Spaceborne optical imaging payload

Abstract

The application provides a spaceborne optical imaging load, comprising a short-wave camera connected with an on-board processing unit, a data transmission and storage unit and a comprehensive electronic unit; a long-wave camera connected with the on-board processing unit, the data transmission and storage unit and the comprehensive electronic unit; an instrument management and power supply box connected with the short-wave camera, the long-wave camera and the comprehensive electronic unit and a power distributor; and a refrigerator electric control box connected with the short-wave camera, the long-wave camera, the instrument management and power supply box and the power distributor. The application realizes camera focusing through temperature control means, realizes functions such as on-orbit adjustment of camera imaging polarity, generation of test pattern simulation targets, detector temperature protection and refrigerator driving protection, and realizes lightweight and low-power consumption design, reduces the resource demand of the spaceborne optical imaging load on various satellite platforms, and improves the flexibility and fault tolerance capability of on-orbit use.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of satellite remote sensing imaging, and in particular to a spaceborne optical imaging payload. BACKGROUND

[0002] With the growth of space-based remote sensing demand and the development of optical imaging technology, spaceborne optical imaging payloads are increasingly used. However, the traditional spaceborne optical imaging payload has the problems of single function, poor use flexibility, insufficient fault tolerance in orbit, dependence on a focusing mechanism for in-orbit focusing, large volume and weight, and usually being arranged outside the satellite cabin, high demand for energy of the optical imaging payload for thermal control and heating decontamination. Therefore, it is very meaningful to develop a spaceborne optical payload that can reduce the demand for satellite platform resources, has flexible use in orbit and fault tolerance.

[0003] The patent with publication number CN115072010B relates to a turntable mechanism for a spaceborne optical imaging payload, and in particular to a spaceborne deployable turntable mechanism and a method for testing the hysteresis time thereof, for solving the problems of the existing spaceborne turntable mechanism, i.e., small load or inability to effectively reduce the mechanical vibration and impact experienced by the optical imaging payload. The spaceborne deployable turntable mechanism includes a first rotating arm, a second rotating arm, a deployment driving mechanism and a mechanical locking mechanism. The first rotating arm and the second rotating arm are respectively provided with an azimuth axis and an elevation axis for supporting the optical imaging payload. The support mechanism is in a folded state before being launched into orbit and is converted into a deployed state after being launched into orbit, thereby effectively reducing the mechanical vibration and impact experienced by the optical imaging payload and improving the load ratio and launch reliability. At the same time, the present application discloses a method for testing the hysteresis time of the spaceborne deployable turntable mechanism.

[0004] The patent with publication number CN109141628B discloses a spaceborne optical fiber focal plane detector device, which comprises an entrance focal plane, a mode scrambling fiber, a temperature control box, a fiber light outlet, a collimating lens barrel, a collimating lens, an attenuation sheet, a photomultiplier tube, a thermistor, a semiconductor refrigeration sheet, a heat pipe, a heat dissipation plate, a high-voltage power supply and a signal box, and a temperature control electronics box. The entrance focal plane is connected with the mode scrambling fiber. The mode scrambling fiber passes through the temperature control box and is connected with the fiber light outlet. The fiber light outlet is inserted into the collimating lens barrel. The collimating lens and the attenuation sheet are installed in the collimating lens barrel. The photomultiplier tube is installed at the rear end of the collimating lens barrel. The thermistor and the semiconductor refrigeration sheet are attached to the shell of the photomultiplier tube. The cold end of the heat pipe is attached to the back of the semiconductor refrigeration sheet, and the hot end is attached to the inner side of the heat dissipation plate. The high-voltage power supply and the signal box are connected with the photomultiplier tube. The temperature control electronics box is connected with the thermistor and the semiconductor refrigeration sheet. The present application solves the problem of insufficient response capability of the detector of the satellite optical imaging payload under weak light conditions.

[0005] The patent with publication number CN116039967A discloses an aviation aircraft optical window roller shutter door protection device. The roller shutter door fixing plate serves as the mounting base plate of the device and bears all component mounting and fixation. The long shaft support motor side and the dynamic shaft support realize parallel installation of the motor fixing seat, the driving shaft and the driven shaft. The closing and opening to position switches feed the to position information to make the motor power off. The first, second, third and fourth baffle fixing members are respectively installed on the corresponding sliders. The first slider and the first guide rail combination and the second slider and the second guide rail combination are installed in parallel on the roller shutter door fixing plate to realize parallel sliding of the baffles. The chain pressing piece fixes and connects the chain and the baffle to realize synchronous movement of the chain and the baffle. The sprocket pressing piece realizes axial fixation and pressing of the sprocket. The device has the advantages of simple and compact structure, low cost, high space utilization, long service life, good environmental adaptability and convenient installation and debugging.

