CN117326097A - Reconfigurable satellite platform, installation method thereof and reconfigurable satellite - Google Patents
Reconfigurable satellite platform, installation method thereof and reconfigurable satellite Download PDFInfo
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- CN117326097A CN117326097A CN202311388011.7A CN202311388011A CN117326097A CN 117326097 A CN117326097 A CN 117326097A CN 202311388011 A CN202311388011 A CN 202311388011A CN 117326097 A CN117326097 A CN 117326097A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/10—Artificial satellites; Systems of such satellites; Interplanetary vehicles
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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Abstract
The invention provides a reconfigurable satellite platform, an installation method thereof and a reconfigurable satellite, and belongs to the technical field of aerospace, wherein the reconfigurable satellite platform comprises an unfolding state, a semi-unfolding state and a folding state; in the unfolding state, a seven-unit structure is presented, cavities which are communicated with each other are formed in the seven-unit structure, each surface of the rest areas is covered by a square panel, and the adjacent panels are connected by hinges; in the semi-expanded state, a four-cell structure of the wing is formed containing four peripheral cell units and a wing structure; in the collapsed state, a zero cell structure is formed that does not contain a central cell unit and a peripheral cell unit; the hinge comprises a shape memory hinge, wherein the temporary shape of the shape memory hinge is L-shaped, and the initial shape of the shape memory hinge is one or U. The reconfigurable satellite platform provided by the invention can realize the reconfigurable satellite platform which is modularized, flexible, light, simple in reconstruction process and easy to assemble.
Description
Technical Field
The invention relates to the technical field of aerospace, in particular to a reconfigurable satellite platform, an installation method thereof and a reconfigurable satellite.
Background
The reconfigurable satellites are in a box plate type structure, and are mainly characterized in that a central bearing cylinder is used as a main bearing piece, and an instrument plate supported by the central bearing cylinder is used as a mounting plate. At present, a bearing barrel plate type structure is adopted as a main structure for a plurality of large satellites at home and abroad. But the bearing barrel plate type structure is not suitable for medium and small satellites with total weight within 1000 kg. The satellite has low requirements on bearing capacity, the satellite is relatively small in size, the layout difficulty is often increased due to the central cylindrical bearing cylinder under the condition, and meanwhile, the space inside the bearing cylinder cannot be fully utilized under the condition of openness requirements because a small satellite does not need a large storage tank.
The CAST968 series of platforms consists of a common platform section and payload bay, the common platform structure consisting of a base plate, two long bulkheads, two short bulkheads and a docking collar. Inside the platform, four partition boards are used as instrument mounting boards and form a main bearing structure of the satellite together with the docking ring, the platform bottom board and the load cabin bottom board. The payload bay structure includes a load bay floor, a load bay roof, and 4 peripheral outer wall panels, the 4 outer wall panels enclosing the common platform and the load bay structure into a generally square-like overall structure. The platform is oriented to small and medium-sized satellites without large propellant storage tanks, has the advantages of compact structure, good openness, high space utilization rate and low manufacturing cost, and has a plurality of advantages in the field of small satellites.
The four-point connection installation mode has good shock resistance, can adapt to various loads, utilizes parallel emission of a plurality of satellites of an arrow, has good heat dissipation capability, can adapt to satellite layout and new satellite structures with high heat flux density, and the new structure enables the minisatellite to have high modularization and capability of rapidly responding to different task demands.
However, there are still many disadvantages in the prior art solutions, such as: at present, most of reconfigurable satellites are boxboard satellites, and all the box shells of the satellites are assembled as independent modularized panels, however, the design among all the panels is not completely the same at present, and the modularized substitution is difficult to truly realize; the assembly mode among the panels often depends on bolts or complex fasteners, and time and labor are consumed in the assembly process, which contradicts the characteristics of light weight, flexibility and timely response to different task demands of the reconfigurable satellite; the reliability of the allosteric process is insufficient, the state change in the allosteric process is complex, and the situation that the motion state between the control mechanism and the component is not coordinated and is blocked easily occurs; the production and assembly period is longer, and the cost consumption is larger.
Disclosure of Invention
The invention solves the problem of providing a reconfigurable satellite platform which can realize modularization, is flexible and light, has a simple allosteric process and is easy to assemble.
