Reconfigurable satellite platform and installation method thereof, and reconfigurable satellite

Abstract

The present invention provides a reconfigurable satellite platform and an installation method thereof, and a reconfigurable satellite, belonging to the field of aerospace technology. The reconfigurable satellite platform includes an expanded state, a semi-expanded state, and a folded state. In the expanded state, it presents a seven-unit structure, wherein the seven-unit structure is used to form interconnected cavities, and each surface of the remaining area is covered with a square panel, and adjacent panels are connected by hinges. In the semi-expanded state, a four-unit structure containing four peripheral cell units and a wing structure is formed. In the folded state, a zero-unit structure without a central cell unit and a peripheral cell unit is formed. The hinge includes a shape memory hinge, wherein the temporary shape of the shape memory hinge is an "L" shape and the initial shape is a "U" shape. The reconfigurable satellite platform provided by the present invention can realize a modular, flexible and lightweight reconfigurable satellite platform with a simple configuration process and easy assembly.

Description

Technical Field

[0001] The present invention relates to the field of aerospace technology, and in particular to a reconfigurable satellite platform and an installation method thereof, and a reconfigurable satellite. Background Art

[0002] Reconfigurable satellites are mostly box-and-panel structures, featuring a central support tube as the primary load-bearing component, with instrument panels resting on the tube serving as mounting plates. Currently, many large satellites, both domestically and internationally, employ this type of structure. However, this structure is unsuitable for small and medium-sized satellites weighing less than 1,000 kg. Due to the relatively small size of satellites and the relatively low load-bearing capacity requirements, the presence of a central cylindrical support tube often complicates layout. Furthermore, since small satellites do not require large tanks, the internal space within the support tube cannot be fully utilized when openness is required.

[0003] The CAST968 series platform consists of a common platform and a payload bay. The common platform structure comprises a base plate, two long bulkheads, two short bulkheads, and a docking ring. Inside the platform, the four bulkheads serve as instrument mounting plates and, together with the docking ring, platform base plate, and payload bay base plate, form the satellite's primary load-bearing structure. The payload bay structure comprises the bay base plate, the bay roof, and four surrounding outer panels, which enclose the common platform and payload bay structure into a nearly cubical overall satellite structure. This platform is designed for small and medium-sized satellites that do not require large propellant tanks. Its compact structure, excellent openness, high space utilization, and low manufacturing cost offer numerous advantages in the small satellite sector.

[0004] The four-point connection installation method has good impact resistance, can adapt to a variety of payloads, and uses multiple satellites launched in parallel with one rocket. It has good heat dissipation capabilities and can adapt to satellite layouts with high heat flux density and new satellite structures. This new structure enables small satellites to be highly modular and able to quickly respond to different mission requirements.

[0005] However, there are still many shortcomings in the existing technical solutions. For example, most of the current reconfigurable satellites are box-panel satellites, and the outer shells of the satellites are assembled as independent modular panels. However, the designs of the panels are not exactly the same, making it difficult to truly achieve modular replacement. The assembly method between the panels often relies on bolts or complex fasteners, which is time-consuming and labor-intensive, and contradicts the characteristics of reconfigurable satellites that are light and flexible and can respond promptly to different mission requirements. The reliability of the configuration change process is insufficient, and the state changes during the configuration change process are complex, which can easily lead to jamming due to the lack of coordination between the motion state of the control mechanism and the components. The production and assembly cycle is long, and the cost is high. Summary of the Invention

[0006] The problem solved by the present invention is how to provide a reconfigurable satellite platform which can realize modularization, is flexible and lightweight, has a simple configuration change process and is easy to assemble.

[0007] To solve at least one aspect of the above problems, the present invention provides a reconfigurable satellite platform, comprising a deployed state, a semi-deployed state, and a folded state;

[0008] In the deployed state, the reconfigurable satellite platform presents a seven-unit structure, including a cube-shaped central cell unit and peripheral cell units, one central cell unit is located at the center, and six peripheral cell units are respectively arranged coplanar with different faces of the central cell unit;

[0009] In the seven-unit structure, each surface of the central cell unit is open in the normal direction, forming interconnected cavities, and each surface of the remaining area is covered with a square panel, and adjacent panels are connected by hinges;

[0010] In the semi-expanded state, based on the seven-unit structure, the central cell unit and the two peripheral cell units arranged on opposite sides of the central cell unit are folded into a planar structure along the diagonal line, forming a wing-spreading four-unit structure containing four peripheral cell units and a wing-spreading structure;

[0011] In the folded state, on the basis of the wing-spreading four-unit structure, the four peripheral cell units are folded along the diagonal line into a planar structure, forming a zero-unit structure that does not contain the central cell unit and the peripheral cell unit;

[0012] Wherein, the hinge includes a shape memory hinge, the temporary shape of the shape memory hinge is an "L" shape, and the initial shape is an "I" shape or a "U" shape. When the shape memory hinge is converted from the temporary shape to the initial shape, the reconfigurable satellite platform is used to realize the conversion from the deployed state to the semi-deployed state and the folded state.

