Satellite load system and control method

Abstract

The embodiment of the invention provides a satellite load system and a control method. The system comprises a satellite load camera, a data communication load module and an inter-satellite communication load module. After an instruction for establishing the inter-satellite communication link is received, attitude adjustment can be performed, so that the inter-satellite communication unit of the inter-satellite communication load module points to the direction of the communication satellite. And the inter-satellite communication unit and / or the data communication load module are / is used for sending a connection instruction to the communication satellite and receiving a receipt signal, so that an inter-satellite communication link with the communication satellite is established according to the receipt signal. The system can solve the problem of low load utilization rate during in-orbit operation of a satellite through linkage among the satellite load camera, the data communication load module and the inter-satellite communication load module.

Description

Technical Field

[0001] The present application relates to the technical field of intelligent payload satellites, and in particular to a satellite payload system and a control method. Background Art

[0002] Optical payload is a kind of payload carried on satellite, including various optical devices and instruments installed on satellite. According to the pre-set tasks, optical payload can collect optical signals in specific mission areas to obtain optical information on the earth or in space. Optical payload is a key equipment in satellite remote sensing, earth observation and deep space exploration.

[0003] For example, the optical payload can include an optical payload camera, which can achieve 2-meter panchromatic resolution and 10-meter multispectral resolution with a width of 10 kilometers in a 500-kilometer orbit. The optical payload camera can also support push-broom imaging, covering panchromatic and multispectral bands, to meet the optical information collection needs of different on-orbit missions.

[0004] However, satellite payloads have a single function. For example, in almost all mission phases except for on-orbit measurement and control missions, optical payloads are turned off or in standby mode, which reduces the utilization rate of optical payloads. In addition, since payload equipment is specialized, payloads deployed for one mission phase are difficult to apply to other mission phases, further reducing the utilization rate of payloads. Summary of the invention

[0005] In view of this, an embodiment of the present application provides a satellite payload system and a control method to solve the problem of low payload utilization during the on-orbit operation of the satellite.

[0006] According to one aspect of the present application, a satellite payload system is provided, the system comprising:

[0007] A satellite payload camera comprises a camera body, a camera focal plane electric box, a camera focusing mechanism and a camera lower computer; the camera focal plane electric box is electrically connected to the camera body, the camera focusing mechanism and the camera lower computer; the camera focusing mechanism is connected to the optical lens of the camera body; the camera lower computer is connected to the camera focusing mechanism;

[0008] A data communication payload module, comprising a plurality of transponders and data communication antennas based on different communication standards; the data communication payload module is configured to receive narrowband communication data and forward the narrowband communication data to a target component;

[0009] The intersatellite communication payload module comprises an intersatellite communication unit and a communication control unit; the intersatellite communication unit is connected to the communication control unit; the communication control unit is also connected to the data communication payload module;

[0010] The communication control unit is configured as follows:

[0011] In response to an instruction to establish an intersatellite communication link, sending an attitude adjustment instruction to the intersatellite communication unit, wherein the attitude adjustment instruction is used to drive the intersatellite communication unit to point to the direction of the communication satellite;

[0012] Sending a connection instruction to the communication satellite through the intersatellite communication unit and / or the data communication payload module;

[0013] receiving a receipt signal captured by the intersatellite communication unit and / or the data communication payload module, wherein the receipt signal is a signal fed back by the communication satellite in response to the connection instruction;

[0014] An intersatellite communication link is established between the intersatellite communication unit and the communication satellite according to the receipt signal, and the intersatellite communication link is used to send or receive intersatellite communication data.

[0015] Optionally, the camera body includes an optical lens, a lens barrel, a light shield and a camera bracket;

[0016] The optical lens is arranged in the lens barrel; the light shield is arranged at one end of the lens barrel, and the camera lower computer is arranged at the other end of the lens barrel; the camera bracket is located on the outer wall of the lens barrel, and the camera bracket is connected to the camera lower computer; a photosensitive element is arranged on the camera lower computer, and the photosensitive element is configured to convert an optical signal into image data.

[0017] Optionally, the optical lens includes a primary mirror assembly and a secondary mirror assembly; the camera lower computer includes a back plate assembly and a focal plane assembly;

[0018] One end of the lens barrel is fixedly connected to the back plate assembly, and the other end of the lens barrel is movably connected to the light shield; the secondary mirror assembly is arranged on a side of the lens barrel close to the light shield, and the primary mirror assembly is arranged on a side of the lens barrel close to the back plate;

[0019] The focal plane assembly is bonded to the back plate assembly, and the photosensitive element is arranged on the focal plane assembly; the main mirror assembly is movably connected to the back plate assembly through the camera focusing mechanism.

[0020] Optionally, the primary mirror assembly includes a first reflective lens and a transmissive lens group; the secondary mirror assembly includes a second reflective lens;

[0021] The first reflective lens is a concave mirror provided with a reflective layer, and is used to reflect the light entering the lens barrel to converge onto the second reflective lens; the second reflective lens is also provided with a reflective layer, and is used to reflect the light reflected and converged by the first reflective lens to the position of the transmission lens group;

[0022] The transmission lens group includes a plurality of transmission lenses, which are used to refract the light reflected by the second reflection lens onto the photosensitive device.

[0023] Optionally, the primary mirror assembly includes a third reflective lens and a fourth reflective lens; the secondary mirror assembly includes a fifth reflective lens;

[0024] The third reflective lens, the fourth reflective lens and the fifth reflective lens are all provided with a reflective layer; the third reflective lens and the fourth reflective lens are concave mirrors;

[0025] The third reflecting lens is used to reflect the light entering the lens barrel and converge it onto the fifth reflecting lens; the fifth reflecting lens is used to reflect the light reflected and converged by the third reflecting lens and converge it onto the fourth reflecting lens; the fourth reflecting lens is used to reflect the light reflected by the third reflecting lens and converge it onto the photosensitive device.

[0026] Optionally, the camera slave computer is further configured as:

[0027] receiving an attitude detection instruction sent by the communication control unit, wherein the attitude detection instruction is a control instruction generated by the communication control unit in response to the establishment instruction, and the attitude detection instruction is used to control the satellite payload camera and the attitude detection sensor on the current satellite to send attitude detection data to the communication control unit;

[0028] In response to the posture detection instruction, setting the focal length adjustment amount of the camera focusing mechanism according to the current task stage;

[0029] Controlling the camera focusing mechanism to adjust the imaging focal length of the camera body according to the adjustment amount, and recording current camera parameters of the camera body, wherein the current camera parameters at least include focal length;

[0030] Controlling the satellite payload camera to capture a reference image according to the current camera parameters;

[0031] The reference image is sent to the communication control unit, so that the communication control unit calculates the current running posture according to the reference image and the posture detection data collected by the posture detection sensor.

[0032] Optionally, the intersatellite communication unit is a laser terminal based on intersatellite laser communication; the intersatellite communication unit includes an optical component and an electronic component, the optical component is configured to send and receive intersatellite communication optical signals, and perform angle adjustment within a preset angle range of freedom; the electronic component is configured to perform power conversion and conversion between intersatellite communication optical signals and electrical signals; the communication control unit is further configured to:

[0033] Receiving the reference image sent by the camera lower computer and the posture detection data collected by the posture detection sensor;

[0034] Calculate the current running posture according to the reference image and the posture detection data;

[0035] Acquiring the position information of the communication satellite;

[0036] Calculate the attitude angle adjustment amount according to the orientation information and the current running attitude;

[0037] The adjustment instruction is generated according to the attitude angle adjustment amount, and the adjustment instruction is sent to the optical component of the intersatellite communication unit, so that the optical component performs angle adjustment according to the attitude angle adjustment amount.

[0038] Optionally, the communication control unit is further configured to:

[0039] Receiving real-time attitude parameters sent by the communication satellite through the intersatellite communication link, the real-time attitude parameters being attitude data of the communication satellite collected by an attitude detection sensor on the communication satellite after the intersatellite communication link is established;

[0040] Calculate the signal transmission path of the communication satellite according to the real-time attitude parameter;

[0041] Calculating a signal tracking adjustment amount according to the signal transmission path;

[0042] An attitude tracking instruction is generated according to the signal tracking adjustment amount, and the attitude tracking instruction is sent to the intersatellite communication unit, so that the intersatellite communication unit adjusts the intersatellite signal receiving and sending direction to coincide with the signal transmission path according to the attitude tracking instruction.

