Wherein the infrared beam emitted by the infrared laser is coaxial with the emitted light of the visible laser.
The utility model relates to an infrared pneumatic optical distortion wind-tunnel test system beneficial effect:
an infrared beam emitted by an infrared laser sequentially passes through a collimator, a target, a visible light laser, a first optical window, a test model, a second optical window and a receiver; the infrared beam data received by the receiver is stored in a data processor for storage of test data. Compared with the traditional pneumatic optical wind tunnel test method and system, the infrared laser is adopted, so that the simulation of the pneumatic optical effect of the high-speed aircraft seeker (test model) is more real and closer to a real actual combat environment. The infrared light path system is arranged to meet the wind tunnel conditions, which is beneficial to the development of the test and the acquisition of the test data.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the embodiments or the technical solutions in the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic diagram of an infrared aerodynamic optical distortion wind tunnel test system of the present invention;
FIG. 2 is a schematic diagram of a target of the infrared aerodynamic optical distortion wind tunnel test system of the present invention;
fig. 3 is the utility model relates to an infrared pneumatic optical distortion wind-tunnel test system's experimental model schematic diagram.
Description of reference numerals:
1. an infrared laser; 2. a collimator; 3. a target; 4. a visible light laser; 5. a first optical window; 6. a test model; 7. a second optical window; 8. a receiver; 9. a data processor; 10. an active vibration reduction platform.
Detailed Description
The technical solution of the present invention will be described clearly and completely with reference to the following embodiments, and it should be understood that the described embodiments are some, but not all embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", "clockwise", "counterclockwise", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and to simplify the description, but do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be construed as limiting the present invention.
Furthermore, the terms "first", "second" and "first" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, features defined as "first", "second", may explicitly or implicitly include one or more of the described features. In the description of the present invention, "a plurality" means two or more unless specifically limited otherwise. Furthermore, the terms "mounted," "connected," and "connected" are to be construed broadly and may, for example, be fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Referring to fig. 1, an infrared pneumatic optical distortion wind tunnel test system includes: the device comprises an infrared laser 1, wherein an infrared beam emitted by the infrared laser 1 sequentially passes through a collimator 2, a target 3, a visible laser 4, a first optical window 5, a test model 6, a second optical window 7 and a receiver 8; the infrared beam data received by the receiver 8 is stored in a data processor 9.
The infrared laser 1 emits infrared beams which pass through the collimator 2 to form equal-phase infrared parallel beams, the infrared parallel beams pass through the target 3 to become beams with patterns at the hollow part of the specific target 3, and the infrared beams enter a test stage after passing through an infrared optical window with infrared optical glass. The infrared light beam passes through the pneumatic flow field around the test model 6 to generate pneumatic optical distortion, then is emitted from a second optical window 7 arranged on the other side, is received by an infrared seeker or an infrared camera (a receiver 8), is collected and stored on a data processing computer (a data processor 9), and is calculated to obtain the infrared pneumatic optical distortion of the test flow field. Since the infrared light is invisible to the naked eye, the light path is adjusted by a small visible laser 4. In order to reduce the influence of the vibration of the test wind tunnel on the test measurement, the whole infrared pneumatic optical testing system needs to be placed on the active vibration reduction platform 10.
The infrared laser 1 is an infrared pulse laser or an infrared continuous laser, the pulse frequency of the infrared pulse laser is not less than 1000Hz, the pulse energy is between 50 muJ and 5000 muJ, the power of the infrared continuous laser is between 0.05mW and 5mW, the energy of the laser is too low, the infrared seeker cannot receive images, and the energy of the laser is too high, so that the infrared seeker is damaged. The wave band of the infrared laser 1 is 8-12 mu m, and is the infrared wave band of the far infrared atmospheric window.
Specifically, the collimator 2 is an infrared collimator; the infrared beams pass through the collimator 2 to form infrared parallel beams with equal phases.
Specifically, the target 3 is a hollow flat plate; the hollowed-out patterns are clear in edges and corners.
Referring to fig. 2, fig. 2 is a pattern of the infrared target 3, and the infrared target 3 simulates the infrared radiation of the detection target by hollowing out the pattern on the flat plate. The pattern of the infrared target 3 is generally a clear pattern with sharp edges and corners, so that the judgment of fuzzy distortion is convenient, a triangle or a polygon is generally selected, and a contour pattern of a simulation target, such as the contour of an airplane and a tank, can also be directly selected.
Specifically, after the infrared parallel light beams pass through the target 3, the infrared parallel light beams form infrared light beams in the shape of hollow patterns on the target 3.
Specifically, a first optical window 5 and a second optical window 7 are respectively arranged on two sides of the test model 6; the first optical window 5 and the second optical window 7 are both infrared optical windows.
The first optical window 5 and the second optical window 7 are infrared optical windows. The infrared optical windows are arranged on two sides of the test model 6 and used for infrared beams to pass through, the infrared optical windows are made of infrared optical glass, the transmission wave band is 8-12 microns, common materials are germanium, silicon, sapphire and the like, an antireflection film is plated on the surface of the glass, and the transmission rate of the infrared wave band is not less than 85%. The area of the infrared optical window is not less than the light-emitting area of the infrared collimator 2.
The infrared collimator 2 is suitable for infrared light with a wave band of 8-12 microns, the beam expansion multiplying power and the light-emitting caliber are designed according to test requirements, and the beam expansion multiplying power is recommended to be not less than 10 times, and the light-emitting caliber is recommended to be not less than 100 mm. The infrared collimator 2 should be designed to match the infrared laser 1 to ensure the coincidence of the optical axes during installation.