[0013] Preferably, a rotation pair is further provided between adjacent panels, and the rotation pair includes a first rotation pair and a second rotation pair, the first rotation pair is used to realize a rotation process from 90° to 180°, and the second rotation pair is used to realize a rotation process from 90° to 0°.

[0014] Preferably, the panel includes a honeycomb sandwich layer and skins covering both sides of the honeycomb sandwich layer.

[0015] Preferably, the shape memory hinge comprises a connector, a shape memory arc-shaped sheet and a fixing member, wherein the shape memory arc-shaped sheet is located between two of the connectors;

[0016] The two connecting heads are respectively used to connect two adjacent panels. The shape memory arc layer includes a temporary shape and an initial shape, which is used to realize the conversion of the reconfigurable satellite platform between different states. The fixing part is used to fix the shape memory arc layer on the connecting head.

[0017] Preferably, the hinge is connected to the panel via bolts, an embedded bowl-shaped part is provided in the honeycomb interlayer, and the bolts are used to connect the hinge to the panel via the embedded bowl-shaped part.

[0018] Preferably, the bolt is a shape memory bolt, the shape memory bolt is made of shape memory polymer, and a shape memory alloy spring is provided in the shape memory bolt.

[0019] Preferably, the shape memory polymer includes a matrix phase and a reinforcement phase, the matrix phase includes at least one of an epoxy shape memory polymer and a cyanate shape memory polymer, and the reinforcement phase includes at least one of continuous fibers, short fibers and reinforcement particles.

[0020] The reconfigurable satellite platform provided by the present invention includes deployed, semi-deployed, and folded states. In the deployed state, it is composed of seven identically structured cubical cells, which are interconnected, facilitating satellite expansion. The reconfigurable satellite platform is formed into an integral unit from identically structured square panels and hinges, facilitating modularization and avoiding the time-consuming and labor-intensive nature of traditional bolt assembly. The position of the panels is changed by rotating the hinges, allowing the reconfigurable satellite platform to change between the deployed, semi-deployed, and folded states. The configuration change process is simple and reliable, and the transformation meets the needs of different scenarios. For example, in the folded state, the platform is compact and easy to transport. In the semi-deployed state, it is suitable for installing satellites with fewer modules. In the deployed state, it can further expand space and interfaces, thereby expanding satellite functions. In addition, the deployed and semi-deployed states are compact and symmetrical, making attitude control easy. The hinges include shape memory hinges, which can utilize shape memory properties to conveniently achieve on-orbit configuration change of the reconfigurable satellite platform, significantly improving its on-orbit controllability.

[0021] The present invention also provides a method for installing a reconfigurable satellite platform, which is used to install the reconfigurable satellite platform described above, comprising the following steps:

[0022] Step S1: Assembling a panel and a hinge to obtain a reconfigurable satellite platform in a folded state, wherein the hinge comprises a shape memory hinge, and the shape memory hinge presents an initial shape of a "U" or "I" shape;

[0023] Step S2, heating a portion of the shape memory hinge to above the glass transition temperature, applying an external force to convert the portion of the shape memory hinge into a temporary "L" shape, converting the reconfigurable satellite platform into a semi-deployed state and maintaining the state, and lowering the temperature to below the glass transition temperature to obtain the reconfigurable satellite platform in the semi-deployed state;

[0024] Step S3: heat the remaining shape memory hinges to above the glass transition temperature, apply external force to convert all the shape memory hinges into a temporary "L" shape, convert the reconfigurable satellite platform into an expanded state and maintain it, lower the temperature to below the glass transition temperature, and obtain the reconfigurable satellite platform in the expanded state.

[0025] The beneficial effects of the installation method of the reconfigurable satellite platform provided by the present invention relative to the prior art are the same as those of the reconfigurable satellite platform, and will not be described in detail here.

[0026] The present invention also provides a reconfigurable satellite, comprising the reconfigurable satellite platform described above.

