Full-truss open type modular architecture of SAR (synthetic aperture radar) satellite

Abstract

The invention provides an SAR (synthetic aperture radar) satellite full-truss open type modular framework, which comprises an integrated full-truss structure with a release type cuboid configuration, and a plurality of modular functional units which are integrally enclosed into a hexahedral open type configuration are fixed on the outer side of the full-truss structure by taking the full-truss structure as a backbone. According to the function of each subsystem on a satellite and the layout position of each single machine, each single machine area is integrated with a modularized function unit, and the modularized function unit comprises a load function module, a solar cell array function module and the like and is fixed on the outer side of a full-truss structure. A cellular board single-cabin module is designed, a single machine can be installed, and the whole body flexibly and freely enters and exits in a truss structure. Standardized carbon fiber rod pieces and aluminum alloy connectors are adopted in the integrated full-truss structure, standardized installation interfaces are provided, modularized functional units are developed in parallel, open bus systems are adopted among the modularized functional units, standardized protocols are supported, redundant design is achieved, and the integrated full-truss structure is high in reliability. And data and energy rapid identification and interaction between modular functional units can be realized.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of satellite overall design, and in particular relates to a full-truss open and modular architecture of a SAR satellite. BACKGROUND

[0002] Traditional remote sensing satellites mostly adopt a full honeycomb panel + load-bearing cylinder structure configuration. When they bear a large mass of planar phased array radar load antennas, in order to ensure the bearing stiffness and strength, the load-bearing cylinder is generally taken as the central load-bearing structure, and the side plate and the layer plate are combined with each other as a complete closed configuration to improve the bearing capacity of the satellite structure. However, this will also cause the bearing ratio of the satellite body to decrease, and the satellite structure to occupy a large weight. For small satellites launched in batches, less satellite structure weight ratio, open structure configuration and better modular design are new technical requirements.

[0003] As a new type of lightweight material, the carbon fiber structure has the characteristics of high bearing and light weight. The full carbon fiber material of the load and platform integration is adopted as the main load-bearing structure of the satellite, which will play its outstanding advantages. The satellite structure composed of carbon fiber rods and joints has a good open configuration, which is convenient for subsequent batch production as a skeleton architecture. Each single machine system is designed as a modular unit according to the function, and is installed and fixed on the full truss structure through the standardized interface and the switching structure, forming a new idea of rapid batch production and development.

[0004] The Chinese invention patent with the patent document CN108045597A discloses a modular and assemblable satellite structure. It comprises a service module, a propulsion module connected with one end of the service module, and a load module connected with the other end of the service module. The service module comprises a service module bottom plate connected with the propulsion module, a service module frame which is a polygon and is connected with the service module bottom plate, and a service module side plate connected with the service module frame.

[0005] The Chinese invention patent with the patent document CN108820252B discloses an in-cabin and out-cabin truss combined satellite cabin section structure. It comprises an in-cabin truss, an out-cabin truss, a partition plate, a side plate, a ground plate, and a layer plate composed of a lower cabin bottom plate, a middle cabin bottom plate, an upper cabin bottom plate, and an upper cabin top plate. The in-cabin truss is located in the middle position and is taken as the main load-bearing component of the whole cabin section. The truss is connected with the layer plate and the partition plate through a truss bar, and the flange at the root of the truss is screwed with the lower cabin bottom plate. The ground plate, the II reference side plate, the III reference side plate, and the IV reference side plate surround the whole cabin section to form a closed box. The ground plate is connected with the in-cabin truss, the out-cabin truss, and the layer plate through a buried part, and is taken as the main installation surface of various large detection instruments. The out-cabin truss is located at the top of the whole cabin section and is connected with the ground plate and the upper cabin top plate through a buried part.

[0006] The above published Chinese invention patent has a modular structure and a cabin truss structure, but its core is still to place the cabin plate outside the truss, and the space inside the integrated full truss structure cannot be fully utilized. The total weight of the structure with the same volume is relatively larger, the overall space envelope occupies a large space, and after the installation of the side plate, the structure faces the shortcomings of insufficient openness and the like. During the subsequent single machine assembly integration process, the single machine needs to be frequently disassembled and assembled, which brings repeated progress and operation risks. SUMMARY

[0007] In view of the defects in the prior art, the purpose of the present application is to provide a SAR satellite full truss open and modular architecture.

[0008] According to the present application, a SAR satellite full truss open and modular architecture is provided, characterized in that it comprises an integrated full truss structure, a modular functional unit and a honeycomb plate single machine cabin.

[0009] The integrated full truss structure is a cuboid frame, and the outer side is open and has no structural side plate.