In order to solve at least one of the above problems, the present invention provides a reconfigurable satellite platform, including an unfolded state, a semi-unfolded state, and a folded state;
in the unfolding state, the reconfigurable satellite platform presents a seven-unit structure and comprises a cube-shaped central cell unit and peripheral cell units, wherein one central cell unit is positioned at the central position, and six peripheral cell units are respectively arranged in a coplanar manner with different surfaces in the central cell unit;
in the seven-unit structure, the normal direction of each surface in the central cell unit is open, a cavity which is communicated with each other is formed in the seven-unit structure, each surface of other areas is covered by a square panel, and adjacent panels are connected by hinges;
in the semi-unfolding state, on the basis of the seven-unit structure, the central cell unit and the two peripheral cell units arranged on two opposite sides of the central cell unit are folded into a planar structure along a diagonal line to form a wing-unfolding four-unit structure containing four peripheral cell units and a wing-unfolding structure;
in the folded state, on the basis of the four-unit structure of the unfolding wing, four peripheral cell units are folded into a planar structure along diagonal lines to form a zero-unit structure without the central cell unit and the peripheral cell units;
the hinge comprises a shape memory hinge, wherein the temporary shape of the shape memory hinge is L-shaped, the initial shape of the shape memory hinge is one or U-shaped, and when the shape memory hinge is converted from the temporary shape to the initial shape, the reconfigurable satellite platform is used for realizing the conversion from the unfolded state to the half unfolded state and the folded state.
Preferably, a revolute pair is further arranged between the adjacent panels, the revolute pair comprises a first revolute pair and a second revolute pair, the first revolute pair is used for realizing a 90-180-degree rotation process, and the second revolute pair is used for realizing a 90-0-degree rotation process.
Preferably, the panel comprises a honeycomb interlayer and skins coated on two sides of the honeycomb interlayer.
Preferably, the shape memory hinge comprises a connector, a shape memory arc-shaped sheet layer and a fixing piece, wherein the shape memory arc-shaped sheet layer is positioned between the two connectors;
the two connectors are respectively used for connecting two adjacent panels, the shape memory arc-shaped sheet layer comprises a temporary shape and an initial shape and is used for realizing the conversion of the reconfigurable satellite platform between different states, and the fixing piece is used for fixing the shape memory arc-shaped sheet layer on the connectors.
Preferably, the hinge is connected with the panel through a bolt, an embedded bowl-shaped part is arranged in the honeycomb interlayer, and the bolt is used for enabling the hinge to be connected with the panel through the embedded bowl-shaped part.
Preferably, the bolt is a shape memory bolt, the shape memory bolt is made of a shape memory polymer, and a shape memory alloy spring is arranged in the shape memory bolt.
Preferably, the shape memory polymer includes a matrix phase including at least one of an epoxy-based shape memory polymer and a cyanate-based shape memory polymer, and a reinforcing phase including at least one of continuous fibers, short fibers, and reinforcing particles.
The reconfigurable satellite platform provided by the invention comprises an unfolding state, a semi-unfolding state and a folding state, wherein the unfolding state comprises seven cube-shaped cell units with the same structure, and the cell units are communicated with each other, so that the satellite can be conveniently unfolded; the reconfigurable satellite platform is formed by a square panel with the same structure and a hinge into a whole, so that modularization is convenient to realize, and the problem of time and labor consumption in traditional bolt splicing is avoided; the position change between the panels is realized through the rotation of the hinge, so that the reconfigurable satellite platform can realize the change among an unfolding state, a semi-unfolding state and a folding state, the allosteric process is simple, the reliability is high, the use requirements of different scenes are realized through the change, for example, when the reconfigurable satellite platform is in the folding state, the volume is smaller, the transportation is convenient, when the reconfigurable satellite platform is in the semi-unfolding state, the reconfigurable satellite platform is suitable for the installation of satellites with fewer modules, when the reconfigurable satellite platform is in the unfolding state, the space and the interface can be further expanded, the satellite functions can be expanded, and in addition, when the reconfigurable satellite platform is in the unfolding state and the semi-unfolding state, the reconfigurable satellite platform is compact and symmetrical in structure and easy to control the gestures; the hinge comprises a shape memory hinge, so that the in-orbit reconstruction of the reconfigurable satellite platform can be conveniently realized by utilizing the shape memory performance, and the in-orbit controllability of the reconfigurable satellite platform is remarkably improved.
The invention also provides an installation method of the reconfigurable satellite platform, which is used for installing the reconfigurable satellite platform and comprises the following steps:
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 which takes on an initial shape of a 'one' shape or a 'U' -shape;
s2, heating part of the shape memory hinges to above the glass transition temperature, applying external force to enable part of the shape memory hinges to be converted into an L-shaped temporary shape, converting the reconfigurable satellite platform into a semi-unfolded state and keeping the semi-unfolded state, and reducing the temperature to below the glass transition temperature to obtain the reconfigurable satellite platform in the semi-unfolded state;
and S3, heating the rest part of the shape memory hinges to be above the glass transition temperature, applying external force to enable all the shape memory hinges to be converted into L-shaped temporary shapes, converting the reconfigurable satellite platform into an unfolding state and keeping the unfolding state, and reducing the temperature to be below the glass transition temperature to obtain the reconfigurable satellite platform in the unfolding state.