[0027] Preferably, the reconfigurable satellite further includes a power supply system, a communication system, a sensing system, a control system and a payload system installed in the reconfigurable satellite platform.

[0028] The beneficial effects of the reconfigurable satellite provided by the present invention compared to the prior art are the same as those of the reconfigurable satellite platform, and will not be described in detail here. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] Figure 1 Schematic diagram of the structure of a reconfigurable satellite platform in an unfolded state according to an embodiment of the present invention;

[0030] Figure 2 Schematic diagram of the structure of a reconfigurable satellite platform in a semi-deployed state according to an embodiment of the present invention;

[0031] Figure 3 Schematic diagram of the structure of a reconfigurable satellite platform in a folded state according to an embodiment of the present invention;

[0032] Figure 4 This is a schematic diagram of the numbering of panels and edges in the unfolded state in an embodiment of the present invention;

[0033] Figure 5 A schematic structural diagram of adjacent panels for achieving a 90°-180° transition in an embodiment of the present invention;

[0034] Figure 6 Schematic diagram of the structure of adjacent panels for achieving 90°-0° conversion in an embodiment of the present invention;

[0035] Figure 7Schematic diagram of the structure of the shape memory hinge in an embodiment of the present invention;

[0036] Figure 8 Schematic diagram of the structure of the embedded bowl-shaped part and the shape memory bolt in an embodiment of the present invention.

[0037] Description of reference numerals:

[0038] 1. Panel; 11. Embedded bowl-shaped part; 2. Hinge; 21. Shape memory hinge; 211. Connector; 212. Shape memory arc-shaped sheet; 213. Fixing part; 22. Rotational pair; 3. Shape memory bolt; 31. Shape memory alloy spring. DETAILED DESCRIPTION

[0039] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, specific embodiments of the present invention are described in detail below.

[0040] It should be noted that, unless there is a conflict, the features of the embodiments of the present invention may be combined with each other. It should also be noted that the terms "first," "second," and the like in the description and claims of the present invention and the accompanying drawings are used to distinguish similar objects and are not necessarily used to describe a specific order or precedence. It should be understood that the terms used in this manner are interchangeable where appropriate, such that the embodiments of the present invention described herein can be implemented in an order other than that illustrated or described herein.

[0041] The embodiment of the present invention provides a reconfigurable satellite platform, such as Figure 1-3 As shown, it includes an expanded state, a semi-expanded state and a folded state;

[0042] In the deployed state, the reconfigurable satellite platform presents a seven-unit structure, including a cube-shaped central cell unit and peripheral cell units, one central cell unit is located at the center, and six peripheral cell units are respectively arranged coplanar with different faces of the central cell unit;

[0043] In the seven-unit structure, each surface of the central cell unit is open in the normal direction, and the seven-unit structure is used to form interconnected cavities. Each surface of the remaining area is covered with a square panel 1, and adjacent panels are connected by hinges 2;

[0044] In the semi-expanded state, based on the seven-unit structure, the central cell unit and the two peripheral cell units arranged on opposite sides of the central cell unit are folded into a planar structure along the diagonal line, forming a wing-spreading four-unit structure containing four peripheral cell units and a wing-spreading structure;

[0045] In the folded state, on the basis of the wing-spreading four-unit structure, the four peripheral cell units are folded along the diagonal line into a planar structure, forming a zero-unit structure that does not contain the central cell unit and the peripheral cell unit;

[0046] Among them, the hinge 2 includes a shape memory hinge 21, the temporary shape of the shape memory hinge 21 is "L" shape, and the initial shape includes "I" shape and "U" shape. When the shape memory hinge 21 is converted from the temporary shape to the initial shape, the reconfigurable satellite platform is used to realize the conversion from the deployed state to the semi-deployed state and the folded state.

[0047] The reconfigurable satellite platform provided by the embodiment of the present invention includes deployed, semi-deployed, and folded states. In the deployed state, it is composed of seven identically structured cubic cell units, and the multiple cell units are interconnected, facilitating satellite expansion. The reconfigurable satellite platform is formed into an integral body consisting of identically structured square panels 1 and hinges 2, facilitating modularization and avoiding the time-consuming and labor-intensive issues of traditional bolt splicing. The positions of the panels 1 are changed by rotating the hinges 2, thereby enabling the reconfigurable satellite platform to change between the deployed, semi-deployed, and folded states. The configuration change process is simple and reliable, and the transformation meets the needs of different scenarios. For example, in the folded state, the volume is small and easy to transport. In the semi-deployed state, it is suitable for installing satellites with fewer modules. In the deployed state, it can further expand space and interfaces, thereby expanding satellite functions. In addition, the deployed and semi-deployed states are compact and symmetrical, making attitude control easy. The hinges 2 include shape memory hinges 21, which can utilize shape memory to conveniently achieve on-orbit configuration change of the reconfigurable satellite platform, significantly improving the on-orbit controllability of the reconfigurable satellite platform.

