Earth-moon space large-scale cruise satellite and satellite assembly

Abstract

The invention relates to an earth-moon space large-scale cruise satellite and a satellite assembly, the earth-moon space large-scale cruise satellite comprises a satellite body, a spaceborne atomic clock, a satellite-ground or inter-satellite link measurement and communication load, a space observation camera and an earth-moon space GNSS orbit determination and time service load, and the spaceborne atomic clock is installed on the inner side surface of the satellite body in a heat conduction manner; the satellite-ground or inter-satellite link measurement and communication load comprises an in-satellite transmitting assembly and an out-satellite antenna, the in-satellite transmitting assembly is installed on the inner side face of the satellite body in a heat conduction mode, and the out-satellite antenna is installed on the outer side face of the satellite body in a heat insulation mode; the space observation camera is thermally insulated and mounted on the outer side of the satellite body; one part of the earth-moon space GNSS orbit determination and time service load is installed on the inner side face of the satellite body in a heat conduction mode, and the other part of the earth-moon space GNSS orbit determination and time service load is installed on the outer side face of the satellite body in a heat insulation mode. The earth-moon transfer and large-scale cruise requirements of the satellite can be met under the condition that less fuel is consumed.

Description

Technical Field

[0001] This invention relates to the field of satellite-related technologies, specifically to a large-scale lunar cruise satellite and its components. Background Technology

[0002] The "DRO Exploration and Research in Lunar Space" is one of the strategic leading science and technology projects. It aims to achieve low-energy orbit insertion and long-term stable parking of DROs, verify the autonomous cruise capability of wide-area flight in Lunar space based on DROs, and carry out gamma-ray detection research based on DROs. It can play a strategic leading role in the development and utilization of Lunar space.

[0003] The DRO project includes the development of three small satellites (DRO satellite, cruise satellite, and LEO satellite) and more than 10 payloads. The total mass of satellite A (DRO satellite) and satellite B (cruise satellite) will not exceed 600 kg, and the final mass must match the launch vehicle's carrying capacity. Satellite L (LEO satellite) will not exceed 120 kg. Based on the mission objectives, mission indicators, overall mission plan, and taking full account of the rocket's carrying capacity constraints, satellite A (~320 kg, DRO) and satellite B (~275 kg, Earth-Moon resonance orbit) will be launched as a dual-satellite combination on a single rocket, carrying an application payload with a mass not exceeding 104.6 kg. Satellite L (~120 kg, LEO) will carry an application payload with a mass of approximately 35 kg. The payloads on the three small satellites are designed to support the construction of inter-satellite links in the Earth-Moon constellation, inter-satellite communication measurements, space-based autonomous orbit determination, wide-area autonomous cruise, and other functional requirements, as well as to support space science exploration using the Earth-Moon space. Therefore, the satellite payload layout needs to consider heat dissipation, weight requirements, and link construction requirements. Summary of the Invention

[0004] In order to solve one or more technical problems existing in the prior art, the present invention provides a large-scale cruise satellite and satellite components in the Earth-Moon space.

[0005] The technical solution of this invention to solve the above-mentioned technical problems is as follows: This invention provides a large-scale lunar-Earth space cruise satellite, including a satellite body, an onboard atomic clock, a satellite-to-ground or inter-satellite link measurement and communication payload, a space observation camera, and a lunar-Earth space GNSS orbit determination and timing payload. The onboard atomic clock is thermally conductively mounted on the inner side of the satellite body; the satellite-to-ground or inter-satellite link measurement and communication payload includes an internal transmitting component and an external antenna. The internal transmitting component is thermally conductively mounted on the inner side of the satellite body, and the external antenna is thermally insulatedly mounted on the outer side of the satellite body; the space observation camera is thermally insulatedly mounted on the outer side of the satellite body; a portion of the lunar-Earth space GNSS orbit determination and timing payload is thermally conductively mounted on the inner side of the satellite body, and another portion of the lunar-Earth space GNSS orbit determination and timing payload is thermally insulatedly mounted on the outer side of the satellite body.

[0006] The beneficial effects of this invention are: the large-scale lunar cruise satellite of this invention, through reasonable payload layout, can meet its own weight requirements, and can complete the requirements of lunar transfer and large-scale cruise with less fuel consumption, significantly reducing the cost of entering lunar space and opening up a new path for large-scale lunar development and utilization.

