Six-segment stack type integrated navigation satellite structure suitable for batch production

Abstract

This invention proposes a six-segment stacked integrated navigation satellite structure suitable for mass production, belonging to the field of spacecraft structure design and manufacturing technology. It solves the problem that existing technologies cannot simultaneously meet the requirements of mass production of navigation satellites while maintaining satellite attitude control and structural stability. It comprises, in sequence, an upper payload compartment, an integrated electronics compartment, an attitude control compartment, a two-dimensional solar panel drive compartment, a propulsion compartment, and a lower payload compartment. Each segment is connected by inter-segment locking blocks and slots. All segments are secured by a fixing device. The two-dimensional solar panel drive mechanism of the two-dimensional solar panel drive compartment is connected to the two-dimensional rotating solar panel via a drive shaft. The two-dimensional solar panel drive mechanism includes a drive structure and a locking structure. The drive structure drives the drive shaft to rotate the two-dimensional rotating solar panel in two dimensions. This invention employs a six-segment stacked integrated structure design, enabling satellite production to adapt to a parallel production line model, increasing production efficiency by approximately 70% compared to traditional methods.

Description

Technical Field

[0001] This invention relates to the field of spacecraft structural design and manufacturing technology, specifically covering satellite modular module design, satellite structural design, and satellite mass production. In particular, it relates to a six-segment stacked integrated navigation satellite structure adapted for mass production, suitable for the mass production and performance improvement of navigation satellites. Background Technology

[0002] In recent years, commercial spaceflight has entered a period of rapid development. However, the current mass production of satellites faces numerous technical bottlenecks. Firstly, traditional satellite production processes are cumbersome, and the lack of unified standards for components leads to poor interchangeability. Assembly requires extensive manual debugging and calibration, resulting in relatively low production efficiency. Secondly, with the increase in commercial satellite production, it is difficult to quickly replace faulty components when problems arise during satellite production and testing. This results in long repair cycles, high costs, and impacts the entire satellite development cycle. Thirdly, the structural weight of satellites is excessively high. In traditional designs, the individual unit structure and the overall satellite structure are independent, with numerous redundant components and complex connection structures. This means that the weight of structural components typically exceeds 30%, severely restricting the satellite's payload capacity and energy efficiency. These issues also limit the large-scale development of the commercial spaceflight industry.

[0003] Navigation satellites typically have two types of antennas: a receiving antenna and a transmitting antenna. The receiving antenna must be consistently aligned with the high-orbit satellite, while the transmitting antenna must be stably pointed towards the Earth. This places extremely high demands on the satellite's attitude control and structural stability. However, existing technologies are insufficient to simultaneously meet the needs of mass production of navigation satellites and their special functional requirements, necessitating innovative designs to address these challenges. Summary of the Invention

[0004] In view of this, in order to solve the problem mentioned in the background art that the existing technology cannot simultaneously meet the requirements of mass production of navigation satellites and the requirements of satellite attitude control and structural stability, the present invention proposes a six-segment stacked integrated navigation satellite structure adapted to mass production.

[0005] To achieve the above objectives, the present invention adopts the following technical solution: a six-segment stacked integrated navigation satellite structure suitable for mass production, comprising a payload upper compartment, an integrated electronics compartment, an attitude control compartment, a two-dimensional solar panel drive compartment, a propulsion compartment, and a payload lower compartment connected in sequence. Each compartment is provided with inter-segment locking blocks and inter-segment locking slots for positioning and locking. Each compartment is fixed as a whole by a fixing device. The two-dimensional sailboard drive cabin includes a two-dimensional sailboard drive mechanism, a drive shaft, and a two-dimensional rotating sailboard. The two-dimensional sailboard drive mechanism is connected to the two-dimensional rotating sailboard through the drive shaft. The two-dimensional sailboard drive mechanism includes a drive structure and a locking structure. The drive structure is used to drive the drive shaft to drive the two-dimensional rotating sailboard to rotate in two dimensions.

[0006] Preferably, the fixing device includes a plurality of high-strength titanium alloy long bolts, which sequentially pass through the upper load compartment, the integrated electrical compartment, the attitude control compartment, the two-dimensional solar panel drive compartment, the propulsion compartment, and the lower load compartment, and are fixed by nuts.

[0007] Preferably, the fixing device further includes a number of high-strength titanium alloy short bolts, and each compartment is initially connected and positioned by the high-strength titanium alloy short bolts.

