High and low temperature target simulator and sensitive domain detection method

Abstract

The invention discloses a high and low temperature target simulator and a sensitive domain detection method, the high and low temperature target simulator comprises a lens cone, and the upper surface of the lens cone is provided with a through hole; the lens cone is provided with a light tube shell, the lower surface of the lens cone is provided with a base, and an optical system is arranged in the lens cone; a black body, a diaphragm mechanism and a photoelectric coupling assembly are sequentially arranged in the light tube shell from left to right; when product tracking is detected, a 1000-multiplying-power attenuation piece is additionally arranged on the phi 1.0 diaphragm hole, and radiation energy is reduced to obtain energy needed by product tracking. During sensitive region detection, a 100-multiplying-power attenuation sheet is additionally arranged in a phi0.2 diaphragm hole, so that energy required by a sensitive region of a product is obtained; spectral screening: screening spectral bands required by different products for testing by replacing secondary mirrors plated with transmission films of corresponding product specifications; product tracking energy and sensitive domain detection energy are accurately and effectively provided, detection of different test states of products is met, and performance detection of products of different specifications is also met.

Description

Technical Field

[0001] This invention relates to the field of infrared product testing technology, specifically to a high and low temperature target simulator and a sensitivity range detection method. Background Technology

[0002] Testing the special performance of products requires conducting high and low temperature tests within an incubator. Thermal differences in these environments significantly impact image quality, necessitating the selection of materials with very low coefficients of thermal expansion to minimize these differences. Furthermore, the optical system must be simple in structure, provide excellent imaging, be easily adjustable, compact, and lightweight to meet the testing requirements of various products under different conditions. The incubator testing equipment comprises a turntable, translation stage, target simulator, and tooling fixtures. This equipment occupies a significant portion of the space. Due to the limited size of the incubator, the overall dimensions of the target simulator should be less than or equal to 180×150×150mm, and the product requires a focal length greater than or equal to 320mm. The product tracking conditions are set as follows: aperture 1.0mm, temperature 300℃, target rotation; and the sensitivity detection conditions are set as follows: aperture 0.2mm, temperature 300℃, target stationary. Because the target simulator has a short focal length and high radiated energy, it cannot meet the requirements for tracking and sensitive domain detection. The irradiance of a blackbody is proportional to the fourth power of its Kelvin temperature. Calculations show that when the blackbody temperature drops from 300℃ to 200℃, the energy decreases by only about half. In extremely hot environments, such as 75℃, a certain temperature difference between the blackbody and the background is required; simply cooling is insufficient to reduce the energy to the sensitive domain test value. Generally, energy attenuation is achieved by adding an adjustable aperture at the optical path exit or placing an attenuator between the blackbody and the aperture disk along the target optical axis. However, both methods attenuate the energy of the entire system. The energy received varies depending on the performance of the product being tested; for example, tracking performance requires a higher energy value, approximately 10. -9 W / cm 2 The received energy is relatively small during sensitive domain detection, approximately 10. -10 W / cm 2 The two methods receive energy at different magnitudes and have different energy attenuation rates. Furthermore, the attenuated energy cannot simultaneously meet the energy requirements for product tracking and sensitive domain detection. Additionally, different product models have different response bands, making it difficult for a single target simulator to achieve different wavelength windows. Summary of the Invention

[0003] The purpose of this invention is to overcome the shortcomings of existing technologies and provide a high and low temperature target simulator and a sensitive domain detection method. This method enables the screening of different wavelength windows, allows for the testing of products of different specifications, and accurately and effectively provides the product tracking energy, sensitive domain detection energy, and different wavelength windows required for different product models. It not only meets the testing requirements of products under different testing conditions but also meets the performance testing requirements of products of different specifications. It rigorously examines the performance of different product models in extreme high and low temperature environments, such as -50℃ and 75℃, and repairs and improves products that do not meet the requirements, thus playing a role in environmental testing and screening.

