Two-dimensional single-unfolding hundred-square-meter flexible solar wing

Abstract

The invention discloses a two-dimensional single-unfolding hundred-square-meter-level flexible solar wing which comprises a flexible array surface capable of infinitely transversely and / or longitudinally expanding based on a paper folding structure, an auxiliary unfolding mechanism for assisting the unfolding of the flexible array surface, and an unfolding driving mechanism for driving the unfolding of the whole wing, the flexible array surface is formed by connecting first folding and unfolding units located at the two ends and a second folding and unfolding unit located in the middle through piano type hinges, and the whole wing can be unfolded in the transverse direction and the longitudinal direction from the folded state through single-time unfolding. The two types of folding and unfolding units are double-vertex seven-fold paper folding units, and the flexible array plane has a single degree of freedom; the auxiliary unfolding mechanism is connected with the first type of folding and unfolding units and is connected with the unfolding driving mechanism; the motion trail of the tail end of the auxiliary unfolding mechanism in the unfolding process is consistent with the motion trail of the flexible plates on the two sides of the first folding and unfolding unit. According to the invention, a paper folding configuration is applied to flexible array surface design, two-dimensional single-time unfolding of the whole wing is realized, and the problem of insufficient storage ratio of a traditional one-dimensional unfolding configuration solar wing is solved.

Description

Technical Field

[0001] The present invention relates to the technical field of solar wing technology, and in particular to a two-dimensional single-expandable 100-square-meter flexible solar wing. Background Art

[0002] Solar panels are the sole source of energy for spacecraft in orbit. The effective unfolding area of the solar panels determines their power generation. Solar panels are typically folded at launch and fully unfolded in orbit. Minimizing the folded envelope and achieving an ultra-high fold-to-stretch ratio is a key issue for solar panels.

[0003] Most of the solar wings currently in common use are one-dimensional single-time unfolding, which still has insufficient storage ratio and cannot meet the trend of larger solar wings. Summary of the Invention

[0004] The purpose of the present invention is to overcome the shortcomings and defects of the existing technology and to provide a two-dimensional single-expandable 100-square-meter flexible solar wing with a higher storage ratio, aiming to improve the storage ratio of the entire solar wing and at the same time ensure the high reliability of the deployment of the entire wing to adapt to the trend of large-scale solar wings.

[0005] The present invention is achieved in that:

[0006] A two-dimensional single-expandable 100-square-meter flexible solar wing comprises an origami-based flexible array that can be infinitely expanded laterally and / or longitudinally, an auxiliary expansion mechanism for assisting the expansion of the flexible array, and an expansion drive mechanism for driving the entire wing to expand; the flexible array is composed of a first type of folding and expansion unit located at both ends and a second type of folding and expansion unit located in the middle, which are connected by a piano-type hinge, so that the entire wing can be expanded in both the laterally and longitudinal directions through a single expansion from a folded state; the first type of folding and expansion unit and the second type of folding and expansion unit are both double-vertex seven-fold origami units, and the flexible array has a single degree of freedom; the auxiliary expansion mechanism is connected to the first type of folding and expansion unit of the flexible array, and is also connected to the expansion drive mechanism; the motion trajectory of the auxiliary expansion mechanism at the end of the expansion process is consistent with the motion trajectory of the flexible plates on both sides of the first type of folding unit.

[0007] Preferably, all panels of the second type of folding unit are flexible plates for loading flexible battery cells, and the first type of folding unit includes a rigid plate for pressing the entire flexible array and five flexible plates for loading flexible battery cells, and the rigid plate is located on one side of the middle part of the first type of folding unit.

[0008] Preferably, one end of the auxiliary deployment mechanism is connected to the flexible plate of the first type of folding and unfolding unit of the flexible array, and the other end is fixed to the upper and lower sides of the proximal bracket and the distal bracket of the deployment drive mechanism.

