Payload modularization method and system for cubic satellite architecture

Abstract

The present invention relates to a load modularization method and system of a cubic satellite architecture, which is mainly assembled by a main structure frame, an antenna installation frame arranged on the top of the main structure frame, a stringer arranged at the bottom of the main structure frame, a biological payload cabin module, a power module and a central control module: the biological payload cabin module is installed on the inner side of the main structure frame through a milled vertical positioning slide; the power module is connected and assembled with the central control module and then screwed with the main structure frame; the biological payload cabin module and the propulsion module are respectively located at the upper and lower ends of the satellite body, and the structure is fixed by a positioning pin constraint; a positioning pin protrusion structure is milled at one end of the top cover of the biological payload cabin module, which is plugged and unplugged with the assembled power module and central control module adapter plate; a positioning pin hole structure is included at one end of the bottom surface of the biological payload cabin module shell, which is plugged and unplugged with the positioning pins on the stringer and the antenna installation frame. It has the advantages of high reliability, simple interior cabin, and easy assembly and maintenance.

Description

Technical Field

[0001] The present invention relates to a cubic satellite architecture modularization method, and in particular to a cubic satellite architecture payload modularization method and system. Background Art

[0002] In recent years, with the increasing demand of industry and commercial users for rapid, flexible and personalized application of satellite technology, commercial small satellites have developed rapidly, and various domestic commercial satellite companies have appeared one after another. Commercial small satellites are small in size, low in cost and short in development cycle, and are particularly suitable for space exploration missions such as scientific experiments.

[0003] The structural design and layout of the satellite directly affect the overall performance of the satellite and the convenience of assembly, maintenance and other operations. Traditional barrel-type and plate-type satellites have their own limitations. There are many components in the satellite, the wiring is complicated, the space utilization rate is not high, and the assembly operation is not very convenient. As one of the more mature satellite structures, the truss-type cubic satellite is composed of multiple main frame beams and side beams, and has broad market application prospects. However, in actual use, due to the complex layout of the satellite, system modules such as the biological payload cabin are not convenient to disassemble, repair and replace, which directly affects the user's usability of the product, while increasing the workload of assembly and debugging personnel and reducing production and manufacturing efficiency. Summary of the invention

[0004] The purpose of the present invention is to overcome the above-mentioned defects of the prior art and to provide a payload modularization method for a cubic satellite architecture with high reliability, less cable routing, a simple interior cabin, and easy assembly and maintenance. The present invention also provides a system for implementing the method of the present invention.

[0005] To achieve the above-mentioned purpose, the payload modularization method of the cubic satellite architecture of the present invention is particularly characterized in that it is mainly modularly assembled by a main structure frame 1, an antenna installation frame 3, a beam 7 arranged at the bottom of the main structure frame 1, a first biological payload cabin module 2, a second biological payload cabin module 4, a third biological payload cabin module 6, a power module 5 and a central control module 8: the main structure frame 1 is a cubic main structure frame beam main structure frame 1, an antenna installation frame 3 is arranged on the top of the main structure frame 1, and the biological payload cabin modules (2, 4, 6) are installed on the inner side of the main structure frame 1 through a milled vertical positioning slide; the power module 5 and the central control module 8 are connected to each other. The control module 8 is connected and assembled as one, and then screwed with the main structure frame 1, and is located in the middle section of the satellite; the first biological payload cabin module 2, the second biological payload cabin module 4, the third biological payload cabin module 6, and the propulsion module 11 are respectively located at the upper and lower ends of the satellite, and are fixed by positioning pins in the structure, and assembled in a way that the modules can be quickly disassembled, replaced, and repaired on site; a positioning pin protrusion structure is milled on one end of the top cover of the biological payload cabin module, and is plugged and unplugged with the assembled power module 5 and the central control module 8 adapter plate; a positioning pin hole structure is included on one end of the bottom surface of the biological payload cabin module shell, and is plugged and unplugged with the positioning pins on the beam 7 and the antenna installation frame 3. It has the advantages of high reliability, less cable routing, simple interior cabin, and easy assembly and maintenance.

[0006] As an optimization, the power module 5 is used for attitude adjustment and providing the required power for the satellite; the central control module 8 provides system control services for the satellite; the first biological payload cabin module 2, the second biological payload cabin module 4 and the third biological payload cabin module 6 are connected to the power module 5 and the central control module 8 by connectors; the first biological payload cabin module 2 and the second biological payload cabin module 4 are fixedly constrained to the antenna mounting frame 3 by locating pins; the third biological payload cabin module 6 is fixedly constrained to the beam 7 by locating pins; the beam 7 is arranged below the third biological payload cabin module 6 at the bottom of the main structure frame 1.

