Satellite-borne optical imaging load

Abstract

The invention provides a satellite-borne optical imaging load, which comprises a short-wave camera, and the short-wave camera is connected with an on-satellite processing unit, a data transmission solid storage unit and a comprehensive electronic unit. The long-wave camera is connected with the on-satellite processing unit, the data transmission solid storage unit and the comprehensive electronic unit; the instrument management and power box is connected with the short-wave camera, the long-wave camera, the comprehensive electronic unit and the distributor; and the refrigerator electric cabinet is connected with the short-wave camera, the long-wave camera, the instrument management and power supply box and the power distributor. Camera focusing is achieved through a temperature control means, the functions of camera imaging polarity in-orbit adjustment, test chart simulation target generation, detector temperature protection, refrigerator driving protection and the like are achieved, the lightweight and low-power-consumption design is achieved, the resource requirements of satellite-borne optical imaging loads for various satellite platforms are reduced, and the system is suitable for large-scale popularization and application. And the flexibility and the fault-tolerant capability of in-orbit use are improved.

Description

Technical Field

[0001] The present invention relates to the technical field of satellite remote sensing imaging, and in particular to a satellite-borne optical imaging payload. Background Art

[0002] With the growth of space-based remote sensing demand and the development of optical imaging technology, satellite-borne optical imaging payloads are increasingly being used. Traditional satellite-borne optical imaging payloads have the following problems: single functions, poor flexibility, insufficient fault tolerance in orbit, and reliance on the use of a focusing mechanism for on-orbit focusing. They are large in size and weight and are usually located outside the satellite cabin. Thermal control and heating decontamination of optical imaging payloads require a high energy demand for the entire satellite. Therefore, it is very meaningful to develop a satellite-borne optical payload that can reduce the demand for satellite platform resources, is flexible in on-orbit use, and has fault tolerance.

[0003] The patent with publication number CN115072010B relates to a turntable mechanism for space-borne optical imaging payloads, and specifically to a space-borne deployable turntable mechanism and a test method for its hysteresis time, which is used to solve the shortcomings of existing space-borne turntable mechanisms, such as relatively small loads or inability to effectively reduce the mechanical vibration and impact experienced by the optical imaging payload. The space-borne deployable turntable mechanism includes a first rotating arm, a second rotating arm, an unfolding drive mechanism, and a mechanical locking mechanism. The first rotating arm and the second rotating arm are respectively provided with an azimuth axis and a pitch axis intended to support the optical imaging payload. The supporting mechanism is in a folded state before being launched into orbit, and is converted to an unfolded state after being launched into orbit, which effectively reduces the mechanical vibration and impact experienced by the optical imaging payload, thereby improving the load ratio and launch reliability. At the same time, the present invention discloses a test method for the hysteresis time of a space-borne deployable turntable mechanism.

[0004] The patent with the publication number CN109141628B discloses a satellite-borne fiber focal plane detector device, including: an incident light focal plane end, a scrambled mode fiber, a temperature control box, a fiber light output head, a collimating lens barrel, a collimating mirror, an attenuation plate, a photomultiplier tube, a thermistor, a semiconductor cooling sheet, a heat pipe, a heat sink, a high-voltage power supply, a signal box, and a temperature control electronics box; the incident light focal plane is connected to the scrambled mode fiber; the scrambled mode fiber passes through the temperature control box and is connected to the fiber light output head; the fiber light output head is inserted into the collimating lens barrel; the collimating mirror and the attenuation plate 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 cooling sheet are attached to the photomultiplier tube housing; the cold end of the heat pipe is attached to the back of the semiconductor cooling sheet, and the hot end is attached to the inner side of the heat sink; the high-voltage power supply is connected to the signal box and the photomultiplier tube; the temperature control electronics box is connected to the thermistor and the semiconductor cooling sheet. The present invention solves the problem of insufficient detector response capability of satellite optical imaging payload under weak light conditions.