[0007] Based on the above technical solution, the present invention can be further improved as follows.

[0008] Furthermore, the spaceborne atomic clock includes a rubidium clock, which is thermally mounted on the inner side of the -Y plate of the satellite body via screws.

[0009] The beneficial effects of adopting the above-mentioned further scheme are: although there are many time synchronization methods for large-scale cruise satellites in the Earth-Moon space, there are also situations where the link is interrupted. Therefore, a lightweight rubidium clock is used, and a high-stability isothermal crystal oscillator (placed in the GNSS receiver) is used as a backup.

[0010] Furthermore, the space observation camera includes a narrow field-of-view camera and a wide field-of-view camera, both of which are mounted on the outer side of the +X plate of the satellite body.

[0011] The beneficial effects of adopting the above-mentioned further scheme are: large-scale cruise satellites in the Earth-Moon space need to conduct imaging observations of satellite A, detect the target's location through a wide-field-of-view space camera, and guide a narrow-field-of-view space camera to image the target.

[0012] Furthermore, the Earth-Moon space GNSS orbit determination and timing payload includes a GNSS weak signal navigation receiver, an array antenna, and a quad-helical antenna. The array antenna and the quad-helical antenna are connected to the GNSS weak signal navigation receiver via radio frequency cables. The GNSS weak signal navigation receiver is fixed to the inner side of the -Y plate of the satellite body. The array antenna is heat-insulated and installed on the outer side of the +Z plate of the satellite body. The quad-helical antenna is fixed to the outer side of the -Z plate of the satellite body.

[0013] The beneficial effects of adopting the above-mentioned further scheme are: by configuring a high-sensitivity GNSS weak signal navigation receiver (including a high-gain L-band receiving antenna), it is possible to receive and process GNSS navigation signals in the Earth-Moon space, and realize space-based autonomous navigation and timing.

[0014] Furthermore, the satellite-to-ground or inter-satellite link measurement and communication payload includes a K-processor, an internal satellite transmission component, and an external antenna. The internal satellite transmission component and the K-processor are both thermally conductively mounted on the inner side of the satellite body. The K-processor is connected to the internal satellite transmission component via a cable, and the internal satellite transmission component is connected to the external antenna via a waveguide. The external antenna is thermally insulated and mounted on the outer side of the satellite body.

[0015] The beneficial effects of adopting the above-mentioned further scheme are as follows: The K-processor uses a K-band microwave transmitter / receiver system to construct inter-satellite communication links between any two satellites, realizing communication networking, tracking and measurement, orbit determination, and time synchronization. The K-band microwave transceiver payload is used to establish inter-satellite and satellite-to-ground links, realizing two-way ranging, data communication, and time synchronization, supporting on-orbit demonstration and technology verification of autonomous navigation and autonomous cruise for lunar spacecraft. Large-scale lunar cruise satellites determine their own orbits and clock biases through two-way communication measurements with LEO satellites (L-satellites) and DRO satellites (A-satellites).

[0016] Furthermore, the in-satellite transmission assembly includes a first transmitter and a second transmitter, which are thermally mounted on the inner side of the +Z plate of the satellite body, respectively.

[0017] Furthermore, the satellite antenna includes a 0.22-meter fixed antenna and a 0.22-meter rotating antenna. The 0.22-meter rotating antenna is rotatably mounted on the outer side of the +X plate of the satellite body through a K rotating mechanism, and the 0.22-meter fixed antenna is fixed on the outer side of the +Z plate of the satellite body.

[0018] Furthermore, the thermal insulation installation includes using fiberglass thermal insulation pads for thermal insulation installation.

[0019] Furthermore, the inner surface of the satellite body is provided with heat pipes for heat dissipation.

[0020] The present invention also provides a satellite component, including a large-scale cruise satellite in the Earth-Moon space as described above, and a long-distance retrograde orbit satellite, wherein the long-distance retrograde orbit satellite is connected to the outer surface of the satellite body through a satellite-rocket separation component.