[0007] As an optimization, the first biological payload cabin module 2, the second biological payload cabin module 4 and the third biological payload cabin module 6 are used to carry biological organisms for space experiments; the top cover of the biological payload cabin module contains a positioning pin protrusion structure, the bottom surface of the shell of the biological payload cabin module contains a positioning pin hole structure, and the bottom surface of the antenna mounting frame 3 contains a positioning pin protrusion structure that is plugged into the positioning pin hole structure; the beam 7 is connected to the third biological payload cabin module 6 by positioning pins; there is no screw pin-type positioning connection between the biological payload cabin module and the satellite structure, so it can be quickly disassembled and replaced on site without dismantling the satellite.

[0008] As an optimization, the two ends of the side where the beam 7 is connected to the third biological load chamber module 6 are respectively provided with positioning pin bosses, and the two sides of the bottom surface of the third biological load chamber module 6 are provided with positioning pin holes that are plugged into the positioning pin bosses. The beam 7 is connected to the bottom of the third biological load chamber module 6 at the bottom of the main structural frame 1 by standard fasteners.

[0009] As an optimization, the main structure frame beam 1 is formed by screwing a hollow main frame panel in the middle of the main beams on both sides; the front and rear main beams of the main structure frame beam 1 are connected to form a cubic main structure frame beam through an upper side beam, two upper side beams spaced apart and arranged in parallel, two lower side beams spaced apart and arranged in parallel, and a lower side beam; the antenna installation frame 3 is composed of three left and right horizontal antenna installation frames, and is arranged on the left and right sides of the top of the cubic main structure frame beam in a manner that can be quickly disassembled, replaced and repaired on site; the first biological payload cabin module 2, the second biological payload cabin module 4 and the left and right horizontal antenna installation frame 3 The antenna installation frame 3 is fixed and constrained in the upper and lower parts; the central control module 8 and the power module 5 are arranged in the middle of the main structure frame beam of the cube in a way that they can be quickly disassembled, replaced and repaired on site, and are screwed with the horizontal connecting strip of the hollow main frame panel part screwed in the middle of the main structure frame beam 1 after being assembled into one by a connector; the propulsion module 11 and the third biological payload chamber module 6 are arranged in the lower part of the main structure frame beam of the cube in a way that they can be quickly disassembled, replaced and repaired on site, and are constrained and fixed with the beam 7 fixed in the middle of the bottom of the front and rear middle screwed hollow main frame panels by a positioning pin. The central control module 8 and the power module 5 are assembled and connected into one by a connector and a top plate, and are screwed with the horizontal connecting strip of the front and rear middle screwed hollow main frame panels; the top cover of the first biological payload chamber module 2 and the second biological payload chamber module 4 contains a positioning pin protrusion structure, and the bottom surface of the shell contains a positioning pin hole structure and is positioned and installed with the horizontal connecting strip of the front and rear middle screwed hollow main frame panels. The front and rear middle screwed hollow main frame panels are respectively provided with front and rear solar panels 60 electrically connected to the power module 5, and the left and right foldable antennas and foldable solar sail panels 61 are respectively provided on the left and right sides of the cube main structure frame beam.

[0010] The system for implementing the method of the present invention comprises a main structure frame 1, an antenna installation frame 3, a beam 7 arranged at the bottom of the main structure frame 1, a first biological payload chamber module 2, a second biological payload chamber module 4, a third biological payload chamber module 6, a power module 5, a central control module 8 and a propulsion module 11: the main structure frame 1 is a cubic main structure frame beam main structure frame 1, the antenna installation frame 3 is arranged on the top of the main structure frame 1, and a vertical positioning slideway for installing the biological payload chamber modules (2, 4, 6) is milled on the inner side of the main structure frame 1; the power module 5 is connected and assembled with the central control module 8; After integration, it is screwed to the main structure frame 1 and is located in the middle section of the satellite; the first biological payload cabin module 2, the second biological payload cabin module 4, the third biological payload cabin module 6 and the propulsion module 11 are respectively located at the upper and lower ends of the satellite, and are structurally fixed with locating pins, and assembled by rapid disassembly, replacement and maintenance of the modules on site; a locating pin protrusion structure is milled on one end of the top cover of the biological payload cabin module, which is plugged and unplugged with the assembled power module 5 and the central control module 8 adapter plate; a locating pin hole structure is included on one end of the bottom surface of the biological payload cabin module shell, which is plugged and unplugged with the locating pins on the beam 7 and the antenna mounting frame 3.