[0043] Optionally, the communication control unit is further configured to:

[0044] Based on the communication mode corresponding to the intersatellite communication unit, converting the connection instruction into first communication data, wherein the first communication data includes the position information of the current satellite;

[0045] sending the first communication data to the communication satellite through the intersatellite communication unit, so that the communication satellite adjusts its operating attitude according to the position information of the current satellite;

[0046] receiving the first receipt signal captured by the intersatellite communication unit, where the first receipt signal is a signal fed back by the communication satellite after adjusting its operating attitude;

[0047] If the first receipt signal is not received within a preset capture period, converting the connection instruction into second communication data based on one of the communication modes corresponding to the data communication load module;

[0048] sending the second communication data to the communication satellite through the data communication payload module;

[0049] A second receipt signal captured by the data communication payload module and / or the intersatellite communication unit is received, where the second receipt signal is a signal fed back by the communication satellite in response to the second communication data.

[0050] According to another aspect of the present application, a satellite payload control method is provided, which is applied to the above-mentioned satellite payload system, and the method includes:

[0051] In response to an instruction to establish an intersatellite communication link, sending an attitude adjustment instruction to the intersatellite communication unit, wherein the attitude adjustment instruction is used to drive the intersatellite communication unit to point to the direction of the communication satellite;

[0052] Sending a connection instruction to the communication satellite through the intersatellite communication unit and / or the data communication payload module;

[0053] receiving a receipt signal captured by the intersatellite communication unit and / or the data communication payload module, wherein the receipt signal is a signal fed back by the communication satellite in response to the connection instruction;

[0054] An intersatellite communication link is established between the intersatellite communication unit and the communication satellite according to the receipt signal, and the intersatellite communication link is used to send or receive intersatellite communication data.

[0055] By means of the above technical solution, the embodiment of the present application provides a satellite payload system and a control method, wherein the system includes: a satellite payload camera, a data communication payload module and an intersatellite communication payload module. Among them, the satellite payload camera is used to collect image data. The data communication payload module can send and receive communication data based on different communication standards. The intersatellite communication payload module includes an intersatellite communication unit and a communication control unit. After receiving the establishment instruction for the intersatellite communication link, the attitude adjustment can be performed so that the intersatellite communication unit points to the direction of the communication satellite. Then, the intersatellite communication unit and / or the data communication payload module send a connection instruction to the communication satellite and receive a receipt signal, so as to establish an intersatellite communication link with the communication satellite according to the receipt signal. The system can establish an intersatellite communication connection based on different communication modes through the linkage between the satellite payload camera, the data communication payload module and the intersatellite communication payload module, and adjust the satellite attitude with reference to the image data collected by the satellite payload camera and the attitude parameters detected by the sensor, so that the intersatellite communication unit points to the direction of the communication satellite, so as to solve the problem of low payload utilization during the satellite in-orbit operation.

[0056] The above description is only an overview of the technical solution of the present application. In order to more clearly understand the technical means of the present application, it can be implemented in accordance with the contents of the specification. In order to make the above and other purposes, features and advantages of the present application more obvious and easy to understand, the specific implementation methods of the present application are listed below. BRIEF DESCRIPTION OF THE DRAWINGS

[0057] The drawings described herein are used to provide a further understanding of the present application and constitute a part of the present application. The illustrative embodiments of the present application and their descriptions are used to explain the present application and do not constitute an improper limitation on the present application. In the drawings:

[0058] Figure 1 A schematic diagram of the structure of a satellite constellation system provided in an embodiment of the present application;

[0059] Figure 2 A schematic diagram of the payload satellite structure provided in an embodiment of the present application;

[0060] Figure 3 A schematic diagram of the structure of a satellite payload system provided in an embodiment of the present application;

[0061] Figure 4 A schematic diagram of the structure of a satellite payload camera provided in an embodiment of the present application;

[0062] Figure 5 A schematic diagram of the camera body structure provided in an embodiment of the present application;

[0063] Figure 6 A schematic diagram of the imaging unit structure provided in an embodiment of the present application;

[0064] Figure 7 A schematic diagram of the structure of a coaxial folding optical system provided in an embodiment of the present application;

[0065] Figure 8 A schematic diagram of the off-axis three-mirror optical system structure provided in an embodiment of the present application;

[0066] Fig. 9 A schematic diagram of the matching relationship of the laser communication terminal provided in the embodiment of the present application;

[0067] Fig.10 A schematic diagram of a satellite payload control method flow chart provided in an embodiment of the present application;

[0068] Fig.11 A schematic diagram of the posture tracking process provided in an embodiment of the present application. DETAILED DESCRIPTION

[0069] The present application will be described in detail below with reference to the accompanying drawings and in combination with embodiments. It should be noted that the embodiments and features in the embodiments of the present application can be combined with each other without conflict.

[0070] In an embodiment of the present application, the satellite payload system can be applied to a satellite constellation, which is a distributed satellite collection consisting of multiple satellites that work together to form a whole to achieve specific mission objectives. Compared with a single satellite, a satellite constellation has a wider coverage range and stronger functions, and can provide global or regional services. For example, a satellite constellation can achieve continuous coverage of a specific area by distributing multiple satellites on different orbital planes. By optimizing the orbital plane and phase difference of the satellite, the coverage gap is reduced and the coverage efficiency is improved.

[0071] Satellites included in a satellite constellation can carry payloads of implemented functions, so the satellites can also be called payload satellites. The payload carried by payload satellites generally refers to various equipment and instruments installed on the satellites, which are used to perform specific tasks and collect information from the earth or space. Depending on the functions implemented, the types of payloads carried by payload satellites are also different.

[0072] Satellite constellations can be applied to communications, navigation, remote sensing, environmental monitoring and other fields through communication and collaboration between multiple payload satellites and interactive support from ground control systems.

[0073] In some embodiments, the satellite constellation includes multiple payload satellites, and the multiple payload satellites establish communication connections through inter-satellite communication. The number of payload satellites included in the satellite constellation can be determined according to specific mission requirements, comprehensive constellation orbit design, constellation energy efficiency analysis, illumination condition analysis, and payload mission analysis.

[0074] like Figure 2 As shown, in some embodiments, the payload satellite includes: an integrated electronic subsystem, a communication and navigation subsystem, an attitude and orbit control subsystem, a power supply and distribution subsystem, a thermal control subsystem, and a structural subsystem. Among them, the integrated electronic subsystem is responsible for controlling the operating status of each functional component of the payload satellite, receiving, sending, storing and processing the data generated by the payload satellite during operation. In some embodiments, the integrated electronic subsystem may include an on-board computer (IOBC). The on-board computer is a computer equipped on the payload satellite, which performs satellite control by running the satellite management application. Satellite control may include control items such as satellite management, attitude and orbit control calculation, energy thermal control management, orbit calculation and payload mission management.

[0075] For example, in order to meet the satellite control requirements, the onboard computer of the integrated electronic subsystem needs to meet the set parameter indicators. For example, the processor processing power of the onboard computer is not less than 150MIPS, the FLASH capacity is 3M×8bit, and the MRAM capacity is 8M×8bit. In addition, the onboard computer supports communication interfaces such as RS422 and Controller Area Network (CAN), as well as orbital command (OC) output functions. The onboard computer can also perform analog telemetry acquisition, and the time base accuracy requirement is ≤2×10 -6 , time base stability requirement ≤2×10 -6 / day. Supports external interrupt items such as Global Navigation Satellite System (GNSS) second pulse interrupt, remote control interrupt, and telemetry interrupt.

[0076] The communication and navigation subsystem is used to establish a communication connection between the payload satellite and the ground equipment, send data to the ground equipment, or receive data from the ground equipment. The communication and navigation subsystem may include an antenna assembly and a data conversion circuit. For the data transmission process, the data in the payload satellite is processed by the integrated electronic subsystem and then transmitted to the data conversion circuit. The data conversion circuit converts the data into a radio signal, and transmits the radio signal to the ground equipment or other payload satellites through the antenna assembly. For the data reception process, the radio signal sent by the ground equipment or other payload satellite is sensed by the antenna assembly, and the sensed signal can be transmitted to the data conversion circuit. The data conversion circuit converts the radio signal into data recognizable by the integrated electronic subsystem and transmits it to the integrated electronic subsystem.