[0006] The patent with publication number CN112198628A discloses an optical imaging system, an image taking module and an electronic device having the same. The optical imaging system comprises: an optical lens group, the optical lens group comprising a first lens, a second lens, a third lens, a fourth lens, a fifth lens and a sixth lens arranged in sequence along an optical axis from an object side to an image side; the first lens has a negative refractive power, and an image side surface of the first lens is concave at a near optical axis; the second lens has a positive refractive power; the third lens has a negative refractive power; the fourth lens and the fifth lens both have a positive refractive power; the sixth lens has a negative refractive power; wherein the optical imaging system satisfies: 2.9 < Imgh / Tan(1 / 2 x FOV) < 4.0, Imgh is half of the diagonal line length of the effective pixel area on the imaging surface, FOV is the maximum field of view angle of the optical imaging system, and Tan(1 / 2 x FOV) is the tangent value of half of the maximum field of view angle of the optical imaging system. According to the optical imaging system, a small aperture number is realized, miniaturization and high imaging quality are achieved, and high-definition image shooting is realized.

[0007] The patent with publication number CN114488486A discloses an optical imaging system, which comprises, from the object side of the optical imaging system to the image side of the optical imaging system: a first transmission surface arranged in the outer circumferential region of the object side of the first lens, a first reflection surface arranged in the outer circumferential region of the image side of the first lens, a second reflection surface arranged in the paraxial region of the object side of the first lens, and a second transmission surface arranged in the paraxial region of the image side of the first lens; the second lens has a negative focal power; the third lens has a negative focal power; the fourth lens has a positive focal power; the fifth lens has a focal power; and the sixth lens has a negative focal power. The light rays enter in sequence through the first transmission surface, are reflected by the first reflection surface to the second reflection surface, and then enter the second lens after being reflected by the second reflection surface to the second transmission surface. The total length TTL of the optical imaging system and the effective focal length f of the optical imaging system satisfy: 37.5mm<f*f / TTL<46.5mm. The present application solves the problem that miniaturization and high pixels cannot be considered in the prior art long-focus lens.

[0008] The patent with publication number CN107728315A discloses a space camera system. The space camera system can adjust the secondary mirror according to the imaging condition during on-orbit operation, thereby obtaining good imaging performance. Meanwhile, during ground assembly and adjustment, the secondary mirror can be adjusted after assembly, that is, the secondary mirror is installed and then adjusted, and the final position of the secondary mirror is determined by detecting the wave aberration of the system. In this way, the space camera optical system can be adjusted to the best state.

[0009] The patent with publication number CN107831628A discloses an optoelectromechanical integrated space camera. The camera comprises a lens assembly and a main support located at the periphery of the lens assembly. The main support is a cuboid-shaped frame structure with an installation seat, and the lens assembly is fixed to the front face of the installation seat. A circuit board assembly is fixedly installed on the main support. The circuit board assembly comprises an upper circuit board located at the top of the lens assembly, a lower circuit board located at the bottom of the lens assembly, and a focal plane plate located at the back of the installation seat. The upper circuit board, the lower circuit board, and the focal plane plate are connected by a flexible cable. The main support connects the circuit board assembly and the lens assembly into one body, and the satellite cabin plate is used as a structure cover plate, so that the parts are highly integrated, and the size of the structure body is greatly reduced.

[0010] The above patents only relate to the principle and system of the optical imaging system, and do not involve the in-orbit use flexibility and fault tolerance design, nor the reduction of the demand for the whole satellite platform resources.

[0011] Therefore, a new technical solution is needed to improve the above technical problems. SUMMARY

[0012] Aiming at the defects in the prior art, the present application aims to provide a spaceborne optical imaging load.

[0013] The spaceborne optical imaging load provided by the present application comprises a short-wave camera, a long-wave camera, an on-board processing unit, a data transmission and storage unit, a comprehensive electronic unit, a power distributor, an instrument management and power supply box, and a refrigeration machine control box.