[0009] Preferably, in the double-vertex seven-fold origami unit, the relationship between the number of folds M and the number of vertices N satisfies the formula: M=4N-1=7, including five peak folds L1, L2, L3, L4, L5 and two valley folds H1 and H2; wherein, the valley folds H1 and H2 are arranged along the length direction of the origami unit, respectively connecting the upper and lower panels at the two ends of the origami unit, the peak fold L5 connects the upper and lower panels in the middle, the peak folds L1 and L2 connect the upper and lower panels at one end with the corresponding upper and lower panels in the middle, and the peak folds L3 and L4 connect the upper and lower panels at the other end with the corresponding upper and lower panels in the middle.

[0010] Preferably, the auxiliary deployment mechanism includes a proximal auxiliary deployment mechanism and a distal auxiliary deployment mechanism, and the proximal auxiliary deployment mechanism and the distal auxiliary deployment mechanism each include two auxiliary deployment modules, which are generally symmetrically distributed on the entire wing of the solar wing.

[0011] Preferably, the auxiliary deployment module of the proximal auxiliary deployment mechanism includes a fixed seat, a motor, an auxiliary long rod, an auxiliary short rod, and a constant force coil spring. The fixed seat is connected to the proximal bracket of the driving mechanism through a rigid hinge, and is connected to one end of the auxiliary short rod. The other end of the auxiliary short rod is connected to the body of the motor, and the output shaft of the motor is connected to the auxiliary long rod. The auxiliary long rod and the auxiliary short rod are both provided with spring connectors to connect the constant force coil spring. The other end of the constant force spring is connected to two flexible plates at both ends of the first type of folding and deployment unit at the proximal end.

[0012] Preferably, the auxiliary deployment module of the distal auxiliary deployment mechanism includes a fixed seat, a motor, an auxiliary long rod, an auxiliary short rod, and a tension coil spring. The fixed seat is connected to the proximal bracket of the driving mechanism through a rigid hinge, and is connected to one end of the auxiliary short rod. The other end of the auxiliary short rod is connected to the body of the motor, and the output shaft of the motor is connected to the auxiliary long rod. The auxiliary long rod is evenly distributed with tension springs, and the other end of the tension spring is connected to two flexible plates at both ends of the distal first-type folding unit.

[0013] Preferably, the flexible array achieves longitudinal expansion by adding a second type of folding unit in the middle area between the proximal end and the distal end, and / or achieves lateral expansion by adding Miura origami units between the middle plate and the two side plates of a single folding unit; after expansion, the entire flexible array based on the origami configuration has a single degree of freedom.

[0014] Preferably, the deployment drive mechanism includes a scissors-fork type deployment drive mechanism.

[0015] Preferably, the scissors-type deployment drive mechanism includes a proximal bracket, a distal bracket, and a scissors rod module composed of multi-stage scissors units arranged between the proximal bracket and the distal bracket; under the drive of the driving and transmission module, the scissors rod module can be gradually deployed or retracted.

[0016] The two-dimensional single-deployment 100-square-meter flexible solar wing of the present invention is based on the rigid origami theory and the double-vertex seven-fold origami unit design, achieving an ultra-high storage ratio and two-way expandability of the 100-square-meter array surface. When not in operation, the solar wing can be completely folded to achieve a smaller envelope volume, and then unfolded to the designated working position during the working phase.

[0017] The two-dimensional single-expansion hundred-square-meter flexible solar wing of the present invention achieves an ultra-large folding and unfolding ratio and two-dimensional single expansion through a new array surface with an origami configuration, avoiding additional drive motors. Compared with traditional solar wings, it has great advantages in performance such as expansion area and modal fundamental frequency. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A schematic diagram of the unfolded state structure of a two-dimensional single-expanded 100-square-meter flexible solar wing according to an embodiment of the present application is shown.

[0019] Figure 2 A schematic diagram of the folded state structure of a two-dimensional single-expanded 100-square-meter flexible solar wing according to an embodiment of the present application is shown.

[0020] Figure 3 A schematic structural diagram of a flexible array based on an origami configuration according to an embodiment of the present application is shown.