[0011] As an optimization, the power module 5 is used for attitude adjustment and providing the required power for the satellite; the central control module 8 provides system control services for the satellite; the first biological payload cabin module 2, the second biological payload cabin module 4 and the third biological payload cabin module 6 are connected to the power module 5 and the central control module 8 by connectors; the first biological payload cabin module 2 and the second biological payload cabin module 4 are fixedly constrained to the antenna mounting frame 3 by locating pins; the third biological payload cabin module 6 is fixedly constrained to the beam 7 by locating pins; the beam 7 is arranged below the third biological payload cabin module 6 at the bottom of the main structure frame 1.

[0012] As an optimization, the first biological payload cabin module 2, the second biological payload cabin module 4 and the third biological payload cabin module 6 are used to carry biological organisms for space experiments; the top cover of the biological payload cabin module contains a positioning pin protrusion structure, the bottom surface of the shell of the biological payload cabin module contains a positioning pin hole structure, and the bottom surface of the antenna mounting frame 3 contains a positioning pin protrusion structure that is plugged into the positioning pin hole structure; the beam 7 is connected to the third biological payload cabin module 6 by positioning pins; there is no screw pin-type positioning connection between the biological payload cabin module and the satellite structure, so it can be quickly disassembled and replaced on site without dismantling the satellite.

[0013] As an optimization, the two ends of the side where the beam 7 is connected to the third biological load chamber module 6 are respectively provided with positioning pin bosses, and the two sides of the bottom surface of the third biological load chamber module 6 are provided with positioning pin holes that are plugged into the positioning pin bosses. The beam 7 is connected to the bottom of the third biological load chamber module 6 at the bottom of the main structural frame 1 by standard fasteners.

[0014] As an optimization, the front main frame beam frame 1 is formed by screwing a hollow main frame panel in the middle of the main beams on both sides, and the front and rear main beams are fixedly connected to form a main structure frame 1 through an upper side beam, two upper side beams spaced apart and arranged in parallel, two lower side beams spaced apart and arranged in parallel, and a lower side beam; the antenna installation frame 3 is composed of three left and right horizontal antenna installation frames, and is arranged on the left and right sides of the top of the cubic main structure frame beam in a manner that can be quickly disassembled, replaced and repaired on site; the first biological payload cabin module 2, the second biological payload cabin module 4 and the antenna installation frame 3 are arranged on the left and right horizontal antenna installation frames. The three parts of the mounting frame are fixed and constrained in the upper and lower parts; the central control module 8 and the power module 5 are arranged in the middle of the main structure frame beam of the cube in a way that they can be quickly disassembled, replaced and repaired on site, and are screwed to the cross-connecting strip of the hollow main frame panel part screwed in the middle of the main structure frame beam 1 after being assembled as a whole through the connector; the propulsion module 11 and the third biological payload chamber module 6 are arranged in the lower part of the main structure frame beam of the cube in a way that they can be quickly disassembled, replaced and repaired on site, and are constrained and fixed to the beam 7 fixed to the middle of the bottom of the front and rear middle screwed hollow main frame panel with a positioning pin. The central control module 8 and the power module 5 are assembled and connected as a whole through the connector and the top plate, and are screwed to the cross-connecting strip of the front and rear middle screwed hollow main frame panel; the top cover of the first biological payload chamber module 2 and the second biological payload chamber module 4 contains a positioning pin protrusion structure, and the bottom surface of the shell contains a positioning pin hole structure and is positioned and installed with the cross-connecting strip of the front and rear middle screwed hollow main frame panel. The front and rear middle screwed hollow main frame panels are respectively provided with front and rear solar panels 60 electrically connected to the power module 5, and the left and right foldable antennas and foldable solar sail panels 61 are respectively provided on the left and right sides of the cube main structure frame beam.

[0015] The purpose of the present invention is achieved through the following technical solutions: the framework consists of a main structure frame, an antenna installation frame, three biological payload cabin modules, a power module and a central control module. The power module and the central control module are connected and assembled as one, and then fixedly connected to the main structure frame by screws, and are located in the middle section of the star body; a positioning pin protrusion structure is milled on one end of the top cover of the biological payload cabin module, and is plugged and unplugged with the assembled power module and central control module adapter plate; a positioning pin hole structure is included on one end of the bottom surface of the biological payload cabin module shell, and is plugged and unplugged with the positioning pins on the beam and the antenna installation frame.

[0016] The main structure frame is a truss beam type composite structure, which is fixed together by bolts as the main load-bearing frame of the entire star body; the inner panel of the main structure frame is designed with a slideway to facilitate the accurate positioning and installation of the biological payload cabin module. The biological payload cabin module, its shell and top cover are machined, and a positioning pin hole is milled at one end of the bottom surface of the shell; a positioning pin protrusion structure is milled at one end of the top cover, and it contains a connector connected to the power module and the central control module; the top cover and the shell are sealed with an O-seal strip and fixed together by screws.