[0014] The short-wave camera is connected with the on-board processing unit, the data transmission and storage unit, and the comprehensive electronic unit; the long-wave camera is connected with the on-board processing unit, the data transmission and storage unit, and the comprehensive electronic unit; the instrument management and power supply box is connected with the short-wave camera, the long-wave camera, and the comprehensive electronic unit and the power distributor; and the refrigeration machine control box is connected with the short-wave camera, the long-wave camera, the instrument management and power supply box, and the power distributor.

[0015] Preferably, the short-wave camera is installed outside the satellite cabin; the long-wave camera is installed outside the satellite cabin; the instrument management and power supply box is installed inside the satellite cabin; and the refrigeration machine control box is installed outside the satellite cabin.

[0016] Preferably, the short-wave camera comprises:

[0017] a short-wave refrigeration machine connected with the refrigeration machine control box;

[0018] a short-wave camera temperature control module connected with the instrument management and power supply box;

[0019] a short-wave information acquisition circuit connected with the instrument management and power supply box, the on-board processing unit, the data transmission and storage unit, and the comprehensive electronic unit;

[0020] a short-wave detector connected with the short-wave information acquisition circuit, which is controlled by the short-wave information acquisition circuit for power supply, imaging driving, and data reading, and is refrigerated by the short-wave refrigeration machine;

[0021] a short-wave optical machine assembly comprising a camera structure and a lens barrel and a lens assembly, which realizes closed-loop temperature control through the short-wave camera temperature module, adjusts the temperature of the lens barrel and the lens assembly, and adjusts the focal length of the short-wave camera by changing the refractive index of the lens assembly through temperature change.

[0022] Preferably, the long-wave camera comprises:

[0023] a long-wave refrigeration machine connected with the refrigeration machine control box;

[0024] Long wave camera temperature control module: the long wave camera temperature control module is connected with the instrument management and power supply box;

[0025] Long wave information acquisition circuit: the long wave information acquisition circuit is connected with the instrument management and power supply box, the on-board processing unit, the data transmission and solid storage unit and the integrated electronic unit;

[0026] Long wave detector: the long wave detector is connected with the long wave information acquisition circuit, the long wave detector is powered, driven to image and data read by the long wave information acquisition circuit, and the long wave detector is refrigerated by the long wave refrigerator;

[0027] Long wave optical machine assembly: the long wave optical machine assembly includes a camera structure and a lens barrel, and the long wave optical machine assembly realizes closed-loop temperature control through the long wave camera temperature module, adjusts the temperature of the lens barrel and the lens assembly, adjusts the focal length of the short wave camera by changing the refractive index of the lens assembly through temperature change.

[0028] Preferably, the instrument management and power supply box receives remote control instructions from the integrated electronic unit, and forwards the remote control instructions to the short wave information acquisition circuit and detector, the long wave information acquisition circuit and detector and the refrigerator electric control box; the instrument management and power supply box receives telemetry feedback from the short wave information acquisition circuit and detector, the long wave information acquisition circuit and detector and the refrigerator electric control box, and returns the telemetry feedback to the integrated electronic unit.

[0029] Preferably, the refrigerator electric control box controls the short wave refrigerator and the long wave refrigerator, and realizes closed-loop refrigeration of the short wave detector and the long wave detector.

[0030] Preferably, the refrigerator electric control box includes a detector refrigeration standby temperature mode and a detector refrigeration working temperature mode.

[0031] The refrigerator electric control box performs refrigerator drive protection, and when the refrigerator drive current exceeds a safe working current threshold, the refrigerator electric control box autonomously performs a refrigerator shutdown operation.

[0032] Preferably, the short wave information acquisition circuit and short wave detector receive high-speed on-orbit data from the integrated electronic unit, the high-speed on-orbit data includes on-orbit programming software data, non-uniform correction parameters and on-orbit adjustment parameters of imaging polarity, and the short wave information acquisition circuit and short wave detector complete on-orbit programming, image non-uniform correction, blind pixel marking and filling, test pattern and simulation target generation, and on-orbit adjustment of imaging polarity.

[0033] The short wave information acquisition circuit and short wave detector output image data to the on-board processing unit and the data transmission and solid storage unit.

[0034] Preferably, the long-wave information acquisition circuit and long-wave detector receive high-speed uplink data from the integrated electronic unit, the high-speed uplink data including in-orbit programming software data, non-uniform correction parameters and in-orbit adjustment parameters of imaging polarity, and the in-orbit programming, image non-uniform correction, blind pixel marking and filling, test pattern and simulation target generation, in-orbit adjustment function of imaging polarity are completed by the long-wave information acquisition circuit and detector;

[0035] The long-wave information acquisition circuit and long-wave detector output image data to the on-board processing unit and the data transmission and storage unit.