[0004] To achieve the above objectives, the present invention adopts the following technical solution: a high and low temperature target simulator, comprising a mirror tube, wherein the mirror tube is a hollow cylindrical structure with open ends, and a through hole is provided on the upper surface of the mirror tube; a light tube housing is provided above the mirror tube, the light tube housing is integrated with the mirror tube through a light tube seat, a base is provided on the lower surface of the mirror tube, and an optical system is provided inside the mirror tube; The optical system includes a primary mirror mount at the left end of the lens barrel, a primary mirror mounted on the primary mirror mount, an elliptical mirror mounted to the right rear of the primary mirror via an elliptical mirror mount, the elliptical mirror being located below the through-hole of the lens barrel, a secondary mirror mount at the right end of the lens barrel, and a replaceable secondary mirror at the outward-facing end of the secondary mirror mount. The secondary mirror 5 is a zinc sulfide corrective lens with a transmission coating on its surface. A plane mirror mount is located in the middle of the other end of the secondary mirror mount, and the plane mirror is integrated with the secondary mirror mount via the plane mirror mount. The horizontal extensions of the centers of the primary mirror, elliptical mirror, secondary mirror, and plane mirror are located on the same horizontal plane. The blackbody, aperture mechanism, and optocoupler assembly are arranged sequentially from left to right inside the optical tube housing; The radiation opening of the blackbody coincides with the through hole of the lens tube and the vertical line of the center of the elliptical mirror. An aviation plug and an observation lens are provided on one side of the light tube housing. A drying seat is provided between the observation lens and the light tube housing, and a desiccant is provided in the drying seat. The blackbody includes a radiation cavity core, a heating element, a heat insulation component, a heat dissipation component, a housing, a high-precision temperature controller, a solid-state relay, a temperature measuring element, and a calibration element; the blackbody is fixed to the optical tube socket via an adapter plate; The aperture mechanism includes an aperture disk and a stepper motor. The stepper motor drives the aperture disk to rotate through a wheel axle. Aperture holes are evenly distributed near the edge of the aperture disk. Attenuation plates with different attenuation factors are added to different aperture holes as needed. One end of the aperture disk is located below the radiation opening of the blackbody. The optocoupler assembly includes an optocoupler bracket, an optocoupler, and an optocoupler plate. The optocoupler bracket is disposed on one side of the stepper motor, and the optocoupler is disposed on the lower end of the optocoupler bracket facing the stepper motor. The optocoupler plate is bolted to the wheel axle disk of the stepper motor. The zero-crossing point is determined by detecting the change in the output signal of the optocoupler. That is, when the optocoupler plate passes the optocoupler, the AC voltage waveform suddenly changes, triggering the optocoupler switch to act and determining the zero position.

[0005] Furthermore, a cover is provided at the left end of the mirror tube, and the main reflector is made of K glass; the end of the main reflector facing the elliptical reflector is set as a concave surface, and a window pressure ring is provided between the secondary mirror and the secondary mirror mount; the mirror surfaces of the main reflector, the elliptical reflector, and the plane reflector are all aluminum-plated surfaces.

[0006] Furthermore, in the radiation cavity core of the blackbody, the distance between the emitting surface of the blackbody and the aperture disk is d0, d0=15mm, and the diameter of the emitting surface φ=12mm; the cavity shape of the blackbody adopts a combination of cylindrical and conical shapes, the material is SiC ceramic material, the temperature controller of the blackbody adopts PID closed-loop temperature control, the power supply is 220V AC power supply, the temperature sensor is PT100 platinum resistance thermometer, and it has a remote control interface.

[0007] Furthermore, the aperture diameters of the aperture holes on the aperture disk include Φ0mm, Φ0.2mm, Φ0.266mm, Φ0.64mm, and Φ1.0mm. The aperture plate is made of 0.1mm thick aluminum sheet with a blackened surface and laser drilling technology is used to attach a layer of polytetrafluoroethylene on the side close to the black body.