[0048] Figure 1This is a schematic diagram of the structure of the reconfigurable satellite platform in its deployed state. At this time, the reconfigurable satellite platform includes seven cell units, namely, a central cell unit located at the center and six peripheral cell units located on the periphery of the central cell unit. All cell units are cubes, and the six peripheral cell units are coplanar with one of the faces of the central cell unit. In the seven cube units, all coplanar faces and faces parallel to the coplanar faces are open, that is, they do not have a panel structure. The other faces use square panels 1, and the adjacent panels 1 are connected by hinges 2. Therefore, the six peripheral cell units can be folded along their diagonals, and the central cell unit can fold along with the folding of each peripheral cell unit. In addition, interconnected cavities are formed between the different cell units in the reconfigurable satellite platform, and by using multiple square panels 1 and connecting adjacent panels 1 by hinges 2, a multi-layer drawer-type main load-bearing structure is formed, which ensures the folding and unfolding rate while further enhancing the rigidity of the cell units and improving the unfolding accuracy. In addition, the embodiment of the present invention uses a shape memory hinge 21, which utilizes its shape memory properties to achieve rapid in-orbit conformational changes.

[0049] like Figure 1 As shown, the reconfigurable satellite platform in the unfolded state can be regarded as a seven-unit structure formed by six cubic cylindrical structures with the same structure. There are no panels 1 on the top and bottom surfaces of the cubic cylindrical structure, and the four sides are covered with panels 1. The adjacent panels 1 are connected by hinges 2. The bottom surfaces of the six cubic cylindrical structures are arranged to form a cubic cavity of the same size as the six cubic cylindrical structures, resulting in a seven-unit structure. The seven-unit structure consists of 24 panels 1 and hinges 2 between the panels 1.

[0050] Figure 2 This diagram shows the structure of a reconfigurable satellite platform in a semi-deployed state. The platform comprises four cells and a wing unit. Transitioning between the deployed and semi-deployed states allows for the modification or reduction of satellite modules while in orbit. Converting from a seven-cell structure to a four-wing unit structure facilitates the on-orbit removal of failed modules and restoration to a state with minimal energy consumption. The reconfigurable satellite platform provided by this embodiment of the present invention is compact and symmetrical in both deployed and semi-deployed states, making it easy to control its attitude.

[0051] Figure 3 This is a structural diagram of the reconfigurable satellite platform when it is in a folded state. At this time, all cell units in the reconfigurable satellite platform are in a folded state, which can compress the volume to the maximum extent and facilitate transportation.

[0052] The shape memory hinge 21 connects two adjacent panels 1, and its temporary shape is "L"-shaped. The two ends of the "L"-shaped shape memory hinge 21 are respectively connected to the two panels 1 so that the two panels 1 are perpendicular. At this time, the cube unit where the two panels 1 are located is in an unfolded cube state. At this time, the reconfigurable satellite platform can be in an unfolded state; the initial shape of the shape memory hinge 21 is "I"-shaped or "U"-shaped. The two ends of the "I"-shaped or "U"-shaped shape memory hinge 21 are respectively connected to the two panels 1, which can make the two panels 1 roughly coplanar or parallel. At this time, the folding of the square unit where the two panels 1 are located can be achieved. When the shape memory hinge 21 is subjected to external stimulation and reaches above the glass transition temperature (Tg), it can return from the temporary shape to the initial shape, thereby realizing the state conversion.

[0053] In order to facilitate understanding of the configuration change process of the reconfigurable satellite platform provided in the embodiment of the present invention, the state change process of the reconfigurable satellite platform is exemplarily described as follows;

[0054] like Figure 4 As shown in (A), the faces in the unfolded state (i.e., seven-unit structure) are numbered, as shown in Figure 4 As described in (B), the edges in the unfolded state (i.e., seven-unit structure) are numbered. Figure 4 As shown in (B), with the center point of the reconfigurable satellite platform in the unfolded state as the origin, a coordinate system is constructed as shown in the figure. The cell structure in the negative direction of the X axis is numbered ①, the cell unit in the positive direction of the Z axis is numbered ②, the cell unit on the X axis square is numbered ③, the cell unit in the negative direction of the Z axis is numbered ④, the cell unit in the negative direction of the Y axis is numbered ⑤, and the cell unit in the positive direction of the Y axis is numbered ⑥; the cell unit in the center is numbered ⑦; then the edges formed between panel 1 and the adjacent panel 1 in each cell unit are numbered, as shown in FIG. Figure 4 As shown in (A) and (B).

