A super-large spacecraft platform system and on-orbit assembly method thereof

Abstract

The present invention provides a super-large spacecraft platform system, including: a plurality of sub-platforms, each of which has the same geometric configuration, and all of the sub-platforms form a super-large array to form a specific plane or curved surface; a core platform, which is responsible for the management and maintenance of the entire platform; a retaining system, which is used to maintain a fixed geometric relationship between the core platform and the super-large array. The present invention also provides a method for assembling the system on orbit. The technical solution of the present invention can solve the technical problems of the difficulties in platform assembly, transportation and maintenance in the prior art, and can flexibly expand or reduce the overall scale of the platform; a sub-platform that has failed can be separated from the entire platform system, and a new replacement sub-platform can be connected to the entire platform system, so the reliability of the entire platform system is greatly improved.

Description

Technical Field

[0001] The present invention relates to the field of spacecraft assembly, and in particular to an ultra-large spacecraft platform system and an on-orbit assembly method thereof. Background Art

[0002] If a spacecraft platform operating in Earth orbit is launched into orbit in one go, its weight and size are limited by the carrying capacity of the launch vehicle. Therefore, super-large Earth orbit platforms are all assembled in orbit. In the research of super-large platform programs abroad, space shuttles or launch vehicles are generally used to launch various parts of the platform in batches into low orbits near the space station. The robotic arm of the space station or astronauts are used to assemble the various parts of the platform into an integral structure in orbit, and then the orbital transfer vehicle is used to transport it to Earth orbit.

[0003] This super-large track platform is connected by a truss structure. Once assembled, the configuration of the platform cannot be changed, which has the following disadvantages:

[0004] (1) The platform is assembled in a low orbit and then transferred to a high orbit. The weight of the platform is restricted by the carrying capacity of the orbit transfer vehicle, and the overall size of the platform is limited. The platform structure must maintain sufficient rigidity and avoid structural vibration during the orbit change ignition. Therefore, it is difficult to design an ultra-large-scale flexible structure.

[0005] (2) During the platform's on-orbit operation, the on-orbit reconstruction problem was not considered, and maintenance in the event of a failure was very difficult. Once a platform failure occurred, it might cause the entire platform to fail. Summary of the invention

[0006] 1. Purpose:

[0007] In order to build a very large-scale Earth orbit platform with the ability to expand and reconstruct the platform, it is necessary to adopt a method of directly assembling very large-scale platforms in Earth orbit.

[0008] The present invention proposes a super-large spacecraft platform system and an on-orbit assembly method thereof. The super-large earth orbit platform is composed of a plurality of sub-platforms having the same geometric configuration. Each sub-platform can be directly launched into the earth orbit by a carrier and assembled in the earth orbit. By increasing or decreasing the number of sub-platforms, the overall scale of the platform can be flexibly expanded or reduced; a sub-platform that fails can be separated from the entire platform system, and a new replacement sub-platform can be connected to the entire platform system, so the reliability of the entire platform system is greatly improved. This patent is applicable to super-large geosynchronous orbit spacecraft.

[0009] 2. Technical solution:

[0010] The present invention provides a super-large spacecraft platform system, comprising:

[0011] A plurality of sub-platforms, each of which has the same geometric configuration, and all of the sub-platforms form a super-large array to form a specific plane or curved surface;

[0012] The core platform is responsible for the management and maintenance of the entire platform;

[0013] A retaining system is used to maintain a fixed geometric relationship between the core platform and the ultra-large array. For example, in order to achieve ground communication or electromagnetic wave reception, the ultra-large array composed of sub-platforms serves as an antenna reflection surface, and the core platform is located at the focus of the antenna, and is equipped with a feed source and electronic equipment to form a complete ultra-large-scale antenna.

[0014] Further, the holding system is a formation flight control system or a rope or rod connecting the core platform and the very large array.