[0008] Preferably, the upper payload compartment is equipped with a receiving antenna for receiving signals, the lower payload compartment is equipped with a transmitting antenna for transmitting signals, the integrated electronics compartment is equipped with integrated electronic equipment and a power controller for satellite electronic control and processing, the attitude control compartment is equipped with satellite attitude control equipment for satellite attitude control, the two-dimensional solar panel drive compartment is equipped with solar panels and solar panel drive equipment for solar panel rotation, and the propulsion compartment is equipped with a Hall electric propulsion system for satellite orbit maintenance and orbit change.

[0009] Preferably, the two-dimensional sailboard drive mechanism is locked in the ground state, and the drive shaft, as the main load-bearing component, transmits the mechanical load. When running on the rail, it is unlocked and drives the two-dimensional rotating sailboard to rotate in two dimensions. The two-dimensional sailboard drive mechanism uses the residual magnetic force generated by the permanent magnet to enable the sailboard drive mechanism to achieve ground self-locking in the absence of power.

[0010] Preferably, the drive structure includes a large shaft drive system and a small shaft drive system. The large shaft drive system drives the large shaft rotating bracket to rotate 360° around the Z-axis, and the small shaft drive system drives the small shaft connecting the sail to rotate 360° around the Y-axis, so as to realize the 360° rotation of the two axes of the two-dimensional rotating sail.

[0011] Preferably, the main shaft drive system includes a main shaft stator assembly and a main shaft rotor assembly. The main shaft stator assembly is rigidly connected to the cabin frame to form a stationary base. The main shaft rotor assembly is supported on the main shaft stator assembly and can rotate freely around the Z-axis, and is rigidly connected to the main shaft rotation bracket. The secondary shaft drive system includes a secondary shaft stator assembly and a secondary shaft rotor assembly. The secondary shaft stator assembly is rigidly connected to the cabin frame to form a stationary base. The secondary shaft rotor assembly is supported on the secondary shaft stator assembly and can rotate freely around the Y-axis, and is rigidly connected to the secondary shaft connecting the sail.

[0012] Preferably, the main shaft stator assembly includes an upper fixed flange, a fixed ring, a main shaft permanent magnet, a permanent magnet fixing bracket, and a lower fixed flange. The main shaft permanent magnet and the permanent magnet fixing bracket are fixed to form a stationary permanent magnet unit. This unit is rigidly connected to the upper fixed flange through the fixed ring. The upper fixed flange is connected to the attitude control cabin, and the lower fixed flange is fixed to the propulsion cabin. The main shaft rotor assembly includes a main shaft coil, a main shaft rotating bracket, a main shaft bearing, and an intermediate rotating housing. The main shaft coil is rigidly connected to the intermediate rotating housing through the main shaft rotating bracket and supported by the main shaft bearing on the lower fixed flange, and can rotate freely around the Z-axis.

[0013] Preferably, the small shaft stator assembly includes a small shaft coil bracket and a small shaft coil, wherein the small shaft coil bracket is fixed to the intermediate rotating housing, and the small shaft coil is embedded inside the small shaft coil bracket; The small shaft rotor assembly includes a small shaft permanent magnet and a connecting small shaft for the sail, wherein the small shaft permanent magnet is rigidly connected to the connecting small shaft for the sail.

[0014] Compared with existing technologies, the beneficial effects of the six-segment stacked integrated navigation satellite structure adapted for mass production described in this invention are: (1) Improved production efficiency and maintainability: The integrated structure design of the six-section stacked modules enables satellite production to adapt to the parallel production line mode, and the production efficiency is increased by about 70% compared with the traditional method; the interchangeability of components is significantly enhanced, and faulty modules or components can be quickly replaced during maintenance, reducing maintenance time by about 65% and effectively reducing operation and maintenance costs.

[0015] (2) Significant effect of structural lightweighting: The integrated design of the single-unit structure and the whole satellite structure reduces the weight of structural components to 15%, effectively reducing the overall weight of the satellite, increasing the payload capacity, improving the energy utilization efficiency of the satellite, and providing strong support for the large-scale development of the aerospace industry.

[0016] (3) Functional realization and performance optimization: The six-section stacked module structure rationally divides the functional areas. Combined with the new solar panel drive mechanism and high-precision attitude control equipment, it ensures that the navigation satellite receiving antenna is stably aligned with the high orbit and the transmitting antenna is accurately aligned with the Earth while achieving stable satellite operation, thus meeting the special functional requirements of the navigation satellite and improving the accuracy and service quality of satellite navigation and positioning.

