Infrared polarization image measuring device of space target and use method thereof

Abstract

The invention discloses an infrared polarization image measuring device of a space target and a using method thereof, and belongs to the field of space image measurement. According to the method, the device comprises a satellite model, a guide rail, a translation platform, an electric rotary table, a wide-spectrum infrared polarization sensor and a light source, the wide-spectrum infrared polarization sensor is arranged at the tail end of the guide rail, and the wide-spectrum infrared polarization sensor is used for shooting infrared polarization images of the satellite model under different conditions; the satellite model is arranged on the electric turntable, and the electric turntable is used for adjusting the rotation angle of the satellite model according to a preset direction instruction; the electric rotary table is arranged on the translation platform, and the translation platform is used for performing displacement on the guide rail according to a preset displacement instruction so as to adjust the distance between the satellite model and the wide-spectrum infrared polarization sensor; the light source is used for adjusting illumination conditions of the satellite model. According to the invention, infrared polarization images of various space targets under different conditions can be obtained.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of space image measurement, in particular to an infrared polarization image measurement device for space targets and a use method thereof. BACKGROUND

[0002] Infrared radiation measurement technology in the field of space exploration is based on the thermal radiation characteristics of objects, and captures electromagnetic radiation of targets in the 0.75-1000 μm wave band through infrared detectors, combined with special infrared optical systems (and low-temperature refrigeration technology to suppress noise, realize high-precision data acquisition, which is widely used in earth observation, deep space exploration and missile early warning missions.

[0003] In the prior art, the radiation of an object in the infrared wave band is not related to the illumination condition, but is determined by the temperature of the object itself; the infrared polarized light of each spectrum reflected or radiated by objects of different materials and surface states at multiple angles has obvious differences and recognition, but traditional binocular cameras and TOF cameras cannot accurately obtain relevant information.

[0004] Therefore, there is an urgent need for an infrared polarization image measurement device for space targets and a use method thereof to solve the above technical problems. SUMMARY

[0005] The present application provides an infrared polarization image measurement device for space targets and a use method thereof, which can obtain infrared polarization images of various space targets under different conditions. The technical solution is as follows: On the one hand, an infrared polarization image measurement device for space targets is provided, which comprises a satellite model, a guide rail, a translation platform, a motorized turntable, a wide-spectrum infrared polarization sensor and a light source, wherein: The wide-spectrum infrared polarization sensor is arranged at the end of the guide rail, and the wide-spectrum infrared polarization sensor is used to shoot infrared polarization images of the satellite model under different conditions; The satellite model is arranged on the motorized turntable, and the motorized turntable is used to adjust the rotation angle of the satellite model according to a preset direction instruction; The motorized turntable is arranged on the translation platform, and the translation platform is used to displace on the guide rail according to a preset displacement instruction to adjust the distance between the satellite model and the wide-spectrum infrared polarization sensor; The light source is used to adjust the illumination condition of the satellite model.

[0006] On the other hand, a use method of an infrared polarization image measurement device for space targets is provided, which comprises: S1, mounting the satellite model on the motorized turntable; S2, under the same light and the same rotation angle conditions, using the wide spectrum infrared polarization sensor to collect and store the infrared polarization image and the infrared intensity image of the satellite model at the target orbit position; S3, under the same light and the same orbit position conditions, using the wide spectrum infrared polarization sensor to collect and store the infrared polarization image and the infrared intensity image of the satellite model at the target rotation angle; S4, under the same orbit position and the same rotation angle conditions, using the wide spectrum infrared polarization sensor to collect and store the infrared polarization image and the infrared intensity image of the satellite model at the target light; S5, repeating steps S2-S4 until the infrared polarization image and the infrared intensity image of the satellite model under all conditions are collected and stored.

[0007] The technical scheme provided by the present application can bring at least the following beneficial effects: the present application uses high-precision electric control trolley and high-precision electric control turntable and other equipment to collect and store the infrared polarization and intensity images of all space targets under different light conditions, different distances and different angles, which is easy to simulate by software and realize by hardware, has low requirements for hardware configuration of the equipment, is practical, can greatly save manpower, material and time costs compared with the high manpower and time costs caused by the traditional hardware acceleration method, and has a wide application prospect. BRIEF DESCRIPTION OF DRAWINGS

[0008] In order to more clearly illustrate the technical schemes in the embodiments of the present application or the prior art, the following will briefly introduce the drawings needed to be used in the embodiments or the prior art description. Obviously, the drawings in the following description are some embodiments of the present application, and those skilled in the art can also obtain other drawings according to these drawings without creative labor.