[0010] The modular functional unit is fastened to the outer side of the integrated full truss structure, and the modular functional unit as a whole forms a hexahedral configuration.

[0011] The honeycomb plate single machine cabin is a plurality of independent modules installed inside the integrated full truss structure.

[0012] Preferably, the modular functional unit comprises a plurality of functional modules; the functional unit comprises a solar cell array module functional unit and / or a SAR load antenna module functional unit.

[0013] Preferably, a plurality of "drawer type" honeycomb plate single machine cabins are installed inside the integrated full truss structure, the honeycomb plate single machine cabin is used for installing single machines in the cabin, and each honeycomb plate single machine cabin as a whole serves as a module and can be moved and disassembled inside the integrated full truss structure.

[0014] Preferably, the modular functional unit and the honeycomb plate single machine cabin are integrated according to the functions of each subsystem on the satellite and the layout positions of the single machines, and the single machine regions are modularized. The propulsion functional module, the control functional module, the load functional module, the solar cell array energy functional module and the relay data transmission functional module can be provided, and the modules are quickly integrated and assembled on the truss structure or the honeycomb plate single machine cabin inside through standardized interfaces.

[0015] Preferably, the SAR load antenna module is a planar phased array antenna, and the solar cell array module selects a rigid substrate solar cell array. The solar cell array module functional unit and the SAR load antenna module functional unit are respectively rigidly fastened and connected to the outer surface of the integrated full truss structure.

[0016] Preferably, the integrated full truss structure is a cuboid frame composed of standardized truss rods and embedded joint, the truss rod is made of lightweight carbon fiber material, the embedded joint is made of aluminum alloy, and the truss rod and the aluminum alloy embedded joint are connected to form a firm full truss bearing structure.

[0017] Preferably, a standardized mounting interface is provided on the integrated full truss structure rod, which can adapt to the installation and fixation of different platform spectrum single machines or be used for the installation of external antennas and single machines.

[0018] Preferably, the integrated full truss structure is provided with a satellite-rocket docking interface and a lifting point interface joint, the satellite-rocket docking interface is arranged at the lower end of the integrated full truss structure and can be connected to the support cabin of a carrier rocket, and the lifting point interface joint is arranged at the top of the integrated full truss structure and can be connected to a lifting tool.

[0019] Preferably, the open CAN bus system is adopted between the modular functional units, the standardized SpaceVPX protocol is supported, and the modular functional units are provided with a redundant design, so that the data and energy between the modular functional units can be quickly identified and interacted.

[0020] Preferably, the satellite propulsion functional module unit generally adopts an electric propulsion system, the propellant is pre-filled and pre-packaged, and is installed as a relatively independent structural module.

[0021] Compared with the prior art, the present application has the following beneficial effects:

[0022] 1. The present application provides a SAR satellite full truss open and modular architecture, which is designed for the urgent needs of small satellite rapid batch production, lightweight structure, high bearing ratio and open operation space, and a new type of architecture design of SAR satellite is created through the innovative design of integrated full carbon fiber structure configuration of load and platform and modular design of each single machine functional unit module, and a new way suitable for rapid batch production of small satellites is explored.

[0023] 2. The present application provides a SAR satellite full truss open and modular architecture, the integrated full truss structure is designed as a cuboid with an empty shell in the middle, a I-shaped combination plate is designed, which can be fitted into the inside of the integrated full truss structure, the single machine is installed in the open state of the I-shaped combination plate, and then the I-shaped combination plate is fitted into the integrated full truss structure, the antenna and the solar wing are directly installed to the outside of the truss structure, and no structural side plate is installed outside the truss, which has the obvious advantages of the lightest weight under the same volume and the smallest envelope occupied.

[0024] 3. The application provides a SAR satellite full-truss open and modular architecture. After the single machine is installed on the I-shaped combined plate and is sleeved into the integrated full-truss structure, the openness is sufficient at any time, the operation of the single machine is greatly facilitated, and the risk of frequent opening of side plates for disassembly and assembly of the single machine is avoided. The I-shaped combined plate and the integrated full-truss structure are respectively modularly produced, and are conveniently assembled in the later period. After combination, the openness is good, the external space envelope required by the overall structure is also the smallest, and it is the preferred solution for small satellite configurations with high requirements for weight, envelope, and operation space convenience. BRIEF DESCRIPTION OF DRAWINGS

[0025] Other features, objects and advantages of the application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0026] Figure 1 It is a schematic diagram of the SAR satellite modular functional unit architecture of the application.

