CN114056609A - Target detection environment ground simulation system - Google Patents
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Abstract
本发明涉及航空航天实验技术领域，尤其是涉及一种目标探测环境地面模拟系统，包括探测目标模拟模块、云雾环境模拟模块、飞行器流场模拟模块和光束接收模块；所述探测目标模拟模块用于提供模拟的探测目标的辐射光束；所述云雾环境模拟模块用于提供模拟的大气云雾环境；所述飞行器流场模拟模块用于提供模拟的流场环境；所述光束接收模块用于接收由所述探测目标模拟模块发出并穿过所述云雾环境模拟模块和飞行器流场模拟模块之后的辐射光束并成像和记录存储。本发明能够实现目标光束经过大气云雾模拟模块和飞行器流场模拟模块的光学传输路径的模拟，研究目标光束的大气传输衰减和偏折规律，为飞行器目标探测精度的提高提供依据。
The invention relates to the technical field of aerospace experiments, in particular to a target detection environment ground simulation system, comprising a detection target simulation module, a cloud and fog environment simulation module, an aircraft flow field simulation module and a beam receiving module; the detection target simulation module is used for Provide a simulated radiation beam of the detection target; the cloud environment simulation module is used to provide a simulated atmospheric cloud and fog environment; the aircraft flow field simulation module is used to provide a simulated flow field environment; the beam receiving module is used to receive The radiation beam emitted by the detection target simulation module and after passing through the cloud and fog environment simulation module and the aircraft flow field simulation module is imaged, recorded and stored. The invention can realize the simulation of the optical transmission path of the target beam passing through the atmospheric cloud and fog simulation module and the aircraft flow field simulation module, study the atmospheric transmission attenuation and deflection law of the target beam, and provide a basis for improving the detection accuracy of the aircraft target.
Description
Technical Field
The invention relates to the technical field of aerospace experiments, in particular to a ground simulation system for a target detection environment.
Background
With the development of modern national defense science and technology, the requirements of various aircrafts such as missiles, airplanes, helicopters and the like on high-precision detection capability are increasingly strong. Cloud and mist in the atmosphere are the most common meteorological phenomena, and after the detection light enters the cloud and mist, cloud droplet particles (including liquid and solid particles) in the cloud and mist can have the effects of reflection, absorption, scattering and refraction on the detection light, so that the detection light generates serious energy attenuation and direction deviation, the imaging fuzzy identification of a detection system is difficult, and the detection distance is greatly shortened. In addition, the target signal received by the detection device is subjected to the combined action of the aerodynamic optical effect near the target and the atmospheric optical effect between the target and the detection device, and the target image can generate serious energy attenuation and distortion. Therefore, the bottleneck of the target detection capability can be broken through only by the deeper essential understanding of the pneumatic optics and atmospheric light transmission effect of the target light beam.
In the united states and the european union, a great deal of research on complex meteorological conditions (such as clouds, fog, rain and snow) has been conducted to improve the infrared optical imaging detection or terminal guidance capability from high-speed aircrafts to unmanned aerial vehicles, but the research results mainly focus on theoretical analysis and flight tests. For example, in countries such as the united states, a great number of flight tests were carried out in the last 90 th century, and the optical transmission of the real atmosphere is directly measured, so that the relationship between the mid-infrared/far-infrared light transmittance and the transmission distance is obtained. However, the actual atmospheric environmental characteristics are complex, and the simulation is difficult under the laboratory conditions, so that a physical model under the complex meteorological conditions cannot be established.
Disclosure of Invention
The invention aims to provide a target detection environment ground simulation system which can realize the simulation of an optical transmission path of a target light beam passing through an atmospheric cloud simulation module and an aircraft flow field simulation module, study the atmospheric transmission attenuation and deflection rule of the target light beam and provide a basis for improving the target detection precision of an aircraft.
The invention provides a target detection environment ground simulation system, which comprises a detection target simulation module, a cloud and fog environment simulation module, an aircraft flow field simulation module and a light beam receiving module, wherein the detection target simulation module is used for simulating the cloud and fog environment;
the detection target simulation module is used for providing simulated radiation beams of the detection target;
the cloud environment simulation module is used for providing a simulated atmospheric cloud environment;
the aircraft flow field simulation module is used for providing a simulated flow field environment;
the light beam receiving module is used for receiving the radiation beam which is emitted by the detection target simulation module and passes through the cloud fog environment simulation module and the aircraft flow field simulation module, and imaging, recording and storing the radiation beam.
Preferably, the detection target simulation module comprises a high-energy pulse laser and a beam lifter;
the high-energy pulse laser is used for simulating a radiation beam emitted by a detection target;
the beam lifter comprises an optical supporting rod and two adjustable reflectors, and the height of a radiation beam emitted by the high-energy pulse laser is increased by adjusting the angles of the two reflectors.