Compared with the prior art, the installation method of the reconfigurable satellite platform has the same beneficial effects as those of the reconfigurable satellite platform, and is not repeated here.
The invention also provides a reconfigurable satellite comprising a reconfigurable satellite platform as described above.
Preferably, the reconfigurable satellite further comprises a power supply system, a communication system, a sensing system, a control system and a loading system installed in the reconfigurable satellite platform.
Compared with the prior art, the reconfigurable satellite provided by the invention has the same beneficial effects as the reconfigurable satellite platform, and is not described in detail herein.
Drawings
FIG. 1 is a schematic view of a reconfigurable satellite platform in an unfolded state according to an embodiment of the present invention;
FIG. 2 is a schematic structural diagram of a reconfigurable satellite platform in a semi-deployed state according to an embodiment of the present invention;
FIG. 3 is a schematic view of a reconfigurable satellite platform in a folded state according to an embodiment of the present invention;
FIG. 4 is a schematic numbered view of the panels and ribs in the unfolded state according to the embodiment of the invention;
FIG. 5 is a schematic view of the structure of adjacent panels for 90-180 conversion in an embodiment of the present invention;
FIG. 6 is a schematic view of the structure of adjacent panels for 90-0 conversion in an embodiment of the present invention;
FIG. 7 is a schematic view of a shape memory hinge according to an embodiment of the present invention;
FIG. 8 is a schematic diagram of the structure of the embedded bowl and shape memory bolt in an embodiment of the invention.
Reference numerals illustrate:
1. a panel; 11. embedding bowl-shaped parts; 2. a hinge; 21. a shape memory hinge; 211. a connector; 212. a shape memory arcuate sheet; 213. a fixing member; 22. a revolute pair; 3. a shape memory bolt; 31. a shape memory alloy spring.
Detailed Description
In order that the above-recited objects, features and advantages of the present invention will become more readily apparent, a more particular description of embodiments of the invention will be rendered by reference to specific embodiments thereof which are illustrated in the appended drawings.
It should be noted that, without conflict, features in the embodiments of the present invention may be combined with each other. Also, it is noted that the terms "first," "second," and the like in the description and claims of the present invention and in the above-described figures are used for distinguishing between similar objects and not necessarily for describing a particular sequential or chronological order. It is to be understood that the data so used may be interchanged where appropriate such that the embodiments of the invention described herein may be implemented in sequences other than those illustrated or otherwise described herein.
The embodiment of the invention provides a reconfigurable satellite platform, which is shown in figures 1-3 and comprises an unfolding state, a semi-unfolding state and a folding state;
in the unfolding state, the reconfigurable satellite platform presents a seven-unit structure and comprises a cube-shaped central cell unit and peripheral cell units, wherein one central cell unit is positioned at the central position, and six peripheral cell units are respectively arranged in a coplanar manner with different surfaces in the central cell unit;
in the seven-unit structure, the normal directions of the surfaces of the central cell units are all open, cavities which are communicated with each other are formed in the seven-unit structure, each surface of other areas is covered by a square panel 1, and the adjacent panels are connected by a hinge 2;
in the semi-unfolding state, on the basis of the seven-unit structure, the central cell unit and the two peripheral cell units arranged on two opposite sides of the central cell unit are folded into a planar structure along a diagonal line to form a wing-unfolding four-unit structure containing four peripheral cell units and a wing-unfolding structure;
in the folded state, on the basis of the four-unit structure of the unfolding wing, four peripheral cell units are folded into a planar structure along diagonal lines to form a zero-unit structure without the central cell unit and the peripheral cell units;
wherein the hinge 2 comprises a shape memory hinge 21, the temporary shape of the shape memory hinge 21 is an L shape, the initial shape comprises a one shape and a U shape, and the reconfigurable satellite platform is used for realizing the transition from the unfolded state to the semi-unfolded state and the folded state when the shape memory hinge 21 is converted from the temporary shape to the initial shape.