[0008] A method for detecting the sensitivity range of a high and low temperature target simulator includes the following steps: Energy attenuation: When detecting product tracking, a 1000x attenuator is installed on the Ф1.0 aperture to reduce the radiated energy and obtain the energy required for product tracking; when detecting the sensitive region, a 100x attenuator is installed on the Ф0.2 aperture to obtain the energy required for the product's sensitive region; by adding attenuators with different attenuation factors to different apertures, energy values ​​for different detection states are obtained, enabling performance detection under different states; Spectral screening: Since secondary mirror 5 uses a zinc sulfide lens and is coated with a transmission film of the corresponding specification, it can be used to test products of different specifications. By replacing the secondary mirror with a transmission film of the corresponding product specification, it has different light wave transmission effects, selectively transmits or blocks light of specific wavelengths or bands, thereby adjusting the spectral distribution, realizing wavelength selective control, and realizing the functions of spectral dispersion and stray light filtering, and screening the spectral bands required by different products for testing.

[0009] Working principle: Its optical principle is that the light source illuminates the pinhole aperture. The aperture disk is equipped with multiple apertures, which can be rotated to be parallel to the optical axis, forming a point light source that diverges outward. After passing through the elliptical mirror and the plane mirror, the light finally converges on the concave surface of the primary mirror to form parallel light, thus achieving the parallel light required in the technical specifications. The light is transmitted to the product under test through the secondary mirror. By adding energy attenuators of different magnifications along the target optical axis in the parallel optical path, different spectral radiation energies can be obtained. The secondary mirror surface along the target optical axis in the parallel optical path is coated with a transmission film corresponding to the specifications of the product being tested. This allows for the selection of different spectral bands for transmission, improving transmittance, reducing the number of optical components, and reducing weight, thus meeting the testing requirements of different product models and different testing conditions.

[0010] The beneficial effects of this invention are as follows: Under different test conditions, placing attenuators with different attenuation factors along the target optical axis at different apertures not only does not affect tracking but also enables sensitive domain detection. By replacing secondary mirrors coated with transmission films of different specifications, different wavelength windows can be selected, enabling testing of products of different specifications. It accurately and effectively provides product tracking energy, sensitive domain detection energy, and different wavelength windows required for different product models. This not only satisfies the testing requirements of products under different test conditions but also meets the performance testing requirements of products of different specifications. It rigorously examines the performance of different product models in extreme high and low temperature environments, such as -50℃ and 75℃, and repairs and improves products that do not meet the requirements, thus playing a role in environmental testing and screening. Areas not detailed in this invention are existing commonly used technologies. Attached Figure Description

[0011] The present invention will be further described below with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the rear view structure; Figure 2 This is a front view structural diagram; Figure 3 yes Figure 2 Schematic diagram of the cross-sectional structure along the middle AA direction; Figure 4 This is a schematic diagram of the three-dimensional structure of the lens barrel; Figure 5 This is a schematic diagram of the three-dimensional structure of the final assembly. Figure 6 This is a schematic diagram of a parallel optical path; Figure 7 This is the transfer function diagram of the primary mirror at a low temperature of -55°C; Figure 8 This is the transfer function diagram of the primary reflector at a high temperature of 75°C; Figure 9 This is a top view of the internal structure of the optical tube housing; In the diagram: 1. Lens tube; 2. Base; 3. Optical tube housing; 4. Optical tube mount; 5. Secondary mirror; 6. Window retaining ring; 7. Secondary mirror mount; 8. Plane mirror mount; 9. Primary mirror mount; 10. Plane mirror; 11. Elliptical mirror mount; 12. Elliptical mirror; 13. Blackbody; 14. Stepper motor; 15. Aperture plate; 16. Optical coupler bracket; 17. Optocoupler; 18. Optical coupler chip; 19. Aviation plug; 20. Observation mirror; 21. Cover; 22. Detailed Implementation

[0012] The present invention will be further described in detail below with reference to embodiments and specific implementation methods: Example 1