[0055] Based on this, the state transformation process of the reconfigurable satellite platform is described, as shown in Table 1:

[0056] Table 1 Description of the state transformation process of the reconfigurable satellite platform

[0057]

[0058] In Table 1, ΔV cell Represents the volume change, where ΔV cell =0 means that the volume of the cell unit has not changed, ΔV cell =L 3 It means that the cell unit changes from a cube to a planar structure.

[0059] As shown in Table 1, during the transition from the expanded state to the semi-expanded state, the volume of the peripheral cell units numbered ①-④ did not change, while the volume of the peripheral cell units numbered ⑤, ⑥ and the central cell unit numbered ⑦ changed, with a volume change of L 3 (L is the side length of the cell unit), that is, the cube structure is transformed into a planar structure. The hinges on the edges of 6.2, 5.2, 5.2, and 5.4 change from 90° to 180°, that is, from "L" shape to "I" shape structure. The hinges on the edges of 6.1, 6.3, 5.1, and 5.3 change from 90° to 0°, that is, from "L" shape to "U" shape structure.

[0060] During the transition from the semi-expanded state to the expanded state, the volume of the peripheral cell units numbered ①-④ changes, and the volume change is L 3 (L is the side length of the cell unit), that is, the cube structure is transformed into a planar structure, the hinges on the edges of 1.2, 1.4, 2.2, 2.4, 3.2, 3.4, 4.2, and 4.4 change from 90° to 180°, that is, from "L" shape to "I" shape structure, and the hinges on the edges of 1.1, 1.3, 2.1, 2.3, 3.1, 3.3, 4.1, and 4.3 change from 90° to 0°, that is, from "L" shape to "U" shape structure.

[0061] It should be noted that if the panel structure is thin and light enough, the four-unit structure of the wings in the semi-expanded state can be further converted into a four-unit structure. This can be achieved by folding the wings upward or downward, and then further converted into a zero-unit structure in the folded state. At this time, the zero-unit structure is a planar structure and occupies a smaller volume.

[0062] In one embodiment, a rotation pair 22 is further provided between adjacent panels, and the rotation pair 22 includes a first rotation pair and a second rotation pair. The first rotation pair is used to realize a rotation process from 90° to 180°, and the second rotation pair is used to realize a rotation process from 90° to 0°.

[0063] That is to say, in addition to being connected by the shape memory hinge 21, adjacent panels are also connected by a rotating pair 22. Through the combined design of the two, the reconfigurable satellite platform can achieve smooth and impact-free transitions during state transitions, and at the same time provide sufficient restoring force to drive the folding of the panel 1, thereby realizing the driving folding and self-locking functions after folding.

[0064] The first rotation pair is used to realize the rotation process from 90° to 180°, and the second rotation pair is used to realize the rotation process from 90° to 0°, which are respectively used to cooperate with the shape memory hinge 21 with the initial shape of "I" and "U" to realize the state transformation of the reconfigurable satellite platform.

[0065] For example, Figure 5 As shown, Figure 5 When the adjacent panels 1 in the middle change state, they are converted from 90° to 180°. The structure of the revolving pair 22 is shown in the figure. The temporary shape of the corresponding shape memory hinge 21 is "L" shape, and the initial shape is "-" shape; Figure 6 As shown, Figure 6 When the adjacent panels 2 in the middle change state, the angle is converted from 90° to 180°. The structure of the revolving pair 22 is shown in the figure. The temporary shape of the corresponding shape memory hinge 21 is "L" shape and the initial shape is "U" shape.

[0066] In one embodiment, the panel 1 includes a honeycomb sandwich layer and skins covering both sides of the honeycomb sandwich layer.

[0067] Exemplarily, the honeycomb sandwich includes an aramid paper honeycomb core, and the skin is a carbon fiber panel layer or an aluminum alloy panel layer.

[0068] The panel 1 formed by the honeycomb sandwich and the skin has the characteristics of lightness and high rigidity, and the thickness of the panel 1 can be controlled to be less than 60 mm.

