Near space high-temperature optical window imaging performance evaluation device and evaluation method

Abstract

The invention relates to the technical field of hypersonic optical remote sensing imaging, in particular to a near space high-temperature optical window imaging performance evaluation device and method, and the device comprises a dynamic target generator, an ultra-high temperature experiment box, a temperature-height experiment box, a light adjusting assembly, a photoelectric load and a control system. The dynamic target generator is used for generating a dynamic target for simulating a near space target; the ultra-high temperature experiment box is used for carrying and heating the optical window; the temperature-height experiment box is used for simulating the temperature and air pressure of a near space; the light adjusting assembly is used for guiding the light of the dynamic target to the optical window; the photoelectric load is used for receiving the light penetrating through the optical window and forming a dynamic target image; the control system is used for analyzing a dynamic target image formed by the photoelectric load. Therefore, a high-Mach-number complex flight environment of an aircraft in a near space can be efficiently and accurately simulated on the ground, and the dynamic optical imaging performance of the optical window at different temperatures and air pressures can be rapidly and comprehensively evaluated.

Description

Technical Field

[0001] The present invention relates to the field of hypersonic optical remote sensing imaging technology, and specifically provides a near-space high-temperature optical window imaging performance evaluation device and evaluation method, which are suitable for the research and application of high-temperature optical windows in the fields of aerospace, national defense, etc. Background Art

[0002] With the rapid development of aviation technology, the environment faced by near-space vehicles when performing high-speed flight missions is becoming increasingly complex. Under high Mach number flight conditions, the external structure of the vehicle, especially the optical window, needs to withstand extremely high aerodynamic thermal effects, resulting in a significant increase in the window surface temperature. This extreme high temperature environment has a significant impact on the transmittance, structural stability and imaging quality of the optical window, which in turn affects the reconnaissance and surveillance performance of the aircraft, especially in the imaging quality of the visible light, medium-wave infrared and long-wave infrared bands.

[0003] The existing optical window performance evaluation method mainly relies on actual flight tests, but due to the cumbersome and costly preparation of high Mach number flight platforms, this method faces many challenges in technical verification and window material screening. At the same time, the environmental variables in flight tests are complex and difficult to accurately control, making the experimental results uncertain and difficult to repeat, and unable to meet the needs of optical window performance optimization design and rapid verification. Summary of the invention

[0004] In order to solve the above problems, the present invention provides a near-space high-temperature optical window imaging performance evaluation device and evaluation method, which can efficiently and accurately simulate the complex flight environment of an aircraft with high Mach number in near-space in a ground laboratory, and quickly and comprehensively evaluate the dynamic optical imaging performance of the optical window at different temperatures and air pressures.

[0005] The present invention provides a near-space high-temperature optical window imaging performance evaluation device, which specifically includes a dynamic target generator, an ultra-high temperature test box, a temperature-altitude test box, a light adjustment component, an optoelectronic load and a control system. The dynamic target generator is arranged at the starting position of the optical path of the evaluation device, and the dynamic target generator is used to generate a dynamic target simulating a near-space target; the ultra-high temperature test box is arranged in front of the dynamic target generator, and the ultra-high temperature test box is used to carry and heat the optical window; the temperature-altitude test box is arranged in front of the ultra-high temperature test box, and the temperature-altitude test box is used to simulate the temperature and air pressure of the near space; the light adjustment component is arranged between the dynamic target generator and the ultra-high temperature test box, and the light adjustment component is used to guide the light of the dynamic target to the optical window; the optoelectronic load is arranged inside the temperature-altitude test box, and the optoelectronic load is used to receive the light passing through the optical window and form a dynamic target image; the control system signal is connected to the dynamic target generator, the ultra-high temperature test box, the temperature-altitude test box and the optoelectronic load, and the control system is used to analyze the dynamic target image formed by the optoelectronic load, so as to evaluate the imaging performance of the optical window.

