An extended configuration of satellite payload cabin adapted to high-throughput payloads

Abstract

The present invention provides a satellite payload cabin expansion configuration adapted to high-throughput payloads, comprising an expansion cabin, a connecting waveguide, a feed array, and a receiving device, wherein the expansion cabin is used to form an independent closed cabin body when the satellite is facing the ground, and to provide an installation interface for the feed array, and the connecting waveguide is used to connect the receiving device and the feed array. The present invention overcomes the shortcomings of the prior art, and the proposed expansion configuration can adapt to the carrying requirements of high-throughput satellites with nearly 100 beam configurations, meet the envelope requirements of the CZ‑3B carrier 4000F fairing, and meet the installation requirements of a large-size feed array.

Description

Technical Field

[0001] The invention relates to a payload cabin expansion configuration of a communication satellite, belonging to the technical field of satellites. Background Art

[0002] As users have higher and higher requirements for communication satellite payloads, operators of civil and commercial communication satellites are increasingly deploying high-throughput payload satellites (hereinafter referred to as HTS satellites). The number and proportion of HTS satellites are increasing significantly. HTS satellite payloads are quite different from traditional communication satellites, mainly including two parts:

[0003] On the one hand, in order to achieve regional coverage of the payload, the number of beams has increased dramatically, so there is an urgent need for the application of large-sized multi-beam antenna feed arrays. This makes the antenna structure design different from the single feed or dual feed form of previous communication satellites. The multi-beam feed array and supporting structure are large in size and heavy in weight. Figure 1 The high-throughput satellite configuration and layout design, especially the structural design of the payload cabin, needs to be adaptively adjusted for this large-sized feed array.

[0004] On the other hand, in the design of the transponder channel, the flexible allocation of spectrum and power is taken into consideration, resulting in an exponential increase in the number of transponder equipment compared to previous conventional payload satellites, such as low-noise amplifiers, switching components, input / output multiplexers, etc. Therefore, the layout space and heat dissipation conditions of the satellite payload cabin have increased.

[0005] The increasingly complex payload design has put forward higher and higher requirements on the payload layout capability of the whole satellite. In the past, the structure of the communication cabin was in the shape of a letter "∏", consisting of the floor, the south and north panels of the communication cabin, and the north and south partitions of the communication cabin. The north and south surfaces of the communication cabin serve as heat radiation surfaces. The outer surface of the floor provides an installation surface for traditional communication antennas. The cabin provides layout space for transponder equipment. Figure 2 This traditional communication satellite configuration design can no longer meet the needs of high-throughput satellite transponder and antenna layout.

[0006] This project introduces a method for expanding the payload bay configuration layout of communication satellites. Summary of the invention

[0007] 1. The technical problem solved by the present invention is to overcome the shortcomings of the prior art and propose a load compartment structure

[0008] The expanded configuration of the type layout can adapt to the carrying requirements of high-throughput satellites with nearly 100 beam configurations, meet the envelope requirements of the CZ-3B carrying 4000F fairing, and meet the installation needs of large-size feed arrays.

[0009] 2. A satellite payload cabin expansion configuration adapted to high-throughput payloads, comprising an expansion cabin, a connecting waveguide, a feed array, and a receiving device, wherein the expansion cabin is used to form an independent closed cabin body facing the satellite to the ground and provide an installation interface for the feed array, and the connecting waveguide is used to connect the receiving device and the feed array.

[0010] Furthermore, the expansion cabin includes north and south plates of the expansion cabin, east and west plates of the expansion cabin, a top plate of the expansion cabin, a partition plate of the expansion cabin and a connecting structure.

[0011] Furthermore, the north and south plates of the expansion module are structures that are extended toward the earth from the north and south plates of the original payload module, and their outer surfaces are satellite heat dissipation surfaces, providing heat dissipation conditions for the cabin; the outer surfaces of the east and west plates of the expansion module provide installation surfaces for multi-beam feed needles; the top plate of the expansion module provides installation surfaces for measurement and control antennas, beacon antennas, and out-of-cabin waveguides; the expansion module partition is a wedge-shaped support structure, used to improve the connection strength and structural stability of the east and west plates of the expansion module.

[0012] Furthermore, the satellite heat dissipation surface is pasted with an OSR heat sink, and the distance between the east and west plates of the expansion cabin is 1400-1700 mm.

[0013] Furthermore, the connection structure includes: the structural connection between the east and west plates of the expansion cabin and the bottom plate of the payload cabin, the structural connection between the east and west plates of the expansion cabin and the north and south plates of the expansion cabin, the structural connection between the top plate of the expansion cabin and the east and west plates and the north and south plates, the structural connection between the expansion cabin partition and the east and west plates of the expansion cabin, the structural connection between the expansion cabin partition and the floor of the payload cabin, and the structural connection between the expansion cabin partition and the expansion cabin cover plate.

