Hybrid propulsion satellite layout adapted to complex antenna loads

Abstract

This invention provides a hybrid propulsion satellite layout structure adapted to complex antenna payloads, comprising a payload bay main body, a multi-beam reflector antenna, at least one optical head payload, a telemetry and control (TT&C) antenna tower with at least one pair of vector adjustment mechanisms and electric thruster assemblies, and a pair of solar arrays. The top of the payload bay main body is a ground-facing panel, with at least one extended region formed by a partial outward extension of the upper surface of the ground-facing panel. At least one optical head payload is mounted on the corresponding extended region via elevated supports. Below the extended region is a slanted support structure connected to the payload bay main body, which connects to and supports the extended region. The TT&C antenna tower is installed in the middle of the ground-facing panel. The multi-beam reflector antenna, vector adjustment mechanism and electric thruster assembly, and solar arrays are arranged in an optimized layout. Thus, this invention can optimize the satellite's spatial layout, improve the on-orbit electrical performance of the optical head payload, and enhance the on-orbit mechanical stability of the optical payload.

Description

Technical Field

[0001] This invention relates to the field of satellite design technology, and in particular to a chemical-electric hybrid propulsion satellite layout structure adapted to complex antenna loads. Background Technology

[0002] With the development of satellite technology, the communication satellite market has put forward increasingly higher requirements for the service capabilities of satellite platforms. Geosynchronous orbit communication satellites have been widely used to date. Their structural forms are mostly load-bearing tube type or truss type. The main features are that they have large-area solar panels to provide sufficient power supply, large-area north and south sides as mounting surfaces and heat dissipation surfaces for a large number of payload equipment, and east and west sides and ground surface for mounting antenna main payloads for communication transmission and reception.

[0003] With the continuous expansion of communication needs, large-scale high-throughput fixed beam coverage, point beam antenna coverage adapted to mobile objects, and laser optical communication for high-speed data transmission between satellites and between satellites and ground are increasingly being used on satellites.

[0004] Therefore, adapting satellite configurations to complex antenna payloads and laser optical payloads is a technical challenge that urgently needs to be addressed in current satellite overall design. Summary of the Invention

[0005] The purpose of this invention is to provide a hybrid propulsion satellite layout structure that adapts to complex antenna loads, which can optimize the satellite's spatial layout, improve the on-orbit electrical performance of the optical head load, and enhance the on-orbit mechanical stability of the optical load.

[0006] To achieve the above objectives, this invention provides a hybrid propulsion satellite layout structure adapted to complex antenna payloads, comprising a payload bay main body, a multi-beam reflector antenna, at least one optical head payload, a telemetry and control antenna tower, at least one pair of vector adjustment mechanisms and electric thruster assemblies, and a pair of solar arrays. The payload bay main body includes an east, west, south, and north payload bay plate distributed in four directions. The top of the payload bay main body is a ground-facing module, the upper surface of which extends outward to form at least one extended area. The at least one optical head payload... The payload bay is mounted on the corresponding extended area via an elevated support bracket. Below the extended area is a slanted support structure connected to the main body of the payload bay. The slanted support structure connects to and supports the extended area. The telemetry and control antenna tower is installed in the middle of the ground-facing module. The multi-beam reflector antenna is installed on the ground-facing module and distributed around the telemetry and control antenna tower. The pair of solar panels are respectively installed on the south and north panels of the payload bay below the slanted support structure. At least one pair of vector adjustment mechanisms and electric thruster assemblies are installed below the pair of solar panels.

[0007] Furthermore, it includes a first extended area and a second extended area, which are located on the west side of the ground deck extending north and south, respectively.

[0008] Furthermore, the telemetry and control antenna tower is equipped with a telemetry antenna, a remote control antenna, and a feed horn for a point-beam antenna. Point-beam reflector antennas are installed on the ground-facing module surrounding the telemetry and control antenna tower. The reflector of the point-beam reflector antenna and the feed horn together form N offset-fed first point-beam antennas. M positive-fed second point-beam antennas are also installed on the ground-facing module. Here, M and N are both positive integers greater than or equal to 1.