[0015] Furthermore, the sub-platform includes:

[0016] a sub-platform body, on which an on-orbit system for orbital and attitude maneuvering and control on-orbit is disposed;

[0017] A double-layer hexagonal truss structure, which is configured to be foldable and expandable, includes six vertical poles of the same length, twelve horizontal poles of the same length, and six diagonal poles of the same length, wherein the length relationship of the vertical poles, the horizontal poles, and the diagonal poles can form a right triangle, wherein the length of the diagonal pole is the hypotenuse; wherein the twelve horizontal poles are respectively connected to form two regular hexagonal structures of equal size, the six vertical poles are parallel to each other, the upper end point and the lower end point of each vertical pole are respectively connected to the vertices of two upper and lower parallel regular hexagons formed by the twelve horizontal poles, the upper end point of each vertical pole is connected to the lower end point of the adjacent vertical pole via a diagonal pole, and the lower end points of all the vertical poles are respectively connected to the sub-platform body via a supporting rod;

[0018] Among them, all the above connections are hinged, and the cross bars and diagonal bars are telescopic.

[0019] Furthermore, two adjacent vertical poles and the cross bar connecting them form a rectangular surface, and the four end points of the two vertical poles are provided with docking devices for docking with the rectangular surface formed by any adjacent vertical poles of the other sub-platforms; each vertical pole is provided with a standard pluggable electrical interface, which can serve as a channel for power supply and information interaction.

[0020] Therefore, as long as some sub-platforms are equipped with large solar wings, they can provide power for other sub-platforms, and information exchange between all sub-platforms can be carried out through pluggable electrical interfaces.

[0021] Furthermore, the on-orbit system includes an energy system, a thermal control system, an intersatellite measurement and control system, a control system and a propulsion system.

[0022] Furthermore, a film is disposed on the upper surface of the double-layer hexagonal truss structure, and the material of the film can be selected according to work requirements.

[0023] By changing the properties of the film, it is possible to form ultra-large-scale antenna arrays, solar cell arrays or light reflecting surfaces, which can be used in space electromagnetic signal receiving systems, space solar power stations or space ultra-high resolution imaging systems.

[0024] The present invention also provides an on-orbit assembly method for assembling the above-mentioned super-large spacecraft platform system, comprising the following steps:

[0025] S1: Platform transportation and release, launching the core platform and the sub-platform into the Earth orbit by a transport aircraft, and releasing them from the transport aircraft to a predetermined orbital position;

[0026] The sub-platforms can be stored in an array inside a transport aircraft, so the transport aircraft can transport a large number of sub-platforms at a time, saving transportation costs.

[0027] S2: On-orbit assembly: After the sub-platform is released to the specified position, it is unfolded by the support rod, and the position is adjusted and docked by the on-orbit system to form an ultra-large array, and then connected to the core platform through the retention system.

[0028] Furthermore, step S2 specifically includes the following steps:

[0029] S2-1: After the core platform and sub-platform are released into the predetermined orbit, safe formation flight control is maintained;

[0030] S2-2: The sub-platform controls the support rod to extend outward, and the double-layer hexagonal truss structure gradually expands completely from the folded state to form a stable double-layer hexagonal structure;

[0031] S2-3: The relative position and attitude of the sub-platforms are controlled, and the poles of the double-layer hexagonal truss structure are connected and locked together to form a super-large array;

[0032] S2-4: By adjusting the length of the crossbar on the double-layer hexagonal truss structure, the super-large array is adjusted to the required curved structure;

[0033] S2-5: The core platform is connected to the very large array by maintaining the system and maintaining the geometric relationship connected to the very large array.

[0034] Furthermore, the method further comprises the following steps:

[0035] S3: On-orbit reconstruction. When a sub-platform needs to be ejected, its upright poles are unlocked from the upright poles of the adjacent sub-platform, and the support poles are controlled to retract inward, and the sub-platform is ejected from the super-large array through relative position maneuvers. When a sub-platform needs to be loaded, the sub-platform is adjusted to the target position through relative position maneuvers, and the support poles are controlled to unfold, and then docked with the adjacent sub-platform through the docking device.

[0036] Therefore, the very large array composed of sub-platforms can be reassembled in orbit to meet the needs of functional changes; in addition, a faulty sub-platform can be detached from the very large array and replaced with a new sub-platform to meet the needs of on-orbit maintenance.