[0021] The beneficial effects of this invention are: the large-scale cruise satellite (B satellite) in the Earth-Moon space can simultaneously establish inter-satellite measurement and communication links with DRO satellites (distant retrograde orbit satellites) and LEO satellites, and receive weak GNSS signals, and test various technical aspects of autonomous cruise based on the realization of constellation networking. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the structure of the large-scale cruise satellite in the Earth-Moon space of this invention. Figure 1 ; Figure 2 This is a schematic diagram of the structure of the large-scale cruise satellite in the Earth-Moon space of this invention. Figure 2 ; Figure 3 This is a schematic diagram of the structure of the large-scale cruise satellite in the Earth-Moon space of this invention. Figure 3 ; Figure 4 This is a schematic diagram of the structure of the large-scale cruise satellite in the Earth-Moon space of this invention. Figure 4 ; Figure 5 This is a schematic diagram of the structure of the large-scale cruise satellite in the Earth-Moon space of this invention. Figure 5 ; Figure 6 This is a schematic diagram of the structure of the large-scale cruise satellite in the Earth-Moon space of this invention. Figure 6 ; Figure 7 This is a schematic diagram of the structure of the large-scale cruise satellite in the Earth-Moon space of this invention. Figure 7 .

[0023] The attached diagram lists the components represented by each number as follows: 100. +X board; 101. -X board; 102. +Y board; 103. -Y board; 104. +Z board; 105. -Z board; 200. Rubidium clock; 300, narrow field of view camera; 301, wide field of view camera; 400. GNSS weak signal navigation receiver; 401. Array antenna; 402. Four-arm spiral antenna; 500, K processor; 501, first transmitter; 502, second transmitter; 503, 0.22-meter fixed antenna; 504, 0.22-meter rotating antenna; 505, waveguide; 506, payload management unit; 507, K rotating mechanism; 600. Solar panels; 700. Measurement and control antenna; 800. Working propellant tank; 900. Solar cell array drive circuit box; 901. Measurement and control integrated machine; 902. Measurement and control fixed amplifier; 903. Integrated electronic processor; 904. Star sensor. Detailed Implementation

[0024] The principles and features of the present invention are described below. The examples given are only for explaining the present invention and are not intended to limit the scope of the present invention.

[0025] Example 1 like Figures 1-7As shown, this embodiment of a large-scale lunar-Earth space cruise satellite includes a satellite body, an onboard atomic clock, a satellite-to-ground or inter-satellite link measurement and communication payload, a space observation camera, and a lunar-Earth space GNSS orbit determination and timing payload. The onboard atomic clock is thermally conductively mounted on the inner side of the satellite body. The satellite-to-ground or inter-satellite link measurement and communication payload includes an internal transmitting component and an external antenna. The internal transmitting component is thermally conductively mounted on the inner side of the satellite body, and the external antenna is thermally insulatedly mounted on the outer side of the satellite body. The space observation camera is thermally insulatedly mounted on the outer side of the satellite body. A portion of the lunar-Earth space GNSS orbit determination and timing payload is thermally conductively mounted on the inner side of the satellite body, and another portion of the lunar-Earth space GNSS orbit determination and timing payload is thermally insulatedly mounted on the outer side of the satellite body.

[0026] like Figure 1 and Figure 2 As shown, in one specific embodiment, the onboard atomic clock includes a rubidium clock 200, which is thermally mounted on the inner side of the -Y plate 103 of the satellite body via screws. Although large-scale lunar-Earth space-based cruise satellites have various timekeeping methods, link interruptions are still possible. Therefore, a lightweight rubidium clock is used, and a high-stability, temperature-controlled crystal oscillator (placed within the GNSS receiver) is used as a backup. Onboard timing is a prerequisite and foundation for satellites to achieve autonomous flight and space-based autonomous orbit determination services. A high-precision space atomic clock (or a high-stability crystal oscillator) will provide a stable frequency source for various application payloads and support time-frequency comparison experiments between satellites and ground stations and between satellites. The space atomic clock (or high-stability crystal oscillator / GNSS receiver) remains the most cost-effective onboard autonomous timekeeping technology solution with a high-precision, high-stability frequency source.

[0027] Specifically, such as Figure 4 As shown, the space observation camera includes a narrow field-of-view camera 300 and a wide field-of-view camera 301, both mounted on the outer surface of the +X plate 100 of the satellite body. The large-scale lunar-Earth space cruise satellite needs to perform imaging observations of Satellite A. The wide field-of-view space camera detects the target's azimuth, guiding the narrow field-of-view space camera to image the target. Satellite B is equipped with a narrow / wide field-of-view combined camera, supporting target detection and relative navigation within a range of several kilometers from Satellite A. Due to platform resource limitations, lightweight space camera solutions are adopted.