The reconfigurable satellite platform provided by the embodiment of the invention comprises an unfolding state, a semi-unfolding state and a folding state, wherein the unfolding state comprises seven cube-shaped cell units with the same structure, and the cell units are mutually communicated, so that the satellite can be conveniently expanded; the reconfigurable satellite platform is formed by a square panel 1 and a hinge 2 which are identical in structure, so that modularization is convenient to realize, and the problem of time and labor consumption in traditional bolt splicing is avoided; the position change between the panels 1 is realized through the rotation of the hinge 2, so that the reconfigurable satellite platform can realize the change among an unfolding state, a semi-unfolding state and a folding state, the reconstruction process is simple, the reliability is high, the use requirements of different scenes are realized through the change, for example, the volume is smaller when the reconfigurable satellite platform is in the folding state, the transportation is convenient, the reconfigurable satellite platform is suitable for the installation of satellites with fewer modules when the reconfigurable satellite platform is in the semi-unfolding state, the space and the interface can be further expanded, the satellite functions can be expanded when the reconfigurable satellite platform is in the unfolding state, and in addition, the reconfigurable satellite platform is compact and symmetrical in structure and easy to control the gesture when the reconfigurable satellite platform is in the unfolding state and the semi-unfolding state; the hinge 2 comprises a shape memory hinge 21, which can conveniently realize the in-orbit reconstruction of the reconfigurable satellite platform by utilizing the shape memory property, and remarkably improve the in-orbit controllability of the reconfigurable satellite platform.
Fig. 1 is a schematic structural view of a reconfigurable satellite platform in an unfolded state, where the reconfigurable satellite platform includes seven cell units, namely, a central cell unit located at a central position and six peripheral cell units located at the periphery of the central cell unit, all the cell units are cubes, the six peripheral cell units are respectively arranged coplanar with one of the faces of the central cell unit, among the seven cube units, all the faces arranged coplanar and the faces parallel to and opposite to the coplanar are all arranged open, that is, without a panel structure, the other faces adopt square panels 1, and are connected with adjacent panels 1 through hinges 2, so that the six peripheral cell units can be folded along diagonal lines thereof, and the central cell unit can be folded along with the folding of each peripheral cell unit. In addition, the cavities which are communicated with each other are formed among different cell units in the reconfigurable satellite platform, and the adjacent panels 1 are connected through the hinge 2 by adopting the square panels 1, so that a multi-layer drawer type main bearing structure is formed, the rigidity of the cell units is further enhanced while the folding and unfolding rate is ensured, and the unfolding precision is improved. In addition, the shape memory hinge 21 is adopted in the embodiment of the invention, and the on-orbit quick deformation can be realized by utilizing the shape memory performance of the shape memory hinge.
As shown in fig. 1, the reconfigurable satellite platform in the unfolded state can be regarded as a seven-unit structure formed by surrounding six square tubular structures with the same structure, the top surface and the bottom surface of the square tubular structures are not covered by the panel 1, four side surfaces are covered by the panel 1, the adjacent panels 1 are connected through the hinge 2, the bottom surfaces of the six square tubular structures are surrounded by a square cavity with the same size, and the seven-unit structure is formed by 24 panels 1 and the hinge 2 between the panels 1.
Fig. 2 is a schematic structural diagram of the reconfigurable satellite platform in a semi-deployed state, where the reconfigurable satellite platform includes four cell units and a wing deployment unit, and the conversion from the deployed state to the semi-deployed state provides implementation possibilities for satellite in-orbit modification or reduction modules, and the conversion from a seven-unit structure to a wing deployment four-unit structure provides assistance for restoration to a minimum energy consumption state after in-orbit disassembly of the failure module. The reconfigurable satellite platform provided by the embodiment of the invention has compact and symmetrical structure and is easy to control the gesture when in the unfolding state and the semi-unfolding state.
Fig. 3 is a schematic structural diagram of the reconfigurable satellite platform in a folded state, where all the cell units in the reconfigurable satellite platform are in a folded state, so that the volume can be compressed to the greatest extent, and transportation is facilitated.
The shape memory hinges 21 connect two adjacent panels 1, the temporary shape of the shape memory hinges 21 is L-shaped, and two ends of the L-shaped shape memory hinges 21 are respectively connected with the two panels 1, so that the two panels 1 are vertical, at the moment, the cube unit where the two panels 1 are located is in an unfolded cube state, and at the moment, the reconfigurable satellite platform can be in an unfolded state; the initial shape of the shape memory hinge 21 is a one or a U, two ends of the shape memory hinge 21 are respectively connected with the two panels 1, so that the two panels 1 are approximately coplanar or the two panels 1 are parallel, folding of a square unit where the two panels 1 are located can be achieved at the moment, and the shape memory hinge 21 can return to the initial shape from the temporary shape when the shape memory hinge 21 is stimulated by the outside to reach a glass transition temperature (Tg) or above, thereby achieving state transition.
