A lunar orbit space solar power station system

Abstract

This invention discloses a lunar orbit space solar power station system, belonging to the field of spacecraft structure and energy system technology. Addressing the problems of traditional solar power generation failure in the lunar polar shadow regions and the inability of existing space power station structures to adapt to the lunar orbit environment, a novel system is proposed, comprising: a double-layered box-type central truss made of carbon fiber composite material; 12 thin-film solar subarrays, achieving independent solar tracking via a first conductive rotary joint; 5 laser transmitting antenna subarrays, achieving precise pointing via a second conductive rotary joint; and a rotary connection module. The system adopts a tree-like topological multibody structure, allowing independent attitude adjustment of the solar energy collection and laser transmitting modules, achieving decoupling between solar tracking and laser pointing. This invention offers advantages such as modular on-orbit assembly, lightweight and high rigidity, and flexible vibration suppression, providing continuous wireless energy transmission to the lunar polar regions.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft structure and energy system technology, and relates to a lunar orbit space solar power station system. Background Technology

[0002] The lunar polar shadow regions (SRs) contain abundant water ice resources and are key areas for the construction of future lunar bases. However, these regions are characterized by permanent darkness and extreme low temperatures, rendering traditional solar power generation methods completely ineffective. Energy supply has become a core bottleneck restricting long-term stays and large-scale exploration activities.

[0003] Space Solar Power Station (SPSS) technology offers an effective solution to the above problems: by converting solar energy into laser beams through a lunar polar orbit power station, the solar energy can be wirelessly transmitted over long distances to receiving equipment on the lunar surface, thus achieving continuous and stable wireless power supply.

[0004] Existing space solar power station designs are mainly designed for Earth orbit applications, and their structural configurations are difficult to adapt directly to the lunar orbit environment. The engineering of the Low Lunar Orbit Solar Power Satellite System (LLO-SPSS) faces the following structural challenges: (1) The large-scale flexible structure has high on-orbit assembly complexity, making it difficult to achieve modular expansion; (2) The solar cell array and laser transmitting antenna lack independent pointing capability, limiting energy collection and transmission efficiency; (3) The flexible truss is susceptible to low-frequency vibrations caused by lunar gravity and thermal disturbances during on-orbit operation, resulting in laser pointing deviation; (4) The system has a huge mass, which imposes stringent requirements on lightweight and high-rigidity structural design. Summary of the Invention

[0005] To address the aforementioned technical problems, this invention proposes a novel lunar orbital space solar power station system, comprising: a central truss module, a solar energy collection module, a laser emission module, and a rotating connection module;

[0006] The central truss module includes a rigid central truss, interface nodes, and a base platform. The interface nodes are distributed at both ends and the middle of the central truss and are used to connect the solar energy collection module and the laser emission module. The base platform is located at the center of mass of the central truss and is used to install attitude control and energy management equipment.

[0007] The solar energy collection module includes a thin-film solar subarray, a subarray frame, and a first conductive rotary joint. The thin-film solar subarray is symmetrically arranged around the central truss through the first conductive rotary joint. The first conductive rotary joint enables the thin-film solar subarray to rotate one-dimensionally around the X-axis for solar tracking. The subarray frame is made of lightweight carbon fiber rods to form a mesh support structure, which provides tension for the thin-film solar subarray to maintain its planar shape.

[0008] The laser emitting module includes a laser emitting antenna array, an antenna support frame, and a second conductive rotating joint. The laser emitting antenna subarray is arranged at one end of the central truss via the second conductive rotating joint. The second conductive rotating joint enables the laser emitting antenna array to rotate around a direction parallel to the X-axis for precise pointing at lunar targets. The laser emitting antenna array is arranged in a corresponding layout with the thin-film solar subarray. Each laser emitting antenna subarray receives energy input from 2-3 thin-film solar subarrays. The antenna support frame adopts the same carbon fiber rod mesh structure as the solar subarray, and internally arranges the laser emitting unit and beamforming optical system.

[0009] The rotary connection module includes a joint drive mechanism, an angle encoder, and a locking device. The joint drive mechanism is used to drive the first conductive rotary joint and the second conductive rotary joint. The angle encoder is a photoelectric absolute encoder that provides real-time feedback on the joint rotation angle position. The locking device is activated after the joint reaches the target position to temporarily solidify the rotary joint into a fixed connection.

[0010] The system adopts a tree-like topological multibody structure, with a rigid central truss as the root node. The solar energy collection module is connected through a first conductive rotary joint to form a first-level branch, and the laser emission module is connected through a second conductive rotary joint to form a second-level branch. The solar energy collection module and the laser emission module can be independently adjusted in attitude to achieve decoupled control of solar tracking and laser pointing.