Preferably, the cloud and fog ring simulation module comprises a water tank, an ultrasonic atomizer, a glass frame and a partition plate, wherein purified water is filled in the water tank, and the ultrasonic atomizer is immersed in the water;
the ultrasonic atomizer is used for atomizing the contacted purified water into small water drops through ultrasonic vibration so as to disperse the small water drops in a space surrounded by the glass frame to form a simulated atmosphere cloud environment;
the divider plate is used to vary the thickness of the cloud to simulate different atmospheric transmission distances.
Preferably, the aircraft flow field simulation module comprises a wind tunnel, an aircraft model and a glass window;
the wind tunnel is used for generating high-speed airflow, the high-speed airflow forms a high-speed flow winding field after passing through the aircraft model, and the flow field through which the detection light beam of the aircraft passes is simulated.
Preferably, the light beam receiving module comprises a high-speed camera, an image acquisition card and a data storage computer;
the high-speed camera is electrically connected with the image acquisition card and transmits data;
and the data storage computer is used for storing the light beam image acquired by the image acquisition card.
Preferably, the high-energy pulse laser is a Nd: YAG laser.
Preferably, the glass frame and the separation plate are made of organic glass with optical transmittance of more than 90%.
Preferably, the aircraft model adopts an aircraft equal-scale reduction model.
Preferably, the glass window is made of quartz glass with optical transmittance of more than 95%.
Preferably, the Camera is a CMOS Camera, and the CMOS Camera and the image acquisition card are connected by a Full Camera Link interface.
Has the advantages that:
the target detection environment ground simulation system can simulate a target detection process in a ground environment and research the composite effect of the pneumatic optical effect and the atmospheric optical effect of the detection light beam. Compared with a theoretical analysis method, the method is closer to a real environment; compared with a flight test, the cost is lower, the control of test conditions is more accurate, and the knowledge of regularity is easier to obtain; compared with the traditional wind tunnel test method, the method considers the atmospheric environment influence in the detection process and is more consistent with the real target detection process.
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 description of the embodiments or 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 other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a general schematic diagram of a ground simulation system for an object detection environment according to the present invention;
FIG. 2 is a schematic diagram of a detected object simulation module according to the present invention;
FIG. 3 is a schematic diagram of a cloud environment simulation module according to the present invention;
FIG. 4 is a schematic diagram of an ultrasonic atomizer according to the present invention;
FIG. 5 is a schematic view of an aircraft flow field simulation module of the present invention;
FIG. 6 is a reference beam image received by the beam receiving module of the present invention;
FIG. 7 is a distorted beam image received by the beam receiving module of the present invention;
FIG. 8 is a diagram illustrating the calculated line-of-sight error of the transmission of the target probe beam according to the present invention.
Description of reference numerals: 1-detection target simulation module, 2-cloud and fog environment simulation module, 3-aircraft flow field simulation module, 4-light beam receiving module, 5-active damping platform, 6-high energy pulse laser, 7-light beam lifter, 8-water tank, 9-ultrasonic atomizer, 10-glass frame, 11-partition plate, 12-cloud and fog environment, 13-metal substrate, 14-piezoelectric ceramic chip, 15-micro-cone hole group, 16-liquid to be atomized, 17-simulated cloud and fog, 18-wind tunnel, 19-aircraft model and 20-glass window.
Detailed Description
The technical solutions 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. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within 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 and positional relationships based on those shown in the drawings, and are used only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be considered 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 defined 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 meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
Example 1
A target detection environment ground simulation system is shown in figure 1 and comprises a detection target simulation module 1, a cloud and fog environment simulation module 2, an aircraft flow field simulation module 3, a light beam receiving module 4 and an active vibration reduction platform 5. The simulated detection light beam emitted by the detection target simulation module 1 passes through the simulated cloud and fog environment generated by the cloud and fog environment simulation module 2, and is received, collected and stored by the light beam receiving module 4 after passing through the aircraft simulated winding field generated by the aircraft flow field simulation module 3. In order to reduce the influence of the vibration of the test wind tunnel on the test measurement, the whole target detection environment ground simulation system must be placed on the active vibration reduction platform 5.
FIG. 2 is a schematic diagram of the above-mentioned module 1 for simulating detected objects, wherein the module 1 for simulating detected objects is composed of a high-energy pulse laser 6 and a beam raiser 7, the high-energy pulse laser 6 is an Nd: YAG laser, the pulse wavelength is 532nm, the average power is 200mW, the pulse energy is more than 35 muJ, the pulse width is 10-25ns, and the high-energy pulse laser emitted by the high-energy pulse laser 6 can simulate the radiation beam emitted by the detected objects. The light beam lifter 7 consists of an optical support rod and an adjustable reflector, and the laser emitted by the high-energy pulse laser 6 is lifted to a specific height by adjusting the angles of the two reflectors, so that the test and measurement are convenient.