[0017] The stringer is an independent structural part, located at the lower end of the satellite body, and is screwed to the main structural frame; a positioning pin protrusion structure is milled on one side of the stringer, which is plugged and unplugged into the pin hole on the bottom surface of the biological payload module shell. The antenna installation frame is a machined structural part, used to install the signal transceiver antenna, and is screwed to the main structural frame; a positioning pin protrusion structure is milled on the bottom surface of the frame, which is assembled with the positioning pin hole on the bottom surface of the payload shell, and at the same time plays a role in fixing and supporting the entire satellite. The electrical connection performance of the connectors and other electrical components meets the requirements of space applications.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] (1) The present invention provides a cubic satellite architecture with modular payloads. The biological payload cabin module is located at the upper and lower ends of the satellite structure and is connected to other modules through connectors. There is no screw connection between the biological cabin and the satellite structure. The biological cabin payload module can be quickly disassembled, repaired and replaced on site to meet the user's various immediate mission needs.

[0020] (2) The present invention provides a payload modularized cubic satellite architecture, the design of which fully considers the installation space and operational flexibility of small satellites. The main load-bearing support is a frame beam structure, which is stable and reliable, has strong overall impact and seismic resistance, simple processing technology, and convenient assembly and maintenance operations, which can greatly improve the production and manufacturing efficiency of cubic satellites.

[0021] After adopting the above technical scheme, the payload modularization method and system of the cubic satellite architecture of the present invention is composed of a main structure frame, an antenna installation frame, three biological payload cabin modules, a power module and a central control module; the power module and the central control module are connected and assembled as one, and then screwed with the main structure frame, and located in the middle of the satellite; the biological payload cabin module is located at the upper and lower ends of the satellite, and is connected to the power module and the central control module through connectors, and is constrained and fixed by locating pins in the structure. The cubic satellite architecture of the present invention adopts a truss beam configuration, a modular layout, high structural strength, and strong overall impact and seismic resistance. The biological payload cabin module can be quickly disassembled and replaced on site, which can meet the user's various immediate needs. It is an architecture form with strong market application value in commercial small satellites. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] Figure 1 It is a three-dimensional structural diagram of the payload modularization method and system of the cubic satellite architecture of the present invention; Figure 2 It is a side view structural diagram of the payload modularization method and system of the cubic satellite architecture of the present invention; Figure 3 It is a schematic diagram of the biological payload cabin module structure of the payload modularization method and system of the cubic satellite architecture of the present invention. Figure 4It is a schematic diagram of the assembly structure of the power module and the central control module of the payload modularization method and system of the cubic satellite architecture of the present invention. Figure 5 It is a schematic diagram of the antenna installation structure of the payload modularization method and system of the cubic satellite architecture of the present invention; Figure 6 It is a schematic diagram of the three-dimensional structure of the beams of the load modularization method and system of the cubic satellite architecture of the present invention. DETAILED DESCRIPTION

[0023] As shown in the figure, the payload modularization method of the cubic satellite architecture of the present invention is mainly modularly assembled by a main structure frame 1, an antenna installation frame 3, a beam 7 arranged at the bottom of the main structure frame 1, a first biological payload cabin module 2, a second biological payload cabin module 4, a third biological payload cabin module 6, a power module 5 and a central control module 8: the main structure frame 1 is a cubic main structure frame beam main structure frame 1, an antenna installation frame 3 is arranged on the top of the main structure frame 1, and the biological payload cabin modules (2, 4, 6) are installed on the inner side of the main structure frame 1 through a milled vertical positioning slide; the power module 5 and the central control module 8 is connected and assembled as one, and then screwed with the main structure frame 1, and is located in the middle section of the satellite; the first biological payload cabin module 2, the second biological payload cabin module 4, the third biological payload cabin module 6 and the propulsion module 11 are respectively located at the upper and lower ends of the satellite, and are fixed by positioning pins in the structure, and are assembled in a way that the modules can be quickly disassembled, replaced and repaired on site; a positioning pin protrusion structure is milled on one end of the top cover of the biological payload cabin module, and is plugged and unplugged with the assembled power module 5 and the central control module 8 adapter plate; a positioning pin hole structure is included on one end of the bottom surface of the biological payload cabin module shell, and is plugged and unplugged with the positioning pins on the beam 7 and the antenna installation frame 3. It has the advantages of high reliability, less cable routing, simple interior cabin, and easy assembly and maintenance.