[0021] Figure 4 A schematic structural diagram of the first type of paper folding unit in a folded state according to an embodiment of the present application is shown.

[0022] Figure 5 A structural schematic diagram of the first type of paper folding unit according to an embodiment of the present application is shown.

[0023] Figure 6 A crease diagram of a double-vertex seven-crease basic origami unit according to an embodiment of the present application is shown.

[0024] Figure 7 A schematic diagram of a bidirectional expansion form of a 100-square-meter array based on an origami configuration according to an embodiment of the present application is shown.

[0025] Figure 8 The figure shows the overall structure of the scissor-type drive mechanism according to an embodiment of the present application.

[0026] Figure 9 、 Figure 10 The overall structural schematic diagrams of the deployed state of the auxiliary deployment mechanism according to the embodiments of the present application are respectively shown.

[0027] Figure 11 、 Figure 12Schematic diagrams of the overall structure of the folded state of the auxiliary deployment mechanism according to the embodiments of the present application are respectively shown. DETAILED DESCRIPTION

[0028] The present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not intended to limit the present invention.

[0029] See also Figure 1 as well as Figure 2 As shown, the fully unfolded state of the two-dimensional single-expansion 100-square-meter flexible solar wing of the present invention is as follows Figure 1 As shown, the fully folded state is as follows Figure 2 shown.

[0030] In an exemplary embodiment of the present application, the two-dimensional single-deployment hundred-square-meter flexible solar wing includes a flexible array 1 based on an origami configuration that can be infinitely expanded laterally and / or longitudinally, an auxiliary deployment mechanism 2 for assisting the deployment of the flexible array, and a deployment drive mechanism 3 for driving the entire wing to deploy, wherein the flexible array has a single degree of freedom.

[0031] See also Figure 3 As shown in the embodiment of the present application, the flexible array 1 is composed of a first type of folding unit located at both ends and a second type of folding unit located in the middle connected by a piano hinge 6, so that the entire wing can be expanded in both the horizontal and vertical directions by a single expansion from the folded state. Figure 3 As shown, the first type of folding unit is composed of the proximal first type folding unit 4 and the distal first type folding unit 7, and the second type of folding unit is composed of multiple intermediate second type folding units 5. Specifically, the flexible array 1 based on the origami configuration is composed of two different types of folding units, the first type folding unit 4 and the second type folding unit. The first type of origami unit and the second type of origami unit have the same configuration.

[0032] Among them, the auxiliary deployment mechanism 2 is connected to the first type of folding and unfolding unit of the flexible array 1 and is connected to the deployment drive mechanism; the motion trajectory of the auxiliary deployment mechanism at the end of the deployment process is consistent with the motion trajectory of the flexible plates on both sides of the first type of folding and unfolding unit.

[0033] Exemplarily, the distal end of the deployment drive mechanism is connected to the 100-square-meter flexible array and the auxiliary deployment mechanism via a rigid hinge. The proximal end of the deployment drive mechanism is bolted to the auxiliary deployment mechanism and further connected to the 100-square-meter flexible array via a constant-force coil spring on the auxiliary deployment mechanism. The drive mechanism drives the entire 100-square-meter flexible array into position via a drive and transmission module.

[0034] In the embodiment of the present application, the first type of folding and unfolding unit and the second type of folding and unfolding unit have the same configuration, both of which are double-vertex seven-fold origami units. Figure 4 As shown, the folds are Figure 5 、 Figure 6 The difference between the first type of folding unit and the second type of folding unit is that the first type of folding unit includes a middle rigid plate 401 for compressing the entire array, namely the middle upper plate, and the other plates are all flexible plates for loading flexible battery cells (such as the left upper plate 402, the right upper plate 403, the left lower plate 404, the middle lower plate 405, and the right lower plate 406), while all panels of the second type of folding unit are flexible plates.

[0035] The rigid plate is a flat plate with a certain thickness and high rigidity, and the flexible plate is a flat plate with a very small thickness and high flexibility, and is mainly responsible for loading battery cells.