[0027] Figure 2 It is a schematic diagram of the SAR satellite full-truss open and modular architecture of the application. DETAILED DESCRIPTION

[0028] The application will be described in detail below with reference to specific embodiments. The following embodiments will help those skilled in the art to further understand the application, but do not limit the application in any form. It should be pointed out that those skilled in the art can make several changes and improvements without departing from the concept of the application. These all belong to the protection scope of the application.

[0029] At present, a certain type of SAR satellite configured with a high-resolution planar phased array radar antenna is the first batch of small satellites developed in China, and the load weight directly accounts for more than 60% of the total satellite weight; the satellite also requires batch rapid development and launch, and needs to meet the launch weight and envelope constraints of the carrier rocket, which puts forward high requirements for the lightweight, operation openness and modular rapid integration of the satellite, and the traditional satellite development method has been difficult to solve.

[0030] In view of the above new requirements of the satellite, the application provides a SAR satellite full-truss open and modular architecture, and the innovative design of the open full-truss structure and the modular architecture solves the above problems. The specific application of the application to the above certain type of SAR satellite will be described below.

[0031] As Figure 2As shown, the SAR satellite full truss open and modular architecture provided by the application mainly comprises: an integrated full truss structure, a modular functional unit and a honeycomb plate single machine cabin; the integrated full truss structure is a cuboid frame, and the outside is open and without structural side plates; the modular functional unit is fastened to the outside of the integrated full truss structure, and the modular functional unit as a whole encloses a hexahedral configuration; the honeycomb plate single machine cabin is flexibly installed inside the integrated full truss structure.

[0032] Under the constraints of the carrying envelope and the launch weight, the integrated full truss structure is a cuboid frame mainly composed of standardized lightweight carbon fiber material rods and aluminum alloy embedded joint pieces in the inside, serving as the main load-bearing structure of the SAR satellite. The rods are standard cuboid thin-walled hollow structures, which can be transverse rods or longitudinal rods, and are combined by aluminum alloy embedded joint pieces to form a firm full truss load-bearing structure. The integrated full truss structure has no external side plates, and is completely open to the outside. The truss structure inside can install a "drawer type" honeycomb plate single machine cabin, which can be flexibly disassembled from the integrated full truss structure, facilitating the overall integration and assembly and daily testing of the in-orbit single machine. The load and platform integrated full truss structure greatly improves the stiffness and carrying capacity of the satellite, and realizes that the structure weight accounts for no more than 10% of the total satellite weight.

[0033] The integrated full truss structure installs aluminum alloy material joints at four joint positions of the bottom lower end face, and the four joints can be combined into a satellite-rocket docking interface connected with the point separation mechanism of the carrier and fixed on the support cabin of the carrier rocket. Meanwhile, aluminum alloy material embedded joint pieces are installed at four joint positions of the top upper end face of the truss, and the four joints are combined into a satellite lifting interface connected with a lifting tool to realize the lifting and transfer of the satellite.

[0034] The carbon fiber material rods of the integrated full truss structure can provide standardized installation interfaces, including commonly used threaded holes (such as M3, M4, M5, M6, etc.) and pin holes (such as Φ6, Φ8, etc.) combinations, which can adapt to the installation and fixation of different platform spectrum single machines, and can also increase the adapter combination to provide installation interfaces for external satellite antennas and single machines on the integrated full truss structure.

[0035] As shown, Figure 1As shown, in order to meet the batch parallel development of SAR satellite, according to the functions of each subsystem, a plurality of functional modules can be combined, for example, the planar phased array SAR antenna load is independently formed into a functional module, is folded and fixed and unfolded and spliced through a light standard spectrum unfolding mechanism, and is used for realizing the main load function of the satellite in orbit; the solar cell array adopts a rigid substrate and is also independently formed into a functional module, is folded and unfolded through a light standard spectrum unfolding release device, and is used for providing the energy required by the satellite in orbit; the propulsion functional module unit generally adopts an electric propulsion system, the propellant is pre-filled and pre-packaged, is used as an independent functional module, and is used for providing orbit maintenance in orbit; each functional module can be developed and integrated in parallel, and is quickly integrated on the integrated full truss structure through standardized structure and switching.

[0036] The application designs an independent open honeycomb plate single machine cabin, after the single machine is fixed on the single machine cabin, the single machine cabin as a whole is taken as a structural module functional unit, can be moved and disassembled flexibly in the integrated full truss structure like a drawer, the open single machine cabin in the open integrated full truss structure, the single machine on the single machine cabin has great convenience from external development operation. The integrated full truss structure and the single machine cabin can be developed and manufactured independently in parallel, and the demand of batch rapid development is greatly improved.

