Stacked micro-nano satellite mass production line and assembly method

Abstract

The application relates to a production line and assembling method for batch production of stacked micro-nano satellites, and in particular to a production line and assembling method for batch production of stacked micro-nano satellites, which solves the problems of low production (assembling) efficiency, high cost and long cycle of existing satellites, and the method comprises the following steps: single-machine thermal control implementation and sub-assembly assembly to form a single-machine assembly; cabin section assembly to form a complete cabin section module; platform cabin combination to form a complete satellite platform; load cabin docking to form an intermediate state satellite; and solar wing assembly to form a final satellite to be launched. The production line and assembling method for batch production of stacked micro-nano satellites are suitable for batch production of stacked micro-nano satellites.

Description

Technical Field

[0001] This invention relates to the field of satellite mass production technology, and in particular to a production line and assembly (production) method suitable for the mass production of stacked micro and nano satellites. Background Technology

[0002] With the rapid development of aerospace technology, satellites are increasingly used in many fields such as communication, remote sensing, and navigation, leading to a growing demand for satellites. Traditional satellite production methods typically employ a customized production model, where each satellite is individually designed and manufactured according to specific mission requirements. The production cycle for a single satellite can be as long as 6 months. This method is time-consuming and costly, making it difficult to meet the needs of mass production of satellites.

[0003] The introduction of the stacked design concept into the satellite manufacturing field has enabled standardized production and flexible combination of modules by decomposing the satellite into multiple functionally independent modules, making mass production of satellites possible.

[0004] However, existing stacked micro / nano satellite production lines have the following drawbacks: (1) The time consumption of each work station was not balanced, resulting in a mismatch in the assembly process cycle. For example, in a satellite production line, the difference in cycle time between the thermal control implementation process (15h) and the module assembly (10h) caused the latter to wait for the former to complete, resulting in a 5h idle time loss.

[0005] (2) The layout of the production line is unreasonable, with problems such as overlapping process routes, detours in logistics paths and frequent conflicts in resource occupation, which cannot give full play to the advantages of stacked design.

[0006] (3) The lack of effective coordination and integration in each production link and the unclear boundaries of work station tasks lead to repetitive inspection or calibration work, resulting in a loss of 2 hours of effective working time per day.

[0007] (4) The work schedule is frequently adjusted dynamically, the job responsibilities of operators are unclear, tasks are switched repeatedly, cross-position collaboration consumes energy, and it is difficult to optimize the operation process through repeated practice, resulting in low efficiency.

[0008] (5) It is difficult to identify the responsible party and there is a lack of a dedicated personnel mechanism. For example, when tracing the quality of the thermal control wire welding of a certain batch of satellites, it was found that three operators were involved in the process, making it difficult to identify the responsible party.

[0009] Therefore, there is an urgent need for a production line and assembly method suitable for the mass production of stacked micro and nano satellites to solve the above problems. Summary of the Invention

[0010] This invention proposes a production line and assembly method for mass production of stacked micro and nano satellites, which solves the problems of low efficiency, high cost and long cycle of existing satellite production (assembly).

[0011] The stacked micro-nano satellite mass production line of the present invention includes multiple workstations; the multiple workstations include a preparation workstation, workstation one, workstation two, workstation three, workstation four, and workstation five; the multiple workstations adopt a parallel pulsed production architecture. The preparation station is used for pre-satellite installation preparation, including implementation of single-unit thermal control and assembly of components to form single-unit components. Workstation 1 serves as the propulsion module assembly station, and workstation 2 serves as the attitude control module assembly station: these are used to assemble modules based on single-unit components to form complete module modules. Workstation 3 serves as the platform merging workstation: it is used to merge the platform modules to form a complete satellite platform. The fourth workstation serves as the payload docking workstation: it is used to dock the upper and lower payload compartments on the basis of the entire satellite platform to form a satellite in an intermediate state. Workstation five serves as the solar panel assembly station: it is used to assemble the solar panels on the satellite in its intermediate state to form the final satellite ready for launch. The given standard working hours for the preparation station, station one to station four are 2N hours, and the given standard working hours for station five are N hours. The preparation station and stations one through four adopt a dual-station parallel layout to construct two synchronous production lines, which are used to complete the assembly of two satellites within a 2N-hour cycle. Workstation 5 is set up with only a single workstation, which matches the production capacity with the preceding workstation, ultimately achieving an assembly efficiency of N hours per satellite for the entire production line.

[0012] Furthermore, a preferred embodiment is provided, wherein the preparation station includes the following components: Unit and structural component outbound assembly: Used to issue the required unit and structural components according to the matching list of each satellite and to verify the materials; Standalone thermal control implementation component: used to attach thermistors and heaters at designated locations on a standalone unit, and to perform multi-layer wrapping and surface coating of the standalone unit with F46 film; Sub-component assembly: Used to assemble the single unit that has completed thermal control implementation with the corresponding structural components to form a single unit assembly; Classification and transfer components: used to move individual components to subsequent workstations according to their individual machine type.

[0013] Furthermore, a preferred embodiment is provided, wherein the workstation one includes the following components: Propulsion compartment pretreatment components: used to attach cable clamps to the surface of the propulsion compartment and protect the cable outlet holes; Propulsion compartment cable laying assembly: used to arrange individual unit components inside the propulsion compartment, lay the propulsion compartment cable network, and pre-bind and fix it; Propulsion compartment assembly components: used to connect individual unit components with cable networks and thermal control wiring to complete the assembly of the propulsion compartment; Propulsion module transfer assembly: used to move the assembled propulsion module into workstation three.

[0014] Furthermore, in a preferred embodiment, the second workstation includes the following components: Attitude control cabin pretreatment components: used to attach cable clamps to the surface of the attitude control cabin and protect the cable exit holes; Attitude control cabin internal cable laying assembly: used to arrange individual components inside the attitude control cabin, lay the internal cable network of the attitude control cabin and pre-bind and fix it; Attitude control cabin assembly components: used to connect individual components with cable networks and thermal control wiring to complete the assembly of the attitude control cabin; Attitude control cabin cable routing assembly: used to pre-thread the connectors that need to be routed through the attitude control cabin according to the requirements of the process documents; Attitude control cabin transfer assembly: used to move the assembled attitude control cabin into workstation three.

[0015] Furthermore, in a preferred embodiment, the third workstation includes the following components: Propulsion module installation components: used to complete the assembly of the propulsion module on the module mounting vehicle; Sailboard drive mechanism mounting assembly: used to install the sailboard drive mechanism to a designated location in the propulsion pod; Attitude control cabin hoisting and cable insertion assembly: used to hoist the attitude control cabin above the solar panel drive mechanism and insert the cabling inside the attitude control cabin into the corresponding interfaces of the solar panel drive mechanism and the propulsion cabin; Attitude control cabin installation and cable management assembly: used to install the attitude control cabin onto the solar panel drive mechanism, organize all cables inside the cabin, plug and fix the adapter cable plugs to form a satellite cable network; it is also used to pass through the cabin cables from each exit hole. Integrated electrical system and power controller assembly mounting kit: used to install the integrated electrical system and power controller assembly to the corresponding positions in the attitude control cabin and connect the relevant cables; External unit installation and cable management component: Used to install external unit equipment and manage all external cables to complete the assembly of the entire satellite platform.