[0005] The patent with the publication number CN116039967A discloses a rolling shutter door protection device for an aircraft optical window. The rolling shutter door fixing plate serves as the mounting base of the device, and carries all the parts for installation and fixing. The long axis supports the motor side and the driving shaft support to realize the parallel installation of the motor fixing seat, the driving shaft, and the driven shaft. The closed position switch and the open position switch feedback the position information to cut off the power of the motor. The first baffle fixing member, the second baffle fixing member, the third baffle fixing member, and the fourth baffle fixing member are respectively installed on the corresponding sliders. The first slider, the first guide rail combination and the second slider, the second guide rail combination are parallelly installed on the rolling shutter door fixing plate to realize the parallel sliding of the baffle. The chain pressing plate fixes the chain and the baffle to realize the synchronous movement of the chain and the baffle. The sprocket pressing plate completes the axial fixed crimping of the sprocket. The device has a simple and compact structure, low cost, high space utilization, long life, good environmental adaptability, and convenient installation and debugging.

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

[0007] The patent with the publication number CN114488486A discloses an optical imaging system. From the object side to the image side of the optical imaging system, it includes: a first transmission surface is arranged in the outer circumferential region of the object side surface of the first lens, a first reflection surface is arranged in the outer circumferential region of the image side surface of the first lens, a second reflection surface is arranged in the paraxial region of the object side surface of the first lens, and a second transmission surface is arranged in the paraxial region of the image side surface 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; the sixth lens has a negative focal power; light enters successively through the first transmission surface, is reflected by the first reflection surface to the second reflection surface, and is reflected by the second reflection surface to the second transmission surface and then enters the second lens; 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 invention solves the problem in the prior art that long-focus lenses cannot兼顾miniaturization and high pixel count.

[0008] The patent with the publication number CN107728315A discloses a space camera system. The space camera system provided by this invention can adjust the secondary mirror according to the imaging situation during on-orbit operation, so as to obtain good imaging performance. At the same time, during ground alignment, post-assembly adjustment can be carried out, that is, after the secondary mirror is installed, adjustment is carried out. By detecting the wavefront aberration of the system, the final position of the secondary mirror is determined. In this way, the optical system of the space camera can be adjusted to the best state.

[0009] The opto-mechatronic space camera disclosed in the patent with the publication number CN107831628A belongs to the field of space optical technology, and specifically relates to an opto-mechatronic space camera. The camera includes a lens assembly and a main bracket located outside the lens assembly. The main bracket is a frame structure in the shape of a cuboid with an installation seat. The lens assembly is fixed to the front of the installation seat; a circuit board assembly is fixedly installed on the main bracket; the circuit board assembly includes an upper circuit board located on the top of the lens assembly, a lower circuit board located on the bottom of the lens assembly, and a focal plane board located on the back of the installation seat. The upper circuit board, the lower circuit board, and the focal plane board are connected by flexible cables. The present invention connects the circuit board assembly and the lens assembly into one body through the main bracket, and uses the satellite cabin panel as a structural cover plate, so that each part is highly integrated, greatly reducing the size of the structural body.

[0010] The above patents only involve the principles and component systems of optical imaging systems, and do not involve the design of on-orbit use flexibility and fault tolerance capabilities, nor do they involve the content of reducing the resource requirements for the entire satellite platform.

[0011] Therefore, a new technical solution needs to be proposed to improve the above technical problems. Summary of the Invention

[0012] In view of the defects in the prior art, an object of the present invention is to provide a satellite-borne optical imaging payload.

[0013] A satellite-borne optical imaging payload provided by the present invention comprises: a short-wave camera and an on-board processing unit, a data transmission storage unit, an integrated electronic unit, a long-wave camera and an on-board processing unit, a distributor, a short-wave camera, a long-wave camera, an instrument management and power supply box, and a refrigerator electrical control box;

[0014] The shortwave camera is connected to the onboard processing unit, the data transmission and storage unit, and the integrated electronic unit; the longwave camera is connected to the onboard processing unit, the data transmission and storage unit, and the integrated electronic unit; the instrument management and power supply box is connected to the shortwave camera, the longwave camera, the integrated electronic unit, and the distributor; the refrigerator electrical control box is connected to the shortwave camera, the longwave camera, the instrument management and power supply box, and the 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 refrigerator electrical control box is installed outside the satellite cabin.