[0011] The advantages of this invention compared to existing technologies are as follows: It adopts an "integrated collection and transmission" configuration, integrating solar energy collection and laser emission functions onto the same platform, reducing energy conversion and transmission links; it employs a double-layer box-type central truss made of carbon fiber composite material, achieving structural lightweighting while ensuring high rigidity; it uses conductive rotary joints to achieve independent solar tracking of the solar subarray, improving energy collection efficiency; it uses pointing joints to achieve precise pointing of the laser emission antenna, meeting the requirements for micro-radius-level beam alignment; it adopts a flexible structural design based on modal synthesis, taking into account both the dynamic characteristics and on-orbit stability of large flexible accessories; and it employs a tree-like topology multibody structure, supporting modular on-orbit assembly and system expansion, possessing excellent mission adaptability. Attached Figure Description

[0012] Figure 1This is an overall structural diagram of the lunar orbit space solar power station system of the present invention.

[0013] Figure 2 This is a structural schematic diagram of the central truss module of the present invention.

[0014] Figure 3 This is a structural diagram of the laser emission module of the present invention.

[0015] Figure 4 This is a schematic diagram of the rotary connection module of the present invention.

[0016] The components include: 1. Rigid central truss; 2. Base platform; 3. Angle encoder; 4. Thin-film solar subarray; 5. Subarray frame; 6. First conductive rotary joint; 7. Laser transmitting antenna; 8. Antenna support frame; 9. Second conductive rotary joint; 10. Reinforcing ribs; 11. Carbon fiber housing. Detailed Implementation

[0017] Exemplary embodiments of the present disclosure will now be described in more detail with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be implemented in various forms and should not be limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art.

[0018] like Figure 1 As shown, a lunar orbit space solar power station system includes a central truss module, a solar energy collection module, a laser emission module, a rotary connection module, and a flexible support module.

[0019] like Figure 2 As shown, the central truss module includes a rigid central truss 1 and a base platform 2. The rigid central truss 1 adopts a double-layer box structure design of carbon fiber composite material, which is composed of two nested layers of carbon fiber boxes 11, with reinforcing ribs 10 connecting the layers. The overall length is 200m, the cross-sectional dimensions are 8m×8m, and the mass is 8000kg. The interface nodes are distributed at both ends and the middle of the rigid central truss 1, and are used to connect the solar energy collection module and the laser emission module. The base platform 2 is located at the center of mass of the rigid central truss 1 and is used to install attitude control and energy management equipment.

[0020] The solar energy collection module includes a thin-film solar subarray 4, a subarray frame 5, and a first conductive rotating joint 6; the thin-film solar subarray 4 consists of 12 subarrays, each measuring 100m × 10m, employing thin-film photovoltaic cell technology, with a total area of ​​0.12km². 2 The total mass is 36,000 kg, and the surface density is less than 1 kg / m³. 2Twelve thin-film solar subarrays 4 are symmetrically arranged around the rigid central truss 1 via the first conductive rotary joint 6, with five subarrays on each side (top and bottom) and one on each side (left and right). The first conductive rotary joint 6 enables one-dimensional rotation of the solar subarrays around the X-axis for solar tracking. The conductive rotary joint uses conductive slip rings to ensure continuous power transmission while achieving mechanical rotation, transmitting power to the central truss and laser emission module. The subarray frame 5 uses lightweight carbon fiber rods to form a mesh support structure, providing tension for the thin-film solar subarrays 4 to maintain their planar shape.

[0021] like Figure 3 As shown, the laser emitting module includes a laser emitting antenna 7, an antenna support frame 8, and a second conductive rotating joint 9. The laser emitting antenna 7 has five subarrays, each measuring 10m × 10m, with a total mass of 6000kg and an areal density of less than 12kg / m². 2 Five laser transmitting antenna subarrays are arranged at one end of the rigid central truss 1 via a second conductive rotating joint 9, forming an "integrated collection and transmission" configuration with the solar energy collection module. The second conductive rotating joint 9 enables the laser transmitting antenna 7 to rotate about a direction parallel to the X-axis, used for precise pointing at lunar targets. The laser transmitting antenna 7 is arranged correspondingly to the thin-film solar subarray 4, with each laser transmitting antenna subarray receiving energy input from 2-3 solar subarrays. The antenna support frame 8 adopts the same carbon fiber rod mesh structure as the solar subarray, and internally houses the laser transmitting unit and beamforming optical system. The laser pointing accuracy of the laser transmitting antenna 7 is better than 100 μrad, and the steady-state pointing error is less than 5 μrad.

[0022] The first natural frequency of the solar energy collection module is designed to be 0.05 Hz, corresponding to the first out-of-plane bending vibration mode; the first natural frequency of the laser emission module is designed to be 0.08 Hz, corresponding to the torsional vibration mode.