[0016] Furthermore, a preferred embodiment is provided, wherein the fourth workstation includes the following components: Payload Upper Cabin Installation Assembly: Used to install the payload upper cabin to the integrated electrical system, and adjust the cabin mounting bracket to rotate 90° so that the entire satellite platform is in a horizontal state; Lower Load Capsule Lifting and Docking Assembly: Used to lift the lower load capsule and dock it onto the bracket of the docking support vehicle; operate the docking support vehicle to dock the lower load capsule with the propulsion module to complete the load docking; The satellite transfer and attitude adjustment assembly is used to lift the entire satellite platform horizontally after the payload docking is completed and transfer it to the transfer support vehicle; it is also used to rotate the transfer support vehicle 90° so that the entire satellite platform is in a vertical state, obtain the satellite in an intermediate state and move it into workstation five.

[0017] Furthermore, in a preferred embodiment, the fifth workstation includes the following components: Solar panel mounting assembly: Used to suspend the solar panel above the truss and adjust the position and angle of the solar panel to ensure correct installation polarity; Taimin mounting assembly: used to assemble the Taimin and its cables, complete the electrical assembly of the thermal control wiring, and ensure reliable connection of each component; Solar wing and satellite connection assembly: connects the hinges and expansion joints of the solar wing to the satellite platform; connects, binds, and secures the solar wing cables; Solar wing deployment and retraction test component: Tests the deployment and retraction of the solar wings to obtain the final launch-ready state of the entire satellite.

[0018] Furthermore, in a preferred embodiment, the production line further includes an anomaly detection and replacement component: The anomaly detection and replacement component is used to detect single-unit faults and replace the faulty module with a backup module.

[0019] Furthermore, in a preferred embodiment, the production line further includes a time monitoring component: The time monitoring component is used to monitor the time taken for each workstation and its components to perform work processes, and to determine whether there is a risk of exceeding the given standard working hours. If there is a risk of timeout, an early warning will be issued.

[0020] This invention also proposes an assembly method for mass production of stacked micro / nano satellites, the method comprising the following steps: Step S1: Preparations before satellite installation, including implementation of single-unit thermal control and assembly of components to form single-unit components; Step S2: Based on the single-unit components, assemble the compartments to form complete compartment modules; Step S3: Based on the module segments, the platform is assembled to form a complete satellite platform; Step S4: Based on the satellite platform, dock the upper and lower payload compartments to form the satellite in an intermediate state; Step S5: Based on the intermediate state of the satellite, assemble the solar panels to form the final satellite ready for launch.

[0021] The present invention has the following beneficial effects: 1. The assembly line for mass production of stacked micro-nano satellites described in this invention allows multiple assembly stations, such as preparation station and station one to station five, to work in parallel (multi-station parallel mode). Different stations simultaneously perform assembly tasks under different conditions, thereby improving production efficiency (assembly efficiency), shortening the final assembly cycle, and realizing the mass production of stacked micro-nano satellites.

[0022] 2. The stacked micro-nano satellite mass production line described in this invention uses multiple workstations with basically the same assembly cycle, has the ability to produce simultaneously, realizes a pulsed production mode, and ensures the stable operation of the production line and the continuity of production.

[0023] 3. The stacked micro-nano satellite mass production line of the present invention has clearly defined assembly content for each individual workstation. Once the fixed assembly content is completed at the previous workstation, it is delivered to the next workstation to start the next stage of final assembly.

[0024] 4. The assembly line for mass production of stacked micro-nano satellites described in this invention introduces industrial assembly line management thinking, deeply integrates aerospace assembly with a pulsed production mode, solves the problem of high demand for resource synchronization in the satellite manufacturing process, reduces the production cost of mass-produced satellites, and meets the requirements of stacked micro-nano satellites for mass production efficiency.

[0025] The assembly line and method for mass production of stacked micro-nano satellites described in this invention are applicable to the mass production of stacked micro-nano satellites. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 This is a schematic diagram of the process flow of a production line for mass production of stacked micro-nano satellites in one embodiment of the present invention. It should be noted that some component names have been abbreviated or omitted in the accompanying drawings. For example, the single unit and structural component outbound components are abbreviated as single unit outbound in the accompanying drawings, but the overall process is the same. Figure 2This is a schematic diagram of a dual-station parallel layout for mass production of stacked micro-nano satellites, as described in one embodiment of the present invention. Detailed Implementation

[0028] To make the technical solutions and advantages of the present invention clearer, the specific embodiments of the present invention will be described in further detail and completely below with reference to the accompanying drawings. The various embodiments described below are only some preferred embodiments of the present invention, and not all of them; the various embodiments described below are intended to explain the present invention and should not be construed as limiting the present invention; reasonable combinations of the technical features defined in the various embodiments of the present invention, as well as all other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort, are all within the scope of protection of the present invention.

[0029] Implementation method 1: A production line for mass production of stacked micro-nano satellites, the production line including multiple workstations; the multiple workstations include a preparation workstation, workstation one, workstation two, workstation three, workstation four and workstation five; the multiple workstations adopt a parallel pulsed production architecture; the workstations are connected by gantry robotic arms, so that each module is hoisted above the workstation in sequence to complete the docking of the module. The preparation station is used for pre-satellite installation preparation, including implementation of single-unit thermal control and assembly of components to form single-unit components. Workstation 1 serves as the propulsion module assembly station, and workstation 2 serves as the attitude control module assembly station: both are used to assemble modules based on single-unit components to form complete module modules; both the propulsion module assembly station and the attitude control module assembly station include a multi-degree-of-freedom operating table to assist operators in completing assembly in various postures. Workstation 3 serves as the platform merging workstation: it is used to merge the platform modules on the basis of the module segments to form a complete satellite platform; this workstation includes a truss robotic arm and a (dedicated) merging support vehicle, which is used to accurately lift the module segments to the merging support vehicle and operate the merging support vehicle to merge the modules. The fourth workstation serves as the payload docking workstation: it is used to dock the upper and lower modules of the payload on the satellite platform to form an intermediate satellite state; this workstation includes a truss robotic arm and a (dedicated) docking support vehicle, which is used to accurately lift the payload onto the docking support vehicle on the satellite platform and operate the docking support vehicle to dock the upper and lower modules of the payload. Workstation five serves as the solar panel assembly station: it is used to assemble the solar panels on the satellite in its intermediate state to form the final satellite ready for launch; this station includes a fixed parking support vehicle for parking the assembled satellite.

[0030] In this embodiment, the production line adopts a multi-station parallel pulsed production architecture, and realizes standardized operation throughout the entire process based on stacked design. Each (satellite) single module can be assembled and tested independently, and the work of each type of work is reasonably interspersed and effectively arranged.

[0031] In this embodiment, during the satellite assembly process using the assembly line, multiple (assembly) stations are carried out in parallel, performing assembly work in multiple states.

[0032] In this embodiment, the assembly line is used to solve problems such as chaotic processes, low production efficiency, and long waiting cycles in the existing satellite assembly process, thereby avoiding resource waste.

[0033] In this embodiment, the assembly content of each individual workstation is clearly divided. Once the previous workstation completes the fixed assembly content, it is delivered to the next workstation to start the next stage of final assembly work.

[0034] In this embodiment, the concept of industrial assembly line management is introduced, which deeply integrates aerospace assembly with a pulsed production mode. This solves the problem of high demand for resource synchronization in the satellite manufacturing process, reduces the production cost of mass-produced satellites, meets the batch production efficiency requirements of stacked micro-nano satellites, and solves problems such as long assembly cycles for multiple satellites, chaotic assembly processes, and insufficient personnel proficiency.