[0013] A high and low temperature target simulator includes a lens tube 1, which is a hollow cylindrical structure with open ends. A through hole is provided on the upper surface of the lens tube 1. A light tube housing 3 is provided on the upper part of the lens tube 1. The light tube housing 3 is connected to the lens tube 1 by a light tube seat 4. A base 2 is provided on the lower surface of the lens tube 1. An optical system is provided inside the lens tube 1. To minimize light energy attenuation while maintaining transmittance in the corresponding wavelength band, the optical system employs an off-axis parabolic mirror to generate parallel light. The system includes a primary mirror mount 9 at the left end of a lens barrel 1, a primary mirror 10 mounted on the primary mirror mount 9, and an elliptical mirror 13 mounted to the right rear of the primary mirror 10 via an elliptical mirror mount 12. The elliptical mirror 13 is located below the through-hole of the lens barrel 1. A secondary mirror mount 7 is located at the right end of the lens barrel 1, with a replaceable secondary mirror 5 mounted on its outer end face. The secondary mirror 5 is a zinc sulfide lens with a transmission coating. A plane mirror mount 8 is mounted on the inner end face of the secondary mirror mount 7, and a plane mirror 11 is integrated with the secondary mirror mount 7 via the plane mirror mount 8. The horizontal extensions of the centers of the primary mirror 10, elliptical mirror 13, secondary mirror 5, and plane mirror 11 are located on the same horizontal plane. Its optical principle is that the light source illuminates the aperture of the aperture mechanism, forming a point light source that diverges outward. After being reflected by the elliptical mirror 13 and the plane mirror 11, the light finally converges to the main mirror 10 to form parallel light, thus achieving the parallel light required by the technical specifications. Figure 6 As shown; Thermal difference in high and low temperature environments is a significant factor affecting image quality. The optical system uses an off-axis parabolic mirror to generate parallel light, and the primary mirror 10 is made of K9 glass with a very low coefficient of thermal expansion. The transfer function of the primary mirror 10 at low temperature (-5°C) and high temperature (75°C) is as follows: Figure 7 , Figure 8As shown, the end of the primary reflector 10 facing the plane reflector 8 is set as a concave surface. The mirror surfaces of the primary reflector 10, the elliptical reflector 13, and the plane reflector 11 are all aluminum-plated surfaces, which have good reflectivity: efficiency > 95%, which can ensure that the energy in this band can be output well. The secondary mirror 5 is placed in the parallel optical path along the target optical axis, and its surface is coated with transmission films of different specifications. Therefore, the lens can both achromatic and select wavelength windows of different specifications, reduce the number of optical elements, and reduce weight.

[0014] Inside the light tube housing 3, from left to right, a blackbody 14, an aperture mechanism, and an optocoupler are arranged sequentially. The radiation opening of the blackbody 14 coincides with the through hole of the lens tube 1 and the vertical line of the center of the elliptical reflector 13. An aviation plug 20 and an observation mirror 21 are arranged on one side of the light tube housing 3. A drying seat is arranged between the observation mirror 21 and the light tube housing 3, and a desiccant is provided in the drying seat.

[0015] The blackbody 14 includes a radiation cavity core, a heating element, a heat insulation component, a heat dissipation component, a housing, a high-precision temperature controller, a solid-state relay, a temperature measuring element, and a calibration element. The heating element uses an electric heating device and can support heating up to 1000 degrees Celsius. The blackbody 14 is fixed to the optical tube socket 4 via an adapter plate. In the radiation cavity core of the blackbody 14, in order to achieve good energy uniformity at the aperture and prevent the aperture plate from overheating, the distance between the emitting surface of the blackbody 14 and the aperture disk 16 is d0, where d0 = 15 mm, and the diameter of the emitting surface φ = 12 mm. The cavity of the blackbody 14... The body shape combines cylindrical and conical forms, and the material is SiC ceramic. The temperature controller of the blackbody 14 adopts PID closed-loop temperature control. The temperature controller is installed on the control box panel of the target simulation system in the cabinet. It has manual adjustment buttons and a temperature parameter display panel, as well as a remote control interface. In actual use, it communicates with the control computer through the RS422 interface. The control program completes the control command issuance and parameter reading, and displays them centrally on the software interface. The temperature sensing element is a PT100 platinum resistance thermometer, and the power supply is 220V AC.