[0016] Preferably, the shortwave camera comprises:

[0017] Short-wave refrigerator: the short-wave refrigerator is connected to the refrigerator electric control box;

[0018] Shortwave camera temperature control module: the shortwave camera temperature control module is connected to the instrument management and power supply box;

[0019] Shortwave information acquisition circuit: the shortwave information acquisition circuit is connected with the instrument management and power supply box, the onboard processing unit, the data transmission storage unit and the integrated electronic unit;

[0020] Shortwave detector: the shortwave detector is connected to the shortwave information acquisition circuit, the shortwave detector is controlled by the shortwave information acquisition circuit for power supply, driving imaging and data reading, and the shortwave detector is cooled by the shortwave refrigerator;

[0021] Shortwave optical mechanical assembly: The shortwave optical mechanical assembly includes a camera structure, a lens barrel, and a lens assembly. The shortwave optical mechanical assembly realizes closed-loop temperature control through the shortwave camera temperature module, adjusts the temperature of the lens barrel and the lens assembly, and adjusts the focal length of the shortwave camera by changing the refractive index of the lens assembly through temperature changes.

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

[0023] Long-wave refrigerator: the long-wave refrigerator is connected to the refrigerator electrical control box;

[0024] Long-wave camera temperature control module: the long-wave camera temperature control module is connected to 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 storage unit and the integrated electronic unit;

[0026] Long-wave detector: the long-wave detector is connected to the long-wave information acquisition circuit, the long-wave detector is controlled by the long-wave information acquisition circuit for power supply, driving imaging and data reading, and the long-wave detector is cooled by the long-wave refrigerator;

[0027] Long-wave optical mechanical assembly: The long-wave optical mechanical assembly includes a camera structure, a lens barrel, and a lens assembly. The long-wave optical mechanical assembly realizes closed-loop temperature control through the long-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 changes.

[0028] Preferably, the instrument management and power supply box receives remote control instructions from the integrated electronic unit, which are forwarded by the instrument management and power supply box to the shortwave information acquisition circuit and detector, the longwave information acquisition circuit and detector, and the refrigerator electrical control box; the instrument management and power supply box receives remote control feedback from the shortwave information acquisition circuit and detector, the longwave information acquisition circuit and detector, and the refrigerator electrical control box, and returns it to the integrated electronic unit.

[0029] Preferably, the refrigerator electrical control box controls the short-wave refrigerator and the long-wave refrigerator to achieve closed-loop cooling of the short-wave detector and the long-wave detector.

[0030] Preferably, the refrigerator electrical control box includes a detector refrigeration standby temperature mode and a detector refrigeration operating temperature mode;

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

[0032] Preferably, the shortwave information acquisition circuit and the shortwave detector receive high-speed on-board data from the integrated electronic unit, wherein the high-speed on-board data include on-orbit programming software data, non-uniformity correction parameters and imaging polarity on-orbit adjustment parameters, and the shortwave information acquisition circuit and the detector complete on-orbit programming, image non-uniformity correction, blind pixel marking and filling, test pattern and simulation target generation, and imaging polarity on-orbit adjustment functions;

[0033] The shortwave information acquisition circuit and the shortwave detector output image data to the onboard processing unit and the data transmission storage unit.

[0034] Preferably, the long-wave information acquisition circuit and the long-wave detector receive high-speed on-board data from the integrated electronic unit, the high-speed on-board data including on-orbit programming software data, non-uniformity 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-uniformity correction, blind pixel marking and filling, test pattern and simulation target generation, and imaging polarity on-orbit adjustment functions;

[0035] 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.

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

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

[0038] When the temperature of the long-wave detector exceeds the safe operating temperature threshold, the instrument management and power supply 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 operating temperature threshold in the powered-on state, the instrument management and power supply box can autonomously send a long-wave detector power-off instruction to the long-wave information acquisition circuit.

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

[0040] 1. The split design of the present invention separates the power supply, instrument management and refrigeration control circuits into a single unit, which is installed in the satellite cabin, reducing the energy consumption of the entire satellite for thermal control of the optical imaging payload and heating decontamination; the refrigerator control designs the detector refrigeration standby temperature mode (low power consumption mode) and the detector refrigeration working temperature mode. The normal state is the low power consumption mode, and the detector working temperature mode is used only when the detector works for a short time, reducing the energy consumption of the entire satellite;

[0041] 2. The present invention has a detector temperature protection function. If the detector exceeds the safe working temperature threshold, the detector power-on instruction is shielded. If the detector exceeds the safe working temperature threshold in the powered-on state, the detector power-off operation is automatically executed; it has a refrigerator drive protection function. If the refrigerator drive current exceeds the safe working current threshold, the refrigerator shutdown operation is automatically executed;