[0017] (4) Dual function of mechanism cabin and single unit: The six-section cabin can function as a single unit with equipment function and as a load-bearing component function. Through the partition design, the internal structure of the two-dimensional solar panel drive cabin and the reserved cable channel of the cabin can be precisely matched, eliminating the redundant connection structure in the traditional design, which is very beneficial to the weight reduction of the satellite structure.

[0018] (5) Flexible solar panel drive mode: The solar panel drive mechanism uses the residual magnetic force generated by the permanent magnet to enable the solar panel drive mechanism to achieve ground self-locking in the absence of power, and achieve rigid connection with the upper and lower sections, and transmit mechanical load as the main load-bearing component; when running in orbit, it is unlocked and drives the solar panel to rotate in two dimensions, which can achieve 360° rotation of the solar panel while maintaining the basic attitude of the satellite, thus meeting the satellite's needs for solar energy collection and angle adjustment. Attached Figure Description

[0019] The accompanying drawings, which form part of this invention, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a schematic diagram of the six-segment stacked integrated navigation satellite structure adapted for mass production as described in this invention; Figure 2 This is an assembly diagram of the six stacked compartments described in this invention; Figure 3 A schematic diagram of the production process in each section of a parallel assembly line; Figure 4 A schematic diagram of the entire star stack assembly; Figure 5 This is a schematic diagram of the locking mechanism for high-strength titanium alloy short bolts; Figure 6 This is a schematic diagram of the locking mechanism for a high-strength titanium alloy long bolt. Figure 7 A schematic diagram illustrating the mass production process of a six-segment stacked integrated navigation satellite structure; Figure 8 A schematic diagram showing the ground locking status of the six stacked modules; Figure 9 This is a schematic diagram of the on-orbit deployment of the six stacked modules. Figure 10 This is a top view of the two-dimensional solar panel drive mechanism; Figure 11 for Figure 10 Sectional view of plane AA; Figure 12 This is an exploded view of the small shaft drive system of the two-dimensional sail plate drive mechanism; Figure 13 An exploded view of the main shaft drive system of the two-dimensional sailboard drive mechanism; Figure 14 This is a cloud map showing the lateral overload stress of the satellite. Figure 15 This is a cloud map showing the axial overload stress of the satellite. In the diagram: 1-Upper payload compartment, 2-Integrated electrical module compartment, 3-Attitude control module compartment, 4-2D solar panel drive compartment, 5-Propulsion module, 6-Lower payload compartment, 7-High-strength titanium alloy short bolt, 8-High-strength titanium alloy long bolt, 9-Inter-module locking block, 10-Inter-module locking slot, 11-Satellite hull, 12-2D rotating solar panel in locked state, 13-2D solar panel drive mechanism in locked state, 14-2D rotating solar panel in unlocked state, 15-2D solar panel drive mechanism in unlocked state, 16-Drive shaft, 17-Upper fixed flange, 18-Fixing ring. 19-Main shaft coil, 20-Main shaft fixing bracket, 21-Main shaft permanent magnet, 22-Permanent magnet fixing bracket, 23-Main shaft rotating bracket, 24-Main shaft bearing, 25-Lower fixing flange, 26-Intermediate rotating housing, 27-Small shaft coil bracket, 28-Small shaft permanent magnet, 29-Small shaft permanent magnet bracket, 30-Connecting small shaft to the sailboard, 31-Small shaft coil, 32-Small shaft bearing, 33-Small shaft top cover, 34-Small shaft top cover fixing screw, 35-Connecting small shaft to the sailboard fixing screw, 36-Main coil bracket fixing screw, 37-Bracket fixing screw. Detailed Implementation

[0020] The present invention will now be described in further detail with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are for illustrative purposes only and are not intended to limit the invention. Furthermore, it should be noted that, for ease of description, only the parts relevant to the invention are shown in the drawings, and not all of them. Unless otherwise defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. The terminology used herein is for the purpose of describing specific embodiments only and is not intended to limit the invention.