[0077] In some embodiments, the communication and navigation subsystem may also support communication between multiple payload satellites. That is, the communication and navigation subsystem may establish a communication connection with at least one of the multiple payload satellites. For example, the communication and navigation subsystem may include communication components based on intersatellite laser communication technology, such as a laser, an optical signal transceiver antenna, an optoelectronic signal conversion circuit, etc. When intersatellite communication is required, the optical signal transceiver antenna may be aimed at another payload satellite, the intersatellite communication data to be communicated may be converted through the optoelectronic signal conversion circuit, and modulated with the transmission optical signal sent by the laser, and the intersatellite communication data may be sent to another payload satellite through the optical signal transceiver antenna.

[0078] For ease of description, in the embodiment of the present application, the two payload satellites performing intersatellite communication are respectively referred to as the current satellite and the communication satellite. That is, during the intersatellite communication process, the current satellite can send intersatellite communication data to the communication satellite, and the current satellite can also receive intersatellite communication data from the communication satellite.

[0079] In addition to the communication function, the communication and navigation subsystem can also have a navigation function. For example, the communication and navigation subsystem can have a built-in navigation component, such as a GNSS component. Among them, the real-time position accuracy of the GNSS component is better than 10m (three-axis synthesis, 1σ); the real-time speed accuracy is better than 0.02m / s (1σ, flight direction); and the timing accuracy is better than 100ns.

[0080] The attitude and orbit control subsystem is used to control the operating attitude and orbit of the payload satellite according to the mission phase during the operation of the payload satellite, so that the payload satellite can meet the operating attitude requirements of the preset mission phase. In some embodiments, the attitude and orbit control analysis may include an attitude detection component and at least one attitude adjustment component. The attitude detection component is used to detect the operating attitude of the payload satellite during the on-orbit period; the attitude adjustment component is configured to adjust the operating attitude of the payload satellite.

[0081] For example, the attitude detection component of the attitude and orbit control subsystem may include one or more combinations of detection devices such as gyroscopes, magnetometers, star sensors, and sun sensors. The satellite's operating attitude can be determined through one or more attitude detection components. The attitude adjustment component may include one or more combinations of actuators such as reaction wheels, momentum wheels, magnetic torquers, thrusters, etc. In order to adjust the operating attitude of the payload satellite, the attitude and orbit control subsystem may first perform initial attitude capture, that is, after the satellite is separated, the separation angular velocity of the satellite is reduced within a specified time, the initial attitude deviation is eliminated, and the medium and low precision attitude measurement components are used to achieve the solar orientation of the sailboard and ensure energy supply. Then high-precision and high-stability attitude control is performed. The attitude and orbit control subsystem can overcome various interference torques on the satellite during the normal orbital operation of the satellite to meet the pointing accuracy and stability requirements of the mission.

[0082] The power supply and distribution subsystem is used to provide energy input for various equipment, mechanisms, and devices in the entire payload satellite. For example, the power supply and distribution subsystem may include lithium-ion battery packs, emergency power supply (EPS) main control unit, solar cell arrays, etc. The solar cell array can be used as the energy source for the entire satellite. The lithium-ion battery pack serves as an energy storage unit to provide stable and reliable instantaneous power for the entire satellite. The EPS main control unit uses the maximum power tracking algorithm to charge the lithium-ion battery and monitors the status of the lithium-ion battery and the working status of the solar cell array.

[0083] The thermal control subsystem is used to control the internal temperature of the payload satellite so that the internal components of the payload satellite can operate within the designed operating temperature range. The temperature control methods of the thermal control subsystem can include active thermal control and passive thermal control. Active thermal control is to adjust the regional temperature of a specific area through temperature control devices such as thin film heaters. Passive thermal control is to isolate the temperature of a specific area through temperature control materials such as thermal insulation materials and heat preservation materials, so that the isolated area is maintained within the set temperature range.

[0084] The structural subsystem includes mechanical structures such as support structure, stack, flywheel, star sensor, stand-alone bracket, skin, solar panel, panel deployment mechanism, antenna, camera, etc., which are used to provide support for various functional components in the payload satellite, and cooperate with the control circuit in the payload satellite to form an actuator. For example, the structural subsystem may include an deployment mechanism for realizing the flipping of solar panels and a separation mechanism for realizing the separation of satellites and rockets. Among them, the deployment mechanism can use wires to fix the solar cell array, and burn the connecting wires by heating the wire burning resistance to achieve the purpose of panel deployment. The separation mechanism can use the principle of memory alloy to separate the satellite from the rocket.

[0085] In addition to the subsystems described in the above embodiments, the payload satellite may also include other types of subsystems according to specific design requirements. For example, the payload satellite may also include a propulsion subsystem, an electrical subsystem, etc., which may be applicable to different on-orbit missions. It should be understood that other subsystems that can be associated with the subsystems described in the above embodiments by those skilled in the art also fall within the scope of protection of this application and are not listed here one by one.

[0086] The payload satellite may also carry specific equipment or instruments according to specific mission requirements, and the carried equipment or instruments may be referred to as satellite payloads. To this end, the payload satellite may also include a payload subsystem. The payload subsystem is used to perform specific on-orbit tasks according to the design requirements of the payload satellite. For ease of description, in some embodiments of the present application, the payload subsystem is also referred to as a payload system.

[0087] In order to solve the problem of low payload utilization during satellite in-orbit operation, a satellite payload system is provided in an embodiment of the present application, such as Figure 3 As shown, the system includes: a satellite payload camera, a data communication payload module and an inter-satellite communication payload module.

[0088] Among them, the satellite payload camera, as an optical payload, can be used to collect graphic data according to the planned on-orbit mission. For example, according to the mission requirements, the resolution of the satellite payload camera is sub-meter level, such as using an optical payload camera with a resolution of 1m@500km. According to this resolution index, the satellite payload camera is analyzed and designed by comprehensively considering the camera's miniaturization, light weight, low power consumption, and the requirements of achieving wide width and height imaging quality as much as possible.

[0089] like Figure 4 As shown, in some embodiments, the satellite payload camera includes a camera body, a camera focal plane electrical box, a camera focusing mechanism, and a camera lower computer. The camera body is used to convert optical signals into image data. The camera focal plane electrical box is electrically connected to the camera body, the camera focusing mechanism, and the camera lower computer, and is used to provide energy input for the camera body, the camera focusing mechanism, and the camera lower computer to ensure the normal operation of each mechanism.

[0090] The camera focusing mechanism is connected to the optical lens of the camera body; the camera lower computer is connected to the camera focusing mechanism. The camera focusing mechanism can drive the optical lens in the camera body to move, so as to adjust the focal length of the optical lens. Exemplarily, the camera focusing mechanism can be based on a ball screw structure, that is, the camera focusing mechanism includes a motor, a screw, a moving block and a connecting piece. The optical lens of the camera body can include a plurality of lenses, at least one of which is used as a moving lens, and the moving lens is fixed on the moving block through a connecting piece, and the power output shaft of the motor is connected to the screw. When focusing, the camera lower computer can generate a focusing signal for driving the motor to rotate, and the rotation of the motor drives the screw to rotate, and the rotational motion is converted into a linear motion through the ball screw structure, so that the moving block moves. The moving block then drives the movable lens to move through the connecting piece to adjust the focal length of the optical lens.

[0091] like Figure 5 As shown, in some embodiments, the camera body may include an optical lens, a lens barrel, a light shield, and a camera bracket. The optical lens is disposed in the lens barrel. The optical lens may refract or reflect imaging light through a plurality of lenses or reflectors so that the imaging light can be incident on a photosensitive element.

[0092] The light shield is arranged at one end of the lens barrel, and the camera lower computer is arranged at the other end of the lens barrel. The light shield can be arranged on the light incident side of the lens barrel, which can suppress stray light interference, protect the camera lens, optimize the camera layout and function, and improve the imaging accuracy and stability. The light shield can be a cylindrical structure, and when installed on the lens barrel, it maintains a coaxial relationship with the lens barrel.

[0093] The lens barrel is used to form a light propagation path, and can be set to a corresponding shape and size according to the optical path design requirements of the payload camera. For example, the lens barrel is a cylindrical structure with multiple optical lenses arranged inside. Multiple bosses are arranged inside the lens barrel for mounting multiple optical lenses.