[0035] Implementation Method 2: The preparation station includes the following components: Unit and structural component outbound assembly: Used to issue the required unit and structural components according to the matching list of each satellite and to verify the materials; Standalone thermal control implementation component: used to attach thermistors and heaters at designated locations on a standalone unit, and to perform multi-layer wrapping and surface coating of the standalone unit with F46 film; Sub-component assembly: Used to assemble the single unit that has completed thermal control implementation with the corresponding structural components to form a single unit assembly; Classification and transfer components: used to move individual components to subsequent workstations according to their individual machine type.

[0036] In this embodiment, the stand-alone machine and structural component outbound assembly includes a warehouse and a material verification device; The material verification device is used to verify the required individual units and structural components according to the matching table for each satellite (e.g., verifying information such as model and quantity) to ensure that the materials are accurate. The warehouse is used to store the required individual machines and structural components; it is also used to issue the required individual machines and structural components out of the warehouse based on the verification results.

[0037] In this embodiment, according to the requirements of thermal control technology, thermistors and heaters are attached to designated positions on the unit to achieve monitoring and control of the unit's temperature; In this embodiment, the single unit is wrapped in multiple layers and an F46 film is applied to the surface to meet the requirements of thermal control and other related technologies.

[0038] In this embodiment, the single-machine thermal control implementation component includes a thermal control sensor positioning device and a covering execution mechanism; The thermal control sensor positioning device is used to attach a thermistor and a heater at a designated location on a single unit. The coating actuator is used to perform multi-layer coating on a single unit and to apply F46 film to its surface.

[0039] In this embodiment, the component assembly assembly uses bolt fastening or snap-locking to assemble the single unit that has completed thermal control with the corresponding structural components to form a single unit assembly.

[0040] In this embodiment, the component assembly includes a bolt fastening mechanism; the bolt fastening mechanism is used to assemble the single unit that has completed the thermal control implementation with the corresponding structural components to form a single unit assembly by means of bolt fastening connection.

[0041] In this embodiment, the component assembly includes a snap-fit ​​positioning mechanism; the snap-fit ​​positioning mechanism is used to assemble the single unit that has completed thermal control and the corresponding structural components into a single unit component by snap-fit ​​positioning and fixing.

[0042] In this embodiment, the sorting and transfer component moves individual components to subsequent workstations according to their type. Specifically: The individual components used for assembling the module sections, as well as the modules themselves (propulsion module and attitude control module), are moved to workstations one and two for subsequent module assembly. The individual components used for mounting the platform or payload are moved to stations three and four for subsequent satellite integration. The solar panel assembly is moved to station five for subsequent solar panel assembly.

[0043] In this embodiment, the sorting and transfer component includes a transfer robotic arm (such as a gantry robotic arm) and a sorting controller; The classification controller assigns target workstations based on single-machine type; The transfer robotic arm performs the movement operation.

[0044] Implementation method 3: The workstation one includes the following components: Propulsion compartment pretreatment components: used to attach cable clamps to the surface of the propulsion compartment and protect the cable outlet holes; Propulsion compartment cable laying assembly: used to arrange individual unit components inside the propulsion compartment, lay the propulsion compartment cable network, and pre-bind and fix it; Propulsion compartment assembly components: used to connect individual unit components with cable networks and thermal control wiring to complete the assembly of the propulsion compartment; Propulsion module transfer assembly: used to move the assembled propulsion module into workstation three.

[0045] In this embodiment, cable clamps are attached to the surface of the propulsion compartment to secure the cables.

[0046] In this embodiment, the cable outlet of the propulsion compartment is protected to prevent debris from entering or damaging the cable.

[0047] In this embodiment, the propulsion cabin pretreatment assembly includes a pretreatment operating table, a clamp pasting device, and a cable outlet protective cover. The pre-processing workbench (multi-degree-of-freedom workbench) is used to place the propulsion module body; The clamp pasting device is used to paste cable clamps onto the surface of the propulsion compartment body placed on the pre-treatment operating table; the clamp pasting device is an automatic glue-applying robotic arm. The cable outlet protective cover is used to protect the cable outlet of the propulsion compartment placed on the pre-processing operating table; the cable outlet protective cover is an adjustable size protective structure.

[0048] In this embodiment, the cable laying assembly inside the propulsion compartment lays the cable network according to the position of the individual unit (assembly) inside the propulsion compartment, and pre-ties and fixes it to ensure that the cables are neatly arranged and avoid tangling.

[0049] In this embodiment, the cable laying assembly inside the propulsion compartment includes a single-unit assembly installation robotic arm, a cable laying robotic arm, and a temporary binding mechanism. The single-unit component mounting robotic arm is used to arrange single-unit components within the propulsion module. The cable laying robotic arm automatically lays the cable network according to the individual machine position. The temporary binding mechanism is used to pre-bind and fix the cable network to prevent the cables from getting tangled.

[0050] In this embodiment, the propulsion compartment assembly uses a plug-in connector to connect the internal unit components and cables; the plug-in connector ensures a secure connection.

[0051] In this embodiment, the propulsion compartment assembly includes a connector insertion mechanism (robotic arm). The connector insertion mechanism (robotic arm) is used to connect stand-alone components to cable networks and thermal control cables (via connectors).

[0052] In this embodiment, the propulsion module transfer assembly includes a lifting device and a transfer support vehicle (such as a gantry robotic arm): used to move the propulsion module into workstation three after assembly, waiting for platform closure.

[0053] Implementation method 4: The second workstation includes the following components: Attitude control cabin pretreatment components: used to attach cable clamps to the surface of the attitude control cabin and protect the cable exit holes; Attitude control cabin internal cable laying assembly: used to arrange individual components inside the attitude control cabin, lay the internal cable network of the attitude control cabin and pre-bind and fix it; Attitude control cabin assembly components: used to connect individual components with cable networks and thermal control wiring to complete the assembly of the attitude control cabin; Attitude control cabin cable routing assembly: used to pre-thread the connectors that need to be routed through the attitude control cabin according to the requirements of the process documents; Attitude control cabin transfer assembly: used to move the assembled attitude control cabin into workstation three.

[0054] In this embodiment, cable clamps are attached to the surface of the attitude control cabin to secure the cables.

[0055] In this embodiment, the cable outlet of the attitude control cabin is protected to prevent foreign objects from entering or damaging the cable.

[0056] In this embodiment, the attitude control cabin pre-processing component includes an attitude control cabin pre-processing operating table, an attitude control cabin clamp pasting device, and an attitude control cabin cable outlet protective cover. The attitude control cabin preprocessing workbench (multi-degree-of-freedom workbench) is used to place the attitude control cabin body. The attitude control cabin clamp pasting device is used to paste cable clamps onto the surface of the attitude control cabin body placed on the attitude control cabin pre-processing operation table; the attitude control cabin clamp pasting device is an automatic glue-applying robotic arm. The attitude control cabin cable outlet protective cover is used to protect the cable outlet of the attitude control cabin body placed on the attitude control cabin preprocessing operation table; the attitude control cabin cable outlet protective cover is an adjustable size protective structure.