[0042] 3. The present invention has the function of generating test pattern simulation targets, which is convenient for self-testing of optical imaging payload functions and verification testing of the whole satellite information loop; it has the function of adjusting the camera imaging polarity on-orbit, which improves the flexibility and fault tolerance of on-orbit use;

[0043] 4. The present invention can perform on-orbit programming and software upgrades through high-speed injection; there is no focusing mechanism to reduce the weight of the optical imaging load; the lens barrel and lens assembly are designed to be thermally conductive, and a heater is provided on the lens barrel. By adjusting the temperature of the lens barrel and lens assembly, the refractive index of the lens assembly is changed by temperature changes to fine-tune the camera focal length, thereby realizing an on-orbit focusing design without a focusing mechanism, and the focusing range can reach more than ±50um. BRIEF DESCRIPTION OF THE DRAWINGS

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

[0045] Figure 1 The present invention is a block diagram of the composition of a satellite-borne optical imaging payload. DETAILED DESCRIPTION

[0046] The present invention is described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0047] Embodiment 1:

[0048] Reference Figure 1 According to the present invention, a satellite-borne optical imaging payload includes: a short-wave camera and an on-board processing unit, a data transmission storage unit, an integrated electronic unit, a long-wave camera and an on-board processing unit, a power distributor, a short-wave camera, a long-wave camera, an instrument management and power supply box, and a refrigerator electrical control box; the short-wave camera is connected to the on-board processing unit, the data transmission storage unit, and the integrated electronic unit; the long-wave camera is connected to the on-board processing unit, the data transmission storage unit, and the integrated electronic unit; the instrument management and power supply box is connected to the short-wave camera, the long-wave camera, the integrated electronic unit, and the power distributor; the refrigerator electrical control box is connected to the short-wave camera, the long-wave camera, the instrument management and power supply box, and the power distributor.

[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 refrigerator electric control box is installed outside the satellite cabin.

[0050] Shortwave cameras include:

[0051] Short-wave refrigerator: the short-wave refrigerator is connected to the refrigerator electric control box;

[0052] Shortwave camera temperature control module: the shortwave camera temperature control module is connected to 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 onboard processing unit, the data transmission storage unit and the integrated electronic unit;

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

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

[0056] Raise the temperature control threshold of the shortwave camera. The temperature control module of the shortwave camera increases the heating power of the camera barrel and lens assembly, increases the temperature of the lens assembly, increases the refractive index of the lens assembly, and reduces the focal length of the shortwave camera.

[0057] Lower the temperature control threshold of the shortwave camera. The temperature control module of the shortwave camera reduces the heating power to the camera barrel and lens assembly, lowers the temperature of the lens assembly, reduces the refractive index between lens groups, and increases the focal length of the camera.

[0058] Long wave cameras include:

[0059] Long-wave refrigerator: the long-wave refrigerator is connected to the refrigerator electrical control box;

[0060] Long-wave camera temperature control module: the long-wave camera temperature control module is connected to 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 storage unit and the integrated electronic unit;

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

[0063] Long-wave optical mechanical assembly: The long-wave optical mechanical assembly includes a camera structure, a lens barrel, and a lens assembly. The long-wave optical mechanical assembly realizes closed-loop temperature control through the long-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 changes.

[0064] Raise the temperature control threshold of the long-wave camera. The temperature control module of the long-wave camera increases the heating power of the camera barrel and 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] By lowering the temperature control threshold of the long-wave camera, the temperature control module of the long-wave camera reduces the heating power of the camera barrel and lens assembly, lowers the temperature of the lens assembly, reduces the refractive index between the lens groups, and increases the focal length of the camera.

[0066] The instrument management and power supply box receives remote control instructions from the integrated electronic unit, which are forwarded by the instrument management and power supply box to the shortwave information acquisition circuit and detector, the longwave information acquisition circuit and detector, and the refrigerator electrical control box; the instrument management and power supply box receives remote control feedback from the shortwave information acquisition circuit and detector, the longwave information acquisition circuit and detector, and the refrigerator electrical control box, and returns it 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 the refrigerator drive current exceeds the safe working current threshold, and autonomously performs the refrigerator shutdown operation.