[0006] Preferably, the ultra-high temperature experimental box includes a first box body, a radiation heating source and a temperature sensor, the first box body is provided with a first optical entrance and a first optical exit relatively to each other, so that an imaging channel is formed between the first optical entrance and the first optical exit, a cooling system is provided on the first optical entrance, and the optical window is connected to the first optical exit; the radiation heating source is provided inside the first box body, and the radiation heating source is used to heat the optical window; the temperature sensor is provided inside the first box body, and the temperature sensor is used to monitor the temperature of the imaging channel; wherein the radiation heating source and the temperature sensor signals are connected to the control system.

[0007] Preferably, the cooling system includes a cooling plate, a heat dissipation component and a cooling pipe, wherein the cooling plate is arranged outside the imaging channel; the heat dissipation component is used for exchanging heat with the outside world; the cooling pipe connects the cooling plate and the heat dissipation component, the interior of the cooling pipe is filled with a cooling medium, and a cooling pump and a temperature control valve are also arranged on the cooling pipe; wherein the cooling pump and the temperature control valve signals are connected to the control system.

[0008] Preferably, the temperature-altitude test box includes a second box body, a temperature control system and a pressure regulating system. The second box body is provided with a second optical entrance, and the second optical entrance is located in front of the optical window; the temperature control system is arranged inside the second box body, and the temperature control system is used to adjust the temperature inside the second box body; the pressure regulating system is arranged inside the second box body, and the pressure regulating system is used to adjust the air pressure inside the second box body; wherein, the temperature control system and the pressure regulating system signals are connected to the control system.

[0009] Preferably, the light adjustment assembly includes a collimator and a folding mirror assembly, the collimator is arranged between the dynamic target generator and the cooling system, and the collimator is used to collimate the light of the dynamic target; the folding mirror assembly is arranged between the collimator and the cooling system, and the folding mirror is used to guide the light of the dynamic target collimated by the collimator to the optical window.

[0010] Preferably, the optoelectronic payload includes a high-precision imaging system and a data acquisition system. The high-precision imaging system is used to receive light passing through the optical window and form a dynamic target image; the data acquisition system is used to store the dynamic target image.

[0011] The present invention provides a near-space high-temperature optical window imaging performance evaluation method, which specifically includes the following steps: S102: Generate a dynamic target simulating a nearby space target; S104: collimating the light of the dynamic target so that the light passes through the optical window in the form of parallel light; S106: heating the optical window to an experimental temperature; S108: adjusting the direction of the light path, receiving the light passing through the optical window under high temperature disturbance and forming a dynamic target image; S110: adjusting temperature parameters and air pressure parameters to obtain dynamic target images formed through the optical window at different temperatures and air pressures; S112: Analyze the transmission wavefront change data and imaging performance index of the dynamic target image, and evaluate the imaging performance of the optical window according to the transmission wavefront change data and the imaging performance index.

[0012] Preferably, the transmission wavefront change data include root mean square value and peak-to-valley difference; and the imaging performance index includes modulation transfer function and point spread function.

[0013] Compared with the prior art, the present invention can achieve the following beneficial effects: (1) The present invention provides a near-space high-temperature optical window imaging performance evaluation device, which can efficiently and accurately simulate the complex high-Mach number flight environment of an aircraft in near-space in a ground laboratory, and quickly and comprehensively evaluate the dynamic optical imaging performance of the optical window at different temperatures and air pressures, thereby significantly reducing the problems of multiple preparation factors, complex work, and high costs before the aircraft performs a flight mission, and improving the accuracy and repeatability of ground experimental verification.

[0014] (2) The present invention provides a near-space high-temperature optical window imaging performance evaluation device, which also includes a cooling system, which is used to cool the imaging channel to prevent the high temperature of the ultra-high temperature test box from affecting the light adjustment components and the laboratory environment.

[0015] (3) The present invention provides a near-space high-temperature optical window imaging performance evaluation device, which also includes a collimator, which is used to collimate the light of a dynamic target so that the dynamic target light can be evenly distributed and stably incident on the optical window in the form of parallel light, thereby simulating a target at infinity.