[0028] like Figure 1 , Figure 3 and Figure 6As shown, the GNSS orbit determination and timing payload in the Earth-Moon space includes a GNSS weak signal navigation receiver 400, an array antenna 401, and a quadruple spiral antenna 402. The array antenna 401 (i.e., a high-gain L-band receiving antenna) and the quadruple spiral antenna 402 are connected to the GNSS weak signal navigation receiver 400 via radio frequency cables. The GNSS weak signal navigation receiver 400 is fixed to the inner side of the -Y plate 103 of the satellite body. The array antenna 401 is thermally insulated and mounted on the outer side of the +Z plate 104 of the satellite body. The quadruple spiral antenna 402 is fixed to the outer side of the -Z plate 105 of the satellite body. By configuring a high-sensitivity GNSS weak signal navigation receiver (including a high-gain L-band receiving antenna), it is possible to receive and process GNSS navigation signals in Earth-Moon space, achieving space-based autonomous navigation and timing.

[0029] GNSS is a highly stable navigation signal source, serving not only ground-based systems but also spacecraft. Spaceborne GNSS receivers are already widely used in low-Earth orbit spacecraft. Satellite B will be equipped with a high-sensitivity receiver (including a high-gain L-band receiving antenna) to receive and process GNSS navigation signals in lunisolar space, forming a cost-effective space-based autonomous navigation and timing method that can significantly reduce the technical costs of ground-based orbit determination and timing. On the other hand, GNSS receivers will be used to conduct GNSS space-based augmented autonomous navigation experiments, i.e., calculating GNSS satellite ephemeris and satellite clocks without relying on ground-based telemetry and control. GNSS orbit determination and timing for lunisolar spacecraft is technically feasible. Utilizing GNSS orbit determination and timing will significantly improve the autonomous flight performance of lunisolar spacecraft, greatly reduce the cost of ground-based orbit determination and timing, and overcome the shortage of ground-based telemetry and control resources.

[0030] like Figure 1 and Figure 2 As shown, the satellite-to-ground or inter-satellite link measurement and communication payload includes a K-processor 500, an internal transmitting component, and an external antenna. Both the internal transmitting component and the K-processor 500 are thermally conductively mounted on the inner surface of the satellite body. The K-processor 500 is connected to the internal transmitting component via a cable, and the internal transmitting component is connected to the external antenna via a waveguide 505. The external antenna is thermally insulated and mounted on the outer surface of the satellite body. The K-processor uses a K-band microwave transmit / receive system to construct inter-satellite communication links between any two satellites, enabling communication networking, tracking and measurement, orbit determination, and time synchronization. The K-band microwave transceiver payload is used for establishing inter-satellite and satellite-to-ground links, enabling two-way ranging, data communication, and time synchronization, supporting on-orbit demonstration and technology verification of autonomous navigation and autonomous cruise for lunisolar spacecraft. The large-scale lunisolar space cruise satellite determines its own orbit and clock bias through two-way communication measurements with LEO satellites (L-satellites) and DRO satellites (A-satellites).

[0031] Specific examples Figure 1 and Figure 2 As shown, the satellite-to-satellite transmission assembly includes a first transmitter 501 and a second transmitter 502, which are thermally mounted on the inner side of the +Z plate 104 of the satellite body.

[0032] Specifically, the external antenna includes a 0.22-meter fixed antenna 503 and a 0.22-meter rotating antenna 504. The 0.22-meter rotating antenna 504 is rotatably mounted on the outer side of the +X plate 100 of the satellite body via a K-rotation mechanism 507, and the 0.22-meter fixed antenna 503 is fixed on the outer side of the +Z plate 104 of the satellite body. A first transmitter 501 is connected to the 0.22-meter rotating antenna 504 via a waveguide for signal transmission and reception, and a second transmitter 502 is connected to the 0.22-meter fixed antenna 503 via a waveguide for signal transmission and reception.

[0033] One specific embodiment of this solution involves using a fiberglass thermal insulation pad for thermal insulation installation. The inner surface of the satellite body is equipped with heat pipes for heat dissipation. Specifically, heat pipes can be installed on the inner surfaces of the +Y plate 102 and the -Y plate 103. The heat pipes on the +Y plate 102 pass through the K-processor 500 and the payload management unit 506, while the heat pipes on the -Y plate 103 also pass through the telemetry and control fixed amplifier 902 and the integrated electronic processor 903, to dissipate heat from the corresponding components.