[0036] Preferably, the instrument management and power supply box performs detector temperature protection;

[0037] When the temperature of the short-wave detector exceeds the safe working temperature threshold, the instrument management and power supply box actively shields the short-wave detector power-on command from the integrated electronic unit; when the temperature of the short-wave detector exceeds the safe working temperature threshold in the powered-on state, the instrument management and power supply box can autonomously send a short-wave detector power-off command to the short-wave information acquisition circuit;

[0038] When the temperature of the long-wave detector exceeds the safe working temperature threshold, the instrument management and power supply box actively shields the long-wave detector power-on command from the integrated electronic unit; when the temperature of the long-wave detector exceeds the safe working temperature threshold in the powered-on state, the instrument management and power supply box can autonomously send a long-wave detector power-off command to the long-wave information acquisition circuit.

[0039] Compared with the prior art, the present application has the following beneficial effects:

[0040] 1、The split design of the present application separates the power supply, instrument management and refrigeration control circuit into single machines, which are installed in the satellite cabin, reducing the energy consumption of the optical imaging load thermal control and heating decontamination on the whole satellite; the refrigeration machine control design has a detector refrigeration standby temperature mode (low power consumption mode) and a detector refrigeration working temperature mode, and the normal state is the low power consumption mode, and only when the detector works for a short time, the detector refrigeration working temperature mode is used, thereby reducing the energy consumption of the whole satellite;

[0041] 2、The present application has a detector temperature protection function, and when the detector exceeds the safe working temperature threshold, the detector power-on command is shielded, and if the detector exceeds the safe working temperature threshold in the powered-on state, the detector power-off operation is autonomously executed; the present application has a refrigeration machine drive protection function, and when the refrigeration machine drive current exceeds the safe working current threshold, the refrigeration machine is autonomously closed;

[0042] 3, The application has test pattern simulation target generation function, which is convenient for optical imaging load function self-test and whole satellite information loop verification test; has camera imaging polarity on-orbit adjustment function, which improves the flexibility and fault tolerance of on-orbit use;

[0043] 4, The application can be programmed and upgraded on-orbit through high-speed injection; the optical imaging load weight is reduced by the focusing mechanism; the heat conduction design of the lens barrel and the lens assembly is provided with a heater on the lens barrel, the camera focal length is adjusted by adjusting the temperature of the lens barrel and the lens assembly, the focusing range can reach more than ± 50um. BRIEF DESCRIPTION OF DRAWINGS

[0044] Other features, objects and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0045] Figure 1 A block diagram of a satellite-borne optical imaging load of the application. DETAILED DESCRIPTION

[0046] The application will be described in detail below with specific embodiments. The following embodiments will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be pointed out that those skilled in the art can make several changes and improvements without departing from the concept of the application. These all belong to the protection scope of the application.

[0047] Example 1

[0048] REFERENCE Figure 1 According to the satellite-borne optical imaging load provided by the application, it comprises: a short-wave camera, a long-wave camera, an on-board processing unit, an instrument management and power supply box and a refrigeration machine electric control box; the short-wave camera is connected with the on-board processing unit, a data transmission solid storage unit and a comprehensive electronic unit; the long-wave camera is connected with the on-board processing unit, the data transmission solid storage unit and the comprehensive electronic unit; the instrument management and power supply box is connected with the short-wave camera, the long-wave camera and the comprehensive electronic unit and a power distribution device; and the refrigeration machine electric control box is connected with the short-wave camera, the long-wave camera, the instrument management and power supply box and the power distribution device.

[0049] The short-wave camera is installed outside the satellite cabin; the long-wave camera is installed outside the satellite cabin; the instrument management and power supply box is installed inside the satellite cabin; and the refrigeration machine electric control box is installed inside and outside the satellite cabin.