[0094] The camera bracket is used to support the entire satellite payload camera so that the satellite payload camera can be installed on the payload satellite. Therefore, the camera bracket can be set on the outer wall of the lens barrel, and the camera bracket is connected to the camera lower computer. For example, Figure 5 As shown, the camera can be a tripod structure, including a bottom support plate, two side support legs and a connecting hinge arranged at the top. The support plate of the camera lower machine can be connected to the camera bracket through a connecting hinge, and the bottom support plate of the camera bracket is arranged on the supporting structure of the structural subsystem of the payload satellite.

[0095] The camera lower computer is used to convert the imaging light collected by the camera body into an electrical signal, thereby generating image data. That is, the camera lower computer is provided with a photosensitive element, and the photosensitive element is configured to convert the optical signal into image data. Among them, the photosensitive element can select an appropriate element type according to the design mission requirements of the payload satellite.

[0096] For example, Figure 6 As shown, according to the design requirements of the satellite constellation on-orbit measurement and control mission, the photosensitive element can be a complementary metal oxide semiconductor (CMOS) imaging unit. The CMOS imaging unit can consume almost no power under static conditions and only consumes a small amount of energy when the signal is switched, thereby achieving low power consumption. The CMOS imaging unit can include a 3-way imaging module board and an interface board, thereby generating an electrical signal according to the imaging light entering the camera body and generating image data.

[0097] In some embodiments, the optical lens includes a primary mirror assembly and a secondary mirror assembly; the camera lower computer includes a back plate assembly and a focal plane assembly. One end of the lens barrel is fixedly connected to the back plate assembly, and the other end of the lens barrel is movably connected to the light shield. The secondary mirror assembly is arranged on a side of the lens barrel close to the light shield, and the primary mirror assembly is arranged on a side of the lens barrel close to the back plate. The focal plane assembly is fitted and connected to the back plate assembly, and the photosensitive element is arranged on the focal plane assembly; the primary mirror assembly is movably connected to the back plate assembly through the camera focusing mechanism.

[0098] A light propagation path can be formed in the lens barrel through the primary mirror assembly and the secondary mirror assembly. In order to obtain a better imaging effect, a folding optical path can be formed in the lens barrel according to a folding optical system structure to converge the light onto the photosensitive element. The folding optical system structure can include a coaxial folding optical system structure and an off-axis three-mirror optical system structure.

[0099] In some embodiments, when the satellite payload camera adopts a coaxial folding optical system structure, the primary mirror assembly includes a first reflective lens and a transmissive lens group; the secondary mirror assembly includes a second reflective lens. The first reflective lens is a concave mirror provided with a reflective layer, which is used to reflect the light entering the lens barrel to the second reflective lens; the second reflective lens is also provided with a reflective layer, which is used to reflect the light reflected and converged by the first reflective lens to the position of the transmissive lens group. The transmissive lens group includes a plurality of transmissive lenses, which are used to refract the light reflected by the second reflective lens to the photosensitive device.

[0100] like Figure 7 As shown, the first reflective lens is arranged on the side where the lens barrel is connected to the camera lower computer, that is, the first reflective lens is arranged on the light exit side of the lens barrel. The first reflective lens can be a circular concave mirror structure with an opening in the middle. The transmission lens group is arranged in the opening space of the first reflective lens. The second reflective lens is arranged on the side where the lens barrel is connected to the light shield, that is, the second reflective lens is arranged on the light entrance side of the lens barrel. The second reflective lens can be one of a plane mirror, a convex mirror and a concave mirror, and the specific mirror form is related to the degree of convergence of the light by the first reflective lens.

[0101] The transmissive lens group includes a plurality of transmissive lenses, and the corresponding number of transmissive lenses and the shape, size, refractive index and other parameters of each transmissive lens can be selected according to the photosensitive area, optical path length and imaging size requirements of the photosensitive element. For example, the transmissive lens group may include a D-shaped convex lens, a concave lens with concave sides and a C-shaped convex lens.

[0102] After the imaging light enters the lens barrel through the light shield, it can be irradiated on the first reflective lens. Since the first reflective lens includes a reflective layer and has a concave mirror structure, the first reflective lens can reflect the light and converge it to the second reflective lens. The second reflective lens then reflects and / or converges the light to the transmission lens group through the reflective layer, and refracts the light through multiple lenses in the transmission lens group, thereby transmitting the imaging light to the photosensitive element, so that the photosensitive element can generate an electrical signal according to the imaging light.

[0103] It can be seen that when the satellite payload camera adopts the coaxial folding optical system structure, the total length and volume of the system can be reduced by folding the optical path, thereby achieving compactness and miniaturization of the satellite payload camera. By reasonably designing the curvature and taper coefficient of the first reflector, the second reflector, and the transmission lens group, the aberration can be effectively corrected, thereby achieving imaging quality close to the diffraction limit.

[0104] like Figure 8 As shown, in some embodiments, when the satellite payload camera adopts an off-axis three-mirror optical system structure, the primary mirror assembly includes a third reflector lens and a fourth reflector lens; the secondary mirror assembly includes a fifth reflector lens. The third reflector lens, the fourth reflector lens, and the fifth reflector lens are all provided with a reflective layer; the third reflector lens and the fourth reflector lens are concave mirrors.

[0105] Among them, the third reflecting lens is used to reflect the light entering the lens barrel and converge it onto the fifth reflecting lens; the fifth reflecting lens is used to reflect the light reflected and converged by the third reflecting lens to the fourth reflecting lens; the fourth reflecting lens is used to reflect the light reflected by the third reflecting lens and converge it onto the photosensitive device.

[0106] After the imaging light enters the lens barrel through the light shield, it can first be irradiated on the third reflective lens. The third reflective lens reflects the light entering the lens barrel through the concave mirror structure and the reflective layer and converges it to the fifth reflective lens. The fifth reflective lens then uses the reflective layer to reflect the light to the fourth reflective lens. The fourth reflective lens then reflects the imaging light through the concave mirror structure and the reflective layer and converges it to the photosensitive device, so that the photosensitive element can generate an electrical signal according to the imaging light.

[0107] When the satellite payload camera adopts an off-axis three-mirror optical system structure, the satellite payload camera can alleviate the center obstruction problem through the design of an offset reflector, so that the satellite payload camera can achieve higher light efficiency and lower stray light interference, significantly improving the imaging quality. In addition, the use of an off-axis three-mirror optical system structure can also achieve large field of view and high-resolution imaging while maintaining a small size and lightweight design. For example, some off-axis three-mirror optical systems can achieve a longer focal length and a larger field of view angle within a shorter system length, meeting the high-resolution requirements in fields such as space remote sensing and infrared detection.

[0108] Satellite payload cameras can perform image acquisition according to mission requirements during the operation of payload satellites. For example, satellite payload cameras are sub-meter optical payloads, which belong to high-resolution, light and small satellite payloads. They use small pixel detection imaging technology, large field of view image telecentric optical imaging technology and time delay integral imaging technology to achieve high-resolution, light and small design. Through the time delay integral (Toluene Diisocyanate, TDI) push-broom imaging mode, the pixel resolution of the sub-satellite point is better than 1m. The RC reentry mechanism is used. Through the optimization design of the system, the optical system can achieve high resolution, wide coverage, light and small, and athermal design.

[0109] Correspondingly, in order to meet the mission requirements of satellite on-orbit missions, the sub-meter optical payload can meet the following technical indicators: the camera type is TDI push-broom; the system spectrum is 450nm±15nm~850nm±15nm; the pixel resolution of the sub-satellite point is panchromatic resolution (PAN), better than 1m@600km; the width is 15km; the focal length is ≥1250mm; the pixel size is 2.5um; the quantization level is 12bits; the average static transfer function is ≥0.11; the signal-to-noise ratio is ≥36dB when the solar altitude angle is 70° and the ground reflectivity is 0.65; at the solar altitude angle of 20° and the ground reflectivity is 0.05, it is ≥23dB; the camera power consumption is not more than 66w in the short term; not more than 14w in the long term; the volume is Φ460×800; the weight is ≤7.5kg; the design life is 5 years; the reliability at the end of 5 years is ≥0.95.