[0034] This embodiment of a large-scale lunar cruise satellite also installs multiple telemetry and control antennas 700 on the +Z and -Z plates for overall satellite signal transmission and reception. An internal propellant tank 800 is installed to provide thrust to the satellite; the propellant tank 800 protrudes outward from the -X plate 101, as shown below. Figure 3 As shown. This embodiment of a satellite service system for a large-scale lunar cruise satellite includes a solar array drive circuit box 900, a telemetry and control integrated unit 901, a telemetry and control fixed amplifier 902, and an integrated electronic processor 903. The solar array drive circuit box 900 and the telemetry and control integrated unit 901 are mounted on the inner surface of the +Y plate 102 and adjacent to the +X plate via heat pipes. The telemetry and control fixed amplifier 902 and the integrated electronic processor 903 are mounted on the inner surface of the -Y plate 103 via heat pipes. The telemetry and control fixed amplifier 902 is adjacent to the +X plate 100, and the integrated electronic processor 903 is adjacent to the -X plate 101.

[0035] In this embodiment, solar panels 600 are installed on the outer surfaces of both the +Y plate 102 and the -Y plate 103 of the large-scale Earth-Moon space cruise satellite. The structure and installation method of the solar panels 600 can adopt the common solar panel structure and installation method used in satellites. A star sensor 904 is installed on the outer surface of the -Z plate 105 of the satellite body. The star sensor 904 is a common satellite component, and its installation method and structure are also common satellite structures.

[0036] In this embodiment, the commonly used XYZ coordinates of satellites are used to indicate the structural orientation of the satellite body. -X, -Y, and -Z are the opposite directions to +X, +Y, and +Z. In this embodiment of a large-scale lunar cruise satellite, the main focus is on setting up the layout of the entire satellite payload to meet the requirements of heat dissipation, weight, and subsequent space link. The satellite payload can use commonly used satellite equipment or structural principles.

[0037] This embodiment of a large-scale lunar cruise satellite is equipped with a payload management unit 506, which realizes data acquisition, processing, storage, and transmission of various payloads, and enables data interaction with the satellite platform. The payload management unit 506 is installed on the inner surface of the +Y plate 102 of the satellite body, and is arranged adjacent to the +Z plate.

[0038] This embodiment of a large-scale lunar cruise satellite, through a reasonable payload layout, can meet its own weight requirements and achieve the satellite's lunar transfer and large-scale cruise needs with less fuel consumption, significantly reducing the cost of entering lunar space and opening up a new path for large-scale lunar development and utilization.

[0039] Example 2 This embodiment also provides a satellite component, including a large-scale cruise satellite in the Earth-Moon space as described above, and a long-distance retrograde orbit satellite, wherein the long-distance retrograde orbit satellite is connected to the outer side of the satellite body through a satellite-rocket separation component.

[0040] Furthermore, the satellite components in this embodiment also include a LEO satellite, which enters a sun-synchronous orbit during the orbit insertion phase, and the +Z plate of the LEO satellite points towards a distant retrograde orbit satellite.

[0041] Launch phase: The +X plate of the large-scale cruise satellite in the Earth-Moon space is connected to the outer side of the +X plate of the long-distance retrograde orbit satellite through the satellite-rocket separation assembly; Orbit insertion phase: The large-scale Earth-Moon space cruise satellite separates from the distant retrograde orbit satellite. Both the distant retrograde orbit satellite and the large-scale Earth-Moon space cruise satellite enter the DRO orbit. The distant retrograde orbit satellite remains in the DRO orbit for an extended period, while the large-scale Earth-Moon space cruise satellite will subsequently enter the RO orbit. The outer surface of the +Z plate of the distant retrograde orbit satellite faces the ground, as does the outer surface of the +Z plate of the large-scale Earth-Moon space cruise satellite.

[0042] This embodiment sends a long-distance retrograde orbit satellite to a DRO orbit. DRO is a type of orbit that is about 310,000 to 450,000 kilometers from Earth and about 70,000 to 100,000 kilometers from the Moon. It can be regarded as a transportation hub connecting Earth, the Moon and deep space, and has the advantages of satellites being able to enter with low energy consumption, park stably, and reach the entire region with low energy consumption.