[0009] Figure 1 is a structure diagram of the infrared polarization image measuring device of the space target provided by an embodiment of the present application; Figure 2 is a simulation schematic diagram of a satellite model provided by an embodiment of the present application; Figure 3 is an installation schematic diagram of a model body and a mounting module provided by an embodiment of the present application. DETAILED DESCRIPTION

[0010] In order to make the purposes, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described clearly and completely below with reference to the drawings in the embodiments of the present application. Obviously, the described embodiments are some but not all of the embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by a person of ordinary skill in the art without creative work fall within the protection scope of the present application.

[0011] Reference is made to Figure 1 The embodiments of the present application provide an infrared polarization image measuring device for a space target, which comprises a satellite model, a guide rail, a translation platform, a motorized turntable, a wide-spectrum infrared polarization sensor and a light source, wherein: The wide-spectrum infrared polarization sensor is arranged at the end of the guide rail, and the wide-spectrum infrared polarization sensor is used for shooting infrared polarization images of the satellite model under different conditions. The satellite model is arranged on the motorized turntable, and the motorized turntable is used for adjusting the rotation angle of the satellite model according to a preset direction instruction. The motorized turntable is arranged on the translation platform, and the translation platform is used for adjusting the distance between the satellite model and the wide-spectrum infrared polarization sensor by performing displacement on the guide rail according to a preset displacement instruction. The light source is used for adjusting the illumination condition of the satellite model.

[0012] The details of each part shown in the following description. Figure 1

[0013] In the embodiments of the present application, as Figure 2 shown, the satellite model comprises a model body and a mounting module, and the mounting module is arranged around the model body to form a plurality of simulation surfaces for simulating remote sensing satellites, communication satellites, small satellites and starship docking rings.

[0014] The mounting module targets for simulating these satellite celestial bodies include celestial bodies, solar panels, satellite antennas, docking rings, thruster nozzles, sensors, cameras, mechanical arms, targets and space debris. Each target has 3 to 6, respectively, for different types of satellites.

[0015] In the embodiments of the present application, the model body, the driving platform and each mounting module have a relatively obvious temperature gradient, so in the design stage, the mounting modules are separated into independent individuals by adding heat insulation pads, and the specific separation structure is as Figure 3 shown, the mounting module is separated and heat-insulated from the model body and the connecting screw by the heat insulation pad to meet the requirement of temperature gradient. The material of the heat insulation pad is asbestos.

[0016] ​Further, in the embodiment of the present application, the electric rotary table is a single-shaft rotary table, the rotary angle of the electric rotary table is not less than 360°, the rotary speed is 0-10° / s, the rotary positioning accuracy of the electric rotary table is greater than 0.5°, and the bearing capacity of the electric rotary table is not less than 100 kg.

[0017] In the embodiment of the present application, the remote control distance of the translation platform is not less than 50 m, the movement speed is 0-0.1 m / s, the positioning accuracy of the translation platform is greater than 5 mm, the bearing capacity of the translation platform is not less than 300 kg, the total length of the guide rail of the translation platform is 15 m, and the width is 1 m.

[0018] In the embodiment of the present application, the illumination conditions include natural light, no light and backlight.

[0019] The embodiment of the present application provides a method for measuring infrared polarization images of space targets, which comprises the following steps: S1, mounting the satellite model on the electric rotary table; S2, under the same illumination and the same rotary angle, using the wide-spectrum infrared polarization sensor to collect and store the infrared polarization images and the infrared intensity images of the satellite model at the target orbit position; S3, under the same illumination and the same orbit position, using the wide-spectrum infrared polarization sensor to collect and store the infrared polarization images and the infrared intensity images of the satellite model at the target rotary angle; S4, under the same orbit position and the same rotary angle, using the wide-spectrum infrared polarization sensor to collect and store the infrared polarization images and the infrared intensity images of the satellite model at the target illumination; S5, repeating steps S2-S4 until the infrared polarization images and the infrared intensity images of the satellite model under all conditions are collected and stored.