In order to facilitate understanding of the reconfiguration process of the reconfigurable satellite platform provided by the embodiment of the present invention, the following exemplary description is made on the state change process of the reconfigurable satellite platform;
as shown in fig. 4 (a), the faces in the unfolded state (i.e., the seven-cell structure) are numbered, and as shown in fig. 4 (B), the edges in the unfolded state (i.e., the seven-cell structure) are numbered. As shown in fig. 4 (B), a coordinate system shown in the figure is constructed with the center point of the reconfigurable satellite platform in the unfolded state as the origin, the cell structure number in the negative X-axis direction is (1), the cell number in the positive Z-axis direction is (2), the cell number in the square X-axis direction is (3), the cell number in the negative Z-axis direction is (4), the cell number in the negative Y-axis direction is (5), and the cell number in the positive Y-axis direction is (6); the cell unit number in the center is (7); the edges formed between the panel 1 and the adjacent panel 1 in each cell unit are then numbered as shown in fig. 4 (a) and (B).
Based on this, a state transformation process of the reconfigurable satellite platform is described as shown in table 1:
table 1 state transition procedure explanatory table for reconfigurable satellite platform
In Table 1, deltaV cell Representing the volume change, wherein DeltaV cell =0 indicates that the volume of the cell unit has not changed, Δv cell ＝L 3 Indicating that the cell unit changed from a square to a planar structure.
As shown in Table 1, in the transition from the expanded state to the semi-expanded state, the peripheral cell units of numbers (1) to (4) were unchanged in volume, the peripheral cell units of numbers (5) and (6) and the central cell unit of number (7) were changed in volume, and the volume was changed to L 3 (L is the side length of the cell unit), namely the square structure is changed into the plane structure, the hinges at the edges of 6.2, 5.2 and 5.4 are changed from 90 degrees to 180 degrees, namely the hinges at the edges of 6.1, 6.3, 5.1 and 5.3 are changed from the L to the one-shaped structure, and the hinges at the edges of 6.1, 6.3 and 5.1 are changed from 90 degrees to 0 degrees, namely the hinges at the edges of 5.2, 5.4 are changed from the L to the U-shaped structure.
In the transition from the semi-expanded state to the expanded state, the peripheral cell units numbered (1) - (4) change in volume to L 3 (L is the side length of the cell unit), namely the square structure is changed into the plane structure, the hinges at the edges of 1.2, 1.4, 2.2, 2.4, 3.2, 3.4, 4.2 and 4.4 are changed from 90 degrees to 180 degrees, namely the L is changed into the one-shaped structure, and the hinges at the edges of 1.1, 1.3, 2.1, 2.3, 3.1, 3.3, 4.1 and 4.3 are changed from 90 degrees to 0 degrees, namely the L is changed into the U-shaped structure.
It should be noted that, if the panel structure is sufficiently light and thin, the wing-stretching four-unit structure in the half-stretching state can be further converted into a four-unit structure, and the wing-stretching structure can be upwards or downwards folded, so that the wing-stretching four-unit structure can be further converted into a zero-unit structure in the folding state, and the zero-unit structure is in a planar structure at the moment, so that the occupied volume is smaller.
In one embodiment, a revolute pair 22 is further disposed between adjacent panels, and the revolute pair 22 includes a first revolute pair for performing a 90 ° to 180 ° rotation process and a second revolute pair for performing a 90 ° to 0 ° rotation process.
That is, adjacent panels are connected through the shape memory hinge 21 and the revolute pair 22, and by the combined design of the two, the reconfigurable satellite platform can realize stable and impact-free conversion in state conversion, and can provide enough restoring force to drive the folding of the panel 1, so that the functions of driving folding and self-locking after folding are realized.
The first revolute pair is used for realizing the rotation process of 90 degrees to 180 degrees, the second revolute pair is used for realizing the rotation process of 90 degrees to 0 degrees, and the second revolute pair is respectively used for being matched with the shape memory hinges 21 with the initial shapes of one and U, so that the state transformation of the reconfigurable satellite platform is realized.
Illustratively, as shown in fig. 5, when the adjacent panel 1 in fig. 5 is converted from 90 ° to 180 ° in state change, the structure of the revolute pair 22 is shown in the figure, the temporary shape of the corresponding shape memory hinge 21 is an "L" shape, and the initial shape is a "one" shape; as shown in fig. 6, when the adjacent panel 2 in fig. 6 is changed from 90 ° to 180 °, the structure of the revolute pair 22 is shown in the figure, the temporary shape of the corresponding shape memory hinge 21 is an "L" shape, and the initial shape is a "U" shape.
In one embodiment, the panel 1 comprises a honeycomb sandwich and skins covering both sides of the honeycomb sandwich.