[0043] In this embodiment, a large-scale lunar cruise satellite (B satellite) needs to establish links with DRO satellites (Distant Retrograde Orbit satellites, A satellite) and LEO satellites (L satellite). As the served satellite, it is considered to be equipped with two sets of medium-gain, medium-aperture antennas (a 0.22-meter fixed antenna 503 and a 0.22-meter rotating antenna 504), respectively mounted on two (or one) two-dimensional rotating mechanisms to achieve arbitrary pointing adjustments. L satellite is only equipped with a high-gain, large-aperture antenna. The ground station is equipped with a high-gain, large-aperture antenna, capable of supporting satellite-to-ground links with A and B satellites over distances up to 1.5 million kilometers.

[0044] Satellites A and B will simultaneously orbit the moon, and can also fly alongside each other (B orbiting A). The primary mission of the space cameras is to search for and explore A during B's approach; and to image both satellites using the space cameras on both satellites during their flybys. Additionally, A's space camera can also image the Earth and the moon.

[0045] The three satellites, A, B, and L, primarily utilize K-band microwave links for inter-satellite communication networking and tracking measurements. K-band microwaves are characterized by high frequency, narrow beamwidth, and concentrated energy, making them suitable for constructing long-distance inter-satellite links in the Earth-Moon space, enabling inter-satellite ranging, time-frequency transmission, and inter-satellite communication. The power consumption and quality requirements of K-band microwave link payloads are suitable for microsatellite platforms and have been applied in inter-satellite communication and onboard relay communication for the BeiDou satellite system. Key hardware technologies are relatively mature, while software systems vary depending on the mission. All three satellites will be equipped with K-band microwave transmitting / receiving systems, with specific configuration schemes differing according to inter-satellite link communication requirements, using a nominal design scheme that can support a link span of at least 500,000 kilometers. Satellite B can transmit data to Earth via the X-band (platform) and K-band (payload) channels. The X-band has a lower data rate and is mainly used for telemetry and remote control data transmission. The K-band has a higher data rate and can transmit more engineering and application data. Various types of data (telemetry, remote control, application data, etc.) from the payloads of the three satellites can be transmitted between satellites via the K-band microwave link. Satellite L can be regarded as a relay for Earth communication between Satellites A and B. In the event of poor weather conditions, Satellites A and B transmit data to Satellite L via the K-band link (a laser link may be used in the future), and Satellite L transmits the data down to the ground station via the X-band link.

[0046] The large-scale lunar cruise satellite (B satellite) in this embodiment can simultaneously establish inter-satellite measurement and communication links with DRO satellites (distant retrograde orbit satellites, A satellite) and LEO satellites (L satellite), and receive weak GNSS signals, testing various technical aspects of autonomous cruise based on the realization of constellation networking.

[0047] In this embodiment, the satellite components involve three satellites and one ground station during missions. Each satellite has different resource conditions and applicable distances for inter-satellite measurements, resulting in different payload configurations and technical requirements for each satellite. Satellite B simultaneously establishes inter-satellite measurement and communication links with satellites A and L, receiving weak GNSS signals. Based on constellation networking, various technical aspects of autonomous navigation are tested. First, autonomous navigation for orbit transfer between DROs is tested, followed by a transfer from DRO to resonant orbit (RO), testing large-scale orbit transfer autonomous navigation and autonomous navigation for orbit transfer between ROs. During and after satellite B's entry into the RO from the DRO, the K-band signal beam of satellite L cannot simultaneously cover satellite B; satellite L primarily points towards satellite B. The inter-satellite link configuration for the three-satellite network is as follows: satellite B has a fixed antenna pointing towards the ground, with the same beam covering satellite L and the ground station; the antenna is rotated to align with satellite A's 0.6m / 0.2m aperture antenna, with satellite A pointing towards satellite B. When other application missions are required, the above inter-satellite link configuration needs to be adjusted, and then restored to this configuration after the mission is completed.

[0048] In the description of this invention, it should be understood that the terms “X”, “Y”, “Z”, etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.

[0049] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of technical features indicated. Thus, a feature defined as "first" or "second" may explicitly or implicitly include at least one of that feature. In the description of this invention, "a plurality of" means at least two, such as two, three, etc., unless otherwise explicitly specified.