[0024] The power module 5 is used for attitude adjustment and providing the required power for the satellite; the central control module 8 provides system control services for the satellite; the first biological payload cabin module 2, the second biological payload cabin module 4 and the third biological payload cabin module 6 are connected to the power module 5 and the central control module 8 by connectors; the first biological payload cabin module 2 and the second biological payload cabin module 4 are fixedly restrained by positioning pins on the antenna mounting frame 3; the third biological payload cabin module 6 is fixedly restrained by positioning pins on the beam 7; the beam 7 is arranged below the third biological payload cabin module 6 at the bottom of the main structure frame 1.

[0025] The first biological payload cabin module 2, the second biological payload cabin module 4 and the third biological payload cabin module 6 are used to carry biological organisms for space experiments; the top cover of the biological payload cabin module contains a positioning pin protrusion structure, the bottom surface of the shell of the biological payload cabin module contains a positioning pin hole structure, and the bottom surface of the antenna installation frame 3 contains a positioning pin protrusion structure that is plugged into the positioning pin hole structure; the stringer 7 is connected to the third biological payload cabin module 6 by a positioning pin; there is no screw pin type positioning connection between the biological payload cabin module and the satellite structure, and it can be quickly disassembled and replaced on site without dismantling the satellite. The two ends of the side where the stringer 7 is connected to the third biological payload cabin module 6 are respectively formed with positioning pin protrusions, and the two sides of the bottom surface of the third biological payload cabin module 6 are formed with positioning pin holes that are plugged into the positioning pin protrusions. The stringer 7 is connected to the bottom of the main structure frame 1 below the third biological payload cabin module 6 through standard fasteners.

[0026] The main structure frame beam 1 is formed by screwing a hollow main frame panel in the middle of the main beams on both sides. The front and rear main beams of the main structure frame beam 1 are connected to form a cubic main structure frame beam through an upper side beam, two upper side beams spaced apart and arranged in parallel, two lower side beams spaced apart and arranged in parallel, and a lower side beam. The antenna installation frame 3 is composed of three left and right horizontal antenna installation frames, and is arranged on the left and right sides of the top of the cubic main structure frame beam in a manner that can be quickly disassembled, replaced and repaired on site. The first biological payload cabin module 2, the second biological payload cabin module 4 and the left and right horizontal antenna installation frames 3 are connected to the antenna installation frame 3. The three parts of the wire installation frame are fixed and constrained in the upper and lower parts; the central control module 8 and the power module 5 are arranged in the middle of the main structure frame beam of the cube in a way that they can be quickly disassembled, replaced and repaired on site, and are screwed with the horizontal connecting strip of the hollow main frame panel part screwed in the middle of the main structure frame beam 1 after being assembled as a whole through the connector; the propulsion module 11 and the third biological payload chamber module 6 are arranged in the lower part of the main structure frame beam of the cube in a way that they can be quickly disassembled, replaced and repaired on site, and are constrained and fixed with the truss 7 fixed in the middle of the bottom of the front and rear middle screwed hollow main frame panels by the positioning pin. The central control module 8 and the power module 5 are assembled and connected as a whole through the connector and the top plate, and are screwed with the horizontal connecting strip of the front and rear middle screwed hollow main frame panels; the top cover of the first biological payload chamber module 2 and the second biological payload chamber module 4 contains a positioning pin protrusion structure, and the bottom surface of the shell contains a positioning pin hole structure and is positioned and installed with the horizontal connecting strip of the front and rear middle screwed hollow main frame panels. The front and rear middle screwed hollow main frame panels are respectively provided with front and rear solar panels 60 electrically connected to the power module 5, and the left and right foldable antennas and foldable solar sail panels 61 are respectively provided on the left and right sides of the cube main structure frame beam.

[0027] The system for implementing the method of the present invention comprises a main structure frame 1, an antenna installation frame 3, a beam 7 arranged at the bottom of the main structure frame 1, a first biological payload chamber module 2, a second biological payload chamber module 4, a third biological payload chamber module 6, a power module 5, a central control module 8 and a propulsion module 11: the main structure frame 1 is a cubic main structure frame beam main structure frame 1, the antenna installation frame 3 is arranged on the top of the main structure frame 1, and a vertical positioning slideway for installing the biological payload chamber modules (2, 4, 6) is milled on the inner side of the main structure frame 1; the power module 5 is connected and assembled with the central control module 8; After integration, it is screwed to the main structure frame 1 and is located in the middle section of the satellite; the first biological payload cabin module 2, the second biological payload cabin module 4, the third biological payload cabin module 6 and the propulsion module 11 are respectively located at the upper and lower ends of the satellite, and are structurally fixed with locating pins, and assembled by rapid disassembly, replacement and maintenance of the modules on site; a locating pin protrusion structure is milled on one end of the top cover of the biological payload cabin module, which is plugged and unplugged with the assembled power module 5 and the central control module 8 adapter plate; a locating pin hole structure is included on one end of the bottom surface of the biological payload cabin module shell, which is plugged and unplugged with the locating pins on the beam 7 and the antenna mounting frame 3.