[0057] In this embodiment, the attitude control cabin cable laying assembly lays the cabin cable network according to the position of the single unit (assembly) in the attitude control cabin, and pre-ties and fixes it to ensure that the cables are neatly arranged and avoid tangling.

[0058] In this embodiment, the attitude control cabin cable laying assembly includes an attitude control cabin single-unit component installation robotic arm, an attitude control cabin cable laying robotic arm, and an attitude control cabin temporary binding mechanism. The attitude control cabin single-unit component mounting robotic arm is used to arrange single-unit components inside the attitude control cabin. The attitude control cabin cable laying robotic arm automatically lays the cable network according to the single-machine position. The attitude control cabin temporary binding mechanism is used to pre-bind and fix the cable network to prevent the cables from getting tangled.

[0059] In this embodiment, the attitude control cabin assembly uses a plug-in connector to connect the cabin's individual components and cables; the plug-in connector ensures a secure connection.

[0060] In this embodiment, the attitude control cabin assembly includes an attitude control cabin connector mating mechanism (robotic arm). The attitude control cabin connector plug-in mechanism (manipulator) is used to connect the single unit components to the cable network and thermal control wiring (through the plug-in).

[0061] In this embodiment, the connectors that need to be pushed out (in the attitude control cabin) are pushed out in advance according to the process documents to reduce the coupling between the cabin sections.

[0062] In this embodiment, the attitude control cabin cable penetration assembly includes a connector penetration guide and a process document actuator; The connector protrusion guide is used to pre-protect the connectors that need to be protruded. The process document actuator is used to control the pass-through operation based on a given process document.

[0063] In this embodiment, the attitude control cabin transfer assembly includes a lifting device and a transfer support vehicle (such as a gantry robotic arm): used to move the attitude control cabin into workstation three after assembly, waiting for platform cabin closure.

[0064] Implementation method 5: The third workstation includes the following components: Propulsion module installation components: used to complete the assembly of the propulsion module on the module mounting vehicle; Sailboard drive mechanism mounting assembly: used to install the sailboard drive mechanism to a designated location in the propulsion pod; Attitude control cabin hoisting and cable insertion assembly: used to hoist the attitude control cabin above the solar panel drive mechanism and insert the cabling inside the attitude control cabin into the corresponding interfaces of the solar panel drive mechanism and the propulsion cabin; Attitude control cabin installation and cable management assembly: used to install the attitude control cabin onto the solar panel drive mechanism, organize all cables inside the cabin, plug and fix the adapter cable plugs to form a satellite cable network; it is also used to pass through the cabin cables from each exit hole. Integrated electrical system and power controller assembly mounting kit: used to install the integrated electrical system and power controller assembly to the corresponding positions in the attitude control cabin and connect the relevant cables; External unit installation and cable management component: Used to install external unit equipment and manage all external cables to complete the assembly of the entire satellite platform.

[0065] In this embodiment, the propulsion module mounting assembly is as follows: Operate the propulsion compartment installation control panel to make the propulsion compartment opening face downwards; use the propulsion compartment installation lifting device to install the propulsion compartment onto the compartment assembly vehicle, thus completing the assembly of the propulsion compartment on the compartment assembly vehicle.

[0066] In this embodiment, the propulsion module installation assembly includes a propulsion module installation operating platform and a propulsion module installation lifting device; The propulsion compartment is equipped with an operating platform (including an operating platform control unit): used to ensure that the propulsion compartment opening faces downwards; The propulsion module is equipped with a lifting device (such as a truss robotic arm): used to install the downward-facing propulsion module onto the hull-mounting support vehicle, thus completing the assembly of the propulsion module on the hull-mounting support vehicle.

[0067] In this embodiment, when the solar panel drive mechanism mounting assembly installs the solar panel drive mechanism to the designated position of the propulsion pod, it must ensure that the installation polarity is correct and the installation is secure.

[0068] In this embodiment, the windsurfing drive mechanism mounting assembly includes a windsurfing drive mechanism mounting robotic arm and a polarity detector mounting assembly. The robotic arm for mounting the solar panel drive mechanism is used to install the solar panel drive mechanism to a designated position in the propulsion pod. The installation polarity detector is used to ensure that the installation polarity is correct.

[0069] In this embodiment, the attitude control cabin hoisting and cable insertion assembly includes a hoisting robotic arm and a cable insertion guide; The hoisting robotic arm is used to lift the attitude control cabin above the sailboard drive mechanism. The cable insertion guide is used to insert the through-cabin cables inside the attitude control cabin into the corresponding interfaces of the solar panel drive mechanism and the propulsion cabin.

[0070] In this embodiment, when the attitude control cabin installation and cable management assembly passes the cabin cables out of each outlet hole, it must ensure that the cable connections are smooth.

[0071] In this embodiment, the attitude control cabin installation and cable management assembly includes an attitude control cabin installation robotic arm, a cable management robotic arm, and a cable outlet guide. The attitude control cabin is equipped with a robotic arm for mounting the attitude control cabin onto the sailboard drive mechanism. The cable sorting robotic arm is used to sort all the cables in the cabin, plug and fix the adapter cable plugs to form a complete satellite cable network. The cable exit guide is used to guide the through-cabin cable out of each exit hole.

[0072] In this embodiment, the integrated power and power controller assembly mounting component includes an assembly mounting robotic arm and a cable connection structure; The assembly installation robotic arm is used to install the integrated electrical system and power controller assembly to the corresponding position in the attitude control cabin. The cable connection structure (robotic arm) is used to connect the relevant cables.

[0073] In this embodiment, the external stand-alone equipment includes an external antenna, a star sensor, etc.

[0074] In this embodiment, the external single-unit installation and cable management component organizes all external cables to ensure that the external cables are neatly arranged and that the routing of the multi-star cables is roughly the same, without any loosening or tangling.

[0075] In this embodiment, the external single-unit installation and cable management component includes an external equipment installation robotic arm and an external cable management robotic arm; The extravehicular equipment installation robotic arm is used to install single extravehicular equipment. The external cable sorting robot is used to sort all external cables.

[0076] Implementation method 6: The fourth workstation includes the following components: Payload Upper Cabin Installation Assembly: Used to install the payload upper cabin to the integrated electrical system, and adjust the cabin mounting bracket to rotate 90° so that the entire satellite platform is in a horizontal state; Lower Load Capsule Lifting and Docking Assembly: Used to lift the lower load capsule and dock it onto the bracket of the docking support vehicle; operate the docking support vehicle to dock the lower load capsule with the propulsion module to complete the load docking; Satellite transfer and attitude adjustment component: used to lift the entire satellite platform horizontally after the payload docking is completed and transfer it to the transfer support vehicle; also used to rotate the transfer support vehicle 90° to make the entire satellite platform vertical, obtain the satellite in the intermediate state and move it into workstation five.

[0077] In this embodiment, the payload upper compartment mounting assembly keeps the entire satellite platform in a horizontal position to facilitate subsequent payload lower compartment docking operations.

[0078] In this embodiment, the load loading assembly includes a load loading robotic arm and a loading support vehicle tilting control unit. The payload upper compartment mounting robotic arm is used to install the payload upper compartment into the integrated power system. The cabin support vehicle tilt control unit is used to adjust the tilt of the cabin support vehicle by 90°.

[0079] In this embodiment, the lower load compartment hoisting and docking assembly operates the docking support vehicle to dock the lower load compartment with the propulsion compartment, ensuring accurate connection of the mechanical and electrical interfaces.