[0050] The short-wave camera comprises:

[0051] Shortwave camera: the shortwave camera is connected with the instrument management and power supply box;

[0052] Shortwave camera temperature control module: the shortwave camera temperature control module is connected with the instrument management and power supply box;

[0053] Shortwave information acquisition circuit: the shortwave information acquisition circuit is connected with the instrument management and power supply box, the on-board processing unit, the data transmission and storage unit and the integrated electronic unit;

[0054] Shortwave detector: the shortwave detector is connected with the shortwave information acquisition circuit, and the shortwave detector is controlled by the shortwave information acquisition circuit for power supply, imaging driving and data reading, and the shortwave detector is cooled by the shortwave refrigerator;

[0055] Shortwave optical machine assembly: the shortwave optical machine assembly includes a camera structure and a lens barrel, and the shortwave optical machine assembly realizes closed-loop temperature control through the shortwave camera temperature module, adjusts the temperature of the lens barrel and the lens assembly, adjusts the focal length of the shortwave camera by changing the refractive index of the lens assembly through temperature change.

[0056] Adjusting the shortwave camera temperature control threshold, the shortwave camera temperature control module increases the heating power of the camera lens barrel and the lens assembly, increases the temperature of the lens assembly, the refractive index of the lens assembly increases, and the focal length of the shortwave camera decreases;

[0057] Adjusting the shortwave camera temperature control threshold, the shortwave camera temperature control module reduces the heating power of the camera lens barrel and the lens assembly, reduces the temperature of the lens assembly, the refractive index of the lens assembly decreases, and the focal length of the camera increases.

[0058] Long-wave camera includes:

[0059] Long-wave refrigerator: the long-wave refrigerator is connected with the refrigerator electric control box;

[0060] Long-wave camera temperature control module: the long-wave camera temperature control module is connected with the instrument management and power supply box;

[0061] Long-wave information acquisition circuit: the long-wave information acquisition circuit is connected with the instrument management and power supply box, the on-board processing unit, the data transmission and storage unit and the integrated electronic unit;

[0062] Long-wave detector: the long-wave detector is connected with the long-wave information acquisition circuit, and the long-wave detector is controlled by the long-wave information acquisition circuit for power supply, imaging driving and data reading, and the long-wave detector is cooled by the long-wave refrigerator;

[0063] Long-wave optical machine assembly: the long-wave optical machine assembly includes a camera structure and a lens barrel, a lens assembly, the long-wave optical machine assembly realizes closed-loop temperature control through the long-wave camera temperature module, adjusts the temperature of the lens barrel and the lens assembly, adjusts the focal length of the short-wave camera by changing the refractive index of the lens assembly through temperature change.

[0064] Adjusting the long-wave camera temperature control threshold, the long-wave camera temperature control module increases the heating power of the camera lens barrel and the lens assembly, increases the temperature of the lens assembly, increases the refractive index of the lens assembly, and reduces the focal length of the long-wave camera;

[0065] Adjusting the long-wave camera temperature control threshold, the long-wave camera temperature control module reduces the heating power of the camera lens barrel and the lens assembly, reduces the temperature of the lens assembly, reduces the refractive index of the lens assembly, and increases the focal length of the camera.

[0066] The instrument management and power box receives remote control commands from the integrated electronic unit, and forwards the remote control commands from the instrument management and power box to the short-wave information acquisition circuit and detector, the long-wave information acquisition circuit and detector, and the refrigerator electric control box; The instrument management and power box receives remote control feedback from the short-wave information acquisition circuit and detector, the long-wave information acquisition circuit and detector, and the refrigerator electric control box, and returns to the integrated electronic unit.

[0067] The refrigerator electric control box controls the short-wave refrigerator and the long-wave refrigerator to realize closed-loop refrigeration of the short-wave detector and the long-wave detector. The refrigerator electric control box includes a detector refrigeration standby temperature mode and a detector refrigeration working temperature mode; The refrigerator electric control box performs refrigerator drive protection, and when the refrigerator drive current exceeds the safe working current threshold, the refrigerator electric control box automatically performs a refrigerator shutdown operation.

[0068] The short-wave information acquisition circuit and the short-wave detector receive high-speed on-board data from the integrated electronic unit, the high-speed on-board data includes on-orbit programming software data, non-uniform correction parameters and imaging polarity on-orbit adjustment parameters, and the short-wave information acquisition circuit and the detector complete on-orbit programming, image non-uniform correction, blind element marking and filling, test pattern and simulation target generation, and imaging polarity on-orbit adjustment functions; The short-wave information acquisition circuit and the short-wave detector output image data to the on-board processing unit and the data transmission and storage unit.