[0110] The data communication payload module includes multiple transponders and data communication antennas based on different communication standards. For example, the data communication payload module can realize C-band feeder link forwarding, ultra-high frequency (UHF) radio frequency band user link forwarding, automatic identification system (AIS) signal link forwarding, and automatic dependent surveillance-broadcast (ADS-B) signal link forwarding.

[0111] Correspondingly, the communication repeater may include a C-band feeder link repeater, a UHF-band user link repeater, an AIS signal link repeater, an ADS-B signal link repeater, and the like. Among them, the C-band repeater can be used to form a feeder link; the UHF-band repeater can be used to form a user link; the AIS repeater (VHF band) can be used to form an AIS link; and the ADS-B repeater (L band) can be used to form an ADS-B link. The antenna may include a C-band receiving antenna, a C-band transmitting antenna, a UHF-band receiving antenna, a UHF-band transmitting antenna, a VHF / L dual-frequency antenna, and the like. This allows the data communication payload module to receive narrowband communication data and forward the narrowband communication data to the target component.

[0112] When setting up the data communication payload module, the feasibility of the UHF band user link, C band feeder link and communication system can be verified based on the main verification indicators of the narrowband communication payload, and the frequency compatibility with other communication systems can be verified; data service demonstration and verification of data exchange, data collection, space-based AIS, space-based ADS-B, satellite broadcasting and other services can be carried out, and the verification of the wide-area enhanced broadcasting function of space-based navigation can be carried out, and frequency resources can be enabled; and cooperation with several miniaturized terminal prototypes and ground stations (including gateway stations and information processing centers) of the ground verification system can be completed to complete the satellite-ground verification test.

[0113] Different communication standards can set different technical indicators. For example, when the data communication payload module includes passive filtering units, microwave channel units, communication payload processor units, antennas and other devices, it can realize the UHF band user link forwarding, AIS signal link forwarding, and ADS-B signal link forwarding functions. Among them, the performance requirements of the C-band feeder link include: the uplink operating frequency is 5091~5101MHz; the operating bandwidth is 10MHz; the uplink polarization mode is right-hand circular polarization (Right-Hand Circular Polarization, RHCP); the uplink code rate is 250kbps\500kbps\1000kbps\2000kbps, and the rate is adjustable; the bit error rate is ≤1×10 -6 The downlink operating frequency is 6701~6711MHz; the operating bandwidth is 10MHz; the downlink polarization mode is Left-Hand Circular Polarization (LHCP); the downlink code rate is 250kbps\500kbps\1000kbps\2000kbps, and the rate is adjustable.

[0114] Similarly, the performance index requirements of the UHF link include: uplink operating frequency of 400-403MHz; operating bandwidth of 4MHz; uplink polarization mode of RHCP; uplink code rate of 0.1kbps\0.2kbps\0.4kbps\4.8kbps\16kbps, and the rate is adjustable; bit error rate ≤1×10 -6 ; The downlink operating frequency is 463~467MHz; the operating bandwidth is 3MHz; the downlink polarization mode is LHCP; the downlink code rate is 1.2kbps\2.4kbps\4.8kbps\9.6kbps\38.4kbps, the rate is adjustable.

[0115] The performance requirements of the AIS link include: uplink operating frequency of 161.975MHz (AIS1) and 162.025MHz (AIS2); G / T value ≥-29dB / K (antenna gain 0dBi); uplink code rate of 9.6kbps; receiving sensitivity of -112dBm@20% packet loss rate. The performance requirements of the ADS-B link include: uplink operating frequency of 1087~1093MHz; working bandwidth of 6MHz; G / T value ≥-19dB / K (antenna gain 9dBi); receiving sensitivity of -85dBm@20% packet loss rate.

[0116] In some embodiments, the data communication payload module can complete the reception, modulation and demodulation processing of C-band feeder link signals, reception and processing of UHF-band user links, space-based AIS, and ADS-B data, and the refresh and on-orbit reconstruction functions of FPGA software through the communication and navigation payload processor application. In this regard, the data communication payload module can include two types of processing chips, one of which is an FPGA for digital signal processing, such as the Xilinx XC5VFX130T chip, a total of 3 chips. The second is an FPGA application for refresh control, such as the Actel A54SX72A chip, a total of 2 chips.

[0117] Combined with the hardware design of the data communication payload module, the application functions used by the data communication payload module can be divided into three configuration items. That is, FPGA1 is responsible for processing C-band feed, including 1 C-band uplink channel demodulation and decoding, 1 C-band downlink channel coding modulation and reconstruction interface processing. FPGA2 is responsible for processing AIS and ADS-B data, including 1 AIS channel demodulation and decoding, 1 ADS-B uplink channel coding modulation and transmission. FPGA3 is responsible for processing UHF band user data, including 1 UHF uplink channel demodulation and decoding and 1 UHF downlink channel coding modulation and transmission.

[0118] The intersatellite communication payload module includes an intersatellite communication unit and a communication control unit. The intersatellite communication unit is used to perform the transmission and reception of intersatellite communication data, and the communication control unit is used to control the intersatellite communication process. To this end, the intersatellite communication unit is connected to the communication control unit. During the intersatellite communication process, the communication control unit can generate, process, and send data or instructions related to the intersatellite communication process to control the intersatellite communication unit to receive and send intersatellite communication data.

[0119] The intersatellite communication payload module can establish an intersatellite communication connection channel based on a specific intersatellite communication method. In some embodiments, the intersatellite communication method can be intersatellite laser communication. Then the intersatellite communication unit is a laser terminal based on intersatellite laser communication; the intersatellite communication unit includes an optical component and an electronic component, the optical component is configured to send and receive intersatellite communication optical signals, and perform angle adjustment within a preset angle range of freedom; the electronic component is configured to perform power conversion and conversion between intersatellite communication optical signals and electrical signals. Intersatellite laser communication can use laser as a carrier for data transmission, and intersatellite laser communication has the advantages of high data transmission rate, low power consumption, small size and high safety.

[0120] For example, Fig. 9 As shown, the laser terminal corresponding to the intersatellite communication payload module may include an optical unit on the same track, an optical unit on a different track, an electronics unit, cables, optical fibers, etc. The optical unit of the laser terminal is responsible for receiving and sending optical signals and rotating in a large angle range on two axes, thereby realizing functions such as target search, capture, and tracking. The electronics unit of the laser terminal is responsible for overall communication with the satellite, secondary power conversion, and communication modulation and demodulation, thereby realizing functions such as power supply, drive, and control of the optical unit. The two stand-alone units cooperate to complete the establishment of the intersatellite laser communication link and high-speed communication verification.

[0121] To meet the requirements of intersatellite laser communication, the intersatellite communication payload module can meet the following technical indicators: communication wavelength is 1550nm; bit error rate is better than 1×10-7; capture probability is not less than 95%; communication system is on-off keying (OOK); communication mode is full-duplex. Accordingly, when the intersatellite communication payload module communicates based on the intersatellite laser communication mode, the communication control unit of the intersatellite communication payload module can perform communication control by running the main control application, the main control information processing application and the communication information processing application.

[0122] The main control application is used to realize CAN bus communication with the satellite platform, realize data analysis, and realize the working mode and state control of the laser communication terminal. It can also be responsible for the pre-pointing angle calculation of the laser communication terminal tracking drive mechanism, responsible for the location information collection of the tracking light detection unit, and control the tracking mechanism, thereby realizing the aiming, capture and tracking functions.

[0123] The master control information processing application can be used to receive serial data from each unit, and send the instructions of the control decision module to each unit through the serial port and realize the reconstruction function. The communication information processing application can be used to realize high-speed data encoding and transmission, and has a built-in forward error correction (FEC) function, as well as output status data to the master control unit (onboard computer).

[0124] In some embodiments, the communication control unit is also connected to the data communication payload module, that is, the intersatellite communication payload module and the data communication payload module can be controlled in linkage, so that the communication control unit can realize the intersatellite communication connection relationship with some communication satellites through the communication standard corresponding to the data communication payload module.

[0125] In order to achieve linkage control, the communication control unit is configured to execute a satellite payload control method such as Fig.10 As shown, the method includes:

[0126] S101. In response to an instruction to establish an inter-satellite communication link, a posture adjustment instruction is sent to an inter-satellite communication unit.