[0020] It is worth noting that after the infrared polarization images and the infrared intensity images of the target are obtained by the above method, they can be fused, classified, trained and tested, and finally a space target attribute library with high accuracy is obtained. The target attribute library contains the spectrum of the target under different conditions, which provides a large amount of queryable data for subsequent detection and recognition of small targets, thereby greatly saving manpower, material and time costs, and has a wide application prospect.

[0021] Finally, it needs to be pointed out that, in this document, relational terms such as first, second, third, and fourth and the like can only be used to distinguish one entity or action from another entity or action, without necessarily requiring or implying any actual relationship or order between or among such entities or actions. Moreover, the terms "comprises", "comprising", or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but can include other elements not expressly listed or inherent to such process, method, article, or apparatus. An element proceeded by "comprises... a" does not, without more constraints, exclude the existence of additional identical elements in the process, method, article, or apparatus that comprises the element.

[0022] The above description is only the preferred embodiment of the present application, and it should be pointed out that, for those skilled in the art, some improvements and refinements can be made without departing from the principles of the present application, and these improvements and refinements should also be considered as the protection scope of the present application.

Claims

1. An infrared polarization image measurement device for a space target, characterized in that, The device includes a satellite model, guide rails, a translational platform, an electric turntable, a broadband infrared polarization sensor, and a light source, wherein: The broadband infrared polarization sensor is disposed at the end of the guide rail and is used to capture infrared polarization images of the satellite model under different conditions. The satellite model is mounted on the electric turntable, which is used to adjust the rotation angle of the satellite model according to a preset direction command. The electric turntable is mounted on the translation platform, which is used to move on the guide rail according to a preset displacement command in order to adjust the distance between the satellite model and the broadband infrared polarization sensor. The light source is used to adjust the lighting conditions of the satellite model.

2. The apparatus as claimed in claim 1, characterized in that, The satellite model includes a model body and a mounting module. The mounting module is set around the model body to simulate remote sensing satellites, communication satellites, small satellites, and starship docking rings. The mounting module includes: a star body, solar panels, satellite antennas, docking rings, thruster nozzles, sensors, cameras, robotic arms, targets, and space debris.

3. The apparatus as described in claim 2, characterized in that, An asbestos-based heat insulation pad is provided between the model body and the mounting module. The heat insulation pad is used to separate and insulate the model body and the mounting module to meet the requirements of temperature gradient.

4. The apparatus as claimed in claim 1, characterized in that, The electric turntable is a single-axis turntable with a rotation angle of not less than 360°, a rotation speed of 0-10° / s, and a rotation positioning accuracy of greater than 0.5°.

5. The apparatus as claimed in claim 1, characterized in that, The remote control distance of the translation platform is not less than 50m, and the movement speed is 0-0.1m / s.

6. The apparatus as claimed in claim 1, characterized in that, The positioning accuracy of the translational platform is greater than 5mm.

7. The apparatus as claimed in claim 1, characterized in that, The load-bearing capacity of the electric turntable is not less than 100 kg.

8. The apparatus as claimed in claim 1, characterized in that, The load-bearing capacity of the translation platform is not less than 300 kg, and the total length of the guide rail of the translation platform is 15 m and the width is 1 m.

9. The apparatus as claimed in claim 1, characterized in that, The lighting conditions include natural light, no light, and backlighting.

10. A method of using an infrared polarization image measurement device for a space target, characterized in that, The method, applied to the apparatus as described in any one of claims 1-9, comprises: S1. Install the satellite model onto the electric turntable; S2. Under the same illumination and the same rotation angle, the infrared polarization image and infrared intensity image of the satellite model at the target orbit position are acquired and stored using the broadband infrared polarization sensor. S3. Under the same illumination and same orbital position conditions, use the broadband infrared polarization sensor to collect and store the infrared polarization image and infrared intensity image of the satellite model at the target rotation angle; S4. Under the same orbital position and the same rotation angle, the infrared polarization image and infrared intensity image of the satellite model under target illumination are acquired and stored using the broadband infrared polarization sensor. S5. Repeat steps S2-S4 until infrared polarization and infrared intensity images of the satellite model under all conditions are acquired and stored.

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