[0021] Detailed Implementation Method 1: See Figures 1-7 as well as Figures 14-15 This embodiment describes a six-segment stacked integrated navigation satellite structure adapted for mass production. The invention's technology is applied in a mass production project of a new type of navigation satellite. Figure 1 As shown, the overall satellite structure, from top to bottom, consists of the upper payload compartment 1, the integrated electrical module 2, the attitude control module 3, the two-dimensional solar panel drive module 4, the propulsion module 5, and the lower payload compartment 6. Each module is connected by inter-module locking blocks 9 and inter-module locking slots 10 for positioning and locking.

[0022] This invention addresses the long-term requirement of navigation satellite receiving antennas pointing towards high orbits and transmitting antennas pointing towards Earth. It designs a six-segment stacked module structure for a navigation satellite, with each module performing its specific function. The upper payload module 1 houses the receiving antenna, enabling signal reception; the lower payload module 6 houses the transmitting antenna, enabling signal transmission. The upper and lower payload modules 1 and 6 are located at the beginning and end of the six modules, respectively, ensuring simultaneous transmission and reception by the satellite antennas. The integrated electronics module 2 contains integrated electronic equipment and a power controller, providing satellite electronic control and processing capabilities. The attitude control module 3 contains satellite attitude control equipment such as flywheels, fiber optic gyroscopes, and MEMS gyroscopes, ensuring stable pointing of the satellite antennas. The two-dimensional solar panel drive module 4 contains solar panels and drive equipment, enabling solar panel rotation and ensuring flexible energy transfer. The propulsion module 5 contains a Hall effect electric propulsion system, providing satellite orbit maintenance and orbit change capabilities. Each module adopts a modular design, allowing for independent production without affecting others. The modules are connected by bolts, and standardized slots and blocks at the top and bottom enable rapid and precise assembly, significantly improving satellite production efficiency. During satellite production and testing, if a module or component malfunctions, the faulty module or component can be quickly replaced without disassembling the entire satellite. This structural design not only meets the functional requirements of navigation satellites but is also suitable for mass production, greatly enhancing production efficiency.

[0023] In the production process of the six stacked modules, according to design standards, six modules are manufactured on an automated production line: upper load module 1, integrated electrical module 2, attitude control module 3, two-dimensional solar panel drive module 4, propulsion module 5, and lower load module 6. First, the module frame is processed, and then the inter-module slots 10 and inter-module blocks 9 are machined before the internal equipment is installed. For example... Figures 2 to 4 As shown, the six modules can be manufactured in parallel, with each subsystem and assembly personnel performing their respective duties, enabling simultaneous production and assembly of different parts of the satellite, greatly improving the efficiency of satellite development and production. After the six modules are produced, the stacking and assembly of the entire satellite begins.

[0024] Each segment of the satellite is equipped with short screw mounting holes, inter-segment slots 10, and inter-segment blocks 9, enabling rapid assembly of each segment. Taking the payload upper module 1, integrated electronics module 2, and attitude control module 3 as examples, the specific implementation steps are as follows: Figure 5As shown, the integrated electronics module 2 and attitude control module 3 achieve precise positioning of the module installation through inter-module slots 10 and inter-module blocks 9 set on different modules. Initial connection between modules is achieved by connecting the mounting holes on the modules with high-strength titanium alloy short bolts 7. After the initial connection between the payload upper module 1 and the integrated electronics module 2, and between the integrated electronics module 2 and the attitude control module 3, is completed using high-strength titanium alloy long bolts 8, the payload upper module 1, integrated electronics module 2, and attitude control module 3 are connected as a whole, achieving overall satellite locking. Following this method, the two-dimensional solar panel drive module 4, propulsion module 5, and payload lower module 6 are then assembled sequentially to complete the overall satellite assembly and locking.

[0025] This study used MSC Apex and MSC Patran for preprocessing the finite element model, and MSC / Nastran, a commonly used finite element analysis software in the aerospace field, was used to perform dynamic analysis on the satellite. The satellite was divided into 48,590 nodes and 25,749 elements. The satellite-rocket docking surface was assumed to be fixed in the launch state, and the mass of the thermal control and cables was assumed to be uniformly distributed on the cabin. A 12g acceleration load was applied to the entire satellite in the X, Y, and Z directions, and the stress distribution of the satellite was analyzed. Figure 14 and Figure 15 As shown in the results, the maximum stress on the satellite under overload is 297 MPa, occurring on the satellite-rocket docking bracket made of 7075 material. The safety factor is 1.53, and the safety margin is 0.53. Compared to the frame structure, the stacked structure of this invention increases the maximum stress by nearly 60 MPa, and both the safety factor and safety margin are improved. Compared to the traditional frame structure, the structural strength is also improved. Modal analysis of the satellite shows that the first-order fundamental frequency of the entire satellite is 25.7 Hz, which meets the rocket's requirement of a fundamental frequency ≥ 25 Hz.