[0127] The establishment instruction is a control instruction for controlling the payload satellite to establish an intersatellite communication link. In some embodiments, the establishment instruction can be actively input through a ground device. For example, when the number of payload satellites deployed in the satellite constellation exceeds 2, in order to test the intersatellite communication function, the user can send an establishment instruction to the payload satellite through the ground device.

[0128] In some embodiments, the establishment instruction can also be generated by the payload satellite according to the judgment result by judging the operation status, mission stage and abnormal situation. For example, during the on-orbit measurement and control mission stage of the payload satellite, when it is detected that the satellite-to-ground communication process of the current payload satellite is abnormal, an establishment instruction can be generated so that the payload satellite can establish a communication connection with the ground equipment through other payload satellites.

[0129] In some embodiments, the establishment instruction may be generated by an onboard computer of the payload satellite and sent to the communication control unit. Therefore, after receiving the establishment instruction, the communication control unit may parse the communication satellite information for establishing the inter-satellite communication connection from the establishment instruction. The communication satellite information may include the satellite identification ID, the current position of the communication satellite, and other contents.

[0130] After parsing the communication satellite information, the communication control unit can generate an attitude adjustment instruction based on the communication satellite information, and send the attitude adjustment instruction to the intersatellite communication unit. The attitude adjustment instruction is used to drive the intersatellite communication unit to point to the direction of the communication satellite. For example, the attitude adjustment instruction may include the adjustment amount when the intersatellite communication unit needs to make an attitude adjustment. Then, after parsing the satellite identification ID and the current position of the communication satellite corresponding to the identification ID, the communication control unit can judge whether the attitude of the current satellite meets the required attitude for intersatellite communication connection with the communication satellite. If the current satellite attitude meets the communication requirements, a connection instruction can be sent directly to the communication satellite. If the current satellite attitude does not meet the communication requirements, an attitude adjustment instruction can be generated and sent to the intersatellite communication unit.

[0131] In order to determine whether the current satellite attitude meets the communication requirements, in some embodiments, the communication control unit may first detect the attitude of the current satellite. That is, after obtaining the establishment instruction, the communication control unit may send an attitude detection instruction to the attitude detection component, and the attitude detection instruction may control the attitude detection component to start running to detect attitude-related data. For example, when the attitude and orbit control subsystem of the payload satellite includes a gyroscope and a star sensor, after receiving the establishment instruction, an attitude detection instruction may be sent to the gyroscope and the star sensor in response to the establishment instruction. The gyroscope and the star sensor may start to detect acceleration and star point coordinates according to the attitude detection instruction. Then, the acceleration and star point coordinates obtained by the detection are sent to the communication control unit (or the onboard computer) so that the communication control unit (or the onboard computer) calculates the current satellite attitude according to the acceleration and the star point coordinates.

[0132] In order to obtain a more accurate attitude judgment result, in some embodiments, the communication control unit may also refer to the image data captured by the satellite payload camera when performing attitude detection. Therefore, the camera lower computer is also configured to: receive an attitude detection instruction sent by the communication control unit. The attitude detection instruction is a control instruction generated by the communication control unit in response to the establishment instruction. The attitude detection instruction is used to control the satellite payload camera and the attitude detection sensor on the current satellite to send attitude detection data to the communication control unit.

[0133] In response to the posture detection instruction, the focal length adjustment amount of the camera focusing mechanism is set according to the current mission stage. Then, the camera focusing mechanism is controlled to adjust the imaging focal length of the camera body according to the adjustment amount, and the current camera parameters of the camera body are recorded. Among them, the recorded current camera parameters should at least include the focal length. Then, the satellite payload camera is controlled to capture a reference image according to the current camera parameters, and the reference image is sent to the communication control unit, so that the communication control unit calculates the current operating posture according to the reference image and the posture detection data collected by the posture detection sensor.

[0134] For example, according to the designed on-orbit mission of the payload satellite, the payload satellite is set with an estimated shooting range of the satellite payload camera under the operating state corresponding to a specific time and a specific position. When performing attitude detection, the image can be captured according to the attitude detection instruction to obtain a reference image. Obviously, under different operating conditions, the theoretical content contained in the reference image is different. For example, in the on-orbit measurement and control mission stage, the reference image should include the landmark features of the mission area. The reference image obtained by shooting is then compared with the theoretical image. If the reference image also contains the landmark features in the theoretical image, and the position of the landmark features in the reference image is the same or similar to that in the theoretical image, the currently detected attitude data is considered valid, so the current operating attitude can be calculated based on the attitude detection data.

[0135] The calculated current operating attitude may include the deflection angle of the payload satellite relative to the standard direction, where the standard direction is the basic coordinate axis constructed according to the satellite's operating trajectory or flight status. For example, the basic coordinate axis includes the coordinate axis constructed based on the gravity direction and the reference bracket in the structural subsystem. When calculating the current operating attitude, the operating attitude can be represented according to the basic coordinate axis. For example, the basic coordinate axis includes the x-axis, y-axis and z-axis that are perpendicular to each other in space. Then the current operating attitude can be represented by the angular components of the deflection angle of the reference bracket on the three coordinate axes, that is, (θ x ,θ y ,θ z ).

[0136] In some embodiments, when the current satellite and the communication satellite establish a communication connection through intersatellite laser communication, the communication control unit can receive the reference image sent by the camera lower computer and the attitude detection data collected by the attitude detection sensor, and calculate the current running attitude based on the reference image and the attitude detection data. Then, the azimuth information of the communication satellite is obtained, and the attitude angle adjustment amount is calculated based on the azimuth information and the current running attitude. Then, the adjustment instruction is generated based on the attitude angle adjustment amount, and the adjustment instruction is sent to the optical component of the intersatellite communication unit, so that the optical component performs the angle adjustment according to the attitude angle adjustment amount.

[0137] For example, the current running posture is calculated based on the reference image and posture detection data as (θ x ,θ y ,θ z ), and the current communication satellite position to be established is P, then according to the communication satellite position and the installation position of the optical signal transceiver antenna in the intersatellite communication unit on the current satellite, it can be calculated that when the optical signal transceiver antenna's optical signal transceiver direction is aligned with the communication satellite position P, the corresponding required attitude is (θ x ',θ y ',θ z '), then the x-axis rotation angle adjustment can be calculated as Δx = θ x '-θ x ; Δy=θ y '-θ y ; Δz=θ z '-θ z .

[0138] It can be seen that after receiving the reference image and attitude detection data, the communication control unit can calculate the current operating attitude based on the reference image and attitude detection data, and calculate the attitude adjustment amount based on the current operating attitude and the orientation information of the communication satellite, so as to generate an attitude adjustment instruction based on the attitude adjustment amount.

[0139] S102: Send a connection instruction to the communication satellite through the intersatellite communication unit and / or the data communication payload module.

[0140] After sending an attitude adjustment instruction to the intersatellite communication unit to adjust the attitude of the intersatellite communication unit so that the intersatellite communication unit points in the direction of the communication satellite, the communication control unit can send a connection instruction to the communication satellite, and the connection instruction can be used to trigger the communication satellite to establish an intersatellite communication connection relationship with the current satellite.

[0141] In order to send a connection instruction to the communication satellite, the communication control unit can select one or more communication modes from the communication modes corresponding to the intersatellite communication unit and the data communication payload module to send the connection instruction to the communication satellite.

[0142] In some embodiments, the communication control unit may first convert the connection instruction into first communication data based on the communication mode corresponding to the intersatellite communication unit. Since the intersatellite communication mode corresponding to the intersatellite communication unit is mostly directional, the first communication data includes the position information of the current satellite. When the position information of the current satellite is carried in the first communication data, the communication satellite may also perform attitude adjustment based on the position information of the current satellite carried, so as to establish a communication connection path.

[0143] After converting the connection instruction into the first communication data, the communication control unit may send the first communication data to the communication satellite through the intersatellite communication unit, so that the communication satellite adjusts its operating attitude according to the position information of the current satellite. After receiving the first communication data, the communication satellite may extract the position information of the current satellite from the first communication data, and perform attitude adjustment based on the position information. As the attitude adjustment process of the current satellite and the communication satellite is performed, the current satellite and the communication satellite may be aligned with each other, thereby realizing the communication function.