[0069] The long-wave information acquisition circuit and the long-wave detector receive high-speed uplink data from the integrated electronic unit, the high-speed uplink data including on-orbit programming software data, non-uniform correction parameters and on-orbit adjustment parameters of imaging polarity, and the on-orbit programming, image non-uniform correction, blind element marking and filling, test pattern and simulation target generation, on-orbit adjustment of imaging polarity are completed by the long-wave information acquisition circuit and the detector; the long-wave information acquisition circuit and the long-wave detector output image data to the on-board processing unit and the data transmission and storage unit.

[0070] The instrument management and power supply box detects the temperature of the detector; when the temperature of the short-wave detector exceeds the safe working temperature threshold, the instrument management and power supply box actively shields the short-wave detector power-on command from the integrated electronic unit; when the temperature of the short-wave detector exceeds the safe working temperature threshold in the powered-on state, the instrument management and power supply box can autonomously send a short-wave detector power-off command to the short-wave information acquisition circuit; when the temperature of the long-wave detector exceeds the safe working temperature threshold, the instrument management and power supply box actively shields the long-wave detector power-on command from the integrated electronic unit; when the temperature of the long-wave detector exceeds the safe working temperature threshold in the powered-on state, the instrument management and power supply box can autonomously send a long-wave detector power-off command to the long-wave information acquisition circuit.

[0071] Example 2

[0072] In view of the limitations of existing products in actual application, the purpose of the present application is to provide a satellite-borne optical imaging payload, which can reduce the resource demand on the satellite platform and improve the flexibility and fault tolerance in on-orbit use.

[0073] The satellite-borne optical imaging payload provided by the present application comprises a short-wave camera, which is connected with an on-board processing unit, a data transmission and storage unit and an integrated electronic unit; a long-wave camera, which is connected with the on-board processing unit, the data transmission and storage unit and the integrated electronic unit; an instrument management and power supply box, which is connected with the short-wave camera, the long-wave camera and the integrated electronic unit and a power distribution device; and a refrigerator electric control box, which is connected with the short-wave camera, the long-wave camera, the instrument management and power supply box and the power distribution device. The present application realizes camera focusing by temperature control, on-orbit adjustment of camera imaging polarity, test pattern simulation target generation, detector temperature protection and refrigerator driving protection, and light weight and low power consumption design, thereby reducing the resource demand of the satellite-borne optical imaging payload on various satellite platforms and improving the flexibility and fault tolerance in on-orbit use.

[0074] A spaceborne optical imaging payload comprises: a short-wave camera, a long-wave camera, an instrument management and power supply box, a refrigerator electrical control box. The short-wave camera comprises: a short-wave refrigerator, a short-wave camera temperature control module, a short-wave information acquisition circuit, a short-wave detector and a short-wave optical machine assembly. The long-wave camera comprises: a long-wave refrigerator, a long-wave camera temperature control module, a long-wave information acquisition circuit, a long-wave detector and a long-wave optical machine assembly.

[0075] The short-wave optical machine assembly comprises a camera structure and a lens barrel, a lens assembly and the like, and the short-wave optical machine assembly realizes closed-loop temperature control through the short-wave camera temperature module, can adjust the temperature of the lens barrel and the lens assembly, adjusts the focal length of the short-wave camera in the manner of changing the refractive index of the lens assembly through temperature change.

[0076] The long-wave optical machine assembly comprises a camera structure and a lens barrel, a lens assembly and the like, and the long-wave optical machine assembly realizes closed-loop temperature control through the long-wave camera temperature module, can adjust the temperature of the lens barrel and the lens assembly, adjusts the focal length of the short-wave camera in the manner of changing the refractive index of the lens assembly through temperature change.

[0077] The short-wave camera is installed outside the satellite cabin, the long-wave camera is installed outside the satellite cabin, the instrument management and power supply box is installed inside the satellite cabin, and the refrigerator electrical control box is installed outside the satellite cabin.

[0078] The short-wave camera is connected with the on-board processing unit, the data transmission and storage unit and the integrated electronic unit; the long-wave camera is connected with the on-board processing unit, the data transmission and storage unit and the integrated electronic unit; the instrument management and power supply box is connected with the short-wave camera, the long-wave camera and the integrated electronic unit and the power distributor; and the refrigerator electrical control box is connected with the short-wave camera, the long-wave camera, the instrument management and power supply box and the power distributor.

[0079] The short-wave refrigerator is connected with the refrigerator electrical control box; the short-wave camera temperature control module is connected with the instrument management and power supply box; the short-wave information acquisition circuit is connected with the instrument management and power supply box, the on-board processing unit, the data transmission and storage unit and the integrated electronic unit; the short-wave detector is connected with the short-wave information acquisition circuit, and the short-wave detector is controlled by the short-wave information acquisition circuit for power supply, imaging driving and data reading, and the short-wave detector is refrigerated by the short-wave refrigerator.