[0080] In this embodiment, the load lower compartment hoisting and docking assembly includes a load lower compartment hoisting robotic arm and a docking support vehicle docking control unit; The lower load compartment hoisting robotic arm (such as a truss robotic arm) is used to lift the lower load compartment and dock it onto the bracket of the docking support vehicle. The docking support vehicle docking control unit is used to operate the docking support vehicle to dock the lower load compartment with the propulsion compartment (ensuring accurate connection of mechanical and electrical interfaces) and complete the load docking.

[0081] In this embodiment, the satellite transfer and attitude adjustment component keeps the satellite platform in a vertical position and moves it into station five, ready for subsequent solar panel assembly.

[0082] In this embodiment, the whole satellite transfer and attitude adjustment assembly includes a whole satellite lifting robotic arm and a transfer support vehicle tilting control unit; The entire satellite lifting robotic arm (such as a gantry robotic arm) is used to horizontally lift the entire satellite platform and transfer it to the transfer support vehicle. The transfer support vehicle tilting control unit is used to tilt the transfer support vehicle by 90° so that the entire satellite platform is in a vertical position. The transfer support vehicle is used to move the satellite in its intermediate state into workstation five.

[0083] Implementation method 7: The fifth workstation includes the following components: Solar panel mounting assembly: Used to suspend the solar panel above the truss and adjust the position and angle of the solar panel to ensure correct installation polarity; Taimin mounting assembly: used to assemble the Taimin and its cables, complete the electrical assembly of the thermal control wiring, and ensure reliable connection of each component; Solar wing and satellite connection assembly: connects the hinges and expansion joints of the solar wing to the satellite platform; connects, binds, and secures the solar wing cables; Solar wing deployment and retraction test component: Tests the deployment and retraction of the solar wings to obtain the final launch-ready state of the entire satellite.

[0084] In this embodiment, the thermocouple and its cable are assembled, and the electrical assembly of the thermal control wiring is completed to ensure reliable connection of each component.

[0085] In this embodiment, the hinges and expansion joints of the solar array are connected to the entire satellite platform to ensure a secure connection.

[0086] In this embodiment, the solar array cable is connected, bound, and secured to prevent the cable from being pulled or damaged during satellite launch and operation.

[0087] In this embodiment, the manual deployment and retraction of the solar array are tested to check whether the deployment and retraction of the solar array are smooth and whether the mechanism operates normally, so as to ensure that the solar array can work normally in orbit and form the whole satellite in the final launch-ready state.

[0088] In this embodiment, the solar panel mounting assembly includes a solar panel suspending robotic arm and a solar panel angle adjustment mechanism: The solar panel hoisting robotic arm is used to hoist the solar panel above the truss. The solar panel angle adjustment mechanism is used to adjust the position and angle of the solar panel to ensure correct installation polarity.

[0089] In this embodiment, the thermocouple mounting assembly includes a thermocouple mounting robotic arm and a thermal control wire assembly. The aforementioned robotic arm for assembling the thermocouple and its cables; The thermal control wire assembly device is used to complete the electrical assembly of the thermal control wire.

[0090] In this embodiment, the solar wing and satellite connection assembly includes a solar wing connection robotic arm and a cable binding and fixing device; The solar wing connecting robotic arm is used to connect the solar wing's hinges and expansion joints to the entire satellite platform. The cable binding and fixing device is used to connect, bind, and fix the solar panel cable.

[0091] In this embodiment, the solar array deployment and retraction test assembly includes a deployment / retraction actuator and a motion detection sensor. The deploy / retract actuator is used to manipulate the solar panels to deploy and retract. The motion detection sensor is used to detect whether the deployment and retraction of the solar panels are smooth and whether the mechanism operates normally.

[0092] Implementation method 8: The production line also includes an anomaly detection and replacement component: The anomaly detection and replacement component is used to detect single-unit faults and replace the faulty module with a backup module.

[0093] It should be noted that, in order to cope with unexpected anomalies during the production process, the stacked micro-nano satellite module adopts a universal mechanical interface, which is compatible with different models of single units; if a single unit failure is detected in a certain process, it can be quickly replaced by a backup module to ensure that the production line cycle is not interrupted.

[0094] Implementation method 9: The assembly line also includes a time monitoring component: The time monitoring component is used to monitor the time taken for each workstation and its components to perform work processes, and to determine whether there is a risk of exceeding the given standard working hours. If there is a risk of timeout, an early warning will be issued.

[0095] In this embodiment, when there is a risk of overtime (i.e. exceeding the given standard working hours) in a certain workstation, an early warning is issued to prompt the corresponding workstation and its components on the production line to speed up the execution, such as by increasing the working frequency of each robotic arm, adding robotic arms or other execution mechanisms, or sending operators to provide support, so as to maintain the overall production rhythm.

[0096] In another embodiment, the given standard working hours for the preparation station, station one to station four are 2N hours, and the given standard working hours for station five are N hours. The preparation station and stations one through four adopt a dual-station parallel layout to construct two synchronous production lines, which are used to complete the assembly of two satellites within a 2N-hour cycle. Workstation five is set up with only a single workstation, which matches the production capacity of the preceding workstations, ultimately achieving an assembly efficiency of N hours per satellite for the entire production line. In another embodiment, N is 16, that is, 2N hours is 32 hours (or expressed as 32h), and N hours is 16 hours (or expressed as 16h), that is, the given standard working hours are as follows: The standard working time for the preparation station is 32 hours. Workstation 1 is the propulsion module assembly workstation, and its standard working time is 32 hours. Workstation 2 is the attitude control cabin assembly workstation, with a given standard working time of 32 hours. Workstation 3 is the platform merging workstation, and its standard working time is 32 hours. The fourth workstation is a load docking workstation, with a given standard working time of 32 hours. Workstation five is the solar panel assembly workstation, with a given standard working time of 16 hours.

[0097] For example: For the preparation workstation: The standard working time for the outbound assembly of single machines and structural components is 2 hours. The standard working time for the single-unit thermal control implementation component to perform the process operation is 20 hours; The standard working time for the assembly and sorting / transfer of components is 10 hours.

[0098] For workstation five: The standard working time for the solar panel installation assembly process is 4 hours. The standard working time for the Taimin installation component to perform the operation is 4 hours; The standard working time for the solar array and satellite connection assembly to perform the operation is 4 hours. The standard working time for the solar array deployment and retraction test assembly to perform the operation is 4 hours.

[0099] In this embodiment, by analyzing the resource utilization rate, assembly complexity, and manpower situation at each stage of satellite assembly, and considering the stable performance and high consistency of mass-produced satellite products, a production line suitable for the mass production of stacked micro-nano satellites was designed, operating according to given standard working hours.

[0100] In this embodiment, a fixed-cycle mode is adopted, and the division of labor is based on the skill level of the personnel to ensure consistent assembly rhythm and guarantee the smooth progress of the mass production satellite assembly process.

[0101] In this embodiment, this type of assembly line is characterized by strong feasibility, flexibility and controllability, and high efficiency. By physically isolating workstations and parallelizing processes, it breaks through the serial bottleneck of traditional satellite assembly. Based on the standardization of module interfaces, it realizes plug-and-play functionality and cross-satellite reuse for modules / units. In another embodiment, the preparation station, station one to station four adopt a dual-station parallel layout to construct two synchronous production lines, which can complete the assembly of two satellites within a 32-hour cycle. Workstation 5 is set up with only a single workstation (because the assembly cycle of workstation 5 is 50% of that of the other workstations), which matches the capacity of the preceding workstations and ultimately achieves an assembly efficiency of 16 hours per satellite for the entire production line.