[0037] 3. Effect

[0038] This method has the following advantages:

[0039] (1) The super-large earth orbit platform is composed of multiple sub-platforms with the same geometric configuration. Each sub-platform can be directly launched into the earth orbit by a carrier and assembled in the earth orbit.

[0040] (2) After the sub-platform is launched into orbit, a hexagonal honeycomb structure is unfolded, and a docking mechanism is installed on the hexagonal honeycomb structure. One sub-platform is connected to a maximum of six other sub-platforms with the same structure through six side edges.

[0041] (3) By connecting sub-platforms, very large earth orbital platforms of different configurations can be formed. By increasing or decreasing the number of sub-platforms, the overall scale of the platform can be flexibly expanded or reduced.

[0042] (4) The top surface of the hexagonal prism of the sub-platform can be configured with various films. By changing the film properties, an ultra-large-scale antenna array, solar cell array or light reflection surface can be formed for use in space electromagnetic signal receiving systems, space solar power stations or space ultra-high resolution imaging systems.

[0043] (5) Sub-platforms can be separated and reconnected, that is, the super-large earth orbit platform can be flexibly reconstructed in orbit.

[0044] (6) A failed sub-platform can be separated from the entire platform system, and a new replacement sub-platform can be added to the entire platform system, improving the maintainability of the ultra-large earth orbit platform. BRIEF DESCRIPTION OF THE DRAWINGS

[0045] Figure 1 A schematic diagram of a super large array in an embodiment of the present invention;

[0046] Figure 2 This is a schematic diagram of the system architecture of a very large earth orbit platform in an embodiment of the present invention;

[0047] Figure 3a This is a schematic diagram of the folded state of the sub-platform in the embodiment of the present invention;

[0048] Figure 3b This is a schematic diagram of the unfolded state of the sub-platform in an embodiment of the present invention;

[0049] Figure 4a This is a schematic diagram of the docking device before docking in an embodiment of the present invention;

[0050] Figure 4b It is a schematic diagram of the docking device after docking in an embodiment of the present invention. DETAILED DESCRIPTION

[0051] In order to make the technical solutions and advantages of the present invention clearer, the technical solutions of the embodiments of the present invention will be fully described below in conjunction with the drawings in the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0052] Embodiments of the present invention are described in detail below, and examples of the embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals throughout represent the same or similar elements or elements having the same or similar functions. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and cannot be understood as limiting the present invention.

[0053] The specific implementation process of the present invention is as follows:

[0054] (1) Platform system architecture: Figure 1 The very large earth orbit platform is composed of multiple sub-platforms with the same geometric configuration combined into a very large array to form a specific plane or curved surface. In addition, it also includes a core platform, which is responsible for the management and maintenance of the entire platform. The core platform and the very large array composed of sub-platforms maintain a fixed geometric relationship through formation flight control or ropes or rods. For example, in order to achieve ground communication or electromagnetic wave reception, the very large array composed of sub-platforms serves as the antenna reflector. The core platform is located at the focus of the antenna and is equipped with feed and electronic equipment to form a complete very large-scale antenna.

[0055] (2) Sub-platform composition: The sub-platform consists of a platform body and a foldable and deployable double-layer hexagonal truss structure. Figure 3a , the expanded state is as follows Figure 3bThe truss structure includes six vertical poles of the same length, and the upper and lower ends of each vertical pole are respectively connected to two horizontal poles of the same length and adjustable through hinges. In addition, the upper end of each vertical pole and the lower end of the corresponding vertical pole are connected to a telescopic inclined rod through a hinge, and the lower end of each vertical pole is connected to a support rod and connected to the platform body through a hinge. By controlling the support rod, the double-layer hexagonal truss structure can be folded and unfolded. Each vertical pole is equipped with a docking device, which can be docked with any vertical pole of other sub-platforms. Specifically, Figure 4a and Figure 4b As shown, two adjacent vertical poles and the crossbars connected therebetween form a rectangular surface, and the four ends of the two vertical poles are provided with docking devices for docking with the rectangular surface formed by any adjacent vertical poles of the other sub-platforms; the platform body of the sub-platform is equipped with energy, thermal control, intersatellite measurement and control, control, propulsion and other subsystems, and can perform orbit and attitude maneuvers and control on orbit; each vertical pole is installed with a standard detachable electrical interface, which can be used as a channel for power supply and information exchange, so as long as some sub-platforms are equipped with large solar wings, they can power other sub-platforms, and all information exchanges between sub-platforms can be exchanged through detachable electrical interfaces. The surface of the double-layer hexagonal truss structure of the sub-platform can be configured with various films, and the properties of the films can be changed to form an ultra-large-scale antenna array, solar cell array or light reflection surface, which is used for space electromagnetic signal receiving systems, space solar power stations or space ultra-high resolution imaging systems.

