Kilometer-level super-large scale space integrated base and on-orbit construction method thereof

Abstract

This invention provides a kilometer-scale ultra-large-scale space integrated base and its on-orbit construction method. The kilometer-scale ultra-large-scale space integrated base is a fullerene-shaped support structure assembled from several modular satellites through on-orbit docking. Each modular satellite includes several telescopic arms and several node satellites interconnected by these arms. The kilometer-scale ultra-large-scale space integrated base has strong scalability, enabling the deployment, upgrading, or replacement of various functional payloads in orbit, achieving integrated detection functions, and improving the utilization rate of the platform's common systems. Attitude control is relatively simple, and it features high load capacity, high power, high heat dissipation, and long lifespan, with a large illuminated area and abundant energy. It breaks through the carrying capacity of existing launch vehicles, solving the fundamental problem of spacecraft efficiency limitations caused by a single launch.

Description

Technical Field

[0001] This invention relates to the aerospace field, specifically to a method for constructing a kilometer-scale ultra-large-scale integrated space base in orbit. Background Technology

[0002] With the development of international space programs and humanity's in-depth exploration of the universe, the demand for ultra-large-scale space structures is becoming increasingly urgent, such as ultra-large-scale space stations, ultra-large-scale space telescopes, and ultra-large-scale satellite platforms. The application of ultra-large-scale space structures can broaden humanity's perspective on the cosmos, extending the boundaries of human civilization from land, ocean, and atmosphere to outer space. Furthermore, they can serve as space infrastructure for developing and utilizing outer space and advancing space technology. Currently, the development of ultra-large-scale space structures still faces the following challenges:

[0003] (1) Due to the limitations of the capabilities of existing launch vehicles, it is impossible to deploy ultra-large-scale structures through a single launch. Ordinary spacecraft launched in a single launch have a single and clear mission and cannot carry too many scientific instruments and equipment for scientific research activities.

[0004] (2) The technical performance of ultra-large-scale structural platforms is developing towards large capacity and high power, which also brings greater challenges to the power supply. For example, for power requirements of several hundred kilowatts, if the power generation efficiency of solar cells is 200-300W per square meter, then hundreds of square meters of solar panel area are required. If a conventional solar panel design is adopted, its structural fundamental frequency will be lower than 1Hz or even 0.1Hz, which will cause the solar panel to couple with the spacecraft's attitude control system and easily cause resonance.

[0005] (3) Traditional large space stations and large satellite structural platforms are mostly closed polyhedrons, such as square prisms, hexagonal prisms, cylinders or cones. The overall structure of the spacecraft is relatively complex, making it difficult to achieve on-orbit maintenance of internal payloads.

[0006] In summary, the primary task for ultra-large-scale space structures should be to overcome the limitations of launch vehicle transport capacity. Furthermore, on-orbit scalable and maintainable designs should be considered, and the advantages of their ultra-large scale should be leveraged to deploy diverse payloads and achieve comprehensive detection capabilities. Summary of the Invention

[0007] To overcome the above-mentioned technical defects, the first aspect of the present invention provides a kilometer-scale ultra-large-scale space complex, which is a fullerene configuration support structure assembled by on-orbit docking of several modular stars. Each modular star includes several telescopic arms and several node stars interconnected through the telescopic arms.

[0008] Furthermore, the fullerene configuration support structure is a highly uniform and spherical hollow structure composed of 32 modular stars. The 32 modular stars include 12 pentagonal modular stars and 20 hexagonal modular stars. Each pentagonal modular star includes five telescopic arms and five node stars connected in series through the telescopic arms. Each hexagonal modular star includes six telescopic arms and six node stars connected in series through the telescopic arms. The 32 modular stars together include 60 node stars and 90 telescopic arms. When all the telescopic arms are fully extended, the fullerene configuration support structure includes 12 regular pentagonal facets and 20 regular hexagonal facets.

