A large-area flexible solar cell wing capable of step-by-step secondary deployment

Abstract

The application discloses a large-area flexible solar cell wing capable of being stepwise and twice unfolded, which comprises a lifting mechanism, an unfolding mechanism, twice unfolded flexible solar cell arrays, compacting and releasing devices and a box unfolding locking mechanism; two twice unfolded flexible solar cell arrays are arranged at the top of the two ends of the unfolding mechanism, and the box unfolding locking mechanism is connected at the connecting position of the twice unfolded flexible solar cell arrays and the unfolding mechanism; the top of the lifting mechanism is connected with the bottom of the unfolding mechanism; a plurality of compacting points are arranged on the unfolding mechanism and the twice unfolded flexible solar cell arrays respectively, and each compacting and releasing device is arranged at the corresponding compacting point position; compacting of the unfolding mechanism and the twice unfolded flexible solar cell arrays is realized by exerting compacting force at the compacting points. The flexible solar cell wing has the advantages of small folding envelope, stepwise unfolding, large unfolding area and stable unfolding configuration, and is suitable for high-load or high-control high-power spacecraft platforms.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of spacecraft, and particularly relates to a large-area flexible solar cell wing capable of being unfolded in two steps. BACKGROUND

[0002] With the development of space technology, the power demand of spacecraft is increasing. At present, the spacecraft generally adopts rigid and semi-rigid solar cell wings, which have the problems of large size in folding, limited unfolding area, and inability to meet the demand of large-power spacecraft, etc. The flexible solar cell wing has the technical advantages of small folding envelope, large unfolding and folding ratio, large power-to-weight ratio, and stable unfolding configuration, and is the development trend of the solar cell wing suitable for large-power spacecraft platforms.

[0003] However, the large-area flexible solar cell wing has a large unfolding area, a relatively low fundamental frequency, and a large control difficulty, which brings great difficulty to the on-orbit attitude adjustment, orbit transfer, and docking of the spacecraft. Meanwhile, the large area and large inertia bring about a larger load bearing. SUMMARY

[0004] The present application overcomes the shortcomings of the prior art and provides a large-area flexible solar cell wing capable of being unfolded in two steps. Two secondary unfolding flexible solar cell arrays in two folding states are arranged on both sides of the stretching mechanism, and the large-area flexible solar cell wing has the advantages of small folding envelope, two-step unfolding, large unfolding area, and stable unfolding configuration, and is suitable for large-power spacecraft platforms with high load requirements or high control requirements.

[0005] To solve the above technical problems, the present application discloses a large-area flexible solar cell wing capable of being unfolded in two steps, which comprises a lifting mechanism, a stretching mechanism, secondary unfolding flexible solar cell arrays, a compression releasing device, and a box unfolding locking mechanism. The secondary unfolding flexible solar cell arrays comprise secondary unfolding flexible solar cell array A and secondary unfolding flexible solar cell array B.

[0006] The secondary unfolding flexible solar cell array A and the secondary unfolding flexible solar cell array B are respectively arranged at the top of both ends of the stretching mechanism, and the connection positions of the secondary unfolding flexible solar cell array A and the secondary unfolding flexible solar cell array B and the stretching mechanism are respectively provided with box unfolding locking mechanism connections. The top of the lifting mechanism is connected with the bottom of the stretching mechanism. The stretching mechanism and the secondary unfolding flexible solar cell arrays are respectively provided with a plurality of compression points, and each compression releasing device is arranged at the corresponding compression point position. By applying a compression force at the compression point, the compression of the stretching mechanism and the secondary unfolding flexible solar cell arrays is realized, and the compression and anti-overload of the flexible solar cell wing in the launch section are realized.

[0007] In the initial state, the secondary flexible solar cell array A and the secondary flexible solar cell array B are folded on both sides of the stretching mechanism, and the stretching mechanism, the secondary flexible solar cell array A and the secondary flexible solar cell array B are located on the same side of the deployment baseline;

[0008] In the deployment process, the secondary flexible solar cell array is stepwise unfolded under the action of the stretching mechanism and the box body deployment locking mechanism.

[0009] In the large-area flexible solar cell wing which can be stepwise unfolded, the lifting mechanism comprises a fixed joint, a rotating joint, a lifting mechanism driving assembly and a locking assembly.

[0010] The fixed joint and the rotating joint are coaxially designed and connected by bearings to form a rotating pair.

[0011] The lifting mechanism driving assembly is connected with the rotating joint, and the rotating joint is connected with the bottom of the storage cylinder of the stretching mechanism; wherein, the lifting mechanism driving assembly outputs torque when working, drives the rotating joint to rotate relative to the fixed joint, and further drives the whole large-area flexible solar cell wing to rotate, so that the large-area flexible solar cell wing is changed from the initial state to the vertical state with the cabin body.

[0012] The locking assembly is connected with the rotating joint, and when the large-area flexible solar cell wing is changed to the vertical state with the cabin body, the rotating joint is locked; wherein, the locking assembly comprises a locking pin, a slide and a locking hole; the locking pin is located in the slide and can slide in the slide; when the large-area flexible solar cell wing is changed to the vertical state with the cabin body, the locking pin is inserted into the locking hole to lock the rotating joint.

[0013] In the large-area flexible solar cell wing which can be stepwise unfolded, the stretching mechanism comprises a stretching arm, a storage cylinder and a stretching mechanism driving assembly.

[0014] In the initial state, the stretching arm is folded in the storage cylinder.

[0015] In the deployment process, the stretching mechanism driving assembly outputs a positive torque when working, drives the stretching arm to be one-dimensionally and orderly unfolded from the storage cylinder and locked.

[0016] In the large-area flexible solar cell wing which can be stepwise unfolded, the secondary flexible solar cell array A and the secondary flexible solar cell array B have the same structure, comprising a lower storage box, an upper storage box, a constraint release mechanism, an upper cell panel, a lower cell panel, an isolation plate, a tensioning mechanism and a guide mechanism.