[0026] Based on the satellite mode shape and modal mass ratio, the modal characteristics of each order are determined, and the modal mass ratio is shown in the table below.

[0027] Table 1. Fundamental Mode Quality of Stacked Structure

[0028] Table 2 Fundamental Frequency Modal Quality of Frame Structure

[0029] The modal mass table above shows that the satellite's first mode is the overall Y-axis translational mode, the second mode is the overall X-axis translational mode, the third mode is the overall X-axis translational mode, the fourth mode is the overall Z-axis translational mode, the fifth mode is the overall X-axis translational Z-axis rotational mode, and the sixth mode is the overall X-axis translational mode. Comparing the data in Table 1-2, it can be seen that the stacked structure has a higher fundamental frequency than the frame structure, making it more stable and more conducive to the satellite withstanding vibration test conditions within the rocket.

[0030] Detailed Implementation Method 2: See Figures 8-13 In this embodiment, the two-dimensional sailboard drive cabin 4 includes a two-dimensional sailboard drive mechanism, a drive shaft 16, and a two-dimensional rotating sailboard. The two-dimensional sailboard drive mechanism is connected to the two-dimensional rotating sailboard via the drive shaft 16. The two-dimensional sailboard drive mechanism includes a drive structure, which drives the drive shaft 16 to rotate the two-dimensional rotating sailboard in two dimensions. The drive shaft 16 is a collective term for the main shaft drive system's main shaft rotating bracket 23, the intermediate rotating housing 26, and the small shaft drive system's connecting small shaft 30 for the sailboard.

[0031] The drive structure includes a large shaft drive system and a small shaft drive system. The large shaft drive system drives the large shaft rotating bracket 23 to rotate 360° around the Z-axis, and the small shaft drive system drives the small shaft 30 connecting the sail to rotate 360° around the Y-axis, so as to realize the 360° rotation of the two axes of the two-dimensional rotating sail.

[0032] The main shaft drive system includes a main shaft stator assembly and a main shaft rotor assembly. The main shaft stator assembly is rigidly connected to the cabin frame to form a stationary base. The main shaft rotor assembly is supported on the main shaft stator assembly and can rotate freely around the Z-axis. It is also rigidly connected to the main shaft rotating bracket 23 and the intermediate rotating outer shell 26.

[0033] The main shaft stator assembly is the fixed end of the main shaft, including an upper fixed flange 17, a fixing ring 18, a main shaft permanent magnet 21, a permanent magnet fixing bracket 22, and a lower fixed flange 25. The main shaft permanent magnet 21 and the permanent magnet fixing bracket 22 constitute a stationary permanent magnet unit. This unit is rigidly connected to the upper fixed flange 17 via the fixing ring 18. The upper fixed flange 17 is connected to the attitude control cabin, and the lower fixed flange 25 is fixed to the propulsion cabin by bolts, forming a stationary base structure. The main shaft permanent magnet 21 is fixed by the permanent magnet fixing bracket 22, and its magnetic field spatial position is strictly limited, providing a stable magnetic field environment for the rotating end. The rigid connection between the upper and lower fixed flanges constrains the axial and circumferential displacement of the system.

[0034] The main shaft rotor assembly is the rotating end of the main shaft, including a main shaft coil 19, a main shaft fixing frame 20, a main shaft rotating support 23, and a main shaft bearing 24. The main shaft coil 19 is embedded in the main shaft fixing frame 20 to form a rotating electromagnetic field generating unit. This unit is rigidly connected to the intermediate rotating housing 26 through the main shaft rotating support 23 and supported on the lower fixed flange 25 through the main shaft bearing 24, and can rotate freely around the Z-axis. The tight connection between the main shaft fixing frame 20, the main shaft rotating support 23, and the intermediate rotating housing 26 ensures that the entire rotating end rotates synchronously, driving the two-dimensional rotating sail.