[0016] The aperture mechanism includes an aperture disk 16 and a stepper motor 15. The stepper motor 15 drives the aperture disk 16 to rotate via a wheel axle. The aperture disk 16 has evenly distributed groove-shaped aperture holes near its edge. Different attenuation factors are added to different aperture holes according to requirements. The aperture hole at one end of the aperture disk 16 is located below the radiation opening of the blackbody 14, used to adjust the light intensity. The aperture holes on the aperture disk 16 have diameters of Φ0mm, Φ0.2mm, Φ0.266mm, and Φ0.64mm. The aperture has a diameter of Φ1.0mm, and the repeatability of the aperture relative to the focal point is ±0.1mm. The aperture should be smooth and burr-free, and heat insulation measures should be taken around it to prevent heat radiation from the aperture itself. No other heat radiation should enter the optical system except for the aperture. The rotation radius of the aperture on the aperture disk 16 is 40mm. The stepper motor 15 used has a step angle of 1.8°, a driver microstepping of 16, and a gear ratio of 1:4. For each step of the stepper motor, the aperture rotates by the following angle: 1.8 ÷ 16 ÷ 4 = 0.028° The positioning accuracy of the aperture plate 16 is calculated based on one step angle, and the repeatability of the aperture hole is: 40 × 3.14 × 0.028 ÷ 180 = 0.02 (mm) The aperture is made of 0.1mm thick aluminum sheet with a blackened surface. It is made using laser drilling technology, and the edges of the holes are smooth and burr-free. A layer of polytetrafluoroethylene is attached to the side of the aperture closest to the blackbody 14 to reduce the temperature rise of the aperture due to blackbody radiation.

[0017] The optocoupler assembly includes an optocoupler bracket 17, an optocoupler 18, and an optocoupler plate 19. The optocoupler bracket 17 is disposed on one side of the stepper motor 15. The optocoupler 18 is disposed on the lower end of the optocoupler bracket 17 facing the stepper motor 15. The optocoupler plate 19 is bolted to the wheel axle disk of the stepper motor 15. As the motor rotates, the optocoupler 18 remains stationary. When the optocoupler plate 19 passes the optocoupler 18, the AC voltage waveform of the optocoupler 18 suddenly changes, triggering the optocoupler switch to operate and determining the zero position. Example 2

[0018] Product testing requires tracking energy and sensitivity range energy. Taking a product responding to the 3~5µm band as an example: Calculation of maximum radiant energy Infrared radiation calculations are proportional to the fourth power of temperature, with a radiation band of 3μm–5μm, a blackbody temperature of 300℃, and an aperture of 1mm. The aperture value is obtained by referring to a table based on temperature. Maximum radiant energy calculation: a) Converted to thermodynamic temperature: T = 300 + 273 = 573K b) Fiber retardation in the 3μm–5μm band:

[0019] c) Auxiliary flux of the aperture:

[0020] d) Auxiliary flux emitted through the optical system:

[0021] e) The simulator emits light as If the central shield is Φ32mm, then the actual output flux is:

[0022] f) Energy received by the product, with a product diameter of 5mm.

[0023]

[0024] g) Calculation based on the receiving area: Assuming a diameter of 1cm, the irradiance is: / cm 2

[0025] 2. Calculation of minimum radiated energy Given a blackbody temperature of 300℃, an aperture of 0.2mm, and a radiation band of 3μm~5μm, the minimum emissivity is calculated as follows: a) Converted to thermodynamic temperature: T = 300 + 273 = 573K b) Auxiliary output in the 3~5μm band:

[0026] c) Auxiliary flux of the aperture:

[0027] d) Auxiliary flux emitted through the optical system:

[0028] e) The simulator emits light as If the central shield is Φ32mm, then the actual output flux is:

[0029] f) Energy received by the product, with a product diameter of 5mm.