[0080] The long-wave refrigerator is connected with the refrigerator electrical control box; the long-wave camera temperature control module is connected with the instrument management and power supply box; the long-wave information acquisition circuit is connected with the instrument management and power supply box, the on-board processing unit, the data transmission and storage unit and the integrated electronic unit; the long-wave detector is connected with the long-wave information acquisition circuit, and the long-wave detector is controlled by the long-wave information acquisition circuit for power supply, imaging driving and data reading, and the long-wave detector is refrigerated by the long-wave refrigerator.

[0081] The instrument management and power box receives remote control instructions from the integrated electronic unit, which are forwarded by the instrument management and power box to the short-wave information acquisition circuit and detector, the long-wave information acquisition circuit and detector, and the refrigerator electric control box; the instrument management and power box receives remote control feedback from the short-wave information acquisition circuit and detector, the long-wave information acquisition circuit and detector, and the refrigerator electric control box, and returns to the integrated electronic unit.

[0082] The refrigerator electric control box controls the short-wave refrigerator and the long-wave refrigerator to realize closed-loop refrigeration of the short-wave detector and the long-wave detector; the refrigerator electric control box has a detector refrigeration standby temperature mode (low-power mode) and a detector refrigeration working temperature mode, and has a refrigerator drive protection function, which autonomously performs a refrigerator shutdown operation when the refrigerator drive current exceeds a safe working current threshold.

[0083] The short-wave information acquisition circuit and detector receive high-speed uploading data from the integrated electronic unit, which includes on-orbit programming software data, non-uniform correction parameters, and on-orbit adjustment parameters of imaging polarity, etc., and completes on-orbit programming, image non-uniform correction, blind pixel marking and filling, test pattern and simulation target generation, and on-orbit adjustment of imaging polarity; the short-wave information acquisition circuit and detector output image data to the on-board processing unit and the data transmission and storage unit.

[0084] The long-wave information acquisition circuit and detector receive high-speed uploading data from the integrated electronic unit, which includes on-orbit programming software data, non-uniform correction parameters, and on-orbit adjustment parameters of imaging polarity, etc., and completes on-orbit programming, image non-uniform correction, blind pixel marking and filling, test pattern and simulation target generation, and on-orbit adjustment of imaging polarity; the long-wave information acquisition circuit and detector output image data to the on-board processing unit and the data transmission and storage unit.

[0085] The instrument management and power box is designed with a detector temperature protection function.

[0086] When the temperature of the short-wave detector exceeds the safe working temperature threshold, the instrument management and power box actively shields the short-wave detector power-on instruction from the integrated electronic unit; when the temperature of the short-wave detector exceeds the safe working temperature threshold in the powered-on state, the instrument management and power box can autonomously send a short-wave detector power-off instruction to the short-wave information acquisition circuit.

[0087] When the temperature of the long-wave detector exceeds the safe working temperature threshold, the instrument management and power box actively shields the long-wave detector power-on instruction from the integrated electronic unit; when the temperature of the long-wave detector exceeds the safe working temperature threshold in the powered-on state, the instrument management and power box can autonomously send a long-wave detector power-off instruction to the long-wave information acquisition circuit.

[0088] Those skilled in the art can understand the present embodiment as a more specific description of embodiment 1.

[0089] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0090] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict.

Claims

1. A space-borne optical imaging payload, characterized in that, The short-wave camera, the long-wave camera, the on-board processing unit, the data transmission and storage unit, the integrated electronic unit, the power distribution device, the instrument management and power supply box, and the refrigeration machine control box are connected. The short-wave camera is installed outside the satellite cabin, the long-wave camera is installed outside the satellite cabin, the instrument management and power supply box is installed inside the satellite cabin, and the refrigeration machine control box is installed outside the satellite cabin. The short-wave camera comprises a short-wave refrigeration machine, a short-wave camera temperature control module, a short-wave information acquisition circuit, and a short-wave detector. The long-wave camera comprises a long-wave refrigeration machine, a long-wave camera temperature control module, a long-wave information acquisition circuit, and a long-wave detector. The short-wave camera temperature control module is connected with the instrument management and power supply box. The short-wave information acquisition circuit is connected with the instrument management and power supply box, the on-board processing unit, the data transmission and storage unit, and the integrated electronic unit.