[0016] (4) The present invention provides a near-space high-temperature optical window imaging performance evaluation device, which also includes a folding mirror assembly, which is used to change the direction of the light path and guide the collimated dynamic target light to the optical window, so that the light path has flexibility. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] The accompanying drawings constituting a part of the present invention are used to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation of the present invention. In the accompanying drawings: Figure 1 It is a schematic structural diagram of a near-space high-temperature optical window imaging performance evaluation device provided by an embodiment of the present invention; Figure 2 It is a structural schematic diagram of an ultra-high temperature test chamber and a cooling system provided by an embodiment of the present invention; Figure 3 is a schematic cross-sectional structure diagram of an ultra-high temperature test chamber and a cooling system provided by an embodiment of the present invention; Figure 4 It is a schematic diagram of the structure of a temperature-altitude test box provided in an embodiment of the present invention; Figure 5 is a schematic cross-sectional structure diagram of a temperature-altitude test box provided in an embodiment of the present invention; Figure 6 It is a flow chart of a method for evaluating the imaging performance of a near-space high-temperature optical window provided in an embodiment of the present invention.

[0018] Reference numerals include: 1 dynamic target generator, 2 ultra-high temperature test box, 21 first box, 22 radiation heating source, 3 temperature-altitude test box, 31 second box, 4 light adjustment component, 41 parallel light tube, 421 first folding mirror, 422 second folding mirror, 5 photoelectric load, 7 optical window, 8 cooling system, 81 cooling plate, 91 first vibration isolation platform, 92 second vibration isolation platform. DETAILED DESCRIPTION

[0019] In order to make the purpose, technical scheme and advantages of the present invention clearer, the present invention is further described in detail below in conjunction with the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and do not constitute a limitation of the present invention. Wherein similar elements in different embodiments use associated similar element numbers. In the following embodiments, many detailed descriptions are to enable the present invention to be better understood. However, those skilled in the art can easily recognize that some of the features can be omitted in different situations, or can be replaced by other elements, materials, methods. In some cases, some operations related to the present invention are not shown or described in the specification, this is to avoid the core part of the present invention being overwhelmed by too much description, and for those skilled in the art, it is not necessary to describe these related operations in detail, and they can fully understand the related operations according to the description in the specification and the general technical knowledge in the art.

[0020] It should be noted that, in the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other to form various implementation methods. At the same time, the steps or actions in the method description can also be interchanged or adjusted in a manner that is obvious to those skilled in the art. Therefore, the various sequences in the specification and the drawings are only for the purpose of clearly describing a certain embodiment and are not meant to be a necessary sequence, unless otherwise specified that a certain sequence must be followed.

[0021] In the description of the present invention, it should be understood that the terms "center", "longitudinal", "lateral", "length", "width", "thickness", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", "clockwise", "counterclockwise", etc., indicating the orientation or positional relationship, are based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as limiting the present invention. In addition, the terms "first", "second", etc. are only used for descriptive purposes, and cannot be understood as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Therefore, the features defined as "first", "second", etc. may explicitly or implicitly include one or more of the features. In the description of the present invention, unless otherwise specified, the meaning of "multiple" is two or more.

[0022] In the description of the present invention, it should be noted that, unless otherwise clearly specified and limited, the terms "installed", "connected", and "connected" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal communication of two components. For ordinary technicians in this field, the specific meanings of the above terms in the present invention can be understood by specific circumstances.

[0023] The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with embodiments.

[0024] like Figure 1 , Figure 2 and Figure 4 As shown, an embodiment of the first aspect of the present invention provides a near-space high-temperature optical window imaging performance evaluation device, which specifically includes a dynamic target generator 1, an ultra-high temperature test box 2, a temperature-altitude test box 3, a light adjustment component 4, an optoelectronic load 5 and a control system. The dynamic target generator 1 is set at the starting position of the optical path of the evaluation device, and the dynamic target generator 1 is used to generate a dynamic target simulating a near-space target; wherein the dynamic target has a stable high contrast with the background environment; in the simulated near-space scene, by controlling the position and moving speed of the dynamic target simulated by the dynamic target generator 1, it is possible to simulate the target detected by the aircraft when flying at a high Mach number.