Illustratively, the honeycomb sandwich comprises an aramid paper honeycomb core, the skin being a carbon fiber panel layer, or an aluminum alloy panel layer.
The panel 1 formed by the honeycomb interlayer and the skin has the characteristics of light weight and high rigidity, and the thickness of the panel 1 can be controlled below 60 mm.
Illustratively, the reconfigurable satellite platform has an area of 1m in the collapsed state 2 60mm thick, total mass not exceeding 10kg, expansion ratio about 5:1.
in one embodiment, as shown in fig. 7, the shape memory hinge 21 includes a connection head 211, a shape memory arc sheet 212, and a fixing member 213, wherein the shape memory arc sheet 212 is located between the two connection heads 211;
the two connectors 211 are respectively used for connecting two adjacent panels 1, the shape memory arc-shaped sheet 212 comprises a temporary shape and an initial shape, the temporary shape and the initial shape are used for realizing the conversion of the reconfigurable satellite platform between different states, and the fixing piece 213 is used for fixing the shape memory arc-shaped sheet 212 on the connectors 211.
The connectors 211 at both ends are respectively connected with the two adjacent panels 1, and the shape memory arc-shaped sheet 212 is made of a shape memory material. The shape memory arcuate sheet 212 includes two opposing shape memory arcuate sheets therein, which improves strength and reduces the risk of wear and damage. The temporary shape of the shape memory arc-shaped sheet 212 is an "L" shape, the initial shape is an "one" shape or a "U" shape, and in the shape memory hinge 21 shown in fig. 7, the shape memory arc-shaped sheet 212 is an "one" shape, and the shape memory arc-shaped sheet 212 is bent to one side thereof to form an "L" shape or a "U" shape. The fixing piece 213 is used for fixing the shape memory arc-shaped sheet 212 on the connecting head 211, so that the shape memory hinge 21 forms a whole, the stability and reliability of the shape memory hinge 21 during rotation are ensured, the fixing piece 213 can also be made of shape memory materials, and the shape and the position can be changed if necessary.
In one embodiment, as shown in fig. 8, the hinge 2 is connected to the panel 1 by a bolt, and the honeycomb sandwich is provided with a pre-buried bowl 11, and the bolt is used for connecting the hinge 2 to the panel 1 by the pre-buried bowl 11.
Through screwed connection need punch on panel 1, in order to avoid punching and cause stress concentration to panel 1, lead to taking place the problem of extrusion destruction, set up pre-buried bowl type spare 11 in the honeycomb intermediate layer, can be with concentrated load dispersion to panel 1 in, reduce stress concentration problem, reduce the risk of damage.
In one embodiment, as shown in fig. 8, the bolt is a shape memory bolt 3, the shape memory bolt is made of a shape memory polymer, and a shape memory alloy spring 31 is provided in the shape memory bolt 3.
In the state transformation process of the reconfigurable satellite platform, the joint points connected through the bolts are easy to vibrate, the shape memory bolts 3 made of the shape memory polymers can generate larger restoring force in the deformation restoring process, and the vibration can be actively controlled; meanwhile, the shape memory alloy spring 31 is further arranged in the shape memory bolt 3, when vibration occurs, the shape memory alloy spring 31 can generate larger deformation to realize energy consumption, the super elasticity and self hysteresis energy consumption of the shape memory bolt 3 can be fully exerted, and the ideal results of stable structure under vibration, good ductility and self-resetting of the structure after vibration are achieved. Namely, the shape memory bolt 3 plays a role in looseness prevention and vibration reduction by utilizing the unique advantages of the shape memory bolt in vibration reduction and energy absorption and the intelligent feasible structure of self-centering connection.
In one embodiment, the shape memory polymer includes a matrix phase including at least one of an epoxy-based shape memory polymer and a cyanate-based shape memory polymer, and a reinforcing phase including at least one of continuous fibers, short fibers, and reinforcing particles.
The matrix phase in the shape memory polymer is used for providing shape memory performance, the matrix phase can be selected according to the requirements of the use environment, the glass transition temperature of the epoxy shape memory polymer can be obtained by modifying within the range of 80-180 ℃, and the glass transition temperature of the cyanate shape memory polymer can be obtained by modifying within the range of 180-200 ℃. The reinforcing phase can improve strength and comprises continuous fibers, short fibers and reinforcing particles, and further can be carbon fibers, glass fibers, aramid fibers, polyethylene fibers and the like with good mechanical properties.