[0017] The upper storage box, the upper cell panel, the lower cell panel and the lower storage box are sequentially arranged from top to bottom.

[0018] A partition plate is arranged between the upper and lower battery panels; wherein the partition plate is used to realize the step-by-step secondary expansion of the flexible solar cell array during the expansion process.

[0019] One end of the constraint release mechanism is connected with the upper storage box, and the other end is connected with the lower storage box; wherein in the folding state, the constraint release mechanism is locked, and the upper and lower battery panels are folded between the upper and lower storage boxes; in the first expansion, the constraint release mechanism releases the constraint between the upper battery panel and the partition plate; in the secondary expansion, the constraint between the partition plate and the lower battery panel is released after the upper battery panel is fully expanded;

[0020] The guide mechanism is arranged on the lower storage box, and is used to provide guidance for the step-by-step secondary expansion of the flexible solar cell array during the expansion process, and assist the orderly expansion of the flexible solar cell array.

[0021] The tensioning mechanism is arranged on the upper storage box, and is used to apply tensioning force to the upper and lower battery panels after the flexible solar cell array is fully expanded, so as to ensure the in-orbit rigidity of the flexible solar cell array.

[0022] In the above large-area flexible solar cell wing which can be expanded step by step and secondarily, the upper and lower battery panels have the same structure, including: a plurality of flexible substrates, battery circuits and flexible cables;

[0023] The plurality of flexible substrates are sequentially connected in series through a piano hinge to form a flexible substrate assembly; wherein the adjacent two flexible substrates rotate around the piano hinge as the center axis, so as to realize the expansion and folding of the flexible substrate assembly.

[0024] The surface of the flexible substrate assembly is pasted with the battery circuits and the flexible cables.

[0025] In the above large-area flexible solar cell wing which can be expanded step by step and secondarily, the constraint release mechanism includes: a motor drive assembly, a four-bar linkage mechanism and an end assembly; wherein the motor drive assembly is connected with the four-bar linkage mechanism, and the four-bar linkage mechanism is provided with the end assembly at the end; the end assembly includes: a first lock hook, a second lock hook, a blocking block, a hinge clasp, a secondary unlocking rope assembly and a secondary unlocking spring assembly.

[0026] The first lock hook, the second lock hook and the blocking block are fixed on the lower storage box; the secondary unlocking spring assembly is fixed on the partition plate; one end of the hinge clasp is fixed on the upper storage box.

[0027] In the fully folded state, the other end of the hinge clasp is locked in cooperation with the first lock hook; one end of the secondary unlocking rope assembly is connected with the secondary unlocking spring assembly, and the other end is constrained between the second lock hook and the blocking block.

[0028] When the constraint release mechanism is unlocked to the first position under the action of the motor drive assembly and the four-bar linkage mechanism: the constraint between the first unlocking hook and the other end of the hinge ring is released, the constraint on the upper battery panel is released, and the upper battery panel is unfolded; at this time, the other end of the secondary unlocking rope assembly continues to be constrained between the secondary locking hook and the blocking block, and the lower battery panel is kept in the locked state;

[0029] When the constraint release mechanism is unlocked to the second position under the action of the motor drive assembly and the four-bar linkage mechanism: the secondary locking hook and the blocking block move relative to each other to generate a gap, the other end of the secondary unlocking rope assembly is released from the gap, and is retracted under the action of the secondary unlocking spring assembly, releasing the constraint on the lower battery panel, and the lower battery panel is unfolded.

[0030] In the above large-area flexible solar cell wing that can be unfolded in steps, the tensioning mechanism comprises: a tensioning mechanism coil spring assembly, a tensioning mechanism winding wheel, and a tensioning rope;

[0031] The tensioning mechanism coil spring assembly is installed outside the upper storage box of the secondary unfolding flexible solar cell array and is coaxially arranged with the tensioning mechanism winding wheel;

[0032] The tensioning rope is coplanar with the flexible substrate assembly; one end of the tensioning rope is connected with the flexible substrate assembly, and the other end is fixed on the tensioning mechanism winding wheel.

[0033] In the above large-area flexible solar cell wing that can be unfolded in steps, the guide mechanism comprises: a guide mechanism coil spring assembly, a guide mechanism winding wheel, and a guide rope;

[0034] The guide mechanism coil spring assembly is installed outside the lower storage box of the secondary unfolding flexible solar cell array and is coaxially arranged with the guide mechanism winding wheel;

[0035] The guide rope is arranged on the back of the flexible substrate assembly; one end of the guide rope is connected with the upper storage box of the secondary unfolding flexible solar cell array, and the other end is fixed on the guide mechanism winding wheel.

[0036] In the above large-area flexible solar cell wing that can be unfolded in steps, the box unfolding locking mechanism comprises: an upper box unfolding locking mechanism and a lower box unfolding locking mechanism; the upper box unfolding locking mechanism is connected with the extension arm of the extension mechanism and the upper storage box of the secondary unfolding flexible solar cell array, respectively; the lower box unfolding locking mechanism is connected with the storage cylinder of the extension mechanism and the lower storage box of the secondary unfolding flexible solar cell array, respectively; the rotation axis of the box unfolding locking mechanism is coaxially arranged with the rotation axis of the corresponding upper box unfolding locking mechanism, and the upper box unfolding locking mechanism is unfolded to be locked when the lower box unfolding locking mechanism is unfolded.

[0037] The upper box body unfolding locking mechanism comprises a male hinge, a female hinge, a rotating shaft and a locking rod; the male hinge and the female hinge form a rotating pair through the rotating shaft and have a rotating unfolding function; the male hinge is connected with the upper box body, and the female hinge is connected with the stretching arm; the locking rod is locked after unfolding to the position;

[0038] The lower box body unfolding locking mechanism comprises a fixed end, a rotating end, a driving transmission assembly and a locking mechanism; the driving transmission assembly provides a driving torque to make the rotating end rotate around the fixed end; the locking mechanism locks the rotating end after rotating to a set position.