[0025] like Figure 1 and Figure 2 As shown, the ultra-high temperature test box 2 is arranged in front of the dynamic target generator 1. The ultra-high temperature test box 2 is used to carry and heat the optical window 7 by radiation or other means. The ultra-high temperature test box 2 can heat the surface of the optical window 7 to a high temperature state close to that during actual high Mach number flight, thereby simulating the temperature distribution of the optical window 7 under the aerodynamic thermal effect. The temperature-altitude test box 3 is arranged in front of the ultra-high temperature test box 2. The temperature-altitude test box 3 is used to simulate the temperature and air pressure of the near space. The light adjustment component 4 is arranged between the dynamic target generator 1 and the ultra-high temperature test box 2. The light adjustment component 4 is used to guide the light of the dynamic target to the optical window 7, so as to observe the dynamic target through the optical window 7 under high temperature disturbance and evaluate the imaging performance of the optical window 7.

[0026] like Figure 1 and Figure 4As shown, the photoelectric load 5 is arranged at the end position of the optical path of the experimental device. The photoelectric load 5 is used to receive the light passing through the optical window 7 and form a dynamic target image, and monitor the imaging quality of the optical window 7 under high temperature disturbance in real time. The photoelectric load 5 is arranged inside the temperature-altitude test box 3, so that the photoelectric load 5 can operate under the temperature and air pressure conditions simulating the near space, thereby ensuring a comprehensive evaluation of the dynamic imaging performance of the optical window 7 during high Mach number flight, and discovering the imaging distortion, jitter and other phenomena that may occur in the optical window 7 under extreme temperature and pressure. The control system signal is connected to the dynamic target generator 1, the ultra-high temperature test box 2, the temperature-altitude test box 3 and the photoelectric load 5. The control system is used to analyze the dynamic target image formed by the photoelectric load 5, so as to evaluate the imaging performance of the optical window 7.

[0027] Therefore, the present invention provides a near-space high-temperature optical window imaging performance evaluation device, which can efficiently and accurately simulate the complex flight environment of an aircraft with high Mach numbers in near-space in a ground laboratory, and quickly and comprehensively evaluate the dynamic optical imaging performance of the optical window 7 under different temperature and air pressure conditions, thereby significantly reducing the problems of many preparation factors, complex work, and high costs before the aircraft performs a flight mission, and improving the accuracy and repeatability of ground experimental verification.

[0028] like Figure 2 and Figure 3 As shown, the ultra-high temperature test box 2 includes a first box body 21, a radiation heating source 22 and a temperature sensor. A first optical inlet and a first optical outlet are relatively opened on the first box body 21, so that an imaging channel is formed between the first optical inlet and the first optical outlet, so that the light of the dynamic target generated by the dynamic target generator 1 can be transmitted to the optical window 7 through the imaging channel. A cooling system 8 is provided on the first optical inlet, and the cooling system 8 is used to cool the imaging channel to prevent the high temperature of the ultra-high temperature test box 2 from affecting the light adjustment component 4 and the laboratory environment. The optical window 7 is mounted on the first optical outlet, so that the radiation heating source 22 can radiate heat evenly to the surface of the optical window 7, thereby evaluating the surface accuracy and imaging performance of the optical window 7 under high temperature disturbance.

[0029] like Figure 3As shown, the radiation heating source 22 is arranged inside the first box 21, and is used to radiate and heat the optical window 7, so as to simulate the high temperature generated by the aerodynamic thermal effect when the aircraft flies at a high Mach number, and ensure that the experimental conditions are close to the actual flight state. Preferably, the radiation heating source 22 adopts a high-power radiation heating source 22, and the maximum heating temperature can reach 1200K. The temperature sensor is arranged inside the first box 21, and is used to monitor the temperature of the imaging channel in real time. Among them, the radiation heating source 22 and the temperature sensor signal are connected to the control system; by setting an intelligent control system, the heating power of the radiation heating source 22 can be automatically adjusted according to the monitoring result of the temperature sensor.