[0068] The shortwave information acquisition circuit and the shortwave detector receive high-speed onboard data from the integrated electronic unit, wherein the high-speed onboard data include on-orbit programming software data, non-uniformity correction parameters and on-orbit adjustment parameters of imaging polarity. The shortwave information acquisition circuit and the detector complete the on-orbit programming, image non-uniformity correction, blind pixel marking and filling, test pattern and simulation target generation, and on-orbit adjustment of imaging polarity. The shortwave information acquisition circuit and the shortwave detector output image data to the on-board processing unit and the data transmission storage unit.

[0069] The long-wave information acquisition circuit and the long-wave detector receive high-speed on-board data from the integrated electronic unit, wherein the high-speed on-board data include on-orbit programming software data, non-uniformity correction parameters and on-orbit adjustment parameters of imaging polarity. The short-wave information acquisition circuit and the detector complete the on-orbit programming, image non-uniformity 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 the long-wave detector output image data to the on-board processing unit and the data transmission storage unit.

[0070] The instrument management and power supply box performs temperature protection 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 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 supply 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 the safe working temperature threshold, the instrument management and power supply 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 supply box can autonomously send a long-wave detector power-off instruction to the long-wave information acquisition circuit.

[0071] Embodiment 2:

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

[0073] The present invention provides a satellite-borne optical imaging payload, including a short-wave camera, which is connected to an on-board processing unit, a data transmission storage unit, and an integrated electronic unit; a long-wave camera, which is connected to an on-board processing unit, a data transmission storage unit, and an integrated electronic unit; an instrument management and power supply box, which is connected to the short-wave camera, the long-wave camera, the integrated electronic unit, and a distributor; and a refrigerator electrical control box, which is connected to the short-wave camera, the long-wave camera, the instrument management and power supply box, and the distributor. The present invention realizes camera focusing by temperature control means, realizes functions such as on-orbit adjustment of camera imaging polarity, test pattern simulation target generation, detector temperature protection, and refrigerator drive protection, as well as lightweight and low-power design, which reduces the resource requirements of satellite-borne optical imaging payloads on various satellite platforms and improves the flexibility and fault tolerance of on-orbit use.

[0074] A satellite-borne optical imaging payload includes: a short-wave camera, a long-wave camera, an instrument management and power supply box, and a refrigerator electric control box. The short-wave camera includes: a short-wave refrigerator, a short-wave camera temperature control module, a short-wave information acquisition circuit, a short-wave detection and a short-wave optical mechanical component. The long-wave camera includes: a long-wave refrigerator, a long-wave camera temperature control module, a long-wave information acquisition circuit, a long-wave detection and a long-wave optical mechanical component.

[0075] The shortwave optical mechanical assembly includes a camera structure, a lens barrel, a lens assembly, etc. The shortwave optical mechanical assembly realizes closed-loop temperature control through a shortwave camera temperature module, which can adjust the temperature of the lens barrel and the lens assembly, and adjust the focal length of the shortwave camera by changing the refractive index of the lens assembly through temperature changes.

[0076] The long-wave optomechanical assembly includes a camera structure, a lens barrel, a lens assembly, etc. The long-wave optomechanical assembly realizes closed-loop temperature control through a long-wave camera temperature module, which can adjust the temperature of the lens barrel and the lens assembly, and adjust the focal length of the short-wave camera by changing the refractive index of the lens assembly through temperature changes.

[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 box is installed inside the satellite cabin, and the refrigerator electrical control box is installed outside the satellite cabin.

[0078] The shortwave camera is connected to the onboard processing unit, data transmission and storage unit, and integrated electronic unit; the longwave camera is connected to the onboard processing unit, data transmission and storage unit, and integrated electronic unit; the instrument management and power box is connected to the shortwave camera, longwave camera, integrated electronic unit, and distributor; the refrigerator electrical control box is connected to the shortwave camera, longwave camera, instrument management and power box and distributor.

[0079] The shortwave refrigerator is connected to the refrigerator electrical control box; the shortwave camera temperature control module is connected to the instrument management and power box; the shortwave information acquisition circuit is connected to the instrument management and power box, the onboard processing unit, the data transmission storage unit and the integrated electronic unit; the shortwave detector is connected to the shortwave information acquisition circuit, and the shortwave detector is controlled by the shortwave information acquisition circuit for power supply, imaging drive and data reading, and the shortwave detection is cooled by the shortwave refrigerator.