[0009] Furthermore, the reflective surface of the first point beam antenna, the telemetry and control antenna tower, and the surfaces of the reflective surface of the first point beam antenna and the installation area of ​​the telemetry and control antenna tower on the ground-facing module are all made of siloxane film multilayer thermal insulation material.

[0010] Furthermore, a set of double-overlapping antennas is installed on the east and west panels of the payload compartment, respectively. The antenna feeds corresponding to the double-overlapping antennas are installed on the east and west panels of the payload compartment near the ground-facing compartment via feed support structures. The antenna pointing mechanisms corresponding to the double-overlapping antennas are installed on the east and west panels of the payload compartment away from the ground-facing compartment. The main reflector and locking / releasing device of the double-overlapping antennas are installed at the middle positions of the east and west panels of the payload compartment.

[0011] Furthermore, a first inclined support structure and a second inclined support structure are respectively connected below the first extended region and the second extended region, and the pair of solar panels are installed on the corresponding load cells below the first inclined support structure and the second inclined support structure.

[0012] Furthermore, an ion thruster and an electric propulsion vector adjustment mechanism for on-orbit angle adjustment are installed on the payload bay plate corresponding to the lower part of the solar array.

[0013] Furthermore, each of the aforementioned inclined support structures consists of two triangular inclined support plates and a sealing plate. The two triangular inclined support plates are respectively installed on both sides of the sealing plate, and the upper surface formed by the triangular inclined support plates and the sealing plate is connected to the corresponding extended area; the sealing plate is also provided with cable penetration holes.

[0014] The hybrid chemical-electric propulsion satellite layout structure provided by this invention maximizes the utilization of space for antenna and laser payloads by extending the ground. By arranging optical payloads in the north-south extension areas and elevating the laser optical head payload, and using multi-layer thermal insulation components with higher emission-absorption ratio siloxane films for the optical payload accessory compartments and antennas, the thermal radiation impact of the space environment on the optical payload is reduced, improving the on-orbit electrical performance of the optical head payload. Structural reinforcement is achieved by setting a diagonal support structure below the ground extension, improving the mechanical response of the optical head payload during satellite launch and on-orbit phases, and enhancing the on-orbit mechanical stability of the optical payload. A reasonable spatial arrangement of the east and west antenna components reduces the spatial distance between the antenna feed and the internal equipment, lowering the spatial loss of the transponder input and output links, and improving the effective payload electrical performance. Optimized layout of the solar array, electric propulsion ion thruster, and vector adjustment mechanism by rationally utilizing the north and south space improves the satellite's on-orbit efficiency. This invention enables the application of the maximum number of reflector antennas under a hybrid chemical-electric propulsion system based on existing mature satellite platforms, while ensuring the on-orbit application of the laser payload. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the chemical-electric hybrid propulsion satellite layout structure adapted to complex antenna loads provided in the first embodiment of the present invention;

[0016] Figure 2 An exploded view of the payload bay body of the chemical-electric hybrid propulsion satellite layout structure adapted to complex antenna loads provided in the first embodiment of the present invention;

[0017] Figure 3 A schematic diagram of the optical head payload from an upward-looking perspective of the chemical-electric hybrid propulsion satellite layout structure adapted to complex antenna payloads provided in the first embodiment of the present invention;

[0018] Figure 4 This is a top-view structural diagram of the optical head payload of the chemical-electric hybrid propulsion satellite layout structure adapted to complex antenna payloads provided in the first embodiment of the present invention. Detailed Implementation

[0019] To make the objectives, technical solutions, and advantages of this invention clearer, the invention will be further described in detail below with reference to the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are merely illustrative and not intended to limit the invention.