[0144] After sending the first communication data to the communication satellite, the communication control unit may also receive the first receipt signal captured by the intersatellite communication unit. The first receipt signal is a signal fed back by the communication satellite after adjusting its operating attitude. That is, after the communication satellite adjusts its attitude to align the intersatellite communication unit with the current satellite, the first receipt information may be transmitted to the current satellite through the intersatellite communication unit.

[0145] S103: Receive a receipt signal captured by the intersatellite communication unit and / or the data communication payload module.

[0146] The receipt signal is a signal fed back by the communication satellite in response to the connection instruction. After the communication control unit sends the connection instruction to the communication satellite, a receipt signal monitoring process can be started to monitor the receipt signal fed back by the communication satellite. The receipt signal can be captured by the intersatellite communication unit and / or the data communication payload module. When the intersatellite communication unit and / or the data communication payload module captures the receipt signal, it indicates that the communication satellite is ready for communication connection.

[0147] In some embodiments, when the intersatellite communication unit of the current satellite is aimed at the communication satellite, and the intersatellite communication unit of the communication satellite is also aimed at the current satellite, the intersatellite communication unit of the current satellite will capture the first receipt signal. Therefore, if the first receipt signal is received within a preset capture period, an intersatellite communication link can be established between the current satellite and the communication satellite.

[0148] If the first receipt signal is not received within the preset capture period, the communication control unit may convert the connection instruction into second communication data based on one of the communication modes corresponding to the data communication payload module, and send the second communication data to the communication satellite through the data communication payload module, and then receive the second receipt signal captured by the data communication payload module and / or the intersatellite communication unit, wherein the second receipt signal is a signal fed back by the communication satellite in response to the second communication data.

[0149] S104. Establish an intersatellite communication link between the intersatellite communication unit and the communication satellite according to the receipt signal.

[0150] The intersatellite communication link is used to send or receive intersatellite communication data. After receiving the receipt signal, the communication control unit can establish an intersatellite communication link with the communication satellite based on the intersatellite communication unit, thereby sending or receiving intersatellite communication data.

[0151] By applying the technical solution provided in the above embodiment, the satellite payload system can establish an intersatellite communication connection based on different communication methods through the linkage between the satellite payload camera, the data communication payload module and the intersatellite communication payload module, and adjust the satellite attitude with reference to the image data collected by the satellite payload camera and the attitude parameters detected by the sensor, so that the intersatellite communication unit points in the direction of the communication satellite, thereby solving the problem of low payload utilization rate during the satellite's in-orbit operation.

[0152] Further, as a refinement and expansion of the specific implementation of the above embodiment, in order to fully illustrate the specific implementation process of this embodiment, some embodiments of the present application also provide a satellite payload control method, which can be applied to the satellite payload system provided in the above embodiment, and is executed by the communication control unit of the inter-satellite communication payload module in the satellite payload system, such as Fig.11 As shown, the method includes:

[0153] S201. Receive real-time attitude parameters sent by the communication satellite through the inter-satellite communication link.

[0154] The real-time attitude parameter is the attitude data of the communication satellite collected by the attitude detection sensor on the communication satellite after the intersatellite communication link is established. Since the operating state of the payload satellite in the space environment will change with time and mission phase, in order to maintain the intersatellite communication connection relationship, after the intersatellite communication link is established, the communication satellite can send attitude parameters, i.e., real-time attitude parameters, to the current satellite in real time.

[0155] In order to reduce the amount of data transmission and reduce the communication and data processing load, in some embodiments, after establishing the intersatellite communication link, the communication satellite can periodically obtain the real-time operation attitude according to the preset detection frequency, and compare the real-time operation attitude with the recorded historical operation attitude. If the deviation between the real-time operation attitude and the historical operation attitude is greater than the deviation threshold, the real-time operation attitude is sent to the current satellite. The real-time operation attitude is used to update the historical operation attitude.

[0156] S202. Calculate the signal transmission path of the communication satellite according to the real-time attitude parameters.

[0157] After acquiring the real-time attitude parameters sent by the communication satellite, the communication control unit of the current satellite can also calculate the signal transmission path of the communication satellite according to the actual attitude parameters. The signal transmission path is used to characterize the direction in which the intersatellite communication unit points to when the communication satellite is in the real-time operating attitude.

[0158] S203: Calculate a signal tracking adjustment amount according to the signal transmission path.

[0159] According to the signal transmission path obtained by calculation, the communication control unit can calculate the signal tracking adjustment amount according to the signal transmission path. The tracking adjustment amount can be calculated in a manner similar to the manner of calculating the posture adjustment instruction shown in the above embodiment, and the signal tracking adjustment amount can be calculated by comparing the current operating posture and the signal transmission path.

[0160] S204: Generate an attitude tracking instruction according to the signal tracking adjustment amount, and send the attitude tracking instruction to the intersatellite communication unit.

[0161] After calculating the signal tracking adjustment amount, the communication control unit can generate an attitude tracking instruction based on the signal tracking adjustment amount. The attitude tracking instruction can enable the inter-satellite communication unit to adjust the inter-satellite signal receiving and sending direction to coincide with the signal transmission path according to the attitude tracking instruction, thereby tracking the position of the communication satellite and ensuring the normal operation of the inter-satellite communication link.

[0162] Based on the satellite payload system provided in the above embodiments, some embodiments of the present application further provide a satellite payload control method, the method comprising:

[0163] In response to an instruction to establish an intersatellite communication link, sending an attitude adjustment instruction to the intersatellite communication unit, wherein the attitude adjustment instruction is used to drive the intersatellite communication unit to point to the direction of the communication satellite;

[0164] Sending a connection instruction to the communication satellite through the intersatellite communication unit and / or the data communication payload module;

[0165] receiving a receipt signal captured by the intersatellite communication unit and / or the data communication payload module, wherein the receipt signal is a signal fed back by the communication satellite in response to the connection instruction;

[0166] An intersatellite communication link is established between the intersatellite communication unit and the communication satellite according to the receipt signal, and the intersatellite communication link is used to send or receive intersatellite communication data.

[0167] By applying the technical solution of this embodiment, the satellite payload control method can perform attitude adjustment after receiving the establishment instruction for the intersatellite communication link, so that the intersatellite communication unit points to the direction of the communication satellite. Then, the intersatellite communication unit and / or the data communication payload module send a connection instruction to the communication satellite and receive a receipt signal, so as to establish an intersatellite communication link with the communication satellite according to the receipt signal. The method can establish an intersatellite communication connection based on different communication methods through the linkage between the satellite payload camera, the data communication payload module and the intersatellite communication payload module, and adjust the satellite attitude with reference to the image data collected by the satellite payload camera and the attitude parameters detected by the sensor, so that the intersatellite communication unit points to the direction of the communication satellite, so as to solve the problem of low payload utilization during the satellite's in-orbit operation.

[0168] The embodiment of the present application also provides a computer device, which can be a personal computer, a server, a network device, etc. The computer device includes a bus, a processor, a memory and a communication interface, and can also include an input and output interface and a display device. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store location information. The network interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, the steps in each method embodiment are implemented.

[0169] Those skilled in the art will appreciate that the structure of the above-mentioned computer device is only a partial structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components, or combine certain components, or have a different arrangement of components.

[0170] In one embodiment, a computer-readable storage medium is also provided. The computer-readable storage medium may be non-volatile or volatile, and stores a computer program thereon. When the computer program is executed by a processor, the steps in the above-mentioned method embodiments are implemented.

[0171] In one embodiment, a computer program product is also provided, including a computer program, which implements the steps in the above method embodiments when executed by a processor.

[0172] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, stored data, displayed data, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties.

[0173] A person of ordinary skill in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be implemented by instructing related hardware through a computer program. The computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods.

[0174] Among them, any reference to memory, database or other media used in the embodiments provided in this application may include at least one of non-volatile and volatile memory. Non-volatile memory may include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetoresistive random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc.

[0175] Volatile memory may include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM may be in various forms, such as static random access memory (SRAM) or dynamic random access memory (DRAM).

[0176] The database involved in each embodiment provided in this application may include at least one of a relational database and a non-relational database. The non-relational database may include a distributed database based on blockchain, etc., but is not limited thereto. The processor involved in each embodiment provided in this application may be a general-purpose processor, a graphics processor, a digital signal processor, a programmable logic device, a data processing logic device based on quantum computing, etc., but is not limited thereto.