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

[0081] The instrument management and power box receives remote control commands from the integrated electronic unit, which are forwarded by the instrument management and power box to the shortwave information acquisition circuit and detector, the longwave information acquisition circuit and detector, and the refrigerator electrical control box; the instrument management and power box receives remote control feedback from the shortwave information acquisition circuit and detector, the longwave information acquisition circuit and detector, and the refrigerator electrical control box, and returns it to the integrated electronic unit.

[0082] The refrigerator electronic control box controls the shortwave refrigerator and the longwave refrigerator to realize closed-loop cooling of the shortwave detector and the longwave detector; the refrigerator electronic control box has a detector cooling standby temperature mode (low power mode) and a detector cooling working temperature mode, and has a refrigerator drive protection function. When the refrigerator drive current exceeds the safe working current threshold, the refrigerator shutdown operation is performed autonomously.

[0083] The shortwave information acquisition circuit and detector receive high-speed onboard data from the integrated electronic unit. The high-speed onboard data include on-orbit programming software data, non-uniformity correction parameters and on-orbit adjustment parameters of imaging polarity, etc. The shortwave information acquisition circuit and detector complete the on-orbit programming, image non-uniformity correction, blind pixel marking and filling, test pattern and simulated target generation, and on-orbit adjustment of imaging polarity. The shortwave information acquisition circuit and detector output image data to the on-board processing unit and data transmission storage unit.

[0084] The long-wave information acquisition circuit and detector receive high-speed onboard data from the integrated electronic unit. The high-speed onboard data include on-orbit programming software data, non-uniformity correction parameters and on-orbit adjustment parameters of imaging polarity, etc. The short-wave information acquisition circuit and detector complete the on-orbit programming, image non-uniformity correction, blind pixel marking and filling, test pattern and simulated 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 data transmission storage unit.

[0085] Instrument management and power box design detector temperature protection function.

[0086] When the temperature of the shortwave detector exceeds the safe operating temperature threshold, the instrument management and power supply box actively blocks the shortwave detector power-on command from the integrated electronic unit; when the temperature of the shortwave detector exceeds the safe operating temperature threshold in the powered-on state, the instrument management and power supply box can autonomously send a shortwave detector power-off command to the shortwave information acquisition circuit.

[0087] When the temperature of the long-wave detector exceeds the safe operating temperature threshold, the instrument management and power supply box actively blocks the long-wave detector power-on command from the integrated electronic unit; when the temperature of the long-wave detector exceeds the safe operating 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.

[0088] Those skilled in the art may understand this embodiment as a more specific description of Embodiment 1.

[0089] In the description of the present application, it should be understood that the terms "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inside", "outside", etc., indicating orientations or positional relationships, are based on the orientations or positional relationships shown in the accompanying drawings, and are only for the convenience of describing the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore should not be understood as a limitation on the present application.

[0090] The above describes the specific embodiments of the present invention. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A spaceborne optical imaging payload, characterized in that: include: Short-wave camera and on-board processing unit, data transmission storage unit, integrated electronic unit, long-wave camera and on-board processing unit, distributor, short-wave camera, long-wave camera, instrument management and power supply box and refrigerator electrical control box; The shortwave camera is connected to the onboard processing unit, the data transmission and storage unit, and the integrated electronic unit; the longwave camera is connected to the onboard processing unit, the data transmission and storage unit, and the integrated electronic unit; the instrument management and power supply box is connected to the shortwave camera, the longwave camera, the integrated electronic unit, and the distributor; the refrigerator electrical control box is connected to the shortwave camera, the longwave camera, the instrument management and power supply box, and the distributor.

2. The spaceborne optical imaging payload according to claim 1, characterized in that: 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 electric control box is installed outside the satellite cabin.