[0102] In this embodiment, the assembly cycles of multiple workstations are basically the same, enabling simultaneous production and realizing a pulsed production mode to ensure the stable operation of the production line and the continuity of production.

[0103] In another embodiment, the production line also includes an operator authentication device for authenticating the operators of each component at each workstation, so as to achieve "dedicated personnel for each position" in the production process and facilitate traceability of quality issues.

[0104] In this embodiment, the assembly work is assigned to specific personnel, and the operators only perform fixed assembly tasks and repetitive work, thereby continuously improving their operational proficiency and assembly skills.

[0105] In another embodiment, each workstation of the assembly line also includes a dual-shift fixed-station workbench for two operators to perform dual-shift work, with one operator performing assembly operations and the other operator responsible for supervising and passing tools to ensure the production quality of the satellite.

[0106] It should be noted that the flexible requirements of satellite assembly conflict with the rigid design of traditional assembly lines. Directly applying assembly lines from other fields to satellite production can lead to decreased efficiency or quality risks. Specifically: The need for flexibility in satellite assembly: Satellites are typically produced in small batches with customized requirements. Each satellite may be designed and manufactured according to different mission requirements, orbital requirements, etc. The products are highly differentiated and require flexible assembly lines to support rapid reconfiguration (such as adjustable tooling and modular workstations). They rely more on human-machine collaboration and require operators to make precise adjustments. Automated equipment only assists in performing fixed processes.

[0107] Rigid design of traditional large-scale production lines: Traditional assembly lines are typically large-scale continuous production lines that pursue cycle time optimization (such as one car rolling off the line every minute). They feature highly specialized equipment, aim for full automation, reduce human intervention, and solidify processes to improve efficiency.

[0108] In summary, the assembly line model suitable for large-scale mass production emphasizes the efficient and rapid repetitive production of the same products. Its equipment and processes are designed for mass production and are difficult to flexibly adjust to adapt to the small-batch, customized production needs of satellites. The assembly line of this invention is a flexible assembly line. Through modular design and standardized interface design, it can be compatible with different satellite models simultaneously. Traditional workpiece production does not have this flexibility requirement, and traditional assembly lines cannot achieve flexible assembly. For example, an automobile production line can produce a large number of cars of the same model in a short period of time. However, if different models of satellites with different functional requirements are to be produced on such a production line, it is necessary to frequently change tooling fixtures and adjust the process flow, which will consume a lot of time and cost and seriously affect production efficiency.

[0109] Implementation Method 10: An assembly method for mass production of stacked micro / nano satellites, the method comprising the following steps: Step S1: Preparations before satellite installation, including implementation of single-unit thermal control and assembly of components to form single-unit components; Step S2: Based on the single-unit components, assemble the compartments to form complete compartment modules; Step S3: Based on the module segments, the platform is assembled to form a complete satellite platform; Step S4: Based on the satellite platform, dock the upper and lower payload compartments to form the satellite in an intermediate state; Step S5: Based on the intermediate state of the satellite, assemble the solar panels to form the final satellite ready for launch.

[0110] Implementation Method 11: Step S1 (corresponding to the preparation station) includes: Step M1: Outbound of Units and Structural Components: According to the matching list for each satellite, outbound the required units and structural components and verify the materials (verify the unique code, number and quantity) to ensure that the material delivery is correct. This assembly process takes 2 hours. Step M2: Implementation of stand-alone thermal control: Thermistors and heaters are attached to designated locations on the stand-alone unit, and the unit is multi-layered and coated with an F46 film; specifically: For individual units requiring thermal control implementation, pre-processing is carried out. For internal units such as gyroscopes, short message systems, flywheels, and magnetometers, and for external units such as star sensors, solar sensors, solar panel drive mechanisms, and integrated electrical systems, thermistors and heaters are affixed to designated locations according to thermal control implementation requirements. For individual units requiring thermal control wrapping, multi-layer thermal insulation components are installed and F46 film is applied according to relevant documents. This assembly process takes 20 hours. Step M3: Component assembly and sorting transfer: Component assembly: Assembling the single unit with completed thermal control implementation and corresponding structural components to form a single unit component; specifically: Assembling the star sensor and its support, the flywheel and its support, the antenna and its support, the camera and its support, the thruster and its support, the solar sensor and its support, and the star-rocket docking device. Categorized transfer: Used to move individual components to subsequent workstations according to their type; specifically: Each individual component, after thermal control implementation and assembly, is transferred to the following stations: Unit 1 for the propulsion module; Unit 2 for the attitude control module; Unit 3 for the satellite platform; Unit 4 for the payload; and Unit 5 for the solar array. This assembly process takes 10 hours.

[0111] In this embodiment, step S1 requires two operators and takes a total of 32 hours to assemble.

[0112] Implementation Method 12: The module assembly includes the assembly of the propulsion module and the attitude control module; step S2 (corresponding to workstations one and two) includes step S2.1 (propulsion module assembly step, corresponding to workstation one) and step S2.2 (attitude control module assembly step, corresponding to workstation two); step S2.1 includes: Step M4: Propulsion compartment pretreatment: attach cable clamps to the surface of the propulsion compartment and protect the cable outlet holes. This assembly process takes 3 hours. Step M5: Propulsion Module Unit / Cable Assembly: Arrange unit components within the propulsion module, lay the propulsion module's internal cable network, and pre-tie and secure it; specifically: The internal cable network is pre-laid and temporarily tied and fixed; thermal conductive silicone grease is applied between the unit (component) and the mounting surface as required, and heat insulation pads are installed; propulsion-related units such as batteries, electric propulsion power supplies, propulsion systems, and thrusters are installed. This assembly process takes 14 hours. Propulsion module assembly: Connecting individual unit components to the cable network and thermal control wiring to complete the assembly of the propulsion module, including: Step M6: Propulsion module electrical installation: The electrical installation of the thermal control wiring is completed, including the heater and thermistor wiring. The resistance value of the final welded part is checked and confirmed. This process takes 10 hours. Step M7: Propulsion module cable connection and fixing: The cable end connectors are plugged into the single unit end, the module adapter plugs are reserved in the appropriate position, and the internal cable network is organized, tied and fixed; Propulsion module transfer: The propulsion module is transferred to workstation three for platform assembly. This process takes 5 hours. In this embodiment, step S2.1 requires two operators and takes a total of 32 hours to assemble.