[0035] The power transmission process is as follows: When the main shaft coil 19 is energized, the electromagnetic field it generates interacts with the constant magnetic field of the main shaft permanent magnet 21 at the fixed end, directly driving the main coil fixing frame 20 and the main shaft rotating support 23 to rotate around the Z-axis. The rotational torque is transmitted to the intermediate rotating shell 26 through the main shaft rotating support 23, thereby driving the two-dimensional rotating sail to rotate synchronously along the Z-axis. The power transmission path is: magnetic field of main shaft coil 19 → main shaft permanent magnet 21 → main coil fixing frame 20 → main shaft rotating support 23 → intermediate rotating shell 26 → two-dimensional rotating sail, realizing direct drive without mechanical transmission chain, ensuring zero backlash and high response characteristics.

[0036] System stability assurance design: 1. Stator rigid fixation: The permanent magnet fixing bracket 22 is fastened to the upper fixing flange 17 through the fixing ring 18 to ensure that the main shaft permanent magnet 21 is stationary and the magnetic field position is constant; the bolt connection between the upper fixing flange 17 and the lower fixing flange 25 forms a stable base to constrain the overall displacement of the system.

[0037] 2. Rotor support and connection: The main shaft bearing 24 is installed in the lower fixed flange 25 to provide low-friction rotational support for the rotating end and limit radial runout; the main coil fixing bracket 20 is rigidly connected to the main shaft rotating bracket 23 through the main coil bracket fixing screw 36 to ensure that the torque transmission is not loose.

[0038] The small shaft drive system includes a small shaft stator assembly and a small shaft rotor assembly. The small shaft stator assembly is rigidly connected to the cabin frame to form a stationary base. The small shaft rotor assembly is supported by the small shaft stator assembly and can rotate freely around the Y-axis, and is rigidly connected to the connecting sail small shaft 30.

[0039] The small shaft stator assembly is the fixed end of the small shaft, including a small shaft coil bracket 27, a small shaft coil 31, and a small shaft upper cover 33. The small shaft coil bracket 27 is fixed to the intermediate rotating outer shell 26 by screws. The small shaft coil 31 is embedded in the inner side of the small shaft coil bracket 27, and together with the small shaft upper cover 33, they form a stationary stator.

[0040] The small shaft rotor assembly is the rotating end of the small shaft, including a small shaft permanent magnet 28, a connecting small shaft 30 for the sail plate, and a small shaft bearing 32. The small shaft permanent magnet 28 is rigidly connected to the connecting small shaft 30 for the sail plate through a small shaft permanent magnet bracket 29, and the two are supported by the small shaft bearing 32 on the small shaft stator assembly.

[0041] Power transmission process: When the small shaft coil 31 is energized, the generated electromagnetic field directly drives the small shaft permanent magnet 28 and the small shaft permanent magnet bracket 29 fixed thereto, and the small shaft 30 connected to the sail plate to rotate around the Y axis.

[0042] Force constraint: The small shaft cover 33 presses the small shaft bearing 32 axial clearance by the small shaft cover fixing screw 34, and the end of the connecting small shaft 30 of the sailboard is locked by the connecting small shaft fixing screw 35 to the two-dimensional rotating sailboard.

[0043] The technical advantages and innovations of the two-dimensional solar panel drive mechanism are as follows: Advantages of direct drive structure: Zero backlash transmission: The motor rotor is directly and rigidly connected to the two-dimensional rotating sail, eliminating mechanical transmission backlash and achieving positioning accuracy at the micron level. High dynamic response: There is no intermediate transmission loss, power transmission efficiency ≥95%, and dynamic response speed is improved by 30%.

[0044] Extremely simplified structure: Eliminating complex components such as gearboxes reduces volume by 40%, improves reliability, and reduces maintenance costs by 60%. Low noise and energy saving: No gear friction, operating noise <45dB; permanent magnet synchronous technology reduces energy consumption by 20%.

[0045] Dual-axis collaborative innovation: The independent drive design of the large and small axes realizes decoupled motion control of the Z / Y axes, which is suitable for precision scenarios with multiple degrees of freedom. It adopts "magnetic field regulation" technology (such as dynamic demagnetization control) to optimize the start-stop smoothness of the large axis and avoid mechanical shock.

[0046] Lightweight and integrated design: The layout of the outer rotor (such as the intermediate rotating housing 26) and the permanent magnet mounting bracket 22 shortens the axial length, making it suitable for space-constrained systems. The integrated mounting bracket design (such as the upper mounting flange 17 and the lower mounting flange 25) enhances the overall structural rigidity and adapts to high-load conditions.