[0030] like Figure 1 , Figure 2 and Figure 3 As shown, the cooling system 8 includes a cooling plate 81, a heat dissipation component and a cooling pipe. The cooling plate 81 is arranged outside the imaging channel to receive the heat transferred by the imaging channel; the heat dissipation component is used to exchange heat with the outside world, and the cooling pipe connects the cooling plate 81 and the heat dissipation component. The interior of the cooling pipe is filled with a cooling medium, so as to realize the circulation of exchanging the heat absorbed by the cooling plate 81 to the external environment, thereby avoiding the temperature in the imaging channel area being too high. A cooling pump and a temperature control valve are also arranged on the cooling pipe. The cooling pump is used to drive the cooling medium to circulate in the cooling pipe; the cooling pump and the temperature control valve signals are connected to the control system. The cooling pump and the temperature control valve are controlled by the control system, and the flow rate of the cooling medium can be adjusted according to actual needs, so that the cooling system 8 can stably cool the light adjustment component 4 and ensure temperature stability.

[0031] like Figure 1 , Figure 4 and Figure 5 As shown, the temperature-altitude test box 3 includes a second box 31, a temperature control system and a pressure regulating system. A second optical entrance is provided on the second box 31, and the second optical entrance is located in front of the optical window 7, so that the light of the dynamic target can be received by the photoelectric load 5 arranged inside the second box 31 after passing through the optical window 7 under high temperature disturbance. The temperature control system is arranged inside the second box 31, and is used to adjust the temperature inside the second box 31; the pressure regulating system is arranged inside the second box 31, and is used to adjust the air pressure inside the second box 31. Among them, the temperature control system and the pressure regulating system signals are connected to the control system. Considering that the performance of the photoelectric load 5 is different at different flight speeds and altitudes, the temperature control system and the pressure regulating system are controlled by the control system, and the temperature parameters and air pressure parameters inside the second box 31 can be adjusted, thereby simulating the changes in the extravehicular environment when the aircraft flies from low altitude to high altitude at different flight speeds.

[0032] like Figure 1As shown, the light adjustment component 4 includes a collimator 41 and a folding mirror component. The collimator 41 is arranged between the dynamic target generator 1 and the cooling system 8. The collimator 41 is used to collimate the light of the dynamic target so that the light of the dynamic target can enter the optical window 7 in the form of parallel light, ensuring that the light is evenly distributed and stable when entering the optical window 7, that is, simulating a target at infinity. The folding mirror component is arranged between the collimator 41 and the cooling system 8, and is used to change the direction of the light path, and guide the light of the dynamic target collimated by the collimator 41 to the optical window 7.

[0033] In some possible embodiments, the dynamic target generator 1 and the collimator 41 are arranged on the first vibration isolation platform 91; the ultra-high temperature test box 2, the temperature-altitude test box 3, the photoelectric load 5 and the cooling system 8 are arranged on the second vibration isolation platform 92; and the folding mirror assembly includes a first folding mirror 421 and a second folding mirror 422. The first folding mirror 421 and the second folding mirror 422 can transmit the light of the dynamic target passing through the collimator 41 to the imaging channel, making the structure of the evaluation device more compact, and providing space for the precise adjustment of other equipment, thereby making the optical path flexible.

[0034] In some possible embodiments, the optoelectronic payload includes a high-precision imaging system and a data acquisition system. The high-precision imaging system is used to receive light passing through the optical window in real time and form a dynamic target image, thereby accurately measuring the transmittance and imaging performance changes of the optical window 7 under high temperature disturbance. The data acquisition system is used to store the dynamic target image.

[0035] like Figure 6 As shown, the embodiment of the second aspect of the present invention provides a method for evaluating the imaging performance of a near-space high-temperature optical window, which specifically includes the following steps: Specifically, before the experiment begins, first assemble the near-space high-temperature optical window imaging performance evaluation device provided by the embodiment of the first aspect; then mount the optical window 7 to be tested on the first optical outlet of the ultra-high temperature test box 2 to ensure that the position and angle of the optical window 7 are accurately adjusted.

[0036] S102: Start the dynamic target generator 1, and the dynamic target generator 1 generates a dynamic target that simulates a nearby space target.