[0009] Furthermore, the telescopic arm has a maximum length of 30m after unfolding, and the constructed fullerene space base has a radius of 72m and a surface area of ​​up to 60,000m². 2 The volume is 1,500,000 m³ 3 .

[0010] Furthermore, the node star consists of cell stars, a propulsion module, and an active docking mechanism. The node star is a regular hexagonal prism composed of six prismatic cell stars. The cell stars are capable of on-orbit replacement (the cell stars have standard interfaces and can be replaced on-orbit using a robotic arm; the propulsion module controls attitude and orbit, and contains fuel and thrusters; after fuel depletion, it can be replaced or refueled on-orbit). The node star has several extension panels for mounting the telescopic arm, the active docking mechanism, and the propulsion module. The telescopic arm includes the telescopic mechanism body and the passive docking mechanism. The root of the telescopic arm is fixed to the cell star panel, and docking is achieved using a cone-and-rod type docking mechanism. The cone-and-rod type docking mechanism is one of the common docking mechanism types in this field. For example, the active rod head installed on the node star inserts into the bottom slot of the passive cone installed at the end of the telescopic arm to achieve the capture function.

[0011] Furthermore, some or all of the modular satellites each include a central parent satellite, which is fixedly connected to the node satellites of its respective modular satellite via telescopic arms. Each modular satellite consists of 5 or 6 node satellites and a central parent satellite fixedly connected via telescopic arms. During launch, the telescopic arms are in a folded-back state to improve the utilization of the fairing envelope space. After launch and orbit insertion, the node satellites coordinate their flight to the target position, simultaneously extending the telescopic arms to achieve on-orbit deployment of the modular satellite. Furthermore, the kilometer-scale ultra-large-scale space integrated base further includes service payloads, which are mounted on a fullerene-structured support structure. As a platform for various payloads, the kilometer-scale ultra-large-scale space integrated base deploys service utility systems, such as solar cells, propulsion modules, and ground-based antennas, providing unified energy, attitude control, and other services to the payloads. For example, some modular satellites carry functional payloads or payloads, such as solar cells and antennas. This application does not limit the specific location of the service load on the fullerene configuration support structure. For example, the service load may be located in the central parent star, nodal star, telescopic rod, or the hollow interior of the fullerene configuration support structure, depending on the actual situation.

[0012] Furthermore, the service payload includes an energy system, a ground communication system, and an attitude and orbit control system, thereby establishing a comprehensive public service system for the space base.

[0013] A second aspect of the present invention provides an on-orbit construction method for the aforementioned kilometer-scale ultra-large-scale space complex, comprising:

[0014] Step S1: Launch the module satellite to the predetermined orbit in multiple launches; the telescopic arm is in a folded and retracted state during the launch phase to improve the utilization rate of the fairing envelope space;

[0015] Step S2: On-orbit assembly of the modular satellite into a fullerene-shaped support structure: After launch and orbit insertion, the nodal satellites of the modular satellite coordinately control their flight to the target position, simultaneously extending their telescopic arms to achieve on-orbit deployment of the modular satellite. On-orbit docking is achieved through the docking mechanism between the nodal satellites and the telescopic arms, thus realizing on-orbit assembly and reliable connection of the modular satellite. The root of the telescopic arm is fixedly connected to the cell satellite's panel. Because the deployment of the telescopic arm occurs during the autonomous flight of the cell satellite, no additional drive device is required.

[0016] In step S2, the module satellite utilizes the navigation and ranging equipment on the docking satellite to achieve rendezvous and approach between the two module satellites, and then uses a cone-rod type docking mechanism to complete the docking. Rendezvous and docking is a conventional technology in this field. For example, the active rod head installed on the node satellite inserts into the bottom slot of the passive cone installed at the end of the telescopic arm to achieve the capture function. During the docking process, the impact energy is absorbed by the longitudinal buffer, the deflection energy is consumed by the deformation of the active rod of the docking mechanism and other parts, and finally, the 12 pairs of docking locks arranged on the hard docking ring achieve its locking function.