[0014] Furthermore, the connecting waveguide is divided into an input section connecting waveguide and an output section connecting waveguide. The output section connecting waveguide is connected to the feed array by the equipment in the payload cabin. The payload cabin provides corresponding adapters for the floor and the top plate of the expansion cabin, providing a fixed installation interface for the connection through the expansion cabin.

[0015] Furthermore, the receiving device is installed on the inner surfaces of the east and west plates of the expansion cabin, the inner surfaces of the north and south plates of the expansion cabin, and the upper surface of the floor of the payload cabin, and is connected to the antenna feed source through the input section connecting waveguide, and is connected to the external device through a cable.

[0016] 3. Beneficial effects - The advantages of the present invention compared with the prior art are:

[0017] (1) The traditional satellite configuration cannot solve the problem of installing and fixing the support structure of the large-scale feed array. The configuration of the expansion module forms an independent closed cabin body on the ground of the satellite, and by retracting the east and west sides inward, it provides a reliable cabin panel installation interface for the large-scale feed array within the available space of the carrier envelope.

[0018] (2) Traditional satellite transponder receiving devices are arranged inside the cabin, and the antenna feed source is arranged outside the cabin, resulting in a long connecting waveguide length between the feed source and the transponder receiving device, and a large signal loss of the feed source reception. The present invention arranges the transponder receiving device inside the expansion cabin, and arranges the feed source array outside the expansion cabin to ensure that the connecting waveguide length is the shortest, thereby reducing the signal loss of the satellite payload and improving the satellite G / T value performance;

[0019] (3) Traditionally, satellite transponder receiving devices are arranged inside the cabin, and antenna feed sources are arranged outside the cabin. This results in a long waveguide length between the feed source and the transponder receiving device, and a large area of ​​satellite layout space is occupied on the waveguide path. In the present invention, both the antenna feed source and the transponder receiving device are arranged outside the cabin, and the waveguide length is short. The signal received by the feed source passes through the expansion cabin and is connected to the cabin through a high-frequency cable, which effectively saves satellite layout space. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the structure of a large-scale feed array;

[0021] Figure 2 It is a schematic diagram of the traditional payload cabin configuration;

[0022] Figure 3 This is a schematic diagram of the expansion cabin configuration of the present invention;

[0023] Figure 4 This is a schematic diagram of the interior configuration of the expansion cabin of the present invention;

[0024] Figure 5 This is a partial schematic diagram of the north and south sides of the expansion cabin of the present invention;

[0025] Figure 6 This is a schematic diagram of the exterior layout of the expansion cabin of the present invention;

[0026] Figure 7 This is a schematic diagram of the interior layout of the expansion cabin of the present invention. DETAILED DESCRIPTION

[0027] The present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0028] The south plate 2 and the north plate 3 of the payload cabin are extended in the direction of the satellite to the earth. The outer surface of the cabin plate can increase the effective heat dissipation area, and the inner surface of the cabin plate provides space for the layout of equipment, especially the layout of high heat consumption equipment. The structural design of the expansion part is considered. The temperature field and plume field range of the ignition process of the attitude control engine are considered, and the cabin plate opening 10 is added at the corresponding position; Figure 4 shown.

[0029] Considering the size expansion of the south plate 2 and the north plate 3 of the payload cabin, feed mounting plates 6 and 7 are added along the north-south direction on the east-west sides of the original floor panel 1 on the ground. The feed mounting plates adopt a traditional honeycomb sandwich structure, and the height of the cabin panel is set according to the installation requirements of the feed array. The outer surfaces of the feed mounting plates 6 and 7 provide mounting surfaces for the east-west antenna feed array 12, and the cabin panel structure strengthens the local structure according to the results of mechanical analysis. The inner surface of the cabin panel provides a layout position for the forward return low heat consumption equipment, and a structural angle strip connection is established between the feed mounting plates 6 and 7 and the floor panel 1, and a connection is established with the south plate 2 and the north plate 3 of the payload cabin through lateral embedded parts; such as Figure 3 shown.

[0030] The expansion cabin is facing the ground, and an expansion cabin cover plate 8 is added. The expansion cabin cover plate 8 is connected with the south plate 2 of the payload cabin, the north plate 3 of the payload cabin, the east feed source installation plate 6, and the west feed source installation plate 7 by establishing structural angle strips. The expansion cabin forms a closed cabin body, and the structural design state is stable and reliable. The floor-to-ground surface under the original configuration becomes the bottom surface of the expansion cabin, which becomes the equipment installation surface in the cabin, and can provide an equipment installation surface for low-power forward return equipment; Figure 6 shown.