[0039] In the large-area flexible solar cell wing capable of being unfolded in two steps, the compression releasing device comprises a pyrotechnic device, a compression rod assembly and a separation assembly; the pyrotechnic device, the compression rod assembly and the separation assembly are sequentially connected; in the launch section, the stretching mechanism and the secondary unfolding flexible solar cell array are compressed on the cabin side wall through the pre-tightening force applied on the compression rod assembly; after entering the orbit, the pyrotechnic device is unlocked, the compression rod assembly is extracted under the action of the separation assembly, and the large-area flexible solar cell wing is unlocked and separated from the cabin.

[0040] The present application has the following advantages:

[0041] (1) The present application provides a large-area flexible solar cell wing capable of being unfolded in two steps, the solar cell array in the folded state is arranged on both sides of the stretching mechanism, and the folded size is small; through the design of the secondary unfolding device, the unfolding can be realized in steps, part of the solar panels are unfolded, the requirements of bearing or control are met, and the double-sided solar cell array is supported by the high-rigidity stretching mechanism after the secondary unfolding (i.e., complete unfolding), so that the configuration is stable and the fundamental frequency is high.

[0042] (2) The present application provides a large-area flexible solar cell wing capable of being unfolded in two steps, which has the advantages of small folding envelope, step-by-step unfolding, large unfolding and folding ratio, large power-to-weight ratio and stable unfolding configuration. BRIEF DESCRIPTION OF DRAWINGS

[0043] Figure 1 is a structural schematic diagram of a large-area flexible solar cell wing capable of being unfolded in two steps in an embodiment of the present application;

[0044] Figure 2 is a structural schematic diagram of a lifting mechanism in an embodiment of the present application;

[0045] Figure 3 is a structural schematic diagram of a locking assembly in an embodiment of the present application;

[0046] Figure 4 is a structural schematic diagram of a stretching mechanism in an embodiment of the present application;

[0047] Figure 5is a one-time deployment state schematic diagram of a flexible solar cell wing in an embodiment of the present application;

[0048] Figure 6 is a one-time unlocking state schematic diagram of a flexible solar cell wing in an embodiment of the present application;

[0049] Figure 7 is a deployment process schematic diagram of a stretching mechanism with a solar cell array in an embodiment of the present application;

[0050] Figure 8 is a structure schematic diagram of a constraint release mechanism in an embodiment of the present application;

[0051] Figure 9 is a one-time unlocking state schematic diagram of a flexible solar cell wing in an embodiment of the present application;

[0052] Figure 10 is a secondary unlocking state schematic diagram of a flexible solar cell wing in an embodiment of the present application;

[0053] Figure 11 is a structure schematic diagram of a tensioning mechanism in an embodiment of the present application;

[0054] Figure 12 is a structure schematic diagram of a guide mechanism in an embodiment of the present application;

[0055] Figure 13 is a structure schematic diagram of an upper box deployment locking mechanism in an embodiment of the present application;

[0056] Figure 14 is a structure schematic diagram of a lower box deployment locking mechanism in an embodiment of the present application;

[0057] Figure 15 is a structure schematic diagram of a compression release device in an embodiment of the present application;

[0058] Figure 16 is a lifting deployment process schematic diagram of a flexible solar cell wing in an embodiment of the present application;

[0059] Figure 17 is an upper and lower box deployment locking mechanism deployment process schematic diagram of a flexible solar cell wing in an embodiment of the present application. DETAILED DESCRIPTION

[0060] To make the purpose, technical scheme and advantages of the present application clearer, the disclosed embodiments of the present application will be described in further detail below with reference to the drawings.

[0061] The flexible solar cell wing is composed of multiple functional units, and the system configuration, deployment mode and deployment area can be designed according to the requirements of the spacecraft platform. The system configuration is the basis of the design of the flexible solar cell wing system, and reasonable configuration design can better adapt to the cabin requirements, and can optimize the deployment mode of the solar cell wing and improve the deployment reliability of the solar cell wing. The application discloses a large-area flexible solar cell wing capable of being deployed in steps twice, which can be opened through the deployment mode of being deployed in steps twice, so as to reduce the control difficulty or the risk of overload. The flexible solar cell wing deploys part of the solar panel in the initial stage of launching, meets the power demand of the platform, maintains a high frequency, and avoids coupling with the control system. After the control requirements of orbit change, docking and other conditions are completed, the flexible solar cell wing is deployed twice (i.e. completely deployed), the maximum power generation state is realized, and the power demand of various device loads of the spacecraft can be met. The large-area flexible solar cell wing capable of being deployed in steps twice has more flexible and wide application, and the design of being deployed in steps twice increases the designability of the flexible wing, so that the large-area flexible solar cell wing can be applied to more extensive platform requirements.

[0062] As Figure 1 In the embodiment, the large-area flexible solar cell wing capable of being deployed in steps twice comprises a lifting mechanism 1, a stretching mechanism 2, a secondary deployment flexible solar cell array, a compression releasing device 5 and a box deployment locking mechanism. The secondary deployment flexible solar cell array comprises a secondary deployment flexible solar cell array A 3 and a secondary deployment flexible solar cell array B 4, and the secondary deployment flexible solar cell array A 3 and the secondary deployment flexible solar cell array B 4 have the same structure. The specific connection relationship between the parts is as follows:

[0063] The secondary deployment flexible solar cell array A 3 and the secondary deployment flexible solar cell array B 4 are arranged at the top of the two ends of the stretching mechanism 2, and the connection positions of the secondary deployment flexible solar cell array A 3 and the secondary deployment flexible solar cell array B 4 and the stretching mechanism 2 are provided with box deployment locking mechanism connections; the top of the lifting mechanism 1 is connected with the bottom of the stretching mechanism 2; the stretching mechanism 2 and the secondary deployment flexible solar cell array are respectively provided with a plurality of compression points, and the compression releasing devices 5 are arranged at the corresponding compression point positions, so as to realize the compression of the stretching mechanism 2 and the secondary deployment flexible solar cell array by applying compression force at the compression points, and then realize the compression and anti-overload of the flexible solar cell wing in the launch section. In the initial folding state, the secondary deployment flexible solar cell array A 3 and the secondary deployment flexible solar cell array B 4 are folded on the two sides of the stretching mechanism 2, and the stretching mechanism 2, the secondary deployment flexible solar cell array A 3 and the secondary deployment flexible solar cell array B 4 are located on the same side of the deployment baseline. In the deployment process, the secondary deployment flexible solar cell array is deployed in steps twice under the action of the stretching mechanism 2 and the box deployment locking mechanism.