The embodiment of the invention also provides a method for installing the reconfigurable satellite platform, which is used for installing the reconfigurable satellite platform and comprises the following steps of:
s1, assembling a panel 1 and a hinge 2 to obtain a reconfigurable satellite platform in a folded state, wherein the hinge 2 comprises a shape memory hinge 21, and the shape memory hinge 21 presents an initial shape of a 'one' shape or a 'U' shape;
step S2, heating part of the shape memory hinges 21 to above the glass transition temperature, applying an external force to enable part of the shape memory hinges 21 to be converted into an L-shaped temporary shape, converting the reconfigurable satellite platform into a semi-unfolded state and keeping the semi-unfolded state, and reducing the temperature to below the glass transition temperature to obtain the reconfigurable satellite platform in the semi-unfolded state;
and S3, heating the rest part of the shape memory hinges 21 to be above the glass transition temperature, applying an external force to enable all the shape memory hinges 21 to be converted into L-shaped temporary shapes, converting the reconfigurable satellite platform into an unfolding state, maintaining the unfolding state, and reducing the temperature to be below the glass transition temperature to obtain the reconfigurable satellite platform in the unfolding state.
The installation method of the reconfigurable satellite platform provided by the embodiment of the invention has the same beneficial effects as those of the reconfigurable satellite platform in the prior art, and is not repeated here.
The embodiment of the invention also provides a reconfigurable satellite which comprises the reconfigurable satellite platform.
The main structure of the satellite is generally divided into a propulsion cabin, a service cabin, a loading cabin and the like, a satellite platform is formed by connecting a plurality of cabin bodies in series, based on Plug-and-Play (PnP) concept, each independent multifunctional structure is assembled into a cubic satellite prototype through a mechanical arm, the multifunctional structures are interconnected through inter-plate interfaces, and cell satellites of different modules can be integrated and realize different functions. The reconfigurable satellite platform provided by the embodiment of the invention can be suitable for different situations through state transformation.
The reconfigurable satellite independently decomposes the part components of the traditional satellite into a plurality of modules according to different functions, and unified mechanical and electrical interfaces are designed among the modules, so that the functions of flexible assembly, rapid production and functional expansion are achieved. The reconfigurable satellite can realize on-orbit maintenance and module recycling, reduces the maintenance difficulty and cost of the satellite, reduces the generation of space garbage, can reconfigure and optimize according to different task demands, and can realize controllable orbit transfer, rapid networking and the like.
The reconfigurable satellite provided by the embodiment of the invention has lower quality, and can be recycled for the cell satellite structure with faults or the cell units which cannot be reused.
In one embodiment, the reconfigurable satellite further comprises a power supply system, a communication system, a sensing system, a control system, and a loading system mounted in the reconfigurable satellite platform.
Illustratively, the power supply system includes a solar cell and a battery, 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 source, and a power management system, and the load system includes a camera, a spectrometer, and a synthetic aperture radar.
By respectively configuring a power supply system, a communication system, a sensing system, a control system and a load system in each cell unit of the reconfigurable satellite platform provided by the embodiment of the invention, different cell units have independent functionality and expansion characteristics capable of realizing different load tasks, and the different cell units are independently replaceable. After assembly, the cell units work cooperatively, thereby realizing complex platform functions and load task requirements. When part of the cell units are in a closed state, the part of the load system can be closed, part of the functional load and control system is protected, the auxiliary power supply is mainly started, and the solar cell panel continues to work to charge the storage battery. When a task needs to be executed, the control system judges the task demand, and according to a judging result, the control system supplies power to the shape memory composite material hinge structure, drives the whole structure to be unfolded through the driving device, completes platform load configuration, and after the configuration is completed, the satellite can start executing the task demand.
Illustratively, the driving means comprises at least one of an electromagnetic driver, an ultrasonic driver, a piezoelectric driver, a motor driver, a hydraulic driver, and a pneumatic driver.
In addition, on the basis of the reconfigurable satellite provided by the invention, a double-satellite self-serial emission configuration, a single-satellite emission configuration, a satellite running configuration, a space transportation configuration, a space dragging configuration, a space maintenance and filling configuration, a satellite formation flying configuration and the like can be obtained.
Although the invention is disclosed above, the scope of the invention is not limited thereto. Various changes and modifications may be made by one skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications will fall within the scope of the invention.