[0047] like Figure 8 As shown, during satellite production, launch preparation, and launch vehicle flight phases, the two-dimensional solar panel drive mechanism within the two-dimensional solar panel drive module 4 utilizes the residual magnetic force generated by permanent magnets to achieve ground self-locking in a power-free state, forming a rigid support structure. At this time, all modules jointly bear the vibration and impact loads during launch, ensuring the overall structural stability of the satellite. While meeting the satellite's load-bearing function, this reduces the structural weight to 15% of the total satellite weight.

[0048] like Figure 9 As shown, after the satellite enters its predetermined orbit, the satellite unlocking command triggers the two-dimensional solar panel drive mechanism to release its locked state, enabling the satellite's two-dimensional solar panel to move with two degrees of freedom. When the satellite is in orbit, the drive shaft 16 can rotate the solar panel 360° along the Y-axis and Z-axis respectively, depending on the direction of solar orientation. The solar panel can be rotated 360° without the satellite needing to adjust its attitude. This ensures that the satellite obtains sufficient energy while avoiding the problem of unstable attitude or insufficient angle when the solar panel is facing the sun, which is common in traditional satellite configurations. This makes the satellite attitude more stable and significantly improves navigation accuracy.

[0049] The six-segment stacked integrated navigation satellite structure described in this embodiment, adapted for mass production, not only meets the functional requirements of navigation satellites but is also suitable for mass production, significantly improving production efficiency. After satellites using this invention were launched into orbit, long-term operational monitoring showed that all modules functioned normally, satellite attitude control was precise, and the receiving and transmitting antennas were accurately pointed, effectively meeting navigation service requirements and fully verifying the feasibility and superiority of the technical solution of this invention.

[0050] Integrated design of single-unit structure and module structure: By integrating the functional units of each module with the load-bearing structure of the module, the dual function of single-unit operation and mechanical load-bearing is achieved. Taking the two-dimensional solar panel drive module as an example, its transmission mechanism is designed synchronously with the module frame, undertaking both equipment functions (such as solar panel drive and positioning) and serving as part of the overall satellite load-bearing frame, eliminating the need for separately designed load-bearing components. This design reduces the weight of structural components to 15% of the total satellite weight, a reduction of approximately 40% compared to traditional solutions, significantly improving structural efficiency and overall satellite performance. During satellite operation in orbit, the two-dimensional solar panel drive module can accommodate the two-degree-of-freedom motion of the solar panels, enabling 360° rotation of the solar panels while maintaining a relatively constant satellite attitude. This improves the satellite's solar energy utilization rate and avoids the instability or insufficient angle of the solar panels when aligned with the sun, a problem common in traditional satellite configurations. This results in a more stable satellite attitude and significantly improved navigation accuracy.

[0051] The embodiments of the present invention disclosed above are merely illustrative of the invention. These embodiments do not exhaustively describe all details, nor do they limit the invention to the specific implementations described. Many modifications and variations can be made based on the content of this specification. This specification selects and specifically describes these embodiments to better explain the principles and practical applications of the invention, thereby enabling those skilled in the art to better understand and utilize the invention.

Claims

1. A six-segment stacked integrated navigation satellite structure suitable for mass production, characterized in that: The system includes the upper load compartment (1), the integrated electrical compartment (2), the attitude control compartment (3), the two-dimensional solar panel drive compartment (4), the propulsion compartment (5), and the lower load compartment (6) connected in sequence. Each compartment is equipped with inter-compartment locking blocks (9) and inter-compartment locking slots (10) for positioning and locking. Each compartment is fixed as a whole by a fixing device. The two-dimensional sailboard drive cabin (4) includes a two-dimensional sailboard drive mechanism, a drive shaft (16) and a two-dimensional rotating sailboard. The two-dimensional sailboard drive mechanism is connected to the two-dimensional rotating sailboard through the drive shaft (16). The two-dimensional sailboard drive mechanism is used to drive the drive shaft (16) to drive the two-dimensional rotating sailboard to rotate in two dimensions.

2. The six-segment stacked integrated navigation satellite structure adapted for mass production according to claim 1, characterized in that: The fixing device includes several high-strength titanium alloy long bolts (8), which pass through the upper load compartment (1), the integrated electrical compartment (2), the attitude control compartment (3), the two-dimensional sail drive compartment (4), the propulsion compartment (5), and the lower load compartment (6) in sequence, and are fixed by nuts.