[0023] like Figure 4 As shown, the rotary connection module includes a joint drive mechanism, an angle encoder 3, and a locking device. The joint drive mechanism is used to drive the first conductive rotary joint 6 and the second conductive rotary joint 9 to rotate. It is equipped with a precision reduction mechanism driven by a stepper motor, and the rotational accuracy is better than 0.01°. The angle encoder 3 adopts a photoelectric absolute encoder to provide real-time feedback on the joint rotational position. The locking device is activated after the joint reaches the target position, temporarily fixing the rotary pair into a fixed connection.

[0024] The flexible support module includes a constrained modal structure, interface connection points, and a damping and vibration reduction device. The constrained modal structure is designed based on the Craig-Bampton modal synthesis method, which decomposes the flexible body motion of the solar energy collection module and the laser emission module into a linear superposition of constrained modes and fixed interface regular modes. The interface connection points are located at the junction of the first conductive rotary joint and the thin-film solar subarray 4, and at the junction of the second conductive rotary joint 9 and the laser emission antenna 7, and are used to transmit force and torque loads. The damping and vibration reduction device uses viscoelastic damping material arranged at key nodes of the subarray frame 5 to suppress the transmission of low-frequency vibrations. The first natural frequency of the solar energy collection module is 0.05Hz, and the first natural frequency of the laser emission module is 0.08Hz.

[0025] The system adopts a tree-like topology multibody structure, with the rigid central truss 1 as the root node. The solar energy collection module is connected through the first conductive rotary joint 6 to form the first-level branch, and the laser emission module is connected through the second conductive rotary joint 9 to form the second-level branch. Both the solar energy collection module and the laser emission module can be independently adjusted in attitude.

[0026] The system operates in a lunar polar orbit at an altitude of 100km with an inclination of 90°, achieving continuous coverage of the lunar polar regions. The central truss module adopts a modular design, consisting of multiple 10m-class standard sections spliced ​​together in orbit. Both the solar energy collection module and the laser emission module are designed with standardized mechanical interfaces to support in-orbit replacement and maintenance.

[0027] The overall unfolded dimensions of the system are 220m × 110m × 20m, and the total mass is 50,000kg.

[0028] The system supports multi-module collaborative networking. Multiple identical lunar orbit space solar power station systems can be arranged at intervals in the same orbital plane to form an energy transmission network, achieving continuous power supply coverage to multiple target points on the lunar surface.

[0029] When using this invention, the standard section of the central truss module is first launched into lunar orbit by a launch vehicle and assembled in orbit. Then, the solar energy collection module and the laser emission module are transported to the orbit in sequence and connected to the central truss module through a standard interface. After the system is deployed, the solar energy collection module adjusts its attitude through the first conductive rotary joint 6 to achieve solar orientation and convert solar energy into electrical energy. The electrical energy is transmitted to the laser emission module through a conductive slip ring, driving the laser emission unit to generate a high-energy laser beam. The laser emission module adjusts its direction through the second conductive rotary joint 9 to accurately aim the laser beam at the lunar surface receiving station, realizing wireless energy transmission.

[0030] When maintenance or upgrades are needed, the solar energy collection module or laser emission module can be replaced individually by the spacecraft in orbit without decommissioning the entire system. When mission requirements expand, the system scale can be modularly expanded by adding standard sections of the central truss and corresponding functional modules.

[0031] Although the invention has been described with respect to a limited number of embodiments, those skilled in the art will understand from the foregoing description that other embodiments are conceivable within the scope of the invention described herein. Furthermore, it should be noted that the language used in this specification has been chosen primarily for readability and instructional purposes, and not for the purpose of explaining or limiting the subject matter of the invention.