[0037] S104: collimating the light of the dynamic target from the dynamic target generator 1 through the collimator 41 so that the light of the dynamic target passes through the subsequent optical window 7 in the form of parallel light, ensuring that the light of the dynamic target is evenly distributed when incident on the optical window 7.

[0038] S106: Start the ultra-high temperature test chamber 2 to gradually heat the optical window 7 to the test temperature.

[0039] S108: The direction of the optical path is adjusted by the folding mirror assembly so that the light of the dynamic target passes through the optical window 7 under high temperature disturbance, and the photoelectric load 5 receives the light passing through the optical window 7 and forms a dynamic target image. Specifically, the high-precision imaging system receives the light passing through the optical window in real time and forms a dynamic target image, and the data acquisition system stores the dynamic target image.

[0040] S110: Adjust environmental parameters such as temperature parameters and air pressure parameters inside the temperature-altitude test box 3 to simulate the performance changes of the optoelectronic payload 5 at different flight speeds and altitudes, so as to achieve a comprehensive evaluation of the optical performance of the optical window 7 under real flight conditions; obtain dynamic target images of the optical window 7 formed by the optoelectronic payload at different temperatures and air pressures.

[0041] S112: According to the dynamic target image of the optical window 7 at different temperatures and air pressures, a comprehensive analysis is performed to obtain the transmission wavefront change data and imaging performance index of the dynamic target image, and the imaging performance of the optical window 7 is evaluated according to the transmission wavefront change data and the imaging performance index.

[0042] Therefore, the present invention provides a near-space high-temperature optical window imaging performance evaluation method, which can efficiently and accurately simulate the complex flight environment of an aircraft at a high Mach number in near-space in a ground laboratory, and quickly and comprehensively evaluate the dynamic optical imaging performance of the optical window 7 at different temperatures and air pressures, thereby significantly reducing the problems of many preparation factors, complex work, and high costs before the aircraft performs a flight mission, and improving the accuracy and repeatability of ground experimental verification.

[0043] In some possible embodiments, the transmitted wavefront change data includes the root mean square (RMS) and the peak to valley (PV); the imaging performance indicators include the modulation transfer function (MTF) and the point spread function (PSF); they are used to analyze the dynamic imaging performance of the optical window 7 under different environmental conditions, and provide a theoretical basis for the subsequent aberration correction of the optoelectronic payload 5.

[0044] The present invention provides a near-space high-temperature optical window imaging performance evaluation device and evaluation method. Through precise simulation experiments, the reconnaissance technology of the aircraft's reconnaissance system in different spectral ranges such as visible light, medium-wave infrared and long-wave infrared under the conditions of high Mach numbers in near-space can be quickly improved, providing an experimental basis for the design and optimization of optical windows, and promoting the development of near-space aircraft reconnaissance technology.

[0045] Although the embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and cannot be understood as limiting the present invention. Those skilled in the art may change, modify, replace and modify the above embodiments within the scope of the present invention.

[0046] The above specific implementations of the present invention do not constitute a limitation on the protection scope of the present invention. Any other corresponding changes and modifications made based on the technical concept of the present invention should be included in the protection scope of the claims of the present invention.

Claims

1. A near-space high-temperature optical window imaging performance evaluation device, characterized in that: include: A dynamic target generator (1), the dynamic target generator (1) being arranged at a starting position of an optical path of the evaluation device, the dynamic target generator (1) being used to generate a dynamic target simulating a nearby space target; An ultra-high temperature experiment box (2), the ultra-high temperature experiment box (2) being arranged in front of the dynamic target generator (1), the ultra-high temperature experiment box (2) being used to carry and heat the optical window (7); A temperature-altitude test box (3), the temperature-altitude test box (3) is arranged in front of the ultra-high temperature test box (2), and the temperature-altitude test box (3) is used to simulate the temperature and air pressure of the adjacent space; a light adjustment component (4), the light adjustment component (4) being arranged between the dynamic target generator (1) and the ultra-high temperature test chamber (2), the light adjustment component (4) being used for directing the light of the dynamic target to the optical window (7); A photoelectric load (5), wherein the photoelectric load (5) is arranged inside the temperature-altitude test box (3), and the photoelectric load (5) is used to receive the light passing through the optical window (7) and form a dynamic target image; A control system, wherein the control system signal is connected to the dynamic target generator (1), the ultra-high temperature test chamber (2), the temperature-altitude test chamber (3) and the photoelectric load (5), and the control system is used to analyze the dynamic target image formed by the photoelectric load (5), so as to evaluate the imaging performance of the optical window (7).