[0069] For example, the area of the reconfigurable satellite platform in the folded state is 1m 2 , thickness is 60mm, total mass does not exceed 10kg, and the expansion ratio is about 5:1.

[0070] In one embodiment, Figure 7 As shown, the shape memory hinge 21 includes a connector 211, a shape memory arc-shaped sheet 212 and a fixing member 213, and the shape memory arc-shaped sheet 212 is located between the two connectors 211;

[0071] The two connecting heads 211 are respectively used to connect the two adjacent panels 1. The shape memory arc layer 212 includes a temporary shape and an initial shape, which is used to realize the conversion of the reconfigurable satellite platform between different states. The fixing part 213 is used to fix the shape memory arc layer 212 on the connecting head 211.

[0072] The connectors 211 at both ends are connected to two adjacent panels 1 respectively. The shape memory arc layer 212 is made of shape memory material. The shape memory arc layer 212 includes two shape memory arc sheets arranged opposite to each other, which improves strength and reduces the risk of wear and damage. The temporary shape of the shape memory arc layer 212 is "L" shaped, and the initial shape is "Y" or "U" shaped. Figure 7In the shape-memory hinge 21 shown in FIG, the shape-memory arcuate layer 212 is in an "I" shape. The shape-memory arcuate layer 212 can be bent to one side to form an "L" or "U" shape. The fixing member 213 is used to secure the shape-memory arcuate layer 212 to the connector 211, thereby forming the shape-memory hinge 21 as a whole and ensuring the stability and reliability of the shape-memory hinge 21 during rotation. The fixing member 213 can also be made of a shape-memory material, allowing it to change shape and position when necessary.

[0073] In one embodiment, Figure 8 As shown, the hinge 2 is connected to the panel 1 through bolts, and a pre-embedded bowl-shaped part 11 is provided in the honeycomb interlayer. The bolts are used to connect the hinge 2 to the panel 1 through the pre-embedded bowl-shaped part 11.

[0074] The spiral connection requires punching holes on the panel 1. In order to avoid stress concentration on the panel 1 caused by the punching, which may lead to extrusion damage, a pre-embedded bowl-shaped part 11 is provided in the honeycomb interlayer, which can disperse the concentrated load to the panel 1, reduce the stress concentration problem, and reduce the risk of damage.

[0075] In one embodiment, Figure 8 As shown, the bolt is a shape memory bolt 3 , which is made of shape memory polymer, and a shape memory alloy spring 31 is provided in the shape memory bolt 3 .

[0076] During state transitions, the bolted joints of a reconfigurable satellite platform are prone to vibration. Shape memory bolts 3, made of shape memory polymer, generate a significant restoring force during deformation recovery, actively controlling vibration. Furthermore, shape memory bolts 3 are equipped with shape memory alloy springs 31. When vibration occurs, these springs significantly deform to dissipate energy, leveraging the superelasticity and hysteretic energy dissipation capabilities of shape memory bolts 3. This results in structural stability under vibration, good ductility, and self-reset after vibration. In other words, shape memory bolts 3 leverage their unique advantages in vibration and energy absorption, along with their intelligent, self-centering connection structure, to prevent loosening and reduce vibration.

[0077] In one embodiment, the shape memory polymer includes a matrix phase and a reinforcement phase, the matrix phase includes at least one of an epoxy shape memory polymer and a cyanate shape memory polymer, and the reinforcement phase includes at least one of continuous fibers, short fibers, and reinforcement particles.

[0078] The matrix phase in shape memory polymers provides shape memory properties and can be selected based on the application environment. Epoxy shape memory polymers can be modified to have a glass transition temperature between 80-180°C, while cyanate shape memory polymers can be modified to have a glass transition temperature between 180-200°C. The reinforcement phase, which enhances strength, includes continuous fibers, short fibers, and reinforcing particles. Furthermore, it can include carbon fibers, glass fibers, aramid fibers, polyethylene fibers, and other materials with excellent mechanical properties.