2. The space-borne optical imaging payload of claim 1, wherein, The short-wave detector is connected with the short-wave information acquisition circuit, and is controlled by the short-wave information acquisition circuit for power supply, imaging driving, and data reading.

3. The space-borne optical imaging payload of claim 1, wherein, The short-wave optical machine assembly comprises a camera structure and a lens barrel and a lens assembly, and realizes closed-loop temperature control through the short-wave camera temperature control module to adjust the temperature of the lens barrel and the lens assembly, changes the refractive index of the lens assembly through temperature change, and adjusts the focal length of the short-wave camera. The long-wave camera temperature control module is connected with the instrument management and power supply box. The long-wave information acquisition circuit is connected with the instrument management and power supply box, the on-board processing unit, the data transmission and storage unit, and the integrated electronic unit. The long-wave detector is connected with the long-wave information acquisition circuit, and is controlled by the long-wave information acquisition circuit for power supply, imaging driving, and data reading. The long-wave optical machine assembly comprises a camera structure and a lens barrel and a lens assembly, and realizes closed-loop temperature control through the long-wave camera temperature control module to adjust the temperature of the lens barrel and the lens assembly, changes the refractive index of the lens assembly through temperature change, and adjusts the focal length of the short-wave camera. ​ 4. The space-borne optical imaging payload of claim 1, wherein, ​ ​ ​ ​ ​ ​ 5. The space-borne optical imaging payload of claim 1, wherein, The instrument management and power box receives remote control instructions from the integrated electronic unit, which are forwarded by the instrument management and power box to the short-wave information acquisition circuit and detector, the long-wave information acquisition circuit and detector, and the refrigerator control box; the instrument management and power box receives telemetry feedback from the short-wave information acquisition circuit and detector, the long-wave information acquisition circuit and detector, and the refrigerator control box, and returns to the integrated electronic unit.

6. The space-borne optical imaging payload of claim 1, wherein, The refrigerator control box controls the short-wave refrigerator and the long-wave refrigerator, realizing closed-loop refrigeration of the short-wave detector and the long-wave detector.

7. The space-borne optical imaging payload of claim 6, wherein, The refrigerator control box includes a detector refrigeration standby temperature mode and a detector refrigeration working temperature mode. The refrigerator control box performs refrigerator drive protection, and when the refrigerator drive current exceeds a safe working current threshold, the refrigerator control box autonomously performs a refrigerator shutdown operation.

8. The space-borne optical imaging payload of claim 3, wherein, The short-wave information acquisition circuit and short-wave detector receive high-speed on-board data from the integrated electronic unit, which includes on-orbit programming software data, non-uniform correction parameters, and on-orbit adjustment parameters of imaging polarity, and complete on-orbit programming, image non-uniform correction, blind pixel marking and filling, test pattern and simulation target generation, and on-orbit adjustment of imaging polarity. The short-wave information acquisition circuit and short-wave detector output image data to the on-board processing unit and the data transmission and storage unit.

9. The space-borne optical imaging payload of claim 4, wherein, The long-wave information acquisition circuit and long-wave detector receive high-speed on-board data from the integrated electronic unit, which includes on-orbit programming software data, non-uniform correction parameters, and on-orbit adjustment parameters of imaging polarity, and complete on-orbit programming, image non-uniform correction, blind pixel marking and filling, test pattern and simulation target generation, and on-orbit adjustment of imaging polarity. The long-wave information acquisition circuit and long-wave detector output image data to the on-board processing unit and the data transmission and storage unit.

10. The space-borne optical imaging payload of claim 1, wherein, The instrument management and power box performs detector temperature protection. When the temperature of the short-wave detector exceeds a safe working temperature threshold, the instrument management and power box actively shields the short-wave detector power-on instruction from the integrated electronic unit; when the temperature of the short-wave detector exceeds the safe working temperature threshold in the powered-on state, the instrument management and power box can autonomously send a short-wave detector power-off instruction to the short-wave information acquisition circuit; When the temperature of the long-wave detector exceeds a safe working temperature threshold, the instrument management and power box actively shields the long-wave detector power-on instruction from the integrated electronic unit; when the temperature of the long-wave detector exceeds the safe working temperature threshold in the powered-on state, the instrument management and power box can autonomously send a long-wave detector power-off instruction to the long-wave information acquisition circuit.

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