[0064] In this embodiment, the lifting mechanism 1 includes a set of rotating joints, driven by an active motor or a passive spring. After deployment, the lifting mechanism 1 has locking and stiffness-maintaining functions. Figure 2 The lifting mechanism 1 specifically includes: a fixed joint 11, a rotating joint 12, a lifting mechanism drive assembly 13, and a locking assembly 14. The fixed joint 11 and the rotating joint 12 are coaxially designed and connected by bearings, forming a rotating pair. The lifting mechanism drive assembly 13 is connected to the rotating joint 12, and the rotating joint 12 is connected to the bottom of the storage cylinder 22 of the extension mechanism 2. When the lifting mechanism drive assembly 13 operates, it outputs torque, driving the rotating joint 12 to rotate relative to the fixed joint 11, thereby causing the large-area flexible solar cell wing to rotate as a whole, changing the large-area flexible solar cell wing from its initial state to a state perpendicular to the cabin. The locking assembly 14 is connected to the rotating joint 12, and when the large-area flexible solar cell wing is changed to a state perpendicular to the cabin, it locks the rotating joint 12.

[0065] Preferred, such as Figure 3 The locking component 14 may specifically include: a locking pin 141, a slide 142, and a locking hole 143; the locking pin 141 is located in the slide 142 and can slide in the slide 142; when the large-area flexible solar cell wing is displaced to a state perpendicular to the cabin, the locking pin 141 is inserted into the locking hole 143 to lock the rotating joint 12.

[0066] In this embodiment, the extension mechanism 2 has one-dimensional unfolding and retraction capabilities, high stiffness and high strength characteristics, and can support the unfolding of the tensioning mechanism, giving the flexible array a certain stiffness; the extension mechanism can be a hinged extension mechanism, a coiled extension mechanism, a FASTmast configuration extension mechanism, a sleeve extension mechanism, etc., to achieve the unfolding, retraction and support of the flexible solar cell array. Figure 4 The extension mechanism 2 specifically includes an extension arm 21, a storage cylinder 22, and an extension mechanism drive assembly 23. In the initial retracted state, the extension arm 21 is retracted within the storage cylinder 22. During the deployment process, the extension mechanism drive assembly 23 outputs a positive torque, driving the extension arm 21 to deploy and lock in a one-dimensional, orderly manner from the storage cylinder 22. The extension mechanism 2 exhibits high rigidity and strength in its retracted state. It is fixed to the cabin via clamping points on the storage cylinder 22 and can withstand launch loads. The extension mechanism 2 has the capability for partial deployment and locking, possessing sufficient rigidity and strength in its partially deployed state to support the secondary deployment of the flexible solar array. The fully deployed extension mechanism 2 also possesses sufficient rigidity and strength to support the secondary deployment of the flexible solar array in its fully deployed state.

[0067] In this embodiment, as Figures 5 to 7, the structure of the secondary expansion flexible solar cell array A3 and the secondary expansion flexible solar cell array B4 is the same, and the two are mirror-symmetrical about the stretching mechanism 2, and specifically can include: a lower storage box 41, an upper storage box 42, a constraint release mechanism 43, an upper cell panel 44, a lower cell panel 45, a separation plate 46, a tensioning mechanism 47 and a guide mechanism 48. Among them, the upper storage box 42, the upper cell panel 44, the lower cell panel 45 and the lower storage box 41 are arranged in sequence from top to bottom; the separation plate 46 is arranged between the upper cell panel 44 and the lower cell panel 45; the separation plate 46 is used to realize step-by-step secondary expansion of the secondary expansion flexible solar cell array during the expansion process; one end of the constraint release mechanism 43 is connected with the upper storage box 42, and the other end is connected with the lower storage box 41; in the folding state, the constraint release mechanism 43 is locked, and the upper cell panel 44 and the lower cell panel 45 are folded between the upper storage box 42 and the lower storage box 41; in the first expansion, the constraint release mechanism 43 releases the constraint between the upper cell panel 44 and the separation plate 46; in the secondary expansion, the constraint between the separation plate 46 and the lower cell panel 45 is released after the upper cell panel 44 is completely expanded; the guide mechanism 48 is arranged on the lower storage box 41, and is used to provide guidance for step-by-step secondary expansion of the secondary expansion flexible solar cell array during the expansion process, and assist the orderly expansion of the secondary expansion flexible solar cell array; the tensioning mechanism 47 is arranged on the upper storage box 42, and is used to apply a tensioning force to the upper cell panel 44 and the lower cell panel 45 after the secondary expansion flexible solar cell array is completely expanded, so as to ensure the in-orbit rigidity of the secondary expansion flexible solar cell array.

[0068] Preferably, in the folding state, the secondary expansion flexible solar cell array is pressed tightly by the constraint release mechanism 43 between the lower storage box 41 and the upper storage box 42, the pressing force is applied to the cell panel through the buffer foam, the secondary expansion flexible solar cell array forms a whole with certain rigidity and strength, and the secondary expansion flexible solar cell array is fixed to the cabin body through the pressing points arranged on the lower storage box 41 and the upper storage box 42.

[0069] Preferably, after the constraint release mechanism 43 works, the secondary expansion flexible solar cell array is unlocked, the upper storage box 42 is expanded under the driving of the stretching mechanism 2, the cell panel is expanded and finally tensioned by the upper storage box 42 through the tensioning mechanism 47, and the guide mechanism 48 expands with the secondary expansion flexible solar cell array and keeps the cell panel expanded smoothly.