[0020] It should be noted that references to "an embodiment," "embodiment," "example embodiment," etc., in this specification refer to the described embodiment including specific features, structures, or characteristics, but not every embodiment must include these specific features, structures, or characteristics. Furthermore, such expressions do not refer to the same embodiment. Moreover, when describing specific features, structures, or characteristics in conjunction with embodiments, whether or not explicitly described, it is indicated that incorporating such features, structures, or characteristics into other embodiments is within the knowledge of those skilled in the art.

[0021] Furthermore, certain terms are used in the specification and subsequent claims to refer to specific components or parts. Those skilled in the art will understand that manufacturers may use different names or terms to refer to the same component or part. This specification and subsequent claims do not distinguish components or parts by differences in name, but rather by differences in function. The terms "comprising" and "including" used throughout the specification and subsequent claims are open-ended and should be interpreted as "including but not limited to." Additionally, the term "connection" here includes any direct and indirect electrical connection means. Indirect electrical connection means include connections made through other means.

[0022] Figure 1 This invention illustrates a hybrid propulsion satellite layout structure adapted to complex antenna payloads, including a payload bay main body, six sub-beam reflector antennas 31, two optical head payloads 20, a telemetry and control antenna tower 30, and a pair of solar arrays 40. The payload bay main body includes an east plate 11, a west plate 12, a south plate 14, and a north plate 13 distributed in four directions. Figure 2 As shown; the top of the payload compartment body is the ground-facing compartment 5. The upper surface of the ground-facing compartment 15 extends outward to form two extended areas. Two optical head payloads 20 are respectively installed on the corresponding extended areas through the elevated brackets 21. Below the extended areas is a slanted support structure 22 connected to the payload compartment body. The slanted support structure 22 connects to and supports the extended areas. At the same time, four connecting corner boxes 23 improve the connection stiffness between the slanted support structure 22 and the ground-facing compartment 14. The telemetry and control antenna tower 30 is installed in the middle of the ground-facing compartment 15. The multi-beam reflector antenna 31 is installed on the ground-facing compartment 15 and distributed around the telemetry and control antenna tower 30. A pair of solar panels 40 are respectively installed on the south plate 14 and the north plate 13 of the payload compartment below the slanted support structure 22. A pair of vector adjustment mechanisms and electric thruster assemblies 50 are installed below the pair of solar panels 40. In this embodiment, a portion of the upper surface of the ground module 15 that extends outward is used to install the optical head load 20, thereby maximizing the use of space for the antenna load and the laser load.

[0023] Of course, in other examples, the ground panel 15 can be extended outward in multiple extended areas on the upper surface, such as three, four, five, etc., depending on the actual situation, so that a corresponding optical head load 20 is installed on each extended area. Each extended area can install one or more optical head loads 20, and the optical head load 20 is specifically used to install a laser terminal.

[0024] A diagonal support structure 22 is installed below the extended area. This diagonal support structure 22 is connected to the side of the payload compartment body and extends outwards to connect with the lower part of the extended area, thereby supporting and securing the extended area. See also... Figure 3 In this embodiment, the inclined support structure 22 is a triangular prism structure, with one side connected to the side of the main body of the load chamber and the other adjacent side connected to the lower part of the expansion area. Specifically, the inclined support structure 22 is connected and fixed to the lower part of the expansion area through multiple connecting corner boxes 23 to improve the mechanical response of the laser head load.

[0025] See Figures 3-4 Each inclined support structure 22 consists of two triangular inclined support plates and a sealing plate. The two triangular inclined support plates are respectively installed on both sides of the sealing plate, and the upper surface formed by the triangular inclined support plates and the sealing plate is connected to the corresponding extended area. The sealing plate is also provided with cable passage holes for cable routing between the laser cabin equipment and the optical head. The inclined support structure 22 occupies a 200mm space from the ground to the back of the ground, forming a 45° angle with the ground-facing cabin plate 15 to ensure the structural connection strength and stability requirements.