[0037] Each modular functional unit adopts an open CAN bus system, supports a standardized Space VPX protocol, and has a certain redundancy design, so that the data and energy of the modular functional units can be quickly connected, identified and information exchanged.

[0038] The satellite is matched with data transmission communication functional modules of different manufacturers, through the addition of a matching standard switching interface, the products of different manufacturers can be quickly installed on the integrated full truss structure, and the rapid batch development capability of the SAR satellite is improved.

[0039] Meanwhile, the modular electric propulsion system functional unit of the SAR satellite is pre-filled with propellant, realizes the modular delivery of the propulsion unit, has no redundant operation after being installed on the satellite, and does not need to be additionally filled at the launch site, improves the parallel development rhythm of the whole satellite, and greatly improves the large-scale development capability.

[0040] The application innovatively proposes a full truss open type and modular architecture, the satellite is based on the full truss open structure and functional module, meets the light weight, high rigidity and high bearing capacity of the satellite, and the architecture of parallel development and integration test of each functional module, realizes the great improvement of the rapid batch satellite development capability, and will become the first choice of satellite overall designers, and the application will be widely applied in the field.

[0041] In the description of the present application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the purpose of facilitating the description of the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0042] The specific embodiments of the present application are described above. It should be understood that the present application is not limited to the specific embodiments described above, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which do not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict, provided that they do not conflict.

Claims

1. A fully truss-based open, modular architecture for SAR satellites, characterized in that: include: Integrated full-truss structure, modular functional units, and honeycomb panel single-engine cabin; The integrated full truss structure is a cuboid frame with open, unstructured side panels on the outside. Modular functional units are fastened to the outside of the integrated full truss structure, and the modular functional units are arranged in a hexahedral configuration. The honeycomb panel single-unit cabin consists of multiple independent modules installed inside an integrated full-truss structure.

2. The SAR satellite's fully truss-based open, modular architecture according to claim 1, characterized in that, Modular functional units include solar cell array module functional units and / or SAR payload antenna module functional units.

3. The SAR satellite's fully truss-based open, modular architecture according to claim 1, characterized in that, The integrated full truss structure houses multiple drawer-type honeycomb panel single-unit cabins. These cabins are used to install individual units. Each honeycomb panel single-unit cabin is a module that can be moved and disassembled within the integrated full truss structure.

4. The SAR satellite's fully truss-based open, modular architecture according to claim 1, characterized in that, Modular functional units and cellular panel single-unit cabins integrate and modularize each single-unit area according to the functions of each subsystem on the satellite and its single-unit layout position. They are equipped with propulsion function modules, control function modules, payload function modules, solar cell array energy function modules and relay data transmission function modules, and are quickly integrated and assembled on the truss structure or the internal cellular panel single-unit cabin through standardized interfaces.

5. The SAR satellite's fully truss-based open, modular architecture according to claim 1, characterized in that, The SAR payload antenna module is a planar phased array antenna, and the solar cell array module is a rigid substrate solar cell array. The functional units of the solar cell array module and the SAR payload antenna module are respectively rigidly fastened to the outer surface of the integrated full truss structure.

6. The SAR satellite's fully truss-based open, modular architecture according to claim 1, characterized in that, The integrated full truss structure is a rectangular frame composed of standardized truss members and embedded joints with thin walls and hollow interior. The truss members are made of lightweight carbon fiber material, and the embedded joints are made of aluminum alloy. The truss members and aluminum alloy embedded joints are connected and combined to form a strong full truss load-bearing structure.

7. The SAR satellite's fully truss-based open, modular architecture according to claim 1, characterized in that, The integrated full truss structure provides standardized installation interfaces to accommodate the installation and fixation of single units on different platform types or for the installation of satellite antennas and single units.

8. The SAR satellite's fully truss-based open, modular architecture according to claim 1, characterized in that, The integrated full truss structure is equipped with a satellite-rocket docking interface and a lifting point interface joint. The satellite-rocket docking interface is located at the lower end of the integrated full truss structure and can be connected to the support cabin of the launch vehicle. The lifting point interface joint is located at the top of the integrated full truss structure and can be connected to lifting equipment.

9. The SAR satellite's fully truss-based open, modular architecture according to claim 1, characterized in that, The modular functional units adopt an open CAN bus system, support the standardized Space VPX protocol, and have a redundant design, enabling rapid identification and interaction of data and energy between the modular functional units.

10. The SAR satellite's fully truss-based open, modular architecture according to claim 1, characterized in that, The satellite propulsion module unit adopts an electric propulsion system, with the propellant pre-filled and pre-packaged, and is installed as a relatively independent structural module.

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