[0070] Preferably, the guide mechanism 48 is arranged on the upper storage box 42, and can apply a tensioning force to the solar cell array during the first expansion and the secondary expansion (i.e. complete expansion) of the secondary expansion flexible solar cell array, so as to keep the rigidity of the array surface.

[0071] Preferably, the isolation plate 46 has a certain rigidity, and is composed of an upper isolation plate and a lower isolation plate: when unfolded once, the upper isolation plate is unfolded with the upper battery plate, and the lower isolation plate is used to constrain the unfolded lower battery plate through the constraint release mechanism; after the constraint release mechanism is unlocked twice, the lower isolation plate is released from the constraint, and is unfolded with the unfolded lower battery plate under the driving of the stretching mechanism, until the flexible solar wing is unfolded twice (i.e. completely unfolded).

[0072] Further, as shown in Figures 5 to 7 , the upper battery plate 44 and the lower battery plate 45 have the same structure, and specifically include: a plurality of flexible substrates 441, battery circuits 442 and flexible cables 443. Among them, the plurality of (10-100) flexible substrates 441 are sequentially connected in series through a hinge, to form a flexible substrate assembly; adjacent two flexible substrates 441 rotate around the hinge as the central axis, so as to realize the unfolding and folding of the flexible substrate assembly; the surface of the flexible substrate assembly is pasted with the battery circuits 442 and the flexible cables 443.

[0073] Further, the constraint release mechanism 43 has a secondary unlocking function, which can constrain the unfolded lower battery plate on the storage box when the flexible solar array is unfolded once, and can continue to unfold twice to release the constraint on the remaining lower battery plate after receiving a secondary unlocking instruction. As shown in Figure 8 , the constraint release mechanism 43 specifically can include: a motor drive assembly 431, a four-bar linkage mechanism 432 and a terminal assembly. Among them, the motor drive assembly 431 is connected with the four-bar linkage mechanism 432, and the four-bar linkage mechanism 432 is provided with the terminal assembly at the end. As shown in Figures 9 to 10The end components may specifically include: a primary locking hook 433, a secondary locking hook 434, a blocking block 435, a hinge lock ring 436, a secondary unlocking rope assembly 437, and a secondary unlocking spring assembly 438. The primary locking hook 433, secondary locking hook 434, and blocking block 435 are fixed to the lower storage box 41; the secondary unlocking spring assembly 438 is fixed to the partition plate 46; one end of the hinge lock ring 436 is fixed to the upper storage box 42; in the fully retracted state, the other end of the hinge lock ring 436 engages with the primary locking hook 433 for locking; one end of the secondary unlocking rope assembly 437 is connected to the secondary unlocking spring assembly 438, and the other end is constrained between the secondary locking hook 434 and the blocking block 435; when the constraint release mechanism 43 unlocks to its final position under the action of the motor drive assembly 431 and the four-bar linkage 432: the primary locking hook 433 and the hinge lock ring 436... When the constraint at the other end is released, the constraint on the upper battery panel is released, and the upper battery panel 44 unfolds. At this time, the other end of the secondary unlocking rope assembly 437 continues to be constrained between the secondary locking hook 434 and the blocking block 435, and continues to maintain the locked state, constraining the un-unfolded lower battery panel 45. When the constraint release mechanism 43 is in the secondary unlocking position under the action of the motor drive assembly 431 and the four-bar linkage 432: the relative movement of the secondary locking hook 434 and the blocking block 435 creates a gap, the other end of the secondary unlocking rope assembly 437 comes out of the gap, and retracts under the action of the secondary unlocking spring assembly 438, releasing the constraint on the lower battery panel 45, and the lower battery panel 45 unfolds.

[0074] Furthermore, such as Figure 11 The tensioning mechanism 47 may specifically include: a tensioning mechanism spring assembly 471, a tensioning mechanism winding wheel 472, and a tensioning rope 473. The tensioning mechanism spring assembly 471 is installed on the outside of the upper storage box of the secondary unfolding flexible solar cell array and is coaxially arranged with the tensioning mechanism winding wheel 472; the tensioning rope 473 is coplanar with the flexible substrate assembly; one end of the tensioning rope 473 is connected to the flexible substrate assembly, and the other end is fixed to the tensioning mechanism winding wheel 472.

[0075] Furthermore, such as Figure 12 The guiding mechanism 48 may specifically include: a guiding mechanism coil spring assembly 481, a guiding mechanism winding wheel 482, and a guiding rope 483. The guiding mechanism coil spring assembly 481 is installed on the outside of the lower storage box of the secondary unfolding flexible solar cell array and is coaxially arranged with the guiding mechanism winding wheel 482. The guiding rope 483 is arranged on the back of the flexible substrate assembly; one end of the guiding rope 483 is connected to the upper storage box of the secondary unfolding flexible solar cell array, and the other end is fixed to the guiding mechanism winding wheel 482.

[0076] In the embodiment, one end of the box unfolding locking mechanism is connected with the upper storage box of the secondary unfolding flexible solar cell array, and the other end is connected with the stretching arm 21 of the stretching mechanism 2. The mechanism comprises a rotating pair and has the function of rotating unfolding locking. Figure 1 The box unfolding locking mechanism can specifically include an upper box unfolding locking mechanism 6 and a lower box unfolding locking mechanism 7. The upper box unfolding locking mechanism 6 is connected with the stretching arm 21 of the stretching mechanism 2 and the upper storage box of the secondary unfolding flexible solar cell array, respectively. The lower box unfolding locking mechanism 7 is connected with the storage cylinder 22 of the stretching mechanism 2 and the lower storage box of the secondary unfolding flexible solar cell array, respectively. The rotating shaft of the box unfolding locking mechanism 7 is coaxially arranged with the rotating shaft of the corresponding upper box unfolding locking mechanism 6. When the lower box unfolding locking mechanism 7 is unfolded, the upper box unfolding locking mechanism 6 is unfolded and locked.