[0031] After the equipment, waveguides and cables in the expansion cabin are installed on the satellite, the expansion cabin cover 8 is installed on the satellite to form a closed cabin. After the expansion cabin cover 8 is installed on the satellite, the upper surface provides a mounting surface for the beacon antenna 13, the measurement and control antenna 14, and the satellite attitude sensor 15, and also provides a fixing surface for the installation of the waveguide components between the multi-beam feed array and the equipment in the cabin; Figure 5 shown.

[0032] Considering that the design state of the antenna feed array 12 is relatively complex, the number of beams is large, the feed array is large in size and weight, in order to ensure the connection strength between the feed array 12 and the feed mounting plate 7, a wedge-shaped support plate structure 16 is added between the middle part of the feed mounting plate 7 and the ground plane, and the support plate 16 is connected to the ground plane 1 and the feed mounting plate 7 through structural angle strips to strengthen the structural strength of the feed mounting plate 7.

[0033] A large-scale multi-beam antenna feed array 12 is installed on the outer surface of the feed mounting plate 7. The connecting waveguides between the antenna feed array 12 and the equipment in the cabin are led out from the feed array to the ground position. The waveguide crosses the feed mounting plate 7 and is connected to the equipment in the expansion cabin. The expansion cabin cover plate 8 opens corresponding cabin openings according to the waveguide direction requirements.

[0034] In addition to the above expansion configurations, the following satellite configurations are available:

[0035] A load cabin horizontal plate 5 is added to the position below the floor 1. The horizontal plate 5 is connected to the load cabin south plate 2 and the load cabin north plate 3 through lateral embedded parts, and is connected to the central load-bearing cylinder through structural angle bars, which can provide layout space for instruments and equipment. At the same time, a north-south coupling heat pipe 11 is arranged on the horizontal plate to conduct the heat of the equipment to the north and south plates for heat dissipation. Figure 7 shown.

[0036] The contents not described in detail in the specification of the present invention belong to the common knowledge of those skilled in the art.

Claims

1. A satellite payload cabin expansion configuration adapted to high-throughput payloads, characterized in that: It includes an expansion cabin, a connecting waveguide, a feed array, and a receiving device, wherein the expansion cabin is used to form an independent closed cabin body on the ground of the satellite and provide an installation interface for the feed array, and the connecting waveguide is used to connect the receiving device and the feed array; The expansion cabin includes north and south panels, east and west panels, a roof panel, a partition panel and a connecting structure. The north and south plates of the expansion module are structures that extend the north and south plates of the original payload module toward the ground. Their outer surfaces are satellite heat dissipation surfaces, providing heat dissipation conditions for the cabin. The outer surfaces of the east and west plates of the expansion module provide installation surfaces for multi-beam feed needles. The top plate of the expansion module provides installation surfaces for the measurement and control antenna, beacon antenna and outbound waveguide. The expansion module bulkhead is a wedge-shaped support structure used to improve the connection strength and structural stability of the east and west plates of the expansion module. The connecting waveguide is divided into an input section connecting waveguide and an output section connecting waveguide. The output section connecting waveguide is connected to the feed source array by the equipment in the payload cabin. The payload cabin provides corresponding adapters for installing the floor and the top plate of the expansion cabin, and provides a fixed installation interface for the connection through the expansion cabin. The receiving device is installed on the inner surfaces of the east and west plates of the expansion cabin, the inner surfaces of the north and south plates of the expansion cabin, and the upper surface of the floor of the payload cabin, and is connected to the antenna feed source through the input section connecting waveguide and connected to the external device through a cable.

2. The expansion configuration according to claim 1, characterized in that: The satellite heat dissipation surface is pasted with OSR heat sink, and the distance between the east and west plates of the expansion cabin is 1400~1700mm.

3. The expansion configuration according to claim 1, characterized in that: The connection structure includes: the structural connection between the east and west plates of the expansion cabin and the bottom plate of the payload cabin, the structural connection between the east and west plates of the expansion cabin and the north and south plates of the expansion cabin, the structural connection between the top plate of the expansion cabin and the east and west plates and the north and south plates, the structural connection between the expansion cabin partition and the east and west plates of the expansion cabin, the structural connection between the expansion cabin partition and the floor of the payload cabin, and the structural connection between the expansion cabin partition and the expansion cabin cover plate.

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