Referring to fig. 3, in particular, the end of the test model 6 is an arc-shaped test model; and the arc-shaped end of the test model 6 is provided with a flow field blowing to the arc-shaped end.
The test model 6 is a common bullet model, and two side faces of the model are provided with windows (a first optical window 5 and a second optical window 7) for detecting the infrared beam to pass through.
The infrared seeker (receiver 8) is used for receiving the infrared light beams passing through the test flow field and can be replaced by an infrared camera, the infrared seeker or the infrared camera receives infrared light with the wavelength of 8-12 mu m, the resolution ratio is not less than 320 multiplied by 256, and the acquisition frequency is greater than 100 Hz.
Specifically, the receiver 8 is an infrared light receiver; the data processor 9 is a data processing computer.
The computer of the data processor 9 is a conventional data processing computer.
Specifically, an active vibration reduction platform 10 is arranged below the infrared laser 1, the collimator 2, the target 3, the visible light laser 4, the first optical window 5, the test model 6, the second optical window 7 and the receiver 8; the active damping platform 10 comprises: the system comprises an optical flat plate, a displacement detection system and an active vibration reduction module; the infrared laser 1, the collimator 2, the target 3, the visible light laser 4, the first optical window 5, the test model 6, the second optical window 7 and the receiver 8 are arranged on the optical flat plate; an active vibration reduction module is arranged below the optical flat plate; and a vibration frequency and amplitude displacement detection system for monitoring the ground in real time is arranged below the active vibration reduction module.
The active vibration damping platform 10 is composed of an optical flat plate, a displacement detection system and an active vibration damping module, wherein the displacement detection system (conventional structure, belonging to the prior art) monitors the vibration frequency and amplitude of the ground in real time, sends an instruction to the active vibration damping module (the active vibration damping module is a conventional module capable of vibrating, belonging to the prior art, and applied here), and counteracts vibration through opposite displacement. The infrared pneumatic optical testing system needs to be placed on an optical flat plate of the active vibration reduction platform 10, and ground vibration cannot be transmitted to the testing system, so that authenticity and accuracy of an infrared pneumatic optical distortion test are guaranteed.
Specifically, the infrared beam emitted by the infrared laser 1 is coaxial with the emitted light of the visible laser 4.
Visible light laser 4 is small-size visible light laser 4, small-size visible light laser 4 is used for the whole optical path system of auxiliary regulation, because the infrared light naked eye is invisible, consequently can't directly adjust the light path, with small-size visible light laser 4 and infrared laser 1 coaxial arrangement, guarantee that the visible light that visible light laser 4 sent is coaxial parallel with the infrared light that infrared laser 1 sent, adjust the position and the angle of equipment in the optical path system through visible light, then withdraw from small-size visible light laser 4, use infrared light path, can make the light path adjust more convenient rapidly.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention.
Claims (10)
1. An infrared pneumatic optical distortion wind tunnel test system is characterized by comprising:
the infrared laser device is used for emitting an infrared beam which sequentially passes through the collimator, the target, the first optical window, the test model, the second optical window and the receiver; the infrared beam data received by the receiver is stored in a data processor; and a visible light laser is arranged between the target and the first optical window, and the emission direction of the working end of the visible light laser is the same as that of the working end of the infrared laser.
2. The infrared aerodynamic optical distortion wind tunnel test system according to claim 1, wherein the collimator is an infrared collimator; the infrared beams pass through the collimator tube to form infrared parallel beams with equal phases.
3. The infrared pneumatic optical distortion wind tunnel test system according to claim 2, wherein the target is a hollowed flat plate; the hollowed-out patterns are clear in edges and corners.
4. The infrared pneumatic optical distortion wind tunnel test system according to claim 3, wherein after the infrared parallel light beams pass through the target, the infrared parallel light beams form infrared light beams in a hollow pattern shape on the target.
5. The infrared pneumatic optical distortion wind tunnel test system according to claim 4, wherein a first optical window and a second optical window are respectively arranged on two sides of the test model; the first optical window and the second optical window are both infrared optical windows.
6. The infrared pneumatic optical distortion wind tunnel test system according to claim 5, wherein the transmission waveband of the infrared optical window is 8-12 μm, and the infrared waveband transmittance is not less than 85%.
7. The infrared pneumatic optical distortion wind tunnel test system according to claim 4, wherein the end of the test model is an arc-shaped test model; and the arc-shaped end of the test model is provided with a flow field blowing to the arc-shaped end.
8. The infrared aerodynamic optical distortion wind tunnel test system according to claim 1, wherein the receiver is an infrared light receiver; the data processor is a data processing computer.
9. The infrared pneumatic optical distortion wind tunnel test system according to claim 1, wherein an active vibration reduction platform is arranged below the infrared laser, the collimator, the target, the visible light laser, the first optical window, the test model, the second optical window and the receiver; the active damping platform comprises: the system comprises an optical flat plate, a displacement detection system and an active vibration reduction module; the infrared laser, the collimator, the target, the visible laser, the first optical window, the test model, the second optical window and the receiver are arranged on the optical flat plate; an active vibration reduction module is arranged below the optical flat plate; and a vibration frequency and amplitude displacement detection system for monitoring the ground in real time is arranged below the active vibration reduction module.
10. The infrared aerodynamic optical distortion wind tunnel test system according to claim 1, wherein the infrared beam emitted by the infrared laser is coaxial with the emitted light of the visible laser.
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| CN112577694A (en) * | 2020-12-25 | 2021-03-30 | 中国航天空气动力技术研究院 | Infrared pneumatic optical distortion wind tunnel test system |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN112577694A (en) * | 2020-12-25 | 2021-03-30 | 中国航天空气动力技术研究院 | Infrared pneumatic optical distortion wind tunnel test system |
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