[0030]

[0031] g) Calculation based on the receiving area: Assuming a diameter of 1cm, the irradiance is: / cm2

[0032] Product tracking requires significant energy, with an irradiance of approximately 10. -9 W / cm 2 Based on a maximum irradiance of 1.4 × 10^(-6) W / cm^2, this irradiance is greater than the product tracking energy; however, the required energy is smaller for sensitive domain detection, with an irradiance of approximately 10 W / cm^2. -10 W / cm 2 Based on the minimum irradiance of 3.43575×10^(-8)w / cm2, the minimum irradiance is still greater than the energy value detected in the sensitive area. According to actual measurements, both require energy attenuation, but the attenuation ratios are different. Adding an adjustable aperture at the secondary mirror 5 at the optical path exit, or placing an attenuator between the blackbody and the aperture disk along the target optical axis for energy attenuation, would attenuate the entire system's energy at the same ratio. However, the energy received when detecting different product performance characteristics varies, and the energy attenuation ratios also differ. Furthermore, the attenuation energy cannot simultaneously meet the energy requirements for product tracking and sensitive area detection, making it impossible to rigorously examine product performance. Therefore, when designing the target simulator, adding a 1000x attenuator to the Ф1.0 aperture for product tracking can reduce the irradiance and achieve the desired effect. Product tracking irradiance: By adding a 100x attenuator to a Ф0.2 aperture in the detection sensitive region, the irradiance in the product's sensitive region can be obtained. By adding attenuators with different attenuation factors to different apertures, energy values ​​for different detection states can be obtained. Simultaneously, by replacing the secondary mirror 5 with the corresponding transmission film, light of specific wavelengths or bands can be selectively transmitted or blocked, thereby adjusting the spectral distribution, achieving wavelength selective control, and realizing functions such as spectral dispersion and stray light filtering. For example, when testing products in the 3-5µm band, the secondary mirror 5 with a 3-5µm transmission film is used; when testing products in the 8-12µm band, the secondary mirror 5 with an 8-12µm transmission film is used. For testing different product specifications, the required spectral bands can be effectively selected for testing. One target simulator meets the testing needs of multiple products and different states.

[0033] The above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A high and low temperature target simulator, comprising a microscope tube (1), characterized in that: The lens tube (1) is a hollow cylindrical structure with open ends. A through hole is provided on the upper surface of the lens tube (1). A light tube housing (3) is provided above the lens tube (1). The light tube housing (3) is connected to the lens tube (1) as a whole through a light tube seat (4). A base (2) is provided on the lower surface of the lens tube (1). An optical system is provided inside the lens tube (1). The optical system includes a primary mirror mount (9) at the left end of the lens barrel (1), a primary mirror (10) on the primary mirror mount (9), an elliptical mirror (13) on the right rear of the primary mirror (10) via an elliptical mirror mount (12), the elliptical mirror (13) being located below the through hole of the lens barrel (1), a secondary mirror mount (7) at the right end of the lens barrel (1), a replaceable secondary mirror (5) at the outward end of the secondary mirror mount (7), the secondary mirror (5) being a zinc sulfide corrector lens with a transmission coating on its surface, a plane mirror mount (8) at the middle of the other end of the secondary mirror mount (7), and a plane mirror (11) being connected to the secondary mirror mount (7) via the plane mirror mount (8); the horizontal extensions of the centers of the primary mirror (10), the elliptical mirror (13), the secondary mirror (5), and the plane mirror (11) are located on the same horizontal plane; The blackbody (14), aperture mechanism, and optocoupler assembly are arranged sequentially from left to right inside the optical tube housing (3); The radiation opening of the blackbody (14) coincides with the through hole of the lens tube (1) and the vertical line of the center of the elliptical mirror (13). An aviation plug (20) and an observation mirror (21) are provided on one side of the light tube housing (3). A drying seat is provided between the observation mirror (21) and the light tube housing (3), and a desiccant is provided in the drying seat. The blackbody (14) includes a radiation cavity core, a heating element, a heat insulation component, a heat dissipation component, a housing, a high-precision temperature controller, a solid-state relay, a temperature measuring element, and a calibration element; the blackbody (14) is fixed to the optical tube socket (4) via an adapter plate. The aperture mechanism includes an aperture disk (16) and a stepper motor (15). The stepper motor (15) drives the aperture disk (16) to rotate through a wheel axle. The aperture disk (16) has aperture holes evenly distributed near the edge. Attenuation plates with different attenuation ratios are added to different aperture holes as needed. One end of the aperture disk (16) is located below the radiation opening of the blackbody (14). The optocoupler assembly includes an optocoupler bracket (17), an optocoupler (18), and an optocoupler plate (19). The optocoupler bracket (17) is located on one side of the stepper motor (15). The optocoupler (18) is located on the side of the lower end of the optocoupler bracket (17) facing the stepper motor (15). The optocoupler plate (19) is mounted on the wheel axle disk of the stepper motor (15) by bolts. The zero-crossing point is determined by detecting the change in the output signal of the optocoupler (18). That is, when the optocoupler plate (19) passes the optocoupler (18), the AC voltage waveform suddenly changes, triggering the optocoupler switch to act and determining the zero position.