[0079] An embodiment of the present invention further provides a method for installing a reconfigurable satellite platform, which is used to install the reconfigurable satellite platform described above, and includes the following steps:

[0080] Step S1: Assembling a panel 1 and a hinge 2 to obtain a reconfigurable satellite platform in a folded state, wherein the hinge 2 includes a shape memory hinge 21, and the shape memory hinge 21 has an initial shape of a "U" or "I";

[0081] Step S2, heating a portion of the shape memory hinge 21 to above the glass transition temperature, applying an external force to convert the portion of the shape memory hinge 21 into a temporary "L" shape, converting the reconfigurable satellite platform into a semi-expanded state and maintaining it, and lowering the temperature to below the glass transition temperature to obtain the reconfigurable satellite platform in the semi-expanded state;

[0082] Step S3: heat the remaining shape memory hinges 21 to above the glass transition temperature, apply external force to convert all the shape memory hinges 21 into a temporary "L" shape, convert the reconfigurable satellite platform into the deployed state and maintain it, lower the temperature to below the glass transition temperature, and obtain the reconfigurable satellite platform in the deployed state.

[0083] The beneficial effects of the installation method of the reconfigurable satellite platform provided by the embodiment of the present invention relative to the prior art are the same as those of the reconfigurable satellite platform, and will not be described in detail here.

[0084] An embodiment of the present invention further provides a reconfigurable satellite, comprising the reconfigurable satellite platform described above.

[0085] The main structure of a satellite is typically divided into a propulsion module, a service module, and a payload module. Several modules are connected in series to form a satellite platform. Based on the plug-and-play (PnP) concept, independent multifunctional modules are assembled into a cube satellite prototype using a robotic arm. These multifunctional modules are interconnected via inter-board interfaces, allowing different modules to be integrated and perform different functions. The reconfigurable satellite platform provided by the present invention can adapt to different situations through state transitions.

[0086] Reconfigurable satellites break down traditional satellite components into multiple modules based on their functions. These modules are designed with unified mechanical and electrical interfaces, enabling flexible assembly, rapid production, and functional expansion. Reconfigurable satellites allow for on-orbit repair and module reuse, reducing the difficulty and cost of satellite maintenance and the generation of space debris. Reconfigurable satellites can be reconfigured and optimized to meet different mission requirements, enabling controllable orbit changes and rapid networking.

[0087] The reconfigurable satellite provided by the embodiment of the present invention has low mass, and a failed cell satellite structure or a cell unit that can no longer be reused can be recovered for recycling.

[0088] In one embodiment, the reconfigurable satellite further includes a power supply system, a communication system, a sensor system, a control system, and a payload system installed in the reconfigurable satellite platform.

[0089] Exemplarily, the power supply system includes solar cells and batteries, the communication system includes a transmitter, a receiver, a modem and an antenna structure, the sensing system includes an inertial measurement unit, a position sensor, a temperature sensor and an optical sensor, the control system includes a voltage regulator, a secondary power supply and a power management system, and the payload system includes a camera, a spectrometer and a synthetic aperture radar.

[0090] By configuring the power supply system, communication system, sensor system, control system and payload system in each cell unit of the reconfigurable satellite platform provided in the embodiment of the present invention, different cell units have independent functionality and expansion characteristics that can realize different payload tasks, and different cell units are independently replaceable. After assembly, the cell units work together to realize complex platform functions and payload mission requirements. When some cell units are in a closed state, part of the payload system can be shut down, and some functional payloads and control systems can be protected. The auxiliary power supply is mainly started, and the solar panels continue to work to charge the battery. When a mission needs to be executed, the control system will judge the mission requirements. Based on the judgment result, the control system will supply power to the shape memory composite hinge structure and drive the overall structure to unfold through the drive device to complete the platform payload configuration. After the configuration is completed, the satellite can begin to perform the mission requirements.

[0091] Exemplarily, the driving device includes at least one of an electromagnetic driver, an ultrasonic driver, a piezoelectric driver, a motor driver, a hydraulic driver, and a pneumatic driver.

[0092] In addition, based on the reconfigurable satellite provided by the present invention, it is also possible to obtain a dual-satellite self-tandem launch configuration, a single-satellite launch configuration, a binary satellite operation configuration, a space transportation configuration, a space towing configuration, a space maintenance and refueling configuration, a satellite formation flight configuration, etc.

[0093] Although the present invention is disclosed as above, the protection scope of the present invention is not limited thereto. Those skilled in the art may make various changes and modifications without departing from the spirit and scope of the present invention, and these changes and modifications will fall within the protection scope of the present invention.