[0028] The power module 5 is used for attitude adjustment and providing the required power for the satellite; the central control module 8 provides system control services for the satellite; the first biological payload cabin module 2, the second biological payload cabin module 4 and the third biological payload cabin module 6 are connected to the power module 5 and the central control module 8 by connectors; the first biological payload cabin module 2 and the second biological payload cabin module 4 are fixedly restrained by positioning pins on the antenna mounting frame 3; the third biological payload cabin module 6 is fixedly restrained by positioning pins on the beam 7; the beam 7 is arranged below the third biological payload cabin module 6 at the bottom of the main structure frame 1.

[0029] The first biological payload cabin module 2, the second biological payload cabin module 4 and the third biological payload cabin module 6 are used to carry biological organisms for space experiments; the top cover of the biological payload cabin module contains a positioning pin protrusion structure, the bottom surface of the shell of the biological payload cabin module contains a positioning pin hole structure, and the bottom surface of the antenna installation frame 3 contains a positioning pin protrusion structure that is plugged into the positioning pin hole structure; the stringer 7 is connected to the third biological payload cabin module 6 by a positioning pin; there is no screw pin type positioning connection between the biological payload cabin module and the satellite structure, and it can be quickly disassembled and replaced on site without dismantling the satellite. The two ends of the side where the stringer 7 is connected to the third biological payload cabin module 6 are respectively formed with positioning pin protrusions, and the two sides of the bottom surface of the third biological payload cabin module 6 are formed with positioning pin holes that are plugged into the positioning pin protrusions. The stringer 7 is connected to the bottom of the main structure frame 1 below the third biological payload cabin module 6 through standard fasteners.

[0030] The front main frame beam frame 1 is formed by screwing a hollow main frame panel in the middle of the main beams on both sides, and the front and rear main beams are connected to form a main structure frame 1 through an upper side beam, two upper side beams spaced apart and parallel to each other, two lower side beams spaced apart and parallel to each other, and a lower side beam; the antenna installation frame 3 is composed of three left and right horizontal antenna installation frames, and is arranged on the left and right sides of the top of the cubic main structure frame beam in a manner that can be quickly disassembled, replaced and repaired on site; the first biological payload cabin module 2, the second biological payload cabin module 4 and the antenna installation frame 3 are left and right horizontal antenna installation frames The three parts are fixed and constrained in the upper and lower adjacent positions; the central control module 8 and the power module 5 are arranged in the middle of the main structure frame beam of the cube in a way that they can be quickly disassembled, replaced and repaired on site, and are screwed to the cross-connecting strip of the hollow main frame panel part screwed in the middle of the main structure frame beam 1 after being assembled into one by a connector; the propulsion module 11 and the third biological payload chamber module 6 are arranged in the lower part of the main structure frame beam of the cube in a way that they can be quickly disassembled, replaced and repaired on site, and are constrained and fixed to the beam 7 fixed to the middle of the bottom of the front and rear middle screwed hollow main frame panel by a positioning pin. The central control module 8 and the power module 5 are assembled into one by a connector and a top plate, and are screwed to the cross-connecting strip of the front and rear middle screwed hollow main frame panel; the top cover of the first biological payload chamber module 2 and the second biological payload chamber module 4 contains a positioning pin protrusion structure, and the bottom surface of the shell contains a positioning pin hole structure and is positioned and installed with the cross-connecting strip of the front and rear middle screwed hollow main frame panel. The front and rear middle screwed hollow main frame panels are respectively provided with front and rear solar panels 60 electrically connected to the power module 5, and the left and right foldable antennas and foldable solar sail panels 61 are respectively provided on the left and right sides of the cube main structure frame beam.

[0031] In order to make the purpose, technical solution and advantages of the present invention clearer, the embodiments of the present invention will be further described in detail below in conjunction with the accompanying drawings. The architecture consists of a main structure frame, an antenna installation frame, three biological payload cabin modules, a power module and a central control module. The power module is connected and assembled with the central control module as a whole and fixedly connected to the main structure frame by screws, and is located in the middle section of the star body; a positioning pin protrusion structure is milled on one end of the top cover of the biological payload cabin module, which is plugged and unplugged with the assembled power module and central control module adapter plate; a positioning pin hole structure is included at one end of the bottom surface of the biological payload cabin module shell, which is plugged and unplugged with the positioning pins on the beam and the antenna installation frame.