[0017] Further, in step S1: the fullerene configuration support structure includes 12 pentagonal module stars and 20 hexagonal module stars. The 20 hexagonal module stars are launched into the predetermined orbit in multiple launches. The telescopic arms of the hexagonal module stars are in a folded and retracted state during the launch phase.

[0018] Step S2: The 20 hexagonal modular stars are assembled in orbit into a fullerene configuration support structure: After launch and entry into orbit, the node stars of the 20 hexagonal modular stars are coordinated and controlled to fly to the target position. At the same time, the telescopic arms are extended to realize the in-orbit deployment of the modular stars. The in-orbit docking is achieved through the docking mechanism of the node stars and the telescopic arms to realize the in-orbit assembly and reliable connection of the modular stars. Thus, the in-orbit docking and assembly forms a fullerene configuration support structure with 12 pentagonal modular stars and 20 hexagonal modular stars.

[0019] In this scenario, the module stars launched into orbit are only hexagonal module stars in a collapsed state. Pentagonal module stars only form between these hexagonal module stars during subsequent near-interaction phases. In other words, of the 32 module stars, only a portion (20 hexagonal module stars) were launched into orbit; the remaining module stars (12 pentagonal module stars) formed later in orbit.

[0020] Further, in step S1: the fullerene configuration support structure includes 12 pentagonal module stars and 20 hexagonal module stars. The 12 pentagonal module stars are launched into the predetermined orbit in multiple launches. The telescopic arms of the pentagonal module stars are in a folded and retracted state during the launch phase.

[0021] Step S2: The 12 pentagonal module stars are assembled in orbit into a fullerene configuration support structure: After launch and entry into orbit, the node stars of the 12 pentagonal module stars are coordinated and controlled to fly to the target position. At the same time, the telescopic arms are extended to realize the in-orbit deployment of the module stars. The module stars are then docked in orbit through the docking mechanism of the node stars and the telescopic arms to realize the in-orbit assembly and reliable connection of the module stars. Thus, the module stars are assembled in orbit into a fullerene configuration support structure with 12 pentagonal module stars and 20 hexagonal module stars.

[0022] In this scenario, the module stars launched into orbit are initially pentagonal modules in a collapsed state. Hexagonal modules only form from these pentagonal modules during subsequent near-interaction phases. In other words, of the 32 module stars, only a portion (12 pentagonal modules) were launched into orbit; the remaining 20 hexagonal modules formed later within orbit.

[0023] Compared with existing technologies, the above technical solution has the following advantages:

[0024] This invention addresses the challenges of constructing ultra-large-scale space structures and space infrastructure by proposing an on-orbit method for building a kilometer-scale ultra-large-scale integrated space base. The integrated space base utilizes a fullerene configuration as its supporting framework. Due to launch capacity limitations, the base is modularly decomposed into 32 modular satellites. The kilometer-scale base is reconstructed in orbit through multiple launches and on-orbit assembly of these modular satellites. The on-orbit assembly and reliable connection of the modular satellites are achieved through on-orbit docking of the node satellites and the space telescopic arm. Furthermore, the space base, serving as a platform for various payloads, is equipped with service utility systems, such as solar panels, propulsion modules, and ground-based antennas, providing unified energy and attitude control services to the payloads.

[0025] (1) The kilometer-scale ultra-large-scale space integrated base is an ultra-large-scale space structure with strong scalability. It can deploy / upgrade / replace various functional payloads in orbit to achieve comprehensive detection functions.

[0026] (2) The kilometer-scale ultra-large space complex base adopts a fullerene structure composed of multiple basic units. Its interior is hollow, which makes it very convenient for on-orbit maintenance and on-orbit assembly.

[0027] (3) The kilometer-level ultra-large-scale space complex adopts a fullerene configuration, which is structurally stable, has a regular shape, and has a definite windward surface mass ratio. Compared with other ultra-large-scale space structures, its attitude control is less difficult. It has the characteristics of high load-bearing capacity, high power, high heat dissipation, and long life. It also has a large area exposed to light and sufficient energy.