2. The high and low temperature target simulator according to claim 1, characterized in that: The left end of the mirror tube (1) is provided with a cover (22), the main reflector (10) is made of K9 glass; the end of the main reflector (10) facing the elliptical reflector (13) is set as a concave surface, and a window pressure ring (6) is provided between the secondary mirror (5) and the secondary mirror base (7). The mirror surfaces of the main reflector (10), the elliptical reflector (13) and the plane reflector (11) are all aluminum-plated surfaces.

3. The high and low temperature target simulator according to claim 1, characterized in that: In the radiation cavity core of the blackbody (14), the distance between the emitting surface of the blackbody (14) and the aperture disk (16) is d0, d0=15mm, and the diameter of the emitting surface φ=12mm; the cavity shape of the blackbody (14) adopts a combination of cylindrical and conical shape, and the material is SiC ceramic material. The temperature controller of the blackbody (14) adopts PID closed-loop temperature control, the power supply is 220V AC power supply, the temperature sensor is PT100 platinum resistance thermometer, and it has a remote control interface.

4. A high and low temperature target simulator according to claim 1, characterized in that: The aperture diameters of the aperture plates on the aperture disk (16) include Φ0mm, Φ0.2mm, Φ0.266mm, Φ0.64mm and Φ1.0mm. The aperture plates are made of 0.1mm thick aluminum sheets with blackened surfaces. A layer of polytetrafluoroethylene is attached to the side near the blackbody (14) using laser drilling technology.

5. A sensitivity range detection method based on the high and low temperature target simulator according to any one of claims 1-4, characterized in that: Includes the following steps: Energy attenuation: When detecting product tracking, a 1000x attenuator is installed on the Ф1.0 aperture to reduce the radiated energy and obtain the energy required for product tracking; when detecting the sensitive region, a 100x attenuator is installed on the Ф0.2 aperture to obtain the energy required for the product's sensitive region; by adding attenuators with different attenuation factors to different apertures, energy values ​​for different detection states are obtained, enabling performance detection under different states; Spectral screening: Since the secondary mirror uses a zinc sulfide lens and is coated with a transmission film of the corresponding specification, it can be used to test different specifications of products. By replacing the secondary mirror with a transmission film of the corresponding product specification, it has different light wave transmission effects, selectively transmits or blocks light of specific wavelengths or bands, thereby adjusting the spectral distribution, realizing wavelength selective control, realizing the functions of spectral dispersion and stray light filtering, and screening the required spectral bands of different products for testing.

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