Claims (10)
1. The reconfigurable satellite platform is characterized by comprising an unfolding state, a semi-unfolding state and a folding state;
in the unfolding state, the reconfigurable satellite platform presents a seven-unit structure and comprises a cube-shaped central cell unit and peripheral cell units, wherein one central cell unit is positioned at the central position, and six peripheral cell units are respectively arranged in a coplanar manner with different surfaces in the central cell unit;
in the seven-unit structure, the normal direction of each surface in the central cell unit is open, a cavity which is communicated with each other is formed in the seven-unit structure, each surface of other areas is covered by a square panel (1), and the adjacent panels (1) are connected by a hinge (2);
in the semi-unfolding state, on the basis of the seven-unit structure, the central cell unit and the two peripheral cell units arranged on two opposite sides of the central cell unit are folded into a planar structure along a diagonal line to form a wing-unfolding four-unit structure containing four peripheral cell units and a wing-unfolding structure;
in the folded state, on the basis of the four-unit structure of the unfolding wing, four peripheral cell units are folded into a planar structure along diagonal lines to form a zero-unit structure without the central cell unit and the peripheral cell units;
the hinge (2) comprises a shape memory hinge (21), the temporary shape of the shape memory hinge (21) is L-shaped, the initial shape of the shape memory hinge (21) is one or U-shaped, and when the shape memory hinge (21) is converted from the temporary shape to the initial shape, the reconfigurable satellite platform is used for realizing the conversion from the unfolded state to the half unfolded state and the folded state.
2. Reconfigurable satellite platform according to claim 1, characterized in that a revolute pair (22) is further provided between adjacent panels (1), the revolute pair (22) comprising a first revolute pair for effecting a 90 ° to 180 ° rotation and a second revolute pair for effecting a 90 ° to 0 ° rotation.
3. Reconfigurable satellite platform according to claim 1, characterized in that the panel (1) comprises a honeycomb sandwich and skins covering both sides of the honeycomb sandwich.
4. Reconfigurable satellite platform according to claim 1, characterized in that the shape memory hinge (21) comprises a connection head (211), a shape memory arc-shaped sheet (212) and a fixing element (213), the shape memory arc-shaped sheet (212) being located between two connection heads;
the two connectors (211) are respectively used for connecting two adjacent panels (1), the shape memory arc-shaped sheet (212) comprises a temporary shape and an initial shape and is used for realizing the conversion of the reconfigurable satellite platform between different states, and the fixing piece (213) is used for fixing the shape memory arc-shaped sheet (212) on the connectors (211).
5. A reconfigurable satellite platform according to claim 3, characterized in that the hinge (2) is connected to the panel (1) by means of bolts, in which the honeycomb sandwich is provided with pre-buried bowl-shaped pieces (11), the bolts being used to connect the hinge (2) to the panel (1) by means of the pre-buried bowl-shaped pieces (11).
6. Reconfigurable satellite platform according to claim 5, characterized in that the bolts are shape memory bolts (3), the shape memory bolts (3) are made of shape memory polymers, and shape memory alloy springs (31) are provided in the shape memory bolts (3).
7. The reconfigurable satellite platform of claim 6, wherein the shape memory polymer comprises a matrix phase comprising at least one of an epoxy-based shape memory polymer and a cyanate-based shape memory polymer and a reinforcement phase comprising at least one of continuous fibers, short fibers, and reinforcing particles.
8. A method of installing a reconfigurable satellite platform according to any one of claims 1 to 7, comprising the steps of:
s1, assembling a panel (1) and a hinge (2) to obtain a reconfigurable satellite platform in a folded state, wherein the hinge (2) comprises a shape memory hinge (21), and the shape memory hinge (21) presents an initial shape of a 'one' shape or a 'U' shape;
s2, heating part of the shape memory hinges (21) to be above the glass transition temperature, applying external force to enable part of the shape memory hinges (21) to be converted into an L-shaped temporary shape, converting the reconfigurable satellite platform into a semi-unfolded state and keeping the semi-unfolded state, and reducing the temperature to be below the glass transition temperature to obtain the reconfigurable satellite platform in the semi-unfolded state;
and S3, heating the other part of the shape memory hinges (21) to be above the glass transition temperature, applying an external force to enable all the shape memory hinges (21) to be converted into an L-shaped temporary shape, converting the reconfigurable satellite platform into an unfolding state and keeping the unfolding state, and reducing the temperature to be below the glass transition temperature to obtain the reconfigurable satellite platform in the unfolding state.
9. A reconfigurable satellite comprising a reconfigurable satellite platform according to any one of claims 1 to 7.
10. The reconfigurable satellite of claim 9, further comprising a power supply system, a communication system, a sensing system, a control system, and a loading system installed in the reconfigurable satellite platform.
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| CN202311388011.7A CN117326097A (en) | 2023-10-24 | 2023-10-24 | Reconfigurable satellite platform, installation method thereof and reconfigurable satellite |
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| CN202311388011.7A CN117326097A (en) | 2023-10-24 | 2023-10-24 | Reconfigurable satellite platform, installation method thereof and reconfigurable satellite |
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