[0028] (4) The kilometer-scale ultra-large space integrated base constructs ultra-large space infrastructure through modular on-orbit assembly, which breaks through the carrying capacity of existing launch vehicles and solves the fundamental problem of spacecraft efficiency limitation caused by a single launch.

[0029] (5) By deploying service payloads, such as solar cells and propulsion modules, on the space base, the energy attitude control problem of the payload can be solved in a unified manner, and the utilization rate of the platform common system can be improved. Attached Figure Description

[0030] Figure 1 This is a schematic diagram of the configuration of the kilometer-scale ultra-large-scale space complex of the present invention;

[0031] Figure 2 A schematic diagram of the structure of a hexagonal modular star in its collapsed state;

[0032] Figure 3 A schematic diagram of the structure of a hexagonal modular star in its unfolded state;

[0033] Figure 4 This is a schematic diagram of a nodal star structure;

[0034] Figure 5 This is a schematic diagram of the energy module star structure;

[0035] Figure 6 This is a schematic diagram of the orbit control and propulsion module satellite structure.

[0036] Figure 7 This is a schematic diagram of the telescope payload module star structure;

[0037] Figure 8 This is a schematic diagram of the module satellite approaching and rendezvous on orbit.

[0038] Figure 9 This is a schematic diagram of the overall structure of a kilometer-scale, on-orbit, assembleable space complex. Detailed Implementation

[0039] The advantages of the present invention are further illustrated below with reference to the accompanying drawings and specific embodiments. Those skilled in the art should understand that the specific description below is illustrative rather than restrictive and should not be construed as limiting the scope of protection of the present invention. Contents not described in detail in this specification are well-known to those skilled in the art.

[0040] like Figure 1 As shown, this embodiment provides a kilometer-scale ultra-large-scale space complex. This kilometer-scale ultra-large-scale space complex is a fullerene-shaped support structure assembled from several modular satellites 10 via in-orbit docking. Each modular satellite 10 includes several telescopic arms 11 and several node satellites 12 interconnected by the telescopic arms 11. The fullerene-shaped support structure is a hollow structure with uniform height and resembling a sphere, assembled from 32 modular satellites 10 via in-orbit docking. Figures 2-3 As shown, each module star 10 includes five or six telescopic arms 11 and node stars 12 interconnected by the telescopic arms 11. The 32 module stars 10 together comprise 60 node stars 12 and 90 telescopic arms 11, forming 12 regular pentagonal facets and 20 regular hexagonal facets. The maximum length of the telescopic arms 11 after unfolding is 30m, and the radius of the constructed fullerene space base is 72m, with a surface area of ​​up to 60,000 m². 2 The volume is 1,500,000 m³ 3 It can provide a supporting structure for a wide range of functional loads.

[0041] like Figure 4As shown, node star 12 consists of cell star 121, telescopic arm 11, propulsion module 122, and active docking mechanism 123. Node star 12 is a regular hexagonal prism composed of six prismatic cell stars 121. Cell stars 121 have on-orbit replacement capability. Node star 12 has several expansion panels for mounting telescopic arm 11, active docking mechanism 123, and propulsion module 122. Telescopic arm 11 includes a telescopic mechanism body and a passive docking mechanism. The root of telescopic arm 11 is fixedly connected to the cell star 121 panel and docking is achieved using a cone-rod type docking mechanism. The active rod head installed on the node star is inserted into the bottom slot of the passive cone installed at the end of the telescopic arm 11 to achieve the capture function.