[0177] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0178] The above-described embodiments only express several implementation methods of the present application, and the descriptions thereof are relatively specific and detailed, but they cannot be construed as limiting the scope of the present application. It should be noted that, for a person of ordinary skill in the art, several modifications and improvements can be made without departing from the concept of the present application, and these all belong to the protection scope of the present application. Therefore, the protection scope of the present application shall be subject to the attached claims.

Claims

1. A satellite payload system, characterized in that: The system comprises: A satellite payload camera comprises a camera body, a camera focal plane electric box, a camera focusing mechanism and a camera lower computer; the camera focal plane electric box is electrically connected to the camera body, the camera focusing mechanism and the camera lower computer; the camera focusing mechanism is connected to the optical lens of the camera body; the camera lower computer is connected to the camera focusing mechanism; A data communication payload module, comprising a plurality of transponders and data communication antennas based on different communication standards; the data communication payload module is configured to receive narrowband communication data and forward the narrowband communication data to a target component; The intersatellite communication payload module comprises an intersatellite communication unit and a communication control unit; the intersatellite communication unit is connected to the communication control unit; the communication control unit is also connected to the data communication payload module; The communication control unit is configured as follows: In response to an instruction to establish an intersatellite communication link, sending an attitude adjustment instruction to the intersatellite communication unit, wherein the attitude adjustment instruction is used to drive the intersatellite communication unit to point to the direction of the communication satellite; Sending a connection instruction to the communication satellite through the intersatellite communication unit and / or the data communication payload module; receiving a receipt signal captured by the intersatellite communication unit and / or the data communication payload module, wherein the receipt signal is a signal fed back by the communication satellite in response to the connection instruction; An intersatellite communication link is established between the intersatellite communication unit and the communication satellite according to the receipt signal, and the intersatellite communication link is used to send or receive intersatellite communication data.

2. The system according to claim 1, characterized in that The camera body includes an optical lens, a lens barrel, a light shield and a camera bracket; The optical lens is arranged in the lens barrel; the light shield is arranged at one end of the lens barrel, and the camera lower computer is arranged at the other end of the lens barrel; the camera bracket is located on the outer wall of the lens barrel, and the camera bracket is connected to the camera lower computer; a photosensitive element is arranged on the camera lower computer, and the photosensitive element is configured to convert an optical signal into image data.

3. The system according to claim 2, characterized in that The optical lens comprises a primary mirror assembly and a secondary mirror assembly; the camera lower computer comprises a back plate assembly and a focal plane assembly; One end of the lens barrel is fixedly connected to the back plate assembly, and the other end of the lens barrel is movably connected to the light shield; the secondary mirror assembly is arranged on a side of the lens barrel close to the light shield, and the primary mirror assembly is arranged on a side of the lens barrel close to the back plate; The focal plane assembly is bonded to the back plate assembly, and the photosensitive element is arranged on the focal plane assembly; the main mirror assembly is movably connected to the back plate assembly through the camera focusing mechanism.

4. The system according to claim 3, characterized in that The primary mirror assembly includes a first reflective lens and a transmissive lens group; the secondary mirror assembly includes a second reflective lens; The first reflective lens is a concave mirror provided with a reflective layer, and is used to reflect the light entering the lens barrel to converge onto the second reflective lens; the second reflective lens is also provided with a reflective layer, and is used to reflect the light reflected and converged by the first reflective lens to the position of the transmission lens group; The transmission lens group includes a plurality of transmission lenses, which are used to refract the light reflected by the second reflection lens onto the photosensitive device.

5. The system according to claim 3, characterized in that The primary mirror assembly includes a third reflective lens and a fourth reflective lens; the secondary mirror assembly includes a fifth reflective lens; The third reflective lens, the fourth reflective lens and the fifth reflective lens are all provided with a reflective layer; the third reflective lens and the fourth reflective lens are concave mirrors; The third reflecting lens is used to reflect the light entering the lens barrel and converge it onto the fifth reflecting lens; the fifth reflecting lens is used to reflect the light reflected and converged by the third reflecting lens and converge it onto the fourth reflecting lens; the fourth reflecting lens is used to reflect the light reflected by the third reflecting lens and converge it onto the photosensitive device.

6. The system according to claim 1, characterized in that The camera slave computer is also configured as follows: receiving an attitude detection instruction sent by the communication control unit, wherein the attitude detection instruction is a control instruction generated by the communication control unit in response to the establishment instruction, and the attitude detection instruction is used to control the satellite payload camera and the attitude detection sensor on the current satellite to send attitude detection data to the communication control unit; In response to the posture detection instruction, setting the focal length adjustment amount of the camera focusing mechanism according to the current task stage; Controlling the camera focusing mechanism to adjust the imaging focal length of the camera body according to the adjustment amount, and recording current camera parameters of the camera body, wherein the current camera parameters at least include focal length; Controlling the satellite payload camera to capture a reference image according to the current camera parameters; The reference image is sent to the communication control unit, so that the communication control unit calculates the current running posture according to the reference image and the posture detection data collected by the posture detection sensor.

7. The system according to claim 6, characterized in that The intersatellite communication unit is a laser terminal based on intersatellite laser communication; the intersatellite communication unit includes an optical component and an electronic component, the optical component is configured to send and receive intersatellite communication optical signals, and perform angle adjustment within a preset angle range of freedom; the electronic component is configured to perform power conversion and conversion between intersatellite communication optical signals and electrical signals; the communication control unit is also configured to: Receiving the reference image sent by the camera lower computer and the posture detection data collected by the posture detection sensor; Calculate the current running posture according to the reference image and the posture detection data; Acquiring the position information of the communication satellite; Calculate the attitude angle adjustment amount according to the orientation information and the current running attitude; The adjustment instruction is generated according to the attitude angle adjustment amount, and the adjustment instruction is sent to the optical component of the intersatellite communication unit, so that the optical component performs angle adjustment according to the attitude angle adjustment amount.

8. The system according to claim 1, characterized in that The communication control unit is further configured to: Receiving real-time attitude parameters sent by the communication satellite through the intersatellite communication link, the real-time attitude parameters being attitude data of the communication satellite collected by an attitude detection sensor on the communication satellite after the intersatellite communication link is established; Calculate the signal transmission path of the communication satellite according to the real-time attitude parameter; Calculating a signal tracking adjustment amount according to the signal transmission path; An attitude tracking instruction is generated according to the signal tracking adjustment amount, and the attitude tracking instruction is sent to the intersatellite communication unit, so that the intersatellite communication unit adjusts the intersatellite signal receiving and sending direction to coincide with the signal transmission path according to the attitude tracking instruction.

9. The system according to claim 1, characterized in that The communication control unit is further configured to: Based on the communication mode corresponding to the intersatellite communication unit, converting the connection instruction into first communication data, wherein the first communication data includes the position information of the current satellite; sending the first communication data to the communication satellite through the intersatellite communication unit, so that the communication satellite adjusts its operating attitude according to the position information of the current satellite; receiving the first receipt signal captured by the intersatellite communication unit, where the first receipt signal is a signal fed back by the communication satellite after adjusting its operating attitude; If the first receipt signal is not received within a preset capture period, converting the connection instruction into second communication data based on one of the communication modes corresponding to the data communication load module; sending the second communication data to the communication satellite through the data communication payload module; A second receipt signal captured by the data communication payload module and / or the intersatellite communication unit is received, where the second receipt signal is a signal fed back by the communication satellite in response to the second communication data.

10. A satellite payload control method, characterized in that: Applied to the satellite payload system according to any one of claims 1 to 9, the method comprising: In response to an instruction to establish an intersatellite communication link, sending an attitude adjustment instruction to the intersatellite communication unit, wherein the attitude adjustment instruction is used to drive the intersatellite communication unit to point to the direction of the communication satellite; Sending a connection instruction to the communication satellite through the intersatellite communication unit and / or the data communication payload module; receiving a receipt signal captured by the intersatellite communication unit and / or the data communication payload module, wherein the receipt signal is a signal fed back by the communication satellite in response to the connection instruction; An intersatellite communication link is established between the intersatellite communication unit and the communication satellite according to the receipt signal, and the intersatellite communication link is used to send or receive intersatellite communication data.

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