[0032] The main structure frame is a truss beam type composite structure, which is fixed together by bolts as the main load-bearing frame of the entire star body; the inner panel of the main structure frame is designed with a slideway to facilitate the accurate positioning and installation of the biological payload cabin module. The biological payload cabin module, its shell and top cover are machined, and a positioning pin hole is milled at one end of the bottom surface of the shell; a positioning pin protrusion structure is milled at one end of the top cover, and it contains a connector connected to the power module and the central control module; the top cover and the shell are sealed with an O-seal strip and fixed together by screws.

[0033] The stringer is an independent structural part, located at the lower end of the satellite body, and is screwed to the main structural frame; a positioning pin protrusion structure is milled on one side of the stringer, which is plugged and unplugged into the pin hole on the bottom surface of the biological payload module shell. The antenna installation frame is a machined structural part, used to install the signal transceiver antenna, and is screwed to the main structural frame; a positioning pin protrusion structure is milled on the bottom surface of the frame, which is assembled with the positioning pin hole on the bottom surface of the payload shell, and at the same time plays a role in fixing and supporting the entire satellite. The electrical connection performance of the connectors and other electrical components meets the requirements of space applications.

[0034] In summary, the present invention discloses a payload modularization method and system of a cubic satellite architecture, which is composed of a main structure frame, an antenna installation frame, three biological payload cabin modules, a power module and a central control module; the power module and the central control module are connected and assembled as one, and then screwed with the main structure frame, and are located in the middle of the satellite; the biological payload cabin module is located at the upper and lower ends of the satellite, and is connected to the power module and the central control module through connectors, and is constrained and fixed by locating pins in the structure. The cubic satellite architecture of the present invention adopts a truss beam configuration, a modular layout, high structural strength, and strong overall impact and seismic resistance. The biological payload cabin module can be quickly disassembled and replaced on site, which can meet the user's various immediate needs. It is an architecture form with strong market application value in commercial small satellites.

Claims

1. A payload modularization method for a cubic satellite architecture, characterized in that It is mainly assembled modularly by a main structure frame, an antenna installation frame arranged on the top of the main structure frame, a stringer arranged at the bottom of the main structure frame, the first, second and third biological payload cabin modules, a power module and a central control module: the main structure frame is a cubic main structure frame beam main structure frame, and the biological payload cabin module is installed on the inner side of the main structure frame through a milled vertical positioning slide; the power module and the central control module are connected and assembled as a whole and then screwed to the main structure frame, and are located in the middle section of the star body; the first, second and third biological payload cabin modules and the propulsion module are respectively located at the upper and lower ends of the star body, and are fixed and constrained by positioning pins in the structure, and are assembled in a way that the modules can be quickly disassembled, replaced and repaired on site; a positioning pin protrusion structure is milled at one end of the top cover of the biological payload cabin module, which is plugged and unplugged with the assembled power module and central control module adapter plate; a positioning pin hole structure is included at one end of the bottom surface of the biological payload cabin module shell, which is plugged and unplugged with the positioning pins on the stringer and the antenna installation frame; The main structure frame beam is formed by screwing a hollow main frame panel in the middle of the main beams on both sides. The front and rear main beams of the main structure frame beam are connected to form a cubic main structure frame beam through an upper side beam, two upper side beams spaced in parallel, two lower side beams spaced in parallel, and a lower side beam; the antenna installation frame is composed of left and right horizontal antenna installation frame parts, and is arranged on the left and right sides of the top of the cubic main structure frame beam in a way that it can be quickly disassembled, replaced and repaired on site; the left and right horizontal antenna installation frames of the first and second biological payload cabin modules and the antenna installation frame The upper and lower adjacent parts are constrained and fixed; the central control module and the power module are arranged in the middle of the cube main structure frame beam in a way that they can be quickly disassembled, replaced and repaired on site, and are connected and assembled into one body through connectors and then screwed to the cross-connecting strip of the hollow main frame panel part screwed in the middle of the main structure frame beam; the propulsion module and the third biological payload cabin module are arranged in the lower part of the cube main structure frame beam in a way that they can be quickly disassembled, replaced and repaired on site, and are constrained and fixed with positioning pins between the trusses fixedly connected to the middle of the bottom of the front and rear middle screwed hollow main frame panels.

2. The payload modularization method of the cubic satellite architecture according to claim 1, characterized in that The power module is used for attitude adjustment and providing the required power for the satellite; the central control module provides system control services for the satellite; the first, second and third biological payload cabin modules are connected to the power module and the central control module by connectors; the first and second biological payload cabin modules are fixedly restrained to the antenna mounting frame by positioning pins; the third biological payload cabin module is fixedly restrained to the stringer by positioning pins; the stringer is arranged below the third biological payload cabin module at the bottom of the main structure frame.