[0042] Some or all of the module satellites 10 further include a central parent satellite 13, which is fixedly connected to the node satellites 12 of its respective module satellite 10 via telescopic arms 11. The module satellite 10 consists of 5 or 6 node satellites 12 and a central parent satellite 13 fixedly connected via telescopic arms 11, which are in a folded / retracted state during the launch phase (e.g., ...). Figure 2 As shown), to improve the utilization rate of the fairing envelope space, after launch and orbit insertion, node satellite 12 coordinates the flight to the target position, while simultaneously extending telescopic arm 11 (as shown). Figure 3 As shown in the figure, the on-orbit deployment of module star 10 is realized.

[0043] The kilometer-scale ultra-large-scale space base further includes service payloads, which are housed within a fullerene-structured support structure. As a platform supporting various payloads, the kilometer-scale ultra-large-scale space base deploys service utility systems, such as solar panels, propulsion module 122, and ground-reaching antennas, providing unified energy and attitude control services to the payloads. For example, some module satellites carry functional or payloads, such as solar panels and antennas. These service payloads include energy systems, ground-reaching communication systems, and maneuvering orbit control systems, thus establishing a comprehensive utility service system for the space base.

[0044] like Figure 5 To carry the deployable solar array, the modular satellite 10 has a solar array composed of several solar cell patches 30 laid on a flexible substrate 20 directly laid on top of the space telescopic arm 11, which serves as the main load-bearing structure, and connected in a reliable and stable manner, thereby significantly improving the system's rigidity. After entering orbit, the folded solar array unfolds in orbit as the telescopic arm 11 extends, covering the small plane constructed by the modular satellite 10, forming a 2000m... 2 The large surface area of ​​the solar panels, characterized by their large size, light weight, and high rigidity, provides ample energy for space bases. Figure 6 The module-10, which carries thrusters, can be replaced in orbit and installed on top of the six nodal satellites 12, providing orbital maneuverability for the space base. Figure 7 The module satellite 10 carries an on-orbit deployable antenna 40.

[0045] The on-orbit construction method for the aforementioned kilometer-scale ultra-large-scale space complex includes the following steps:

[0046] Step S1: Launch 20 hexagonal module satellites 10 into the predetermined orbit in multiple launches; the telescopic arms 11 of the hexagonal module satellites 10 are in a folded and retracted state during the launch phase to improve the utilization rate of the fairing envelope space; the telescopic arms 11 are in a folded and retracted state during the launch phase.

[0047] Step S2: On-orbit assembly of 20 hexagonal module satellites 10 into a fullerene configuration support structure: After launch and orbit insertion, the node satellites 12 of the 20 hexagonal module satellites 10 collaboratively control their flight to the target position, simultaneously extending the telescopic arm 11 to achieve on-orbit deployment of the module satellites 10. On-orbit docking is achieved through the docking mechanism of the node satellites 12 and the telescopic arm 11, realizing on-orbit assembly and reliable connection of the module satellites 10, thus forming a fullerene configuration support structure with 12 pentagonal module satellites 10 and 20 hexagonal module satellites 10. The root of the telescopic arm 11 is fixedly connected to the panel of the cell satellite 121. Since the deployment of the telescopic arm 11 is achieved during the autonomous flight of the cell satellite 121, no additional drive device is required. Module satellites 10 utilize the navigation and ranging equipment on the docking satellite to achieve rendezvous and approach between two module satellites 10 (e.g., Figure 8 As shown), a cone-rod type docking mechanism is used for docking. The active rod head installed on node 12 is inserted into the bottom slot of the passive cone installed at the end of the telescopic arm 11 to achieve the capture function. During the docking process, the impact energy is absorbed by the longitudinal buffer, and the deflection energy is consumed by the deformation of the active rod of the docking mechanism and some other parts. Finally, the docking lock arranged on the hard docking ring achieves its locking function. The assembled kilometer-scale super-large space complex base is as follows: Figure 9 As shown.

[0048] It should be noted that the embodiments of the present invention have better implementability and are not intended to limit the present invention in any way. Any person skilled in the art may use the above-disclosed technical content to change or modify it into equivalent effective embodiments. However, any modifications or equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall still fall within the scope of the technical solution of the present invention.