[0026] This embodiment includes a first extended region and a second extended region, which are located on the west side of the ground module 15 extending north and south, respectively. Specifically, the first and second extended regions are the protruding areas extending outward from the west side of the ground module 15, forming the upper edges of the payload bay south plate 14 and payload bay north plate 13. Each extended region in this embodiment has a size of 500mm * 250mm; the specific dimensions can be set according to the actual satellite design dimensions.

[0027] Specifically, a first inclined support structure and a second inclined support structure are respectively connected below the first extended region and the second extended region. A pair of solar panels 40 are mounted on the corresponding load cells below the first and second inclined support structures. In this embodiment, an electric propulsion ion thruster and a vector adjustment mechanism for on-orbit angle adjustment are mounted on the load cells below the solar panels 40. Each payload bay has a solar array 40 mounted on its south plate 14 and north plate 13. The solar arrays 40 are distributed opposite each other. Below each solar array 40, on the corresponding payload bay south plate 14 or payload bay north plate 13, is an ion thruster and an electric propulsion vector adjustment mechanism. Specifically, as shown in the figure, the ion thruster and the electric propulsion vector adjustment mechanism form a combination 50. This combination 50 is mounted on the corresponding payload bay plate via a mounting plate 72. The electric propulsion vector adjustment mechanism and the ion thruster are positioned to avoid the solar array 40, with the lower end of the solar array as a reference. Through on-orbit angle adjustment by the electric propulsion vector adjustment mechanism, when the ion thruster is working, the thrust vector passes through the satellite's center of mass, thereby providing the velocity increment required for satellite position maintenance in orbit.

[0028] In this embodiment, a large solar array 40 is arranged below the laser payload and the inclined support structure of the ground extension section to provide sufficient power for the satellite. When the solar array is arranged, the upper end is immediately connected to the inclined support structure of the ground extension section. The specific layout position is with reference to the lower end of the inclined support structure 22 of the optical head. The top of the solar array 40 is preferably 200mm away from the ground.

[0029] Optical head loads 20 are mounted on the first and second extended regions respectively via a high bracket 21. In this embodiment, the height of the high bracket 21 is 200mm, and it is made of high-load material to improve the thermal environment of the optical head.

[0030] In this embodiment, the telemetry and control antenna tower 30 is equipped with a telemetry antenna, a remote control antenna, and a feed horn for a point-beam antenna. The ground-facing module 15 surrounding the telemetry and control antenna tower 30 is equipped with the reflector of a point-beam reflector antenna 31. The reflector of the point-beam reflector antenna 31 and the feed horn together form N offset-fed first point-beam antennas. M positive-fed second point-beam antennas are also installed on the ground-facing module 15; where M and N are both positive integers greater than or equal to 1. Preferably, in this embodiment, N=4 and M=2, meaning that the ground-facing module 15 has 4 offset-fed first point-beam antennas and 2 positive-fed second point-beam antennas; specifically, the 2 positive-fed second point-beam antennas are located on the east side of the ground-facing module 15. Therefore, in this embodiment, the ground-facing module 15 has a total of 6 movable point-beam antennas 31 and 2 sets of laser terminal optical head payloads 20. Specifically, the telemetry and control antenna tower 30 on the ground module 15 adopts a composite material tower structure. The telemetry antenna and remote control antenna are arranged at the top of the tower, and four Ka-band feed horns are arranged on the side of the tower. Four 600mm diameter movable spot beam antenna reflectors are arranged around the tower to the ground module 15. Two 900mm diameter positive feed movable spot beam antennas are arranged on the east side of the ground module 15. The six movable spot beam antennas avoid the field of view of the 10N attitude control thruster and the satellite sensor.