Fig. 3 is a schematic diagram of the cloud and mist environment simulation module 2, the cloud and mist environment simulation module 2 is composed of a water tank 8, an ultrasonic atomizer 9, a glass frame 10 and a partition plate 11, purified water is filled in the water tank 8, the ultrasonic atomizer 9 is completely immersed in water, after the power is turned on, the ultrasonic atomizer 9 atomizes the contacted purified water into small liquid drops through ultrasonic vibration, and the small liquid drops are dispersed in a space surrounded by the glass frame 10 to form a simulated cloud and mist environment 12. The partition plate 11 can move to change the thickness of the cloud mist, and simulate different atmospheric transmission distances. The glass frame 10 and the partition plate 11 are made of organic glass materials with high transmittance, and the optical transmittance is more than 90%.
Fig. 4 is a schematic diagram of the principle of the ultrasonic atomizer 9, the ultrasonic atomizer 9 is composed of a metal substrate 13 and a piezoelectric ceramic plate 14, a micro-cone group 15 is opened in the center of the metal substrate 13, the aperture of the micro-cone group 15 is smaller than 10 μm, the metal substrate 13 is attached to a liquid 16 to be atomized, and the liquid 16 to be atomized is mainly purified water. Ultrasonic frequency oscillation signals generated by the oscillation circuit are transmitted to the piezoelectric ceramic piece 14, the piezoelectric ceramic piece 14 transmits the oscillation signals to the metal substrate 13, so that the metal substrate 13 generates periodic high-frequency oscillation deformation, liquid 16 to be atomized is extruded and crushed into small liquid drops, the small liquid drops are sprayed out from the micro-cone hole group 15, simulated cloud mist 17 containing the small liquid drops is formed, and the particle size of the generated small liquid drops is smaller than 20 micrometers.
Fig. 5 is a schematic diagram of the aircraft flow field simulation module 3, where the aircraft flow field simulation module 3 is composed of a wind tunnel 18, an aircraft model 19, and a glass window 20. The wind tunnel 18 generates high-speed airflow, and the high-speed airflow forms a high-speed flow winding field after passing through the aircraft model 19, so that the flow winding field through which the aircraft detection light beam passes is simulated. The aircraft model 19 adopts a scaled model of an aircraft such as a missile, the glass window 20 adopts quartz glass, the optical transmittance is more than 95 percent, and the attenuation of the light beam energy is weakened as much as possible.
Fig. 6 is a reference beam image received by the beam receiving module 4, that is, a beam image when the detection beam does not pass through the simulated cloud environment and the simulated aircraft flow-around field. The reference beam is unaffected by atmospheric and aerodynamic optical effects and its image is a standard circle.
Fig. 7 is a distorted beam image received by the beam receiving module 4, that is, a beam image when the detection beam passes through the simulated cloud environment and the simulated aircraft flow-around field. The detection light beam is influenced by the composite action of the atmospheric optical effect and the pneumatic optical effect, so that the image of the detection light beam is seriously distorted, the shape of the detection light beam is deformed, the image is blurred, the position of the mass center of the image is shifted, and the sight line error exists.
Fig. 8 is a view of line of sight errors transmitted by target probe beams obtained through calculation, the centroid position of a distorted beam image received by the beam receiving module 4 is calculated and statistically analyzed, and the calculated centroid position is compared with the centroid position of a reference image to obtain a line of sight error distribution rule of the probe beams, so that the line of sight error values of the probe beams after being influenced by the simulated cloud and fog environment and the aircraft flow-around field (after t is 15 s) are greatly increased, and the distribution randomness is strong.
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; while the invention has been described in detail and with reference to the foregoing embodiments, it will 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; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120330633A1 (en) * | 2011-06-21 | 2012-12-27 | Lockheed Martin Corporation | Scintillation generator for simulation of aero-optical and atmospheric turbulence |
| CN108444950A (en) * | 2018-05-21 | 2018-08-24 | 西安微普光电技术有限公司 | A kind of air water mist laser energy decaying simulator |
| 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 |
| CN216270004U (en) * | 2021-12-15 | 2022-04-12 | 中国航天空气动力技术研究院 | Target detection environment ground simulation system |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20120330633A1 (en) * | 2011-06-21 | 2012-12-27 | Lockheed Martin Corporation | Scintillation generator for simulation of aero-optical and atmospheric turbulence |
| CN108444950A (en) * | 2018-05-21 | 2018-08-24 | 西安微普光电技术有限公司 | A kind of air water mist laser energy decaying simulator |
| 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 |
| CN216270004U (en) * | 2021-12-15 | 2022-04-12 | 中国航天空气动力技术研究院 | Target detection environment ground simulation system |
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