[0113] Implementation Method 13: The module assembly includes the assembly of the propulsion module and the attitude control module; step S2 includes step S2.1 (propulsion module assembly step) and step S2.2 (attitude control module assembly step); step S2.2 includes: Step M8: Attitude control cabin pretreatment: Attach cable clamps to the surface of the attitude control cabin and protect the cable outlet holes. This assembly process takes 4 hours. Step M9: Attitude Control Module Unit / Cable Assembly (Attitude Control Module Internal Cable Laying): Arrange unit components inside the attitude control module, lay the internal cable network, and pre-tie and secure it; specifically: The cabling network is pre-laid and temporarily tied and fixed; thermal grease is applied between the unit (component) and the mounting surface as required, and heat insulation pads are installed. Attitude control related units such as short message integrated machine, filter, magnetometer, flywheel, gyroscope, magnetic torque device, and monitoring camera are installed. This assembly process takes 15 hours. Step M10: Attitude control cabin electrical installation (attitude control cabin assembly): Connect the individual components to the cable network and thermal control wiring to complete the assembly of the attitude control cabin; Organize the individual thermal control wiring of the attitude control cabin and weld it to the thermal control adapter plug, including the heater and thermistor. Check and confirm the resistance value of the final welded part. After confirming that there are no errors, plug the thermal control adapter plug in and lock it in place, and connect it to the whole satellite cable network. This assembly process takes 7 hours. Step M11: Connect and secure the cables for the attitude control cabin. Attitude control cabin cable routing: Connectors that need to be routed through the attitude control cabin should be routed in advance according to the process documentation requirements; specifically: The cable end connectors are plugged into the single unit end, the compartment adapter plugs are reserved in appropriate positions, and the cable network inside the compartment is organized, tied and fixed. Attitude control cabin transfer: The assembled attitude control cabin (module) is moved to workstation three for platform assembly. This assembly process takes 6 hours.

[0114] In this embodiment, step S2.2 requires two operators and takes a total of 32 hours to assemble.

[0115] Implementation method 14: Step S3 (corresponding to workstation three) includes: Step M12: Module assembly (propulsion module installation, solar panel drive mechanism installation, attitude control module hoisting and cable routing), carried out after the completion of steps M7 and M11. The specific assembly steps are as follows: The attitude adjustment and cabin assembly support vehicle is in a vertical position; the four corners of the propulsion cabin are hoisted using a truss hoisting platform to complete the connection between the propulsion cabin and the platform; the attitude adjustment and cabin assembly support vehicle is rotated 180° again to a vertical position, so that the propulsion cabin opening faces downward; the solar panel drive mechanism is installed onto the propulsion cabin; the four corners of the attitude control cabin are hoisted above the solar panel drive mechanism using a truss hoisting platform; the through-cabin cable leading to the lower cabin is pre-threaded through the cable outlet hole in the middle of the solar panel drive mechanism and the propulsion cabin; the attitude control cabin is installed onto the solar panel drive mechanism. This assembly process takes 6 hours. Step M13: Insertion and Fixing of Through-Carrier Cables (Attitude Control Module Installation and Cable Management): Organize all cables inside the module, insert and fix the adapter cable plugs to form a complete satellite cable network; this also serves to thread through-carrier cables out of each exit hole; specifically: The adapter plugs of each section are plugged in and fixed according to the corresponding relationship; the load is installed through the upper and lower compartments through the compartment cables; the through cables in the propulsion compartment are arranged, tied and fixed, and the external cables are reserved to an appropriate length according to the process requirements and passed out from the designated outlet hole; the through cables in the attitude control compartment are arranged, tied and fixed, and the external cables are reserved to an appropriate length according to the process requirements and passed out from the designated outlet hole. This process takes 11 hours to assemble. Step M14: Installation of the integrated electrical system and power controller assembly (platform sub-assembly): Install the integrated electrical system and power controller assembly to the corresponding positions in the attitude control cabin and connect the relevant cables; Confirm that all cables that need to be plugged in outside the attitude control cabin have been led out, complete the torque and glue application verification of the single unit inside the cabin, complete the polarity confirmation of all single unit installations, combine the power controller and integrated circuit, install them into the attitude control cabin, and then install all the connectors on the surface of the integrated circuit and power controller. This assembly process takes 5 hours. Step M15: External Unit / Cable Assembly (External Unit Installation and Cable Management): Install external unit equipment and manage all external cables to complete the assembly of the entire satellite platform.

[0116] Install external star sensors, telemetry and control antennas, GNSS antennas and other individual units; install external unit cables and bind and fix all cables on the surface of the external spacecraft. This assembly process takes 10 hours.

[0117] In this embodiment, step S3 requires 4 operators and takes a total of 32 hours to assemble.

[0118] Implementation Method 15: Step S4 (corresponding to workstation four) includes: Step M16: Payload Upper Cabin Installation: Install the payload upper cabin (after thermal control implementation is completed) into the integrated electrical system, and adjust the cabin support vehicle to rotate 90° to make the entire satellite platform horizontal; Lower compartment load hoisting and docking: The lower compartment load is installed on the bracket of the docking support vehicle using a truss hoisting platform; the docking support vehicle is driven to complete the docking of the lower compartment load with the propulsion module. This assembly process takes 12 hours. The docking process between the lower payload compartment and the propulsion compartment also includes: Step M17: Load cable binding and fixing: Assemble and fix load-related cables in the upper and lower compartments, and plug in the connectors. This assembly process takes 10 hours. Step M18: Installation of electrical / thermal control components in the middle compartment: installation of electrical components such as star sensors and thermal control wiring for upper and lower compartments of the satellite; multi-layer and thin-film wrapping and fixing of the satellite thermal control components, confirming that they are in good condition. This assembly process takes 4 hours. Step M19: Assembly of the B-type antenna: Installation, deployment, and retraction of the B-type payload antenna. This assembly process takes 6 hours. Through the above steps, the payload docking is completed; the entire satellite platform is lifted horizontally and transferred to the transfer support vehicle; the transfer support vehicle is rotated 90° to make the entire satellite platform vertical, and the satellite in the intermediate state is obtained and moved into workstation five.

[0119] In this embodiment, step S4 requires 4 operators and takes a total of 32 hours to assemble.

[0120] Implementation method 16: Step S5 (corresponding to workstation five) includes: Step M20: Solar Panel Installation: Suspend the solar panel above the truss, and adjust its position and angle to ensure correct installation polarity; specifically: Take the +Y and -Y side solar panels out of the warehouse and hang them above the truss, making sure they are aligned with the satellite coordinate system. Adjust the clamping seat to make the solar panels in the deployed state. Flip the entire satellite and adjust its attitude to dock it 30cm from the solar panel interface. This assembly process takes 2 hours. Step M21: Taisensor Installation: Assemble the taisensor and its cables, complete the electrical installation of the thermal control wiring, and ensure reliable connections of all components; specifically: Install the +Y and -Y side thermistors onto the outer plate of the solar panel respectively, confirm that the installation polarity is correct, and weld the thermistor and heater thermal control wires of the thermistor to the reserved wires on the solar panel side. After electrical assembly is completed, insert and fix the thermistor connector. This assembly process takes 4 hours. Step M22: Connecting the Solar Array to the Satellite: Connect the hinges and expansion joints of the solar array to the satellite platform; connect, bind, and secure the solar array cables; specifically: Connect the solar panel cables to the solar panel drive mechanism according to their corresponding relationships, install 4 hot knife cables, and bind and fix all solar panel related cables. Note that the cables should have some slack so as not to affect the deployment of the solar panels. This assembly process takes 4 hours. Step M23: Solar wing deployment and retraction test: Test the deployment and retraction of the solar wings to obtain the final launch-ready satellite configuration; specifically: The solar array is retracted to complete the assembly of the solar array hinges and expansion joints. The solar array is then manually deployed for verification and retracted again for assembly, forming the final satellite configuration. This assembly process takes 4 hours.

[0121] In this embodiment, step S5 requires two operators and takes a total of 16 hours to assemble.