Claims

1. A lunar orbital space solar power station system, characterized in that, It includes a central truss module, a solar energy collection module, a laser emission module, and a rotary connection module; The central truss module includes a rigid central truss (1), interface nodes and a base platform (2). The interface nodes are distributed at both ends and the middle of the rigid central truss (1) and are used to connect the solar energy collection module and the laser emission module. The base platform (2) is located at the center of mass of the rigid central truss (1) and is used to install attitude control and energy management equipment. The solar energy collection module includes a thin-film solar subarray (4), a subarray frame (5), and a first conductive rotating joint (6). The thin-film solar subarray (4) is symmetrically arranged around the rigid central truss (1) through the first conductive rotating joint (6). The first conductive rotating joint (6) enables the thin-film solar subarray to rotate around the X-axis in one dimension for solar tracking. The subarray frame (5) is made of lightweight carbon fiber rods to form a mesh support structure, which provides tension for the thin-film solar subarray (4) to maintain its planar shape. The laser emitting module includes a laser emitting antenna (7), an antenna support frame (8), and a second conductive rotating joint (9). The laser emitting antenna subarray is arranged at one end of the rigid central truss (1) through the second conductive rotating joint (9). The second conductive rotating joint (9) enables the laser emitting antenna (7) to rotate around a direction parallel to the X-axis for precise pointing to lunar targets. The laser emitting antenna (7) is arranged in a corresponding manner with the thin-film solar subarray (4). Each laser emitting antenna subarray receives energy input from 2-3 thin-film solar subarrays. The antenna support frame (8) adopts the same carbon fiber rod mesh structure as the solar subarray, and the laser emitting unit and beamforming optical system are arranged inside. The rotary connection module includes a joint drive mechanism, an angle encoder (3) and a locking device. The joint drive mechanism is used to drive the first conductive rotary joint (6) and the second conductive rotary joint (9). The angle encoder (3) is a photoelectric absolute encoder that provides real-time feedback on the joint rotation position. The locking device is activated after the joint reaches the target position to temporarily solidify the rotary joint into a fixed connection. The system adopts a tree-like topology multibody structure with a rigid central truss (1) as the root node. The solar energy collection module is connected through the first conductive rotary joint (6) to form the first-level branch, and the laser emission module is connected through the second conductive rotary joint (9) to form the second-level branch. The solar energy collection module and the laser emission module are independently adjusted in attitude to achieve decoupled control of solar tracking and laser pointing.

2. The lunar orbit space solar power station system as described in claim 1, characterized in that, The rigid central truss (1) adopts a double-layer box structure design of carbon fiber composite material, which is composed of two layers of carbon fiber box (11) nested together, with reinforcing ribs (10) connected between the layers. The overall length is 200m, the cross-sectional size is 8m×8m, and the mass is 8000kg.

3. A lunar orbital space solar power station system as described in claim 1, characterized in that, The thin-film solar subarray (4) consists of 12 subarrays, each measuring 100m × 10m, employing thin-film photovoltaic cell technology, with a total area of ​​0.12km². 2 The total mass is 36,000 kg. The thin-film solar subarray (4) is symmetrically arranged around the rigid central truss (1) through the first conductive rotating joint (6), with 5 subarrays on each side above and below, and one on each side.

4. A lunar orbital space solar power station system as described in claim 1, characterized in that, The first conductive rotary joint (6) adopts a conductive slip ring, which ensures the continuity of power transmission while realizing mechanical rotation; the laser transmitting antenna (7) has 5 subarrays, each subarray is 10m×10m in size, and the total mass is 6000kg; the joint drive mechanism is equipped with a precision reduction mechanism driven by a stepper motor, and the rotation accuracy is better than 0.01°.

5. A lunar orbital space solar power station system as described in claim 1, characterized in that, The central truss module adopts a modular design and is composed of multiple 10m-class standard sections spliced ​​together on the track; the solar energy collection module and the laser emission module are both designed with standardized mechanical interfaces to support on-track replacement and maintenance.

6. A lunar orbital space solar power station system as described in claim 1, characterized in that, It also includes a flexible support module, which includes a constraint modal structure, interface connection points and a damping and vibration reduction device. The constraint modal structure is designed based on the Craig-Bampton modal synthesis method, which decomposes the flexible body motion of the solar energy collection module and the laser emission module into a linear superposition of constraint modes and fixed interface regular modes. The interface connection points are located at the junction of the first conductive rotary joint (6) and the thin-film solar subarray (4), and the junction of the second conductive rotary joint (9) and the laser emission antenna (7), transmitting force and torque loads. The damping and vibration reduction device uses viscoelastic damping material arranged at key nodes of the subarray frame (5) to suppress the transmission of low-frequency vibrations.

7. A lunar orbital space solar power station system as described in claim 4, characterized in that, The first natural frequency of the solar energy collection module is designed to be 0.05 Hz, corresponding to the out-of-plane first bending vibration mode; the first natural frequency of the laser emission module is designed to be 0.08 Hz, corresponding to the torsional vibration mode.

8. A lunar orbital space solar power station system as described in claim 1, characterized in that, The areal density of the thin-film solar subarray (4) is less than 1 kg / m². 2 The areal density of the laser transmitting antenna subarray is less than 12 kg / m². 2 .

9. A lunar orbital space solar power station system as described in claim 1, characterized in that, The overall unfolded dimensions of the system are 220m × 110m × 20m, and the total mass is 50,000kg.

10. A lunar orbital space solar power station system as described in claim 1, characterized in that, The laser pointing accuracy of the laser transmitting antenna (7) is better than 100 μrad, and the steady-state pointing error is less than 5 μrad.

11. A lunar orbital space solar power station system as described in claim 1, characterized in that... The system supports multi-module collaborative networking: multiple identical lunar orbit space solar power station systems are arranged at intervals in the same orbital plane to form an energy transmission network, achieving continuous power supply coverage to multiple target points on the lunar surface.

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