[0031] Furthermore, the reflector surface of the first point-beam antenna, the telemetry and control antenna tower 30, and the surfaces of the reflector surface of the first point-beam antenna and the installation area of ​​the telemetry and control antenna tower 30 on the ground-facing panel 15 are all made of siloxane film multilayer thermal insulation component material. Utilizing the high emission-absorption ratio characteristics of the siloxane film, the thermal radiation impact of surrounding components on the optical head can be effectively reduced. Specifically, the telemetry and control antenna tower 30 is entirely covered with high emission-absorption ratio siloxane film multilayer thermal insulation component material; the four 600mm diameter reflector antennas are made of siloxane film multilayer thermal insulation component material; and the outer surface of the ground-facing panel 15 where the telemetry and control antenna tower 30 and the four 600mm diameter reflector antennas are located is made of siloxane film multilayer thermal insulation component material to reduce the thermal radiation impact of the space environment on the optical load.

[0032] Optionally, a set of double-overlapping antennas is installed on the east and west plates of the payload compartment, respectively. The antenna feed 61 corresponding to the double-overlapping antennas is installed on the east and west plates of the payload compartment 11 and 12 near the ground-facing plate 15 via a feed support structure 71. The antenna pointing mechanism 62 corresponding to the double-overlapping antennas is installed on the east and west plates of the payload compartment 11 and 12 away from the ground-facing plate 15. The main reflector 63 and locking / releasing device corresponding to the double-overlapping antennas are installed at the middle positions of the east and west plates of the payload compartment 11 and 12, respectively. Figure 2As shown, a set of double-overlapping antennas is installed on the east plate 11 and the west plate 12 of the payload compartment. Each double-overlapping antenna includes a corresponding antenna feed 61, an antenna pointing mechanism 62, an antenna main reflector 63, and a locking and releasing device.

[0033] The gas cylinders inside the main body of the payload compartment are arranged on the east and west sides of the central support cylinder 70 through the support assembly. The detailed layout of the gas cylinders on the central support cylinder 70 is adaptively avoided according to the layout space of the east and west antenna feeds 61 and feed support structure 71. The layout of the various structural panels and equipment inside the payload compartment is also adaptively avoided and adjusted. Figure 2 The bottom of the payload compartment shown is the service compartment, which is encapsulated by multiple service compartment panels 73.

[0034] Thus, the satellite in this embodiment achieves an onboard layout structure of 10 reflector antennas, 2 sets of laser optical payloads, a large-area solar array, an electric propulsion vector adjustment mechanism, and an ion thruster assembly.

[0035] In summary, the hybrid propulsion satellite layout structure adapted to complex antenna payloads provided by this invention, while maintaining the basic configuration of the communication satellite platform and payload bay, maximizes the utilization of space for antenna and laser payloads by extending the ground. By arranging optical payloads in the north-south extension areas and elevating the laser optical head payload, and using multi-layered thermal insulation components with higher emission-absorption ratios (PEEP) siloxane films for the optical payload accessory bays and antennas, the thermal radiation impact of the space environment on the optical payloads is reduced, improving the on-orbit electrical performance of the optical head payload. Furthermore, by installing a diagonal support structure below the ground extension, structural reinforcement is provided to improve the performance of the optical head payload during satellite launch. The invention improves the mechanical stability of the optical payload during the on-orbit phase by optimizing the mechanical response of the components of the east and west antennas, reducing the spatial distance between the antenna feed and the equipment inside the cabin, lowering the spatial loss of the transponder input and output links, and improving the electrical performance of the payload. It also optimizes the layout of the solar array, electric propulsion ion thruster, and vector adjustment mechanism by making reasonable use of the space on the north and south sides, thereby improving the satellite's on-orbit utilization efficiency. Furthermore, it enables the application of the maximum number of reflector antennas based on existing mature satellite platforms and a hybrid chemical-electric propulsion system, while ensuring the on-orbit application of the laser payload. Finally, the invention allows multiple movable point-beam antennas, multi-beam antennas, and laser terminal payloads to work collaboratively, ensuring stable satellite operation.