[0036] For example, in the embodiment of the present application, the panels of the entire flexible array 1 based on the origami configuration are connected by piano-type hinges 6 .

[0037] like Figure 6 As shown, in the embodiment of the present application, the double-vertex seven-fold origami unit has a single degree of freedom, and the relationship between the number of folds M and the number of vertices N satisfies the formula: M=4N-1=7, and the seven folds include five peak folds L1, L2, L3, L4, L5 and two valley folds H1, H2.

[0038] like Figure 7 As shown, in the embodiment of the present application, the flexible array 1 based on the origami configuration can be further expanded. The longitudinal expansion can be achieved by adding a second type of folding unit in the middle part, and the lateral expansion can be achieved by adding Miura origami units between the middle plate and the two side plates of a single folding unit, thereby achieving two-way expansion and a larger folding ratio.

[0039] like Figure 8 As shown, in the embodiment of the present application, the deployment drive mechanism can adopt a scissor-type deployment drive mechanism, which includes a proximal bracket 201, a scissor rod module 202, a distal bracket 203, and a drive module and a transmission module 204. During operation, the drive module and the transmission module provide the driving force of the scissor rod, thereby driving the scissor rod module composed of multi-stage scissor units to gradually deploy, thereby driving the distal bracket to move relative to the proximal bracket, increasing or decreasing the relative distance. The drive module and the transmission module 204 can be implemented by a drive mechanism such as a motor or an electric cylinder.

[0040] like Figure 9 ,as well as Figure 10As shown, in the embodiment of the present application, there are four auxiliary deployment mechanisms, two at the proximal end and two at the distal end, which are generally symmetrically distributed. The motion trajectory of the deployment process is consistent with the motion trajectory of the flexible plates on both sides of the first type of folding unit, so as to realize the auxiliary deployment and tensioning function of the flexible plates on both sides of the first type of folding unit of the array.

[0041] For example, in the embodiment of the present application, the two auxiliary deployment mechanisms at the proximal end are connected to the flexible array surface via multiple constant force coil springs 305, and the two auxiliary deployment mechanisms at the distal end are connected to the flexible array surface via multiple tension springs 307. Each auxiliary deployment mechanism at the proximal end is composed of a fixing base 301, an auxiliary short rod 302, a motor 303, an auxiliary long rod 304, a constant force coil spring 305, and a spring connector 306.

[0042] The fixed base 301 is connected to the proximal bracket 201 of the scissor-type drive mechanism via a rigid hinge to form a revolute joint. The fixed base 301 is also connected to the auxiliary short rod. One end of the auxiliary short rod 302 forms a revolute joint with one end of the auxiliary long rod 304. The auxiliary long rod 304 is connected to the flexible plates on both sides of the first type of folding and unfolding unit of the flexible array 1. The motor 303 is arranged on the revolute joint between the auxiliary short rod 302 and the auxiliary long rod 304 to ensure that the auxiliary deployment mechanism can follow the deployment trajectory of the flexible array based on the origami configuration.

[0043] Taking the installation of the proximal bracket as an example, the fixed seat 301 is connected to the proximal bracket 201 of the scissor-type drive mechanism through a rigid hinge; the fixed seat 301 is fixedly connected to one end of the auxiliary short rod 302; the other end of the auxiliary short rod 302 is connected to the body of the motor 303, and the output shaft of the motor 303 is connected to the auxiliary long rod 304 by a top screw. The auxiliary long rod 304 and the auxiliary short rod 302 are evenly provided with spring connectors 306 to connect the constant force coil spring 305, and the other end of the constant force spring 305 is connected to the flexible plates on both sides of the first type of folding unit (such as the left upper plate 402 and the right upper plate 403).

[0044] The main connection method of the two auxiliary deployment mechanisms at the distal end is basically the same as that of the auxiliary deployment mechanism at the proximal end. The difference is that the auxiliary long rod of the distal auxiliary deployment mechanism is connected to the flexible plates on both sides of the first type of folding unit (such as the left upper plate 402 and the right upper plate 403) through the evenly distributed tension spring 307.