[0056] (3) Composition of the core platform: The core platform is equipped with three sub-platforms, which can be released or recovered by ropes. The three sub-platforms will be combined with other sub-platforms to form an ultra-large array structure. The three sub-platforms are located outside the ultra-large array structure. The core platform controls and maintains the geometric relationship with the ultra-large array structure by adjusting the length of the extended ropes to meet specific business needs.

[0057] (4) Platform transportation and release:

[0058] The core platform and each sub-platform are launched into the Earth orbit by a transport aircraft and released from the transport aircraft to a predetermined orbital position. The sub-platforms can be stored in an array inside the transport aircraft, so the transport aircraft can transport a large number of sub-platforms at a time, saving transportation costs.

[0059] (5) On-orbit assembly

[0060] After the core platform and sub-platforms are released to the predetermined orbit, they first maintain safe formation flight control, and then the sub-platform controls the support rods to extend outward, and the double-layer hexagonal truss structure gradually fully unfolds from the folded state to form a stable double-layer hexagonal structure. The sub-platforms perform relative position and attitude control, and the vertical poles of the double-layer hexagonal truss structure are connected and locked together to form a super-large array. By adjusting the length of the crossbar on the double-layer hexagonal truss structure, the super-large array can be adjusted to various curved structures. By fine-tuning the length of the crossbar on the double-layer hexagonal truss structure, the surface accuracy of the super-large array can be guaranteed to meet specific requirements. Figure 2 The core platform releases the three sub-platforms (S1, S2, and S3) installed on it through ropes. The three sub-platforms unfold stable double-layer hexagonal structures respectively, and through relative position and attitude control, they maneuver to the three edges of the assembled very large array and connect with adjacent sub-platforms. The core platform adjusts the length of the rope to control and maintain the geometric relationship with the very large array structure.

[0061] (6) On-orbit reconstruction:

[0062] The poles of each sub-platform can be unlocked from the poles of the adjacent sub-platforms. The platform body can be retracted inward by controlling the support poles. The double-layer hexagonal truss structure can be gradually fully retracted from the fully expanded state. The sub-platforms can be detached from the super-large array by maneuvering relative positions. Therefore, the super-large array composed of sub-platforms can be reassembled on-orbit to meet the needs of functional changes; in addition, the sub-platform that fails can be detached from the super-large array and replaced with a new sub-platform to meet the needs of on-orbit maintenance.

[0063] In a specific embodiment, assuming that an ultra-large antenna with a caliber of 100m is to be realized in the Earth orbit, the on-orbit assembly method of the ultra-large Earth orbit platform adopted in this patent is adopted, and the cross bar length of the double-layer hexagonal truss structure of the sub-platform is designed to be 3m, and the vertical bar length is 1m, then 110 sub-platforms are required for on-orbit assembly, and the antenna feed is installed on the core platform.

[0064] In the description of this specification, reference to the terms "one embodiment" and "example" means that the specific features, structures or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic representation of the above terms does not necessarily refer to the combination in a suitable manner in the relative embodiment or example.

[0065] It must be pointed out that the description of the above embodiments is not intended to be limiting but only to help understand the core idea of ​​the present invention. For ordinary technicians in this technical field, any improvements to the present invention and alternatives equivalent to the product, without departing from the principles of the present invention, also fall within the scope of protection of the claims of the present invention.