2. The near-space high-temperature optical window imaging performance evaluation device according to claim 1, characterized in that: The ultra-high temperature test box (2) comprises: A first housing (21), wherein a first optical inlet and a first optical outlet are provided on the first housing (21) so as to form an imaging channel between the first optical inlet and the first optical outlet, a cooling system (8) is provided on the first optical inlet, and the optical window (7) is connected to the first optical outlet; a radiation heating source (22), the radiation heating source (22) being arranged inside the first housing (21), the radiation heating source (22) being used to heat the optical window (7); A temperature sensor, the temperature sensor being arranged inside the first box (21), and the temperature sensor being used to monitor the temperature of the imaging channel; Wherein, the radiation heating source (22) and the temperature sensor signal are connected to the control system.

3. The near-space high-temperature optical window imaging performance evaluation device according to claim 2, characterized in that: The cooling system (8) comprises: A cooling plate (81), wherein the cooling plate (81) is arranged outside the imaging channel; A heat dissipation component, the heat dissipation component is used to exchange heat with the outside world; A cooling pipeline, the cooling pipeline connecting the cooling plate (81) and the heat dissipation component, the interior of the cooling pipeline is filled with a cooling medium, and the cooling pipeline is also provided with a cooling pump and a temperature control valve; Wherein, the cooling pump and the temperature control valve signals are connected to the control system.

4. The near-space high-temperature optical window imaging performance evaluation device according to claim 1, characterized in that: The temperature-altitude test box (3) comprises: A second box body (31), wherein a second optical entrance is provided on the second box body (31), and the second optical entrance is located in front of the optical window (7); A temperature control system, the temperature control system being arranged inside the second box (31), and the temperature control system being used to adjust the temperature inside the second box (31); a pressure regulating system, the pressure regulating system being arranged inside the second box (31), and the pressure regulating system being used to regulate the air pressure inside the second box (31); Wherein, the temperature control system and the voltage regulation system signals are connected to the control system.

5. The near-space high-temperature optical window imaging performance evaluation device according to claim 2, characterized in that: The light adjustment component (4) comprises: A collimator (41), the collimator (41) being arranged between the dynamic target generator (1) and the cooling system (8), the collimator (41) being used for collimating the light of the dynamic target; A folding mirror assembly is arranged between the collimator (41) and the cooling system (8), and the folding mirror is used to guide the light of the dynamic target collimated by the collimator (41) to the optical window (7).

6. The near-space high-temperature optical window imaging performance evaluation device according to claim 1, characterized in that: The photoelectric load (5) comprises: A high-precision imaging system, the high-precision imaging system is used to receive the light transmitted through the optical window (7) and form the dynamic target image; A data acquisition system is used to store the dynamic target image.

7. A near-space high-temperature optical window imaging performance evaluation method, characterized in that: The evaluation device according to any one of claims 1 to 6, comprising: Generate dynamic targets that simulate nearby space targets; Collimating the light of the dynamic target so that the light passes through the optical window (7) in the form of parallel light; heating the optical window (7) to an experimental temperature; Adjusting the direction of the light path, receiving the light passing through the optical window (7) under high temperature disturbance and forming a dynamic target image; Adjusting temperature parameters and air pressure parameters to obtain dynamic target images formed through the optical window (7) at different temperatures and air pressures; The transmission wavefront change data and imaging performance index of the dynamic target image are analyzed, and the imaging performance of the optical window (7) is evaluated based on the transmission wavefront change data and the imaging performance index.

8. The near-space high-temperature optical window imaging performance evaluation method according to claim 7, characterized in that: The transmission wavefront change data includes a root mean square value and a peak-to-valley difference; The imaging performance indicators include modulation transfer function and point spread function.

Images