[0045] Under the scheme of adopting the above-mentioned auxiliary development mechanism and scissor-type driving mechanism, in the embodiment of the present application,

[0046] Specifically, at the proximal end of the solar wing, the origami-shaped flexible array 1 is connected to the auxiliary deployment mechanism 2 via multiple constant-force coil springs 305 evenly distributed throughout the auxiliary deployment mechanism. One end of the constant-force coil spring 305 is mounted on a spring connector 306 and bolted to the auxiliary long rod 304 of the auxiliary deployment mechanism. The auxiliary deployment mechanism's fixing base 301 is bolted to the proximal bracket 201 of the scissor-type drive mechanism. At the distal end of the solar wing, the intermediate rigid plate 401 of the origami-shaped flexible array 1 is connected to the distal bracket 203 of the scissor-type drive mechanism via a row hinge. The auxiliary deployment mechanism is also bolted to the intermediate rigid plate 401 of the origami-shaped flexible array.

[0047] In the embodiment of the present application, the flexible array 1 based on the origami configuration, the scissor-type drive mechanism 2 and the auxiliary deployment mechanism 3 are connected to form a two-dimensional single-expansion 100-square-meter solar wing, which is folded (such as Figure 2 As shown in the figure, the scissor-type drive mechanism reaches the expected working position, and the driving and transmission module of the scissor-type drive mechanism applies driving force to drive the scissor-type rod module to expand and push out the distal bracket, thereby driving the flexible array based on the origami configuration to expand. In this process, the fixed seat 301 and the proximal bracket 201 of the scissor-type drive mechanism rotate relative to each other as the flexible array expands, and the motor of the auxiliary expansion mechanism drives the auxiliary long rod to move, so that the motion trajectory of the auxiliary long rod during the expansion process is consistent with the motion trajectory of the flexible plates on both sides of the first type of folding and expansion unit, and finally reaches the expanded state of the entire two-dimensional single-expansion 100-square-meter array flexible solar wing (as shown in the figure). Figure 1 shown).

[0048] The basic principles, main features and advantages of the present invention are shown and described above. It is obvious to those skilled in the art that the present invention is not limited to the details of the above exemplary embodiments and that the present invention can be implemented in other specific forms without departing from the spirit or basic features of the present invention.

[0049] The embodiments are therefore to be considered in all respects as illustrative and not restrictive, the scope of the invention being defined by the appended claims rather than the foregoing description, and all changes that come within the meaning and range of equivalents of the claims are therefore intended to be embraced therein.

[0050] In addition, it should be understood that although this specification is described in terms of implementation methods, not every implementation method contains only one independent technical solution. This narrative method of the specification is only for the sake of clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

Claims

1. Two-dimensional single-expansion 100-square-meter flexible solar wing, characterized by: It includes a flexible array based on an origami configuration that can be infinitely expanded laterally and / or longitudinally, an auxiliary deployment mechanism for assisting the deployment of the flexible array, and an deployment drive mechanism for driving the deployment of the entire wing; the flexible array is composed of a first type of folding and deployment unit located at both ends and a second type of folding and deployment unit located in the middle, which are connected by a piano-type hinge, so that the entire wing can be deployed in both the laterally and longitudinal directions through a single deployment from a folded state; the first type of folding and deployment unit and the second type of folding and deployment unit are both double-vertex seven-fold origami units, and the flexible array has a single degree of freedom; the auxiliary deployment mechanism is connected to the first type of folding and deployment unit of the flexible array, and is also connected to the deployment drive mechanism; the motion trajectory of the auxiliary deployment mechanism at the end of the deployment process is consistent with the motion trajectory of the flexible plates on both sides of the first type of folding unit.

2. The two-dimensional single-expansion 100-square-meter flexible solar wing according to claim 1 is characterized in that: All panels of the second type of folding unit are flexible plates for loading flexible battery cells, while the first type of folding unit includes a rigid plate for pressing the entire flexible array and five flexible plates for loading flexible battery cells, and the rigid plate is located on one side of the middle part of the first type of folding unit.