Claims

1. A reconfigurable satellite platform, characterized in that: Including expanded state, semi-expanded state and folded state; In the deployed state, the reconfigurable satellite platform presents a seven-unit structure, including a cube-shaped central cell unit and peripheral cell units, one central cell unit is located at the center, and six peripheral cell units are respectively arranged coplanar with different faces of the central cell unit; In the seven-unit structure, each surface in the central cell unit is open in the normal direction, and interconnected cavities are formed in the seven-unit structure. Each surface in the remaining area is covered with a square panel (1), and adjacent panels (1) are connected by hinges (2); In the semi-expanded state, based on the seven-unit structure, the central cell unit and the two peripheral cell units arranged on opposite sides of the central cell unit are folded into a planar structure along the diagonal line, forming a wing-spreading four-unit structure containing four peripheral cell units and a wing-spreading structure; In the folded state, on the basis of the wing-spreading four-unit structure, the four peripheral cell units are folded along the diagonal line into a planar structure, forming a zero-unit structure that does not contain the central cell unit and the peripheral cell unit; The hinge (2) includes a shape memory hinge (21), the temporary shape of the shape memory hinge (21) is an "L" shape, and the initial shape is an "I" shape or a "U" shape. When the shape memory hinge (21) is converted from the temporary shape to the initial shape, the reconfigurable satellite platform is used to realize the conversion from the expanded state to the semi-expanded state and the folded state.

2. The reconfigurable satellite platform according to claim 1, characterized in that: A rotation pair (22) is also provided between adjacent panels (1), and the rotation pair (22) includes a first rotation pair and a second rotation pair, wherein the first rotation pair is used to realize a rotation process from 90° to 180°, and the second rotation pair is used to realize a rotation process from 90° to 0°.

3. The reconfigurable satellite platform according to claim 1, characterized in that: The panel (1) comprises a honeycomb sandwich layer and skins covering both sides of the honeycomb sandwich layer.

4. The reconfigurable satellite platform according to claim 1, characterized in that: The shape memory hinge (21) comprises a connecting head (211), a shape memory arc-shaped sheet (212) and a fixing member (213), wherein the shape memory arc-shaped sheet (212) is located between two of the connecting heads; The two connecting heads (211) are respectively used to connect two adjacent panels (1); the shape memory arcuate sheet (212) includes a temporary shape and an initial shape, and is used to realize the conversion of the reconfigurable satellite platform between different states; the fixing member (213) is used to fix the shape memory arcuate sheet (212) on the connecting head (211).

5. The reconfigurable satellite platform according to claim 3, characterized in that: The hinge (2) is connected to the panel (1) via bolts, a pre-buried bowl-shaped part (11) is provided in the honeycomb interlayer, and the bolts are used to connect the hinge (2) to the panel (1) via the pre-buried bowl-shaped part (11).

6. The reconfigurable satellite platform according to claim 5, characterized in that: The bolt is a shape memory bolt (3), the shape memory bolt (3) is made of shape memory polymer, and a shape memory alloy spring (31) is provided in the shape memory bolt (3).

7. The reconfigurable satellite platform according to claim 6, characterized in that: The shape memory polymer includes a matrix phase and a reinforcement phase, wherein the matrix phase includes at least one of an epoxy shape memory polymer and a cyanate shape memory polymer, and the reinforcement phase includes at least one of continuous fibers, short fibers, and reinforcement particles.

8. A method for installing a reconfigurable satellite platform, for installing the reconfigurable satellite platform according to any one of claims 1 to 7, characterized in that: The following steps are involved: Step S1: assembling a panel (1) and a hinge (2) to obtain a reconfigurable satellite platform in a folded state, wherein the hinge (2) includes a shape memory hinge (21), and the shape memory hinge (21) presents an initial shape of a "U" or "U" shape; Step S2, heating a portion of the shape memory hinge (21) to a temperature above the glass transition temperature, applying an external force to convert the portion of the shape memory hinge (21) into a temporary "L" shape, converting the reconfigurable satellite platform into a semi-expanded state and maintaining the state, and lowering the temperature to below the glass transition temperature to obtain the reconfigurable satellite platform in the semi-expanded state; Step S3: heating another portion of the shape memory hinges (21) to above the glass transition temperature, applying external force to convert all the shape memory hinges (21) into a temporary "L" shape, converting the reconfigurable satellite platform into an unfolded state and maintaining it, and lowering the temperature to below the glass transition temperature to obtain the reconfigurable satellite platform in the unfolded state.

9. A reconfigurable satellite, characterized in that: The invention comprises a reconfigurable satellite platform according to any one of claims 1 to 7.

10. The reconfigurable satellite according to claim 9, characterized in that: It also includes a power supply system, a communication system, a sensor system, a control system and a payload system installed in the reconfigurable satellite platform.

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