[0122] The above description of several specific embodiments further details the technical solution provided by the present invention in order to highlight the advantages and benefits of the technical solution provided by the present invention. However, the above-described specific embodiments are not intended to limit the present invention. Any reasonable modifications and improvements to the present invention, reasonable combinations of embodiments, and equivalent substitutions based on the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A production line for mass production of stacked micro / nano satellites, characterized in that, The production line includes multiple workstations; the multiple workstations include a preparation workstation, workstation one, workstation two, workstation three, workstation four, and workstation five; the multiple workstations adopt a parallel pulsed production architecture; The preparation station is used for pre-satellite installation preparation, including implementation of single-unit thermal control and assembly of components to form single-unit components. Workstation 1 serves as the propulsion module assembly station, and workstation 2 serves as the attitude control module assembly station: these are used to assemble modules based on single-unit components to form complete module modules. Workstation 3 serves as the platform merging workstation: it is used to merge the platform modules to form a complete satellite platform. The fourth workstation serves as the payload docking workstation: it is used to dock the upper and lower payload compartments on the basis of the entire satellite platform to form a satellite in an intermediate state. Workstation five serves as the solar panel assembly station: it is used to assemble the solar panels on the satellite in its intermediate state to form the final satellite ready for launch. The given standard working time for the preparation station, station one to station four is 2N hours, and the given standard working time for station five is N hours, where N is the production interval of a single satellite in the entire production line. The preparation station and stations one through four adopt a dual-station parallel layout to construct two synchronous production lines, which are used to complete the assembly of two satellites within a 2N-hour cycle. Workstation 5 is set up with only a single workstation, which matches the production capacity with the preceding workstation, ultimately achieving an assembly efficiency of producing 1 satellite every N hours for the entire production line.

2. The production line for mass production of stacked micro / nano satellites according to claim 1, characterized in that, The preparation station includes the following components: Unit and structural component outbound assembly: Used to issue the required unit and structural components according to the matching list of each satellite and to verify the materials; Standalone thermal control implementation component: used to attach thermistors and heaters at designated locations on a standalone unit, and to perform multi-layer wrapping and surface coating of the standalone unit with F46 film; Sub-component assembly: Used to assemble the single unit that has completed thermal control implementation with the corresponding structural components to form a single unit assembly; Classification and transfer components: used to move individual components to subsequent workstations according to their individual machine type.

3. The production line for mass production of stacked micro / nano satellites according to claim 2, characterized in that, The workstation one includes the following components: Propulsion compartment pretreatment components: used to attach cable clamps to the surface of the propulsion compartment and protect the cable outlet holes; Propulsion compartment cable laying assembly: used to arrange individual unit components inside the propulsion compartment, lay the propulsion compartment cable network, and pre-bind and fix it; Propulsion compartment assembly components: used to connect individual unit components with cable networks and thermal control wiring to complete the assembly of the propulsion compartment; Propulsion module transfer assembly: used to move the assembled propulsion module into workstation three.

4. The production line for mass production of stacked micro / nano satellites according to claim 3, characterized in that, The second workstation includes the following components: Attitude control cabin pretreatment components: used to attach cable clamps to the surface of the attitude control cabin and protect the cable exit holes; Attitude control cabin internal cable laying assembly: used to arrange individual components inside the attitude control cabin, lay the internal cable network of the attitude control cabin and pre-bind and fix it; Attitude control cabin assembly components: used to connect individual components with cable networks and thermal control wiring to complete the assembly of the attitude control cabin; Attitude control cabin cable routing assembly: used to pre-thread the connectors that need to be routed through the attitude control cabin according to the requirements of the process documents; Attitude control cabin transfer assembly: used to move the assembled attitude control cabin into workstation three.

5. The production line for mass production of stacked micro / nano satellites according to claim 4, characterized in that, The third workstation includes the following components: Propulsion module installation components: used to complete the assembly of the propulsion module on the module mounting vehicle; Sailboard drive mechanism mounting assembly: used to install the sailboard drive mechanism to a designated location in the propulsion pod; Attitude control cabin hoisting and cable insertion assembly: used to hoist the attitude control cabin above the solar panel drive mechanism and insert the cabling inside the attitude control cabin into the corresponding interfaces of the solar panel drive mechanism and the propulsion cabin; Attitude control cabin installation and cable management assembly: used to install the attitude control cabin onto the solar panel drive mechanism, organize all cables inside the cabin, plug and fix the adapter cable plugs to form a satellite cable network; it is also used to pass through the cabin cables from each exit hole. Integrated electrical system and power controller assembly mounting kit: used to install the integrated electrical system and power controller assembly to the corresponding positions in the attitude control cabin and connect the relevant cables; External unit installation and cable management component: Used to install external unit equipment and manage all external cables to complete the assembly of the entire satellite platform.

6. The production line for mass production of stacked micro / nano satellites according to claim 5, characterized in that, The fourth workstation includes the following components: Payload Upper Cabin Installation Assembly: Used to install the payload upper cabin to the integrated electrical system, and adjust the cabin mounting bracket to rotate 90° so that the entire satellite platform is in a horizontal state; Lower Load Capsule Lifting and Docking Assembly: Used to lift the lower load capsule and dock it onto the bracket of the docking support vehicle; operate the docking support vehicle to dock the lower load capsule with the propulsion module to complete the load docking; Satellite transfer and attitude adjustment component: used to lift the entire satellite platform horizontally after the payload docking is completed and transfer it to the transfer support vehicle; also used to rotate the transfer support vehicle 90° to make the entire satellite platform vertical, obtain the satellite in the intermediate state and move it into workstation five.

7. The production line for mass production of stacked micro / nano satellites according to claim 6, characterized in that, The fifth workstation includes the following components: Solar panel mounting assembly: Used to suspend the solar panel above the truss and adjust the position and angle of the solar panel to ensure correct installation polarity; Taimin mounting assembly: used to assemble the Taimin and its cables, complete the electrical assembly of the thermal control wiring, and ensure reliable connection of each component; Solar wing and satellite connection assembly: connects the hinges and expansion joints of the solar wing to the satellite platform; connects, binds, and secures the solar wing cables; Solar wing deployment and retraction test component: Tests the deployment and retraction of the solar wings to obtain the final launch-ready state of the entire satellite.

8. The production line for mass production of stacked micro / nano satellites according to claim 1, characterized in that, The production line also includes an anomaly detection and replacement component: The anomaly detection and replacement component is used to detect single-unit faults and replace the faulty module with a backup module.

9. The production line for mass production of stacked micro / nano satellites according to claim 1, characterized in that, The production line also includes a time monitoring component: The time monitoring component is used to monitor the time taken for each workstation and its components to perform work processes, and to determine whether there is a risk of exceeding the given standard working hours. If there is a risk of timeout, an early warning will be issued.

10. An assembly method for mass production of stacked micro / nano satellites, characterized in that, The method is implemented based on the production line for mass production of stacked micro / nano satellites as described in any one of claims 1-9, and the method includes the following steps: Step S1: Preparations before satellite installation, including implementation of single-unit thermal control and assembly of components to form single-unit components; Step S2: Based on the single-unit components, assemble the compartments to form complete compartment modules; Step S3: Based on the module segments, the platform is assembled to form a complete satellite platform; Step S4: Based on the satellite platform, dock the upper and lower payload compartments to form the satellite in an intermediate state; Step S5: Based on the intermediate state of the satellite, assemble the solar panels to form the final satellite ready for launch.

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