[0050] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components, unless otherwise explicitly limited. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0051] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can mean that the first feature is in direct contact with the second feature, or that the first feature is in indirect contact with the second feature through an intermediate medium. Furthermore, "above," "over," and "on top" of the second feature can mean that the first feature is directly above or diagonally above the second feature, or simply that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature can mean that the first feature is directly below or diagonally below the second feature, or simply that the first feature is at a lower horizontal level than the second feature.

[0052] In the description of this specification, the references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the present invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples. Moreover, without contradiction, those skilled in the art can combine and integrate the different embodiments or examples described in this specification, as well as the features of different embodiments or examples.

[0053] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. A large-scale cruise satellite in the Earth-Moon space, characterized in that, The system includes a satellite body, an onboard atomic clock, a satellite-to-ground or inter-satellite link measurement and communication payload, a space observation camera, and a lunar-Earth space GNSS orbit determination and timing payload. The onboard atomic clock is thermally conductively mounted on the inner side of the satellite body. The satellite-to-ground or inter-satellite link measurement and communication payload includes an internal transmitting component and an external antenna. The internal transmitting component is thermally conductively mounted on the inner side of the satellite body, and the external antenna is thermally insulatedly mounted on the outer side of the satellite body. The space observation camera is thermally insulatedly mounted on the outer side of the satellite body. A portion of the lunar-Earth space GNSS orbit determination and timing payload is thermally conductively mounted on the inner side of the satellite body, and another portion is thermally insulatedly mounted on the outer side of the satellite body.

2. The large-scale lunar cruise satellite according to claim 1, characterized in that, The onboard atomic clock includes a rubidium clock, which is thermally mounted on the inner side of the -Y plate of the satellite body via screws.

3. The large-scale lunar cruise satellite according to claim 1, characterized in that, The space observation camera includes a narrow field-of-view camera and a wide field-of-view camera, both of which are mounted on the outer side of the +X plate of the satellite body.

4. The large-scale lunar cruise satellite according to claim 1, characterized in that, The Earth-Moon space GNSS orbit determination and timing payload includes a GNSS weak signal navigation receiver, an array antenna, and a quad-helical antenna. The array antenna and the quad-helical antenna are connected to the GNSS weak signal navigation receiver via radio frequency cables. The GNSS weak signal navigation receiver is fixed to the inner side of the -Y plate of the satellite body. The array antenna is heat-insulated and installed on the outer side of the +Z plate of the satellite body. The quad-helical antenna is fixed to the outer side of the -Z plate of the satellite body.

5. A large-scale lunar cruise satellite according to claim 1, characterized in that, The satellite-to-ground or inter-satellite link measurement and communication payload includes a K-processor, an internal satellite transmitter assembly, and an external antenna. The internal satellite transmitter assembly and the K-processor are both thermally conductively mounted on the inner side of the satellite body. The K-processor is connected to the internal satellite transmitter assembly via a cable, and the internal satellite transmitter assembly is connected to the external antenna via a waveguide. The external antenna is thermally insulated and mounted on the outer side of the satellite body.

6. A large-scale lunar cruise satellite according to claim 5, characterized in that, The in-satellite transmission assembly includes a first transmitter and a second transmitter, which are thermally mounted on the inner side of the +Z plate of the satellite body, respectively.

7. A large-scale lunar cruise satellite according to claim 5, characterized in that, The satellite antenna includes a 0.22-meter fixed antenna and a 0.22-meter rotating antenna. The 0.22-meter rotating antenna is rotatably mounted on the outer side of the +X plate of the satellite body through a K rotating mechanism, and the 0.22-meter fixed antenna is fixed on the outer side of the +Z plate of the satellite body.

8. A large-scale lunar cruise satellite according to claim 1, characterized in that, The thermal insulation installation includes using fiberglass thermal insulation pads for thermal insulation installation.

9. A large-scale lunar cruise satellite according to claim 1, characterized in that, The inner surface of the satellite body is equipped with heat pipes for heat dissipation.

10. A satellite component, characterized in that, The satellite includes a large-scale lunar space cruise satellite as described in any one of claims 1 to 9, and also includes a long-distance retrograde orbit satellite, wherein the long-distance retrograde orbit satellite is connected to the outer surface of the satellite body via a satellite-rocket separation assembly.

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