[0077] Preferably, the upper box unfolding locking mechanism 6 can adopt spring driving or passive follow-up mode. Figure 13 The upper box unfolding locking mechanism 6 can specifically include a male hinge 61, a female hinge 62, a rotating shaft 63 and a locking rod 64. The male hinge 61 and the female hinge 62 form a rotating pair through the rotating shaft 63 and have the function of rotating unfolding. The male hinge 61 is connected with the upper box 31, and the female hinge 62 is connected with the stretching arm 21. After unfolding, the locking rod 64 is locked. When the rigidity and stability are required, the upper box unfolding locking mechanism 6 can be arranged with 1-3 sets.

[0078] The lower box unfolding locking mechanism 7 can specifically include a fixed end 71, a rotating end 72, a driving transmission assembly 73 and a locking mechanism 74. Figure 14 The driving transmission assembly 73 provides a driving torque to make the rotating end 72 rotate around the fixed end 71. The locking mechanism 74 locks the rotating end 72 after rotating to a set position. The driving transmission assembly 73 can adopt spring driving or motor active driving.

[0079] In the embodiment, the compression release device 5 can specifically include a pyrotechnic device 51, a compression rod assembly 52 and a separation assembly 53. Figure 15 In the launch section, the stretching mechanism 2 and the secondary unfolding flexible solar cell array are compressed on the cabin side wall through the pre-tightening force applied on the compression rod assembly 52. After entering the orbit, the pyrotechnic device 51 is unlocked, the compression rod assembly 52 is extracted under the action of the separation assembly 53, and the large-area flexible solar cell wing is unlocked and separated from the cabin.

[0080] Preferably, the compression release device 5 can use 20kN-100kN pre-tightening force pyrotechnics to compress the large-area flexible solar cell wing which can be deployed in two steps.

[0081] As can be seen from the above, in the embodiment, the compression release device 5 is mainly used for compression anti-overload of the large-area flexible solar cell wing which can be deployed in two steps in the launch section; the lifting mechanism 1 is mainly used for changing the whole large-area flexible solar cell wing from the initial state to the vertical state with the cabin; the stretching mechanism 2 is mainly used for controlling the deployment and folding of the secondary deployment flexible solar cell array; the box deployment locking mechanism is mainly used for deploying and locking the secondary deployment flexible solar cell array to the two sides. The secondary unlocking device arranged on the secondary deployment flexible solar cell array can be used for distributed deployment of the flexible solar cell wing; the battery circuit and cable arranged on the secondary deployment flexible solar cell array are used for power generation and power transmission of the flexible solar cell wing in orbit.

[0082] On the basis of the above embodiment, the specific deployment process of the large-area flexible solar cell wing which can be deployed in two steps will be described in detail.

[0083] In the embodiment, the large-area flexible solar cell wing which can be deployed in two steps can be deployed in seven steps as follows: Figures 16 to 17

[0084] Firstly, the compression release device 5 is unlocked, and the flexible solar cell wing is unlocked with the cabin.

[0085] Secondly, the lifting mechanism 1 works, and the flexible solar cell wing is changed to the vertical state with the cabin.

[0086] Thirdly, the lower box deployment locking mechanisms 7 on both sides work, driving the secondary deployment flexible solar cell arrays on both sides to deploy and lock, and the upper box deployment locking mechanism 6 is driven to deploy and lock simultaneously.

[0087] Fourthly, the constraint release mechanisms on the secondary deployment flexible solar cell array A3 and the secondary deployment flexible solar cell array B4 work, releasing the constraint between the upper and lower storage boxes.

[0088] Fifthly, the stretching mechanism 2 works, and the stretching mechanism 2 stretches linearly along the radial direction of the cabin, driving the secondary deployment flexible solar cell array to deploy synchronously, and the guide mechanism works to limit the out-of-plane motion of the secondary deployment flexible solar cell array, until the secondary deployment flexible solar cell array is deployed once, and the tensioning mechanism is tensioned for a certain distance to apply the pre-tightening force.

[0089] Sixthly, the constraint release mechanism continues to work, releasing the constraint between the lower isolation plate and the lower storage box. ​

[0090] The seventh step, the stretching mechanism continues to deploy, the guiding mechanism continues to work until the secondary deployment flexible solar cell array is fully deployed, the tensioning mechanism is tensioned for a certain distance, and a pre-tightening force is applied.

[0091] The above process is the deployment process of the large-area flexible solar cell wing which can be deployed in two steps, and the folding process is the reverse process of the deployment process. The large-area flexible solar cell wing which can be deployed in two steps can complete folding according to the seven-step action.

[0092] Although the present application has been disclosed with the above preferred embodiments, it is not intended to limit the present application, and any person skilled in the art can make possible changes and modifications to the technical solutions of the present application by using the disclosed methods and technical contents without departing from the spirit and scope of the present application. Therefore, any simple modification, equivalent change and modification made to the above embodiments according to the technical essence of the present application without departing from the technical solutions of the present application shall fall within the protection scope of the technical solutions of the present application.

[0093] The contents not described in detail in the specification of the present application belong to the known technology of the person skilled in the art.