3. The spaceborne optical imaging payload according to claim 1, characterized in that: The shortwave camera comprises: Short-wave refrigerator: the short-wave refrigerator is connected to the refrigerator electric control box; Shortwave camera temperature control module: the shortwave camera temperature control module is connected to the instrument management and power supply box; Shortwave information acquisition circuit: the shortwave information acquisition circuit is connected with the instrument management and power supply box, the onboard processing unit, the data transmission storage unit and the integrated electronic unit; Shortwave detector: the shortwave detector is connected to the shortwave information acquisition circuit, the shortwave detector is controlled by the shortwave information acquisition circuit for power supply, driving imaging and data reading, and the shortwave detector is cooled by the shortwave refrigerator; Shortwave optical mechanical assembly: The shortwave optical mechanical assembly includes a camera structure, a lens barrel, and a lens assembly. The shortwave optical mechanical assembly realizes closed-loop temperature control through the shortwave camera temperature module, adjusts the temperature of the lens barrel and the lens assembly, and adjusts the focal length of the shortwave camera by changing the refractive index of the lens assembly through temperature changes.

4. The spaceborne optical imaging payload according to claim 1, characterized in that: The long wave camera comprises: Long-wave refrigerator: the long-wave refrigerator is connected to the refrigerator electrical control box; Long-wave camera temperature control module: the long-wave camera temperature control module is connected to the instrument management and power supply box; 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 storage unit and the integrated electronic unit; Long-wave detector: the long-wave detector is connected to the long-wave information acquisition circuit, the long-wave detector is controlled by the long-wave information acquisition circuit for power supply, driving imaging and data reading, and the long-wave detector is cooled by the long-wave refrigerator; Long-wave optical mechanical assembly: The long-wave optical mechanical assembly includes a camera structure, a lens barrel, and a lens assembly. The long-wave optical mechanical assembly realizes closed-loop temperature control through the long-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 changes.

5. The spaceborne optical imaging payload according to claim 1, characterized in that: The instrument management and power supply box receives remote control instructions from the integrated electronic unit, which are forwarded by the instrument management and power supply box to the shortwave information acquisition circuit and detector, the longwave information acquisition circuit and detector, and the refrigerator electrical control box; the instrument management and power supply box receives remote control feedback from the shortwave information acquisition circuit and detector, the longwave information acquisition circuit and detector, and the refrigerator electrical control box, and returns it to the integrated electronic unit.

6. The spaceborne optical imaging payload according to claim 1, characterized in that: The refrigerator electric control box controls the short-wave refrigerator and the long-wave refrigerator to achieve closed-loop cooling of the short-wave detector and the long-wave detector.

7. The spaceborne optical imaging payload according to claim 6, characterized in that: The refrigerator electrical control box includes a detector refrigeration standby temperature mode and a detector refrigeration operating 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 shutdown operation is autonomously executed.

8. The spaceborne optical imaging payload according to claim 3, characterized in that: The shortwave information acquisition circuit and the shortwave detector receive high-speed on-board data from the integrated electronic unit, wherein the high-speed on-board data include on-orbit programming software data, non-uniformity correction parameters and imaging polarity on-orbit adjustment parameters, and the shortwave information acquisition circuit and the detector complete on-orbit programming, image non-uniformity correction, blind pixel marking and filling, test pattern and simulation target generation, and imaging polarity on-orbit adjustment functions; The shortwave information acquisition circuit and the shortwave detector output image data to the onboard processing unit and the data transmission storage unit.

9. The spaceborne optical imaging payload according to claim 4, characterized in that: The long-wave information acquisition circuit and the long-wave detector receive high-speed on-board data from the integrated electronic unit, wherein the high-speed on-board data include on-orbit programming software data, non-uniformity 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-uniformity correction, blind pixel marking and filling, test pattern and simulation target generation, and imaging polarity on-orbit adjustment functions; 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.

10. The spaceborne optical imaging payload according to claim 1, characterized in that: The instrument management and power supply box provide temperature protection for the detector; When the temperature of the shortwave detector exceeds the safe working temperature threshold, the instrument management and power supply box actively shields the shortwave detector power-on instruction from the integrated electronic unit; when the temperature of the shortwave detector exceeds the safe working temperature threshold in the powered-on state, the instrument management and power supply box can autonomously send a shortwave detector power-off instruction to the shortwave information acquisition circuit; When the temperature of the long-wave detector exceeds the safe operating temperature threshold, the instrument management and power supply 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 operating temperature threshold in the powered-on state, the instrument management and power supply box can autonomously send a long-wave detector power-off instruction to the long-wave information acquisition circuit.

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