3. The two-dimensional single-expansion 100-square-meter flexible solar wing according to claim 2 is characterized in that: One end of the auxiliary deployment mechanism is connected to the flexible plate of the first type of folding and deployment unit of the flexible array, and the other end is fixed to the upper and lower sides of the proximal bracket and the distal bracket of the deployment drive mechanism.

4. The two-dimensional single-expansion 100-square-meter flexible solar wing according to claim 1 is characterized in that: In the double-vertex seven-fold origami unit, the relationship between the number of folds M and the number of vertices N satisfies the formula: M=4N-1=7, and includes five peak folds L1, L2, L3, L4, L5 and two valley folds H1 and H2; wherein, the valley folds H1 and H2 are arranged along the length direction of the origami unit, respectively connecting the upper and lower panels at the two ends of the origami unit, the peak fold L5 connects the upper and lower panels in the middle, the peak folds L1 and L2 connect the upper and lower panels at one end with the corresponding upper and lower panels in the middle, and the peak folds L3 and L4 connect the upper and lower panels at the other end with the corresponding upper and lower panels in the middle.

5. The two-dimensional single-expansion 100-square-meter flexible solar wing according to claim 1 is characterized in that: The auxiliary deployment mechanism includes a proximal auxiliary deployment mechanism and a distal auxiliary deployment mechanism. The proximal auxiliary deployment mechanism and the distal auxiliary deployment mechanism each include two auxiliary deployment modules, which are generally symmetrically distributed on the entire wing of the solar wing.

6. The two-dimensional single-expansion 100-square-meter flexible solar wing according to claim 5, characterized in that: The auxiliary deployment module of the proximal auxiliary deployment mechanism includes a fixed seat, a motor, an auxiliary long rod, an auxiliary short rod, and a constant force coil spring. The fixed seat is connected to the proximal bracket of the driving mechanism through a rigid hinge, and is connected to one end of the auxiliary short rod. The other end of the auxiliary short rod is connected to the fuselage of the motor, and the output shaft of the motor is connected to the auxiliary long rod. The auxiliary long rod and the auxiliary short rod are both provided with spring connectors to connect the constant force coil spring. The other end of the constant force spring is connected to the two flexible plates at both ends of the first type of folding and deployment unit at the proximal end.

7. The two-dimensional single-expansion 100-square-meter flexible solar wing according to claim 5, characterized in that: The auxiliary deployment module of the distal auxiliary deployment mechanism includes a fixed seat, a motor, an auxiliary long rod, an auxiliary short rod, and a tension coil spring. The fixed seat is connected to the proximal bracket of the driving mechanism through a rigid hinge, and is connected to one end of the auxiliary short rod. The other end of the auxiliary short rod is connected to the body of the motor, and the output shaft of the motor is connected to the auxiliary long rod. Tension springs are evenly distributed on the auxiliary long rod, and the other end of the tension spring is connected to two flexible plates at both ends of the distal first-type folding unit.

8. The two-dimensional single-expansion 100-square-meter flexible solar wing according to claim 1, characterized in that: The flexible array achieves longitudinal expansion by adding a second type of folding unit in the middle area between the proximal end and the distal end, and / or achieves lateral expansion by adding Miura origami units between the middle plate and the two side plates of a single folding unit; after expansion, the entire flexible array based on the origami configuration has a single degree of freedom.

9. The two-dimensional single-expansion 100-square-meter flexible solar wing according to claim 1, characterized in that: The deployment drive mechanism includes a scissors-fork type deployment drive mechanism.

10. The two-dimensional single-expansion 100-square-meter flexible solar wing according to claim 9, characterized in that: The scissor-type deployment drive mechanism includes a proximal bracket, a distal bracket, and a scissor rod module composed of multi-stage scissor units arranged between the proximal bracket and the distal bracket; under the drive of the drive and transmission module, the scissor rod module can be gradually deployed or retracted.

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