Claims

1. A kilometer-scale ultra-large-scale space complex, characterized in that: The kilometer-scale ultra-large space complex is a fullerene-shaped support structure assembled by on-orbit docking of several modular satellites. Each modular satellite includes several telescopic arms and several node satellites interconnected by the telescopic arms. The fullerene configuration support structure is a highly uniform, spherical hollow structure composed of 32 modular stars. The 32 modular stars include 12 pentagonal modular stars and 20 hexagonal modular stars. Each pentagonal modular star includes five telescopic arms and five node stars connected in series through the telescopic arms. Each hexagonal modular star includes six telescopic arms and six node stars connected in series through the telescopic arms. The 32 modular stars include a total of 60 node stars and 90 telescopic arms. When all the telescopic arms are fully extended, the fullerene configuration support structure includes 12 regular pentagonal facets and 20 regular hexagonal facets. The telescopic arm has a maximum length of 30m when extended, and the constructed fullerene space base has a radius of 72m and a surface area of ​​up to 60,000m². 2 The volume is 1,500,000 m³ 3 ; The node star consists of a cell star, a propulsion module, and an active docking mechanism. The node star is a regular hexagonal prism composed of six prismatic cell stars. The cell stars have the capability to be replaced in orbit. The node star has several extension panels for mounting telescopic arms, active docking mechanisms, and propulsion modules. The telescopic arms include a telescopic mechanism body and a passive docking mechanism located at the end of the telescopic mechanism body. The passive docking mechanism docks with the active docking mechanism on the cell star panel using a cone-rod type docking mechanism. The kilometer-scale ultra-large-scale space complex further includes service payloads, which are mounted on a fullerene-structured support structure. The service payloads include energy systems, ground communication systems, and maneuvering orbit control systems, thereby establishing a comprehensive public service system for the space base.

2. The kilometer-scale ultra-large-scale space complex as described in claim 1, characterized in that, Some or all of the module stars further include a central parent star, and the central parent star and the node stars of the module star to which it belongs are fixedly connected to each other through telescopic arms.

3. The on-orbit construction method of a kilometer-scale ultra-large-scale space complex as described in any one of claims 1 to 2, characterized in that, Step S1: The fullerene-shaped support structure comprises 12 pentagonal module stars and 20 hexagonal module stars. The 20 hexagonal module stars are launched into the predetermined orbit in multiple launches. The telescopic arms of the hexagonal module stars are in a folded and retracted state during the launch phase. Step S2: The 20 hexagonal module stars are assembled into the fullerene-shaped support structure in orbit: After launch into orbit, the nodal stars of the 20 hexagonal module stars are coordinated and controlled to fly to the target position. At the same time, the telescopic arms are extended to realize the in-orbit deployment of the module stars. The nodal stars and the telescopic arms are docked in orbit to realize the in-orbit assembly and reliable connection of the module stars, thereby assembling them in orbit to form a fullerene-shaped support structure with 12 pentagonal module stars and 20 hexagonal module stars.

4. The on-orbit construction method of a kilometer-scale ultra-large-scale space complex as described in any one of claims 1 to 2, characterized in that, Step S1: The fullerene-shaped support structure comprises 12 pentagonal module stars and 20 hexagonal module stars. The 12 pentagonal module stars are launched into the predetermined orbit in multiple launches. The telescopic arms of the pentagonal module stars are in a folded and retracted state during the launch phase. Step S2: The 12 pentagonal module stars are assembled into the fullerene-shaped support structure in orbit: After launch into orbit, the node stars of the 12 pentagonal module stars are coordinated and controlled to fly to the target position. At the same time, the telescopic arms are extended to realize the in-orbit deployment of the module stars. The module stars are docked in orbit through the docking mechanism of the node stars and the telescopic arms to realize the in-orbit assembly and reliable connection of the module stars, thereby assembling them in orbit into a fullerene-shaped support structure with 12 pentagonal module stars and 20 hexagonal module stars.

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