3. The payload modularization method of the cubic satellite architecture according to claim 2 is characterized in that The first, second and third biological payload cabin modules are used to carry biological organisms for space experiments; the top cover of the biological payload cabin module contains a positioning pin protrusion structure, the bottom surface of the shell of the biological payload cabin module contains a positioning pin hole structure, and the bottom surface of the antenna installation frame contains a positioning pin protrusion structure that is plugged into the positioning pin hole structure; the stringer is connected to the third biological payload cabin module with a positioning pin; there is a screw-free pin-type positioning connection between the biological payload cabin module and the satellite structure, and it can be quickly disassembled and replaced on site without dismantling the satellite.

4. The payload modularization method of the cubic satellite architecture according to claim 3, characterized in that The two ends of the side where the beam is connected to the third biological load chamber module are respectively provided with positioning pin bosses, and the two sides of the bottom surface of the third biological load chamber module are provided with positioning pin holes that are plugged into the positioning pin bosses. The beam is connected to the bottom of the third biological load chamber module at the bottom of the main structure frame by standard fasteners.

5. A system for implementing the payload modularization method of the cubic satellite architecture according to claim 1, characterized in that It is mainly assembled modularly by a main structure frame, an antenna installation frame arranged on the top of the main structure frame, a stringer arranged at the bottom of the main structure frame, the first, second and third biological payload cabin modules, a power module and a central control module: the main structure frame is a cubic main structure frame beam main structure frame, and the biological payload cabin module is installed on the inner side of the main structure frame through a milled vertical positioning slide; the power module and the central control module are connected and assembled as a whole and then screwed to the main structure frame, and are located in the middle section of the star body; the first, second and third biological payload cabin modules and the propulsion module are respectively located at the upper and lower ends of the star body, and are fixed and constrained by positioning pins in the structure, and are assembled in a way that the modules can be quickly disassembled, replaced and repaired on site; a positioning pin protrusion structure is milled at one end of the top cover of the biological payload cabin module, which is plugged and unplugged with the assembled power module and central control module adapter plate; a positioning pin hole structure is included at one end of the bottom surface of the biological payload cabin module shell, which is plugged and unplugged with the positioning pins on the stringer and the antenna installation frame; The front main frame beam frame is formed by screwing a hollow main frame panel in the middle of the main beams on both sides, and the front and rear main beams are connected to form a main structure frame through an upper side beam, two upper side beams spaced apart and parallel to each other, two lower side beams spaced apart and parallel to each other, and a lower side beam; the antenna installation frame is composed of left and right horizontal antenna installation frame parts, and is arranged on the left and right sides of the top of the cube main structure frame beam in a manner that can be quickly disassembled, replaced and repaired on site; the first and second biological payload cabin modules are constrained and fixed adjacently to the left and right horizontal antenna installation frame parts of the antenna installation frame in an upper and lower manner; the central control module and the power module are arranged in the middle of the cube main structure frame beam in a manner that can be quickly disassembled, replaced and repaired on site, and are screwed to the horizontal connecting strip of the hollow main frame panel part screwed in the middle of the main structure frame beam after being assembled into one body through connectors; the propulsion module and the third biological payload cabin module are arranged at the lower part of the cube main structure frame beam in a manner that can be quickly disassembled, replaced and repaired on site, and are constrained and fixed to the trusses fixed to the middle of the bottom of the front and rear middle screwed hollow main frame panels by positioning pins.

6. The system according to claim 5, characterized in that The power module is used for attitude adjustment and providing the required power for the satellite; the central control module provides system control services for the satellite; the first, second and third biological payload cabin modules are connected to the power module and the central control module by connectors; the first and second biological payload cabin modules are fixedly restrained to the antenna mounting frame by positioning pins; the third biological payload cabin module is fixedly restrained to the stringer by positioning pins; the stringer is arranged below the third biological payload cabin module at the bottom of the main structure frame.

7. The system according to claim 6, characterized in that The first, second and third biological payload cabin modules are used to carry biological organisms for space experiments; the top cover of the biological payload cabin module contains a positioning pin protrusion structure, the bottom surface of the shell of the biological payload cabin module contains a positioning pin hole structure, and the bottom surface of the antenna installation frame contains a positioning pin protrusion structure that is plugged into the positioning pin hole structure; the stringer is connected to the third biological payload cabin module with a positioning pin; there is a screw-free pin-type positioning connection between the biological payload cabin module and the satellite structure, and it can be quickly disassembled and replaced on site without dismantling the satellite.

8. The system according to claim 7, characterized in that The two ends of the side where the beam is connected to the third biological load chamber module are respectively provided with positioning pin bosses, and the two sides of the bottom surface of the third biological load chamber module are provided with positioning pin holes that are plugged into the positioning pin bosses. The beam is connected to the bottom of the third biological load chamber module at the bottom of the main structure frame by standard fasteners.

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