[0036] Of course, the present invention may have other various embodiments. Without departing from the spirit and essence of the present invention, those skilled in the art can make various corresponding changes and modifications according to the present invention, but these corresponding changes and modifications should all fall within the protection scope of the appended claims.

Claims

1. A hybrid electric propulsion satellite architecture adapted to complex antenna loads, characterized in that, The load cabin body includes a load cabin east plate, a load cabin west plate, a load cabin south plate and a load cabin north plate distributed in four directions, and the top of the load cabin body is a ground-facing cabin plate, the upper surface of which extends outward to form at least one expansion area, and at least one optical head load is installed on the corresponding expansion area through a heightening support, and a slope support structure connected with the load cabin body is arranged below the expansion area, and the slope support structure connects and supports the expansion area; the TT&C antenna tower is installed at the middle position of the ground-facing cabin plate, and the multi-beam reflector antenna is installed on the ground-facing cabin plate and distributed around the TT&C antenna tower, and a pair of solar wings are installed on the load cabin south plate and the load cabin north plate below the slope support structure, and at least one pair of vector adjustment mechanism and electric thruster combination is installed below the pair of solar wings.

2. The hybrid electric propulsion satellite architecture accommodating complex antenna loads according to claim 1, characterized in that, The first expansion area and the second expansion area are respectively located in the south-north extending direction on the west side of the ground-facing cabin plate.

3. The hybrid electric propulsion satellite architecture accommodating complex antenna loads according to claim 1, characterized in that, The TT&C antenna tower is provided with a telemetry antenna, a remote control antenna and a feed horn of a spot beam antenna, and the ground-facing cabin plate around the TT&C antenna tower is provided with a spot beam reflector antenna, the reflector surface of the spot beam reflector antenna and the feed horn form a first spot beam antenna in N pairs of offset feed form, and the ground-facing cabin plate is further provided with M pairs of second spot beam antennas in normal feed form; wherein M and N are positive integers greater than or equal to 1.

4. The hybrid electric propulsion satellite architecture accommodating complex antenna loads according to claim 3, characterized in that, The reflector surface of the first spot beam antenna, the TT&C antenna tower and the surface of the installation area of the reflector surface of the first spot beam antenna and the TT&C antenna tower on the ground-facing cabin plate are all made of a silicone film multilayer thermal insulation assembly material.

5. The hybrid electric propulsion satellite architecture accommodating complex antenna loads according to claim 1, characterized in that, A set of double overlapping antennas is respectively installed on the load cabin east plate and the load cabin west plate, the corresponding antenna feed sources of the double overlapping antennas are respectively installed on the load cabin east plate and the load cabin west plate near the ground-facing cabin plate through a feed support structure, the corresponding antenna pointing mechanisms of the double overlapping antennas are respectively installed on the load cabin east plate and the load cabin west plate away from the ground-facing cabin plate, and the corresponding antenna main reflector surfaces and locking release devices of the double overlapping antennas are respectively installed on the middle positions of the load cabin east plate and the load cabin west plate.

6. The hybrid electric propulsion satellite architecture accommodating complex antenna loads according to claim 2, characterized in that, First and second slope support structures are respectively connected below the first and second expansion areas, and the pair of solar wings are installed on the corresponding load cabin plates below the first and second slope support structures.

7. The hybrid electric propulsion satellite architecture accommodating complex antenna loads according to claim 6, characterized in that, An ion thruster and an electric propulsion vector adjustment mechanism for on-orbit angle adjustment are installed on the corresponding load cabin plates below the solar wings.

8. The hybrid electric propulsion satellite architecture accommodating complex antenna loads according to claim 1, characterized in that, Each of the inclined support structures is composed of two triangular inclined support plates and a blocking plate, the two triangular inclined support plates are respectively installed on the two sides of the blocking plate, and the upper surface formed by the triangular inclined support plates and the blocking plate is connected with the corresponding expansion area; the blocking plate is further provided with a cable cabin-through hole.

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