3. The six-segment stacked integrated navigation satellite structure adapted for mass production according to claim 1, characterized in that: The fixing device also includes several high-strength titanium alloy short bolts (7), and each compartment is initially connected and positioned by the high-strength titanium alloy short bolts (7).

4. The six-segment stacked integrated navigation satellite structure adapted for mass production according to claim 1, characterized in that: The upper payload compartment (1) is equipped with a receiving antenna and has the function of receiving signals. The lower payload compartment (6) is equipped with a transmitting antenna and has the function of transmitting signals. The integrated electronics compartment (2) is equipped with integrated electronic equipment and a power controller and has the function of satellite electronic control and processing. The attitude control compartment (3) is equipped with satellite attitude control equipment and has the function of satellite attitude control. The two-dimensional solar panel drive compartment (4) is equipped with solar panels and solar panel drive equipment and has the function of solar panel rotation. The propulsion compartment (5) is equipped with a Hall electric propulsion system and has the function of satellite orbit maintenance and orbit change.

5. The six-segment stacked integrated navigation satellite structure adapted for mass production according to claim 1, characterized in that: The two-dimensional sailboard drive mechanism is locked in the ground state. The transmission shaft (16) is the main load-bearing component that transmits mechanical loads. When running on the rail, it is unlocked and drives the two-dimensional rotating sailboard to rotate in two dimensions. The two-dimensional sailboard drive mechanism uses the residual magnetism generated by the permanent magnet to make the sailboard drive mechanism self-locked on the ground in the absence of electricity.

6. The six-segment stacked integrated navigation satellite structure adapted for mass production according to claim 1, characterized in that: The drive structure includes a large shaft drive system and a small shaft drive system. The large shaft drive system drives the large shaft rotating bracket (23) to rotate 360° around the Z-axis, and the small shaft drive system drives the small shaft (30) connecting the sailboard to rotate 360° around the Y-axis, so as to realize the two axes of the two-dimensional rotating sailboard to rotate 360°.

7. The six-segment stacked integrated navigation satellite structure adapted for mass production according to claim 6, characterized in that: The main shaft drive system includes a main shaft stator assembly and a main shaft rotor assembly. The main shaft stator assembly is rigidly connected to the cabin frame to form a stationary base. The main shaft rotor assembly is supported on the main shaft stator assembly and can rotate freely around the Z-axis. It is also rigidly connected to the main shaft rotation bracket (23). The secondary shaft drive system includes a secondary shaft stator assembly and a secondary shaft rotor assembly. The secondary shaft stator assembly is rigidly connected to the cabin frame to form a stationary base. The secondary shaft rotor assembly is supported on the secondary shaft stator assembly and can rotate freely around the Y-axis. It is also rigidly connected to the connecting sail secondary shaft (30).

8. The six-segment stacked integrated navigation satellite structure adapted for mass production according to claim 7, characterized in that: The main shaft stator assembly includes an upper fixed flange (17), a fixed ring (18), a main shaft permanent magnet (21), a permanent magnet fixing bracket (22), and a lower fixed flange (25). The main shaft permanent magnet (21) and the permanent magnet fixing bracket (22) are fixed to form a stationary permanent magnet unit. This unit is rigidly connected to the upper fixed flange (17) through the fixed ring (18). The upper fixed flange (17) is connected to the attitude control cabin (3), and the lower fixed flange (25) is fixedly connected to the propulsion cabin (5). The main shaft rotor assembly includes a main shaft coil (19), a main shaft rotating bracket (23), a main shaft bearing (24), and an intermediate rotating housing (26). The main shaft coil (19) is rigidly connected to the intermediate rotating housing (26) through the main shaft rotating bracket (23) and supported on the lower fixed flange (25) through the main shaft bearing (24), and can rotate freely around the Z-axis.

9. The six-segment stacked integrated navigation satellite structure adapted for mass production according to claim 8, characterized in that: The small shaft stator assembly includes a small shaft coil bracket (27) and a small shaft coil (31). The small shaft coil bracket (27) is fixed to the intermediate rotating housing (26), and the small shaft coil (31) is embedded inside the small shaft coil bracket (27). The small shaft rotor assembly includes a small shaft permanent magnet (28) and a connecting sail small shaft (30), wherein the small shaft permanent magnet (28) is rigidly connected to the connecting sail small shaft (30).

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