Claims

1. A large area flexible solar cell wing deployable in steps twice, characterized in that, The utility model relates to a kind of flexible solar cell wing, including: lifting mechanism (1), stretching mechanism (2), secondary deployment flexible solar cell array, compression release device (5) and box deployment locking mechanism;Wherein, secondary deployment flexible solar cell array, including: secondary deployment flexible solar cell array A (3) and secondary deployment flexible solar cell array B (4); Secondary deployment flexible solar cell array A (3) and secondary deployment flexible solar cell array B (4) are respectively arranged at the top of stretching mechanism (2) both ends, and secondary deployment flexible solar cell array A (3) and secondary deployment flexible solar cell array B (4) are respectively provided with box deployment locking mechanism connection at the connecting position of stretching mechanism (2);The top of lifting mechanism (1) is connected with the bottom of stretching mechanism (2);Stretching mechanism (2) and secondary deployment flexible solar cell array are respectively provided with multiple compression points, and each compression release device (5) is respectively arranged at the corresponding compression point position, by exerting compression force at compression point, the compression of stretching mechanism (2) and secondary deployment flexible solar cell array is realized, to realize the compression of flexible solar cell wing in launch section Anti-overload; In initial retracted state, secondary deployment flexible solar cell array A (3) and secondary deployment flexible solar cell array B (4) are retracted in stretching mechanism (2) both sides, and stretching mechanism (2), secondary deployment flexible solar cell array A (3) and secondary deployment flexible solar cell array B (4) are located at the same side of deployment baseline; In deployment process, secondary deployment flexible solar cell array is deployed step by step under the action of stretching mechanism (2) and box deployment locking mechanism; Secondary deployment flexible solar cell array A (3) and secondary deployment flexible solar cell array B (4) are the same structure, and mirror image symmetry about stretching mechanism (2), including: lower storage box (41), upper storage box (42), constraint release mechanism (43), upper cell panel (44), lower cell panel (45), isolation plate (46), tensioning mechanism (47) and guide mechanism (48); Upper storage box (42), upper cell panel (44), lower cell panel (45) and lower storage box (41) are sequentially arranged from top to bottom; Isolation plate (46) is arranged between upper cell panel (44) and lower cell panel (45);Wherein, isolation plate (46) is used to realize the step-by-step secondary deployment of secondary deployment flexible solar cell array in deployment process; Constraint release mechanism (43) is connected with upper storage box (42) at one end, and is connected with lower storage box (41) at the other end;Wherein, in retracted state, constraint release mechanism (43) locks, and upper cell panel (44) and lower cell panel (45) are retracted between upper storage box (42) and lower storage box (41);In primary deployment, constraint release mechanism (43) removes the constraint between upper cell panel (44) and isolation plate (46);In secondary deployment, the constraint between isolation plate (46) and lower cell panel (45) is removed after upper cell panel (44) is completely deployed. ​ The guide mechanism (48) is arranged on the lower storage box (41) and is used for guiding the step-by-step secondary expansion of the secondary expansion flexible solar cell array during the expansion process, assisting the orderly expansion of the secondary expansion flexible solar cell array; The tensioning mechanism (47) is arranged on the upper storage box (42) and is used for applying a tensioning force to the upper cell panel (44) and the lower cell panel (45) after the secondary expansion flexible solar cell array is completely expanded, ensuring the in-orbit rigidity of the secondary expansion flexible solar cell array; The isolation plate (46) has a certain rigidity and is composed of an upper isolation plate and a lower isolation plate: during the primary expansion, the upper isolation plate is expanded with the upper cell panel, and the lower isolation plate is used for restraining the unexpanded lower cell panel through the constraint release mechanism; after the constraint release mechanism is unlocked for the second time, the lower isolation plate is released from the constraint and is expanded with the unexpanded lower cell panel under the driving of the stretching mechanism until the flexible solar cell wing is expanded for the second time, i.e., completely expanded; The constraint release mechanism (43) comprises a motor driving assembly (431), a four-bar linkage mechanism (432) and a terminal assembly; the motor driving assembly (431) is connected with the four-bar linkage mechanism (432), and the four-bar linkage mechanism (432) is provided with the terminal assembly at the terminal end; the terminal assembly comprises a primary locking hook (433), a secondary locking hook (434), a blocking block (435), a hinge ring (436), a secondary unlocking rope assembly (437) and a secondary unlocking spring assembly (438); The primary locking hook (433), the secondary locking hook (434) and the blocking block (435) are fixed on the lower storage box (41); the secondary unlocking spring assembly (438) is fixed on the isolation plate (46); one end of the hinge ring (436) is fixed on the upper storage box (42); In the completely folded state, the other end of the hinge ring (436) is locked in cooperation with the primary locking hook (433); one end of the secondary unlocking rope assembly (437) is connected with the secondary unlocking spring assembly (438), and the other end is restrained between the secondary locking hook (434) and the blocking block (435); When the constraint release mechanism (43) is unlocked to the position for the first time under the action of the motor driving assembly (431) and the four-bar linkage mechanism (432), the other end of the primary locking hook (433) and the hinge ring (436) is released from the constraint, the constraint on the upper cell panel is released, and the upper cell panel (44) is expanded; at this time, the other end of the secondary unlocking rope assembly (437) continues to be restrained between the secondary locking hook (434) and the blocking block (435), continues to keep the locked state, and the unexpanded lower cell panel (45) is constrained; When the constraint release mechanism (43) is unlocked to the position for the second time under the action of the motor driving assembly (431) and the four-bar linkage mechanism (432), the secondary locking hook (434) and the blocking block (435) relatively move to generate a gap, the other end of the secondary unlocking rope assembly (437) is taken out of the gap, is retracted under the action of the secondary unlocking spring assembly (438), the constraint on the lower cell panel (45) is released, and the lower cell panel (45) is expanded; The large-area flexible solar cell wing of the step-by-step secondary expansion is expanded in seven steps: The first step is to unlock the compact release device (5) and unlock the flexible solar wing and the cabin body. The second step is to work the lifting mechanism (1) to change the position of the flexible solar wing to the vertical state with the cabin body. The third step is to work the lower box expansion locking mechanism (7) to drive the two secondary expansion flexible solar arrays to expand and lock, and the upper box expansion locking mechanism (6) is expanded and locked. The fourth step is to work the constraint release mechanism on the secondary expansion flexible solar array A (3) and the secondary expansion flexible solar array B (4) to release the constraint between the upper and lower storage boxes. The fifth step is to work the stretching mechanism (2) to stretch along the radial direction of the cabin body, drive the secondary expansion flexible solar array to expand synchronously, and work the guide mechanism to limit the out-of-plane motion of the secondary expansion flexible solar array until the secondary expansion flexible solar array is expanded once and the tensioning mechanism is tensioned to a certain distance to apply a pre-tightening force. The sixth step is to continue working the constraint release mechanism (43) to release the constraint between the lower isolation plate and the lower storage box. The seventh step is to continue to expand the stretching mechanism (2) and continue to work the guide mechanism until the secondary expansion flexible solar array is fully expanded, and the tensioning mechanism is tensioned to a certain distance to apply a pre-tightening force.