Claims

1. A super-large spacecraft platform system, characterized in that: include: A plurality of sub-platforms, each of which has the same geometric configuration, and all of the sub-platforms form a super-large array to form a specific plane or curved surface; The sub-platform includes: a sub-platform body, on which an on-orbit system for orbital and attitude maneuvering and control on-orbit is disposed; A double-layer hexagonal truss structure, which is configured to be foldable and expandable, includes six vertical poles of the same length, twelve horizontal poles of the same length, and six diagonal poles of the same length, wherein the length relationship of the vertical poles, the horizontal poles, and the diagonal poles can form a right triangle, wherein the length of the diagonal pole is the hypotenuse; wherein the twelve horizontal poles are respectively connected to form two regular hexagonal structures of equal size, the six vertical poles are parallel to each other, the upper end point and the lower end point of each vertical pole are respectively connected to the vertices of two upper and lower parallel regular hexagons formed by the twelve horizontal poles, the upper end point of each vertical pole is connected to the lower end point of the adjacent vertical pole via a diagonal pole, and the lower end points of all the vertical poles are respectively connected to the sub-platform body via a supporting rod; Wherein, all the above connections are hinged, and the crossbar and diagonal bar are retractable; Two adjacent vertical poles and the cross bar connecting them form a rectangular surface, and the four ends of the two vertical poles are provided with docking devices for docking with the rectangular surface formed by any adjacent vertical pole of the other sub-platform; each vertical pole is provided with a standard pluggable electrical interface, which can be used as a channel for power supply and information exchange; The on-orbit system includes an energy system, a thermal control system, an inter-satellite measurement and control system, a control system and a propulsion system; The core platform is responsible for the management and maintenance of the entire platform; A holding system is used to maintain a fixed geometric relationship between the core platform and the ultra-large array. In order to achieve ground communication or electromagnetic wave reception, the ultra-large array formed by the sub-platforms serves as an antenna reflection surface, and the core platform is located at the focus of the antenna, and is equipped with a feed source and electronic equipment, thereby forming a complete ultra-large-scale antenna; The holding system is a formation flight control system or ropes or rods connecting the core platform to the very large array.

2. The ultra-large spacecraft platform system according to claim 1, characterized in that: The surface of the double-layer hexagonal truss structure is provided with a film, and the material of the film can be selected according to work requirements.

3. An on-track assembly method, characterized in that: The method for assembling a very large spacecraft platform system according to any one of claims 1 to 2 comprises the following steps: S1: Platform transportation and release, launching the core platform and the sub-platform into the Earth orbit by a transport aircraft, and releasing them from the transport aircraft to a predetermined orbital position; S2: On-orbit assembly, after the sub-platform is released to the designated position, it is unfolded by the support rods, and its position is adjusted by the on-orbit system, and docked to form a super-large array, and then connected to the core platform by the retention system; Step S2 specifically includes the following steps: S2-1: After the core platform and sub-platform are released into the predetermined orbit, safe formation flight control is maintained; S2-2: The sub-platform controls the support rod to extend outward, and the double-layer hexagonal truss structure gradually expands completely from the folded state to form a stable double-layer hexagonal structure; S2-3: The relative position and attitude of the sub-platforms are controlled, and the poles of the double-layer hexagonal truss structure are connected and locked together to form a super-large array; S2-4: By adjusting the length of the crossbar on the double-layer hexagonal truss structure, the super-large array is adjusted to the required curved structure; S2-5: The core platform is connected to the very large array by maintaining the system and maintaining the geometric relationship connected to the very large array.

4. The method according to claim 3, characterized in that The following steps are also included: S3: On-orbit reconstruction. When a sub-platform needs to be ejected, its upright poles are unlocked from the upright poles of the adjacent sub-platform, and the support poles are controlled to retract inward, and the sub-platform is ejected from the super-large array through relative position maneuvers. When a sub-platform needs to be loaded, the sub-platform is adjusted to the target position through relative position maneuvers, and the support poles are controlled to unfold, and then docked with the adjacent sub-platform through the docking device.

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