2. The stepwise deployable large area flexible solar cell wing according to claim 1, characterized in that, The lifting mechanism (1) includes a fixed joint (11), a rotating joint (12), a lifting mechanism drive assembly (13), and a locking assembly (14). The fixed joint (11) and the rotating joint (12) are coaxially designed and connected by bearings to form a rotating pair. The lifting mechanism drive assembly (13) is connected with the rotating joint (12), and the rotating joint (12) is connected with the bottom of the storage cylinder (22) of the stretching mechanism (2); wherein, the lifting mechanism drive assembly (13) outputs torque when working, drives the rotating joint (12) to rotate relative to the fixed joint (11), and then drives the whole rotation of the large-area flexible solar wing, changes the large-area flexible solar wing from the initial state to the vertical state with the cabin body. The locking assembly (14) is connected with the rotating joint (12), and when the large-area flexible solar wing is changed to the vertical state with the cabin body, the rotating joint (12) is locked; wherein, the locking assembly (14) includes a locking pin (141), a slide (142), and a locking hole (143); the locking pin (141) is located in the slide (142) and can slide in the slide (142); when the large-area flexible solar wing is changed to the vertical state with the cabin body, the locking pin (141) is inserted into the locking hole (143) to lock the rotating joint (12).

3. The stepwise deployable large area flexible solar cell wing of claim 1, wherein, The stretching mechanism (2) includes a stretching arm (21), a storage cylinder (22), and a stretching mechanism drive assembly (23). In the initial folding state, the stretching arm (21) is folded in the storage cylinder (22). In the expansion process, the stretching mechanism drive assembly (23) works to output a positive torque to drive the stretching arm (21) to expand one-dimensionally and orderly from the storage cylinder (22) and lock.

4. The stepwise deployable large area flexible solar cell wing of claim 1, wherein, The upper battery plate (44) and the lower battery plate (45) are the same in structure, comprising: a plurality of flexible substrates (441), battery circuits (442) and flexible cables (443); The plurality of flexible substrates (441) are sequentially connected in series through the piano hinge to form a flexible substrate assembly; wherein, the adjacent two flexible substrates (441) rotate around the piano hinge as the central axis, so that the flexible substrate assembly can be unfolded and folded; The surface of the flexible substrate assembly is pasted with the battery circuits (442) and the flexible cables (443).

5. The stepwise deployable large area flexible solar cell wing according to claim 4, characterized in that, The tensioning mechanism (47) comprises: a tensioning mechanism coil spring assembly (471), a tensioning mechanism winding wheel (472) and a tensioning rope (473); The tensioning mechanism coil spring assembly (471) is installed outside the upper storage box of the secondary unfolding flexible solar cell array and coaxially arranged with the tensioning mechanism winding wheel (472); The tensioning rope (473) is coplanar with the flexible substrate assembly; wherein, one end of the tensioning rope (473) is connected with the flexible substrate assembly, and the other end is fixed on the tensioning mechanism winding wheel (472).

6. The stepwise deployable large area flexible solar cell wing of claim 4, wherein, The guide mechanism (48) comprises: a guide mechanism coil spring assembly (481), a guide mechanism winding wheel (482) and a guide rope (483); The guide mechanism coil spring assembly (481) is installed outside the lower storage box of the secondary unfolding flexible solar cell array and coaxially arranged with the guide mechanism winding wheel (482); The guide rope (483) is arranged on the back of the flexible substrate assembly; wherein, one end of the guide rope (483) is connected with the upper storage box of the secondary unfolding flexible solar cell array, and the other end is fixed on the guide mechanism winding wheel (482).

7. The stepwise deployable large area flexible solar cell wing of claim 4, wherein, The box unfolding locking mechanism comprises: an upper box unfolding locking mechanism (6) and a lower box unfolding locking mechanism (7); wherein, the upper box unfolding locking mechanism (6) is connected with the stretching arm (21) of the stretching mechanism (2) and the upper storage box of the secondary unfolding flexible solar cell array respectively; the lower box unfolding locking mechanism (7) is connected with the storage cylinder (22) of the stretching mechanism (2) and the lower storage box of the secondary unfolding flexible solar cell array respectively; the rotation axis of the lower box unfolding locking mechanism (7) is coaxially arranged with the rotation axis of the corresponding upper box unfolding locking mechanism (6), and when the lower box unfolding locking mechanism (7) is unfolded, the upper box unfolding locking mechanism (6) is unfolded in turn and locked; The upper box unfolding locking mechanism (6) comprises: a male hinge (61), a female hinge (62), a rotating shaft (63) and a locking rod (64); wherein, the male hinge (61) and the female hinge (62) form a rotating pair through the rotating shaft (63) and have the function of rotating unfolding and folding; the male hinge (61) is connected with the upper box (31), and the female hinge (62) is connected with the stretching arm (21); after unfolding, the locking rod (64) is locked; The lower box body unfolding locking mechanism (7) comprises a fixed end (71), a rotating end (72), a driving transmission assembly (73) and a locking mechanism (74); the driving transmission assembly (73) provides a driving torque to make the rotating end (72) rotate around the fixed end (71); the locking mechanism (74) locks the rotating end (72) after the rotating end (72) rotates to a set position.

8. The stepwise, twice deployable, large area flexible solar cell wing according to claim 1, characterized in that, The compression release device (5) comprises a pyrotechnic device (51), a compression rod assembly (52) and a separation assembly (53); the pyrotechnic device (51), the compression rod assembly (52) and the separation assembly (53) are sequentially connected; in the launch section, the stretching mechanism (2) and the secondary unfolding flexible solar cell array are compressed on the cabin body side wall through the pre-tightening force applied on the compression rod assembly (52); after entering the orbit, the pyrotechnic device (51) is unlocked, the compression rod assembly (52) is extracted under the action of the separation assembly (53), and the unlocking and separation of the large-area flexible solar cell wing and the cabin body are realized.

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