Compressing and releasing device of flexible solar wing and spacecraft

Abstract

The invention relates to a pressing and releasing device of a flexible solar wing and a spacecraft. The pressing and releasing device of the flexible solar wing comprises a first plate body, a second plate body, a rotating mechanism, a pressing and releasing mechanism and a restraining assembly. The first plate body is hinged to the second plate body, and is used for clamping the solar wing at the closing position and releasing the solar wing at the opening position; the number of the rotating mechanisms is two. The pressing and releasing mechanism is arranged on the first plate body and the second plate body and used for locking the first plate body and the second plate body and unlocking the first plate body and the second plate body. The number of the restraining assemblies is at least one, the restraining assemblies are arranged at the position between the two rotating mechanisms, each restraining assembly comprises a pressing piece fixed to the first plate body and an abutting piece arranged on the second plate body, and when the first plate body and the second plate body are located at the closing position, the pressing pieces abut against the abutting pieces, and when the first plate body and the second plate body are located at the closing position, the pressing pieces abut against the abutting pieces. The abutting piece provides pressing force towards the direction of the second plate body for the first plate body through the pressing piece.

Description

TECHNICAL FIELD

[0001] The present disclosure relates to the field of aerospace technology, in particular to a compression release device of a flexible solar wing and a spacecraft. BACKGROUND

[0002] With the development of aerospace technology, more and more spacecrafts use flexible solar wings. Before the spacecraft enters the orbit, the flexible battery array of the flexible solar wing needs to be compressed; after the spacecraft enters the orbit, the flexible battery array of the flexible solar wing will be released and deployed. The area of the array of the flexible battery array is large and the rigidity is small, so the reliable compression and release of the flexible battery array is extremely important. If the compression method is improper or the compression force is insufficient, it will cause the flexible battery array to slide or collide with other devices, and then cause the battery pieces of the flexible battery array to break or the flexible battery array to have a hooking risk. If the release resistance is too large, it is easy to cause it to fail to complete the release, and then affect the deployment of the flexible battery array surface, thereby affecting the energy safety of the satellite.

[0003] In order to realize reliable compression, the prior art generally adopts multi-point compression. However, the release scheme of the flexible battery array in the prior art requires a large torque, which increases the design difficulty. In addition, the deformation amount near each compression point is difficult to control and accurately measure, which leads to the problem of poor reliability of the compression and release of the flexible battery array. SUMMARY

[0004] The present disclosure provides a compression release device of a flexible solar wing and a spacecraft to solve the problems in the prior art.

[0005] According to a first aspect of the present disclosure, a compression release device of a flexible solar wing is provided, comprising: a first plate body and a second plate body, the first plate body and the second plate body are hinged and configured to clamp the solar wing in a closed position and release the solar wing in an open position; a rotating mechanism, two rotating mechanisms are provided, one side of the first plate body and the second plate body is configured to be hinged by the two rotating mechanisms; the first plate body is configured to rotate relative to the second plate body with the rotating shaft of the rotating mechanism as the rotation center; a compression release mechanism, the compression release mechanism is provided on the first plate body and the second plate body, and is configured to lock the first plate body and the second plate body when the first plate body and the second plate body are in the closed position, and to unlock the first plate body and the second plate body; The constraint assembly is provided with at least one constraint assembly configured to be arranged between the two rotating mechanisms; the constraint assembly is arranged on the same side of the first plate body and the second plate body as the rotating mechanisms; the constraint assembly comprises a pressing member fixed on the first plate body and an abutting member arranged on the second plate body; when the first plate body and the second plate body are in the closed position, the pressing member is configured to abut against the abutting member, and the abutting member is configured to provide a pressing force to the first plate body in the direction of the second plate body through the pressing member.

[0006] In one embodiment of the present disclosure, when the first plate body and the second plate body move in the direction from the closed position to the open position, the pressing member is configured to move away from the abutting member.

[0007] In one embodiment of the present disclosure, when the first plate body and the second plate body are in the closed position, the pressing member and the abutting member are in surface contact, and the surface of the abutting member is an abutting surface.

[0008] In one embodiment of the present disclosure, the abutting surface is a plane, and the abutting surface is parallel to the plane in which the first plate body is located.

[0009] In one embodiment of the present disclosure, a vertical plane perpendicular to the first plate body is defined, and the rotation axis of the rotating mechanism is located in the vertical plane; the abutting surface and the first plate body are respectively located on opposite sides of the vertical plane.

[0010] In one embodiment of the present disclosure, the pressing member comprises a pressing portion, a fitting portion, and a connecting portion connecting the pressing portion and the fitting portion; wherein the pressing portion is configured to be fixedly connected with the first plate body; and the fitting portion is configured to abut against the abutting member when the first plate body and the second plate body are in the closed position.

[0011] In one embodiment of the present disclosure, the pressing portion is configured to be parallel to the fitting portion, and the connecting portion is configured to be perpendicular to the pressing portion and the fitting portion, respectively.

[0012] In one embodiment of the present disclosure, the side wall of the first plate body is provided with a mounting groove, and the pressing portion is configured to extend into the mounting groove and be fixedly connected with the first plate body.

[0013] In one embodiment of the present disclosure, when the first plate body and the second plate body are in the closed position, the connecting portion adjacent to the side surface of the first plate body is configured to have a predetermined distance from the first plate body.

[0014] In one embodiment of the present disclosure, the first plate body and the second plate body are parallel to each other in the closed position, and the direction of the compression force is perpendicular to the direction of the second plate body.

[0015] In one embodiment of the present disclosure, the first plate body and the second plate body are rectangular, the rotating mechanism is arranged on one long side of the first plate body or the second plate body, the compression release mechanism is arranged on the other long side of the first plate body or the second plate body, and / or the two short sides of the first plate body and the second plate body are arranged.

[0016] According to a second aspect of the present disclosure, a spacecraft is provided, comprising the compression release device of the flexible solar wing according to the first aspect of the present disclosure.

[0017] One beneficial effect of the present disclosure is that the first plate body and the second plate body can preliminarily compress the flexible solar wing in the closed position, and play a role of pre-fixing, and the compression release mechanism locks the first plate body and the second plate body, so as to further compress the flexible solar wing, and achieve a reliable compression effect. The first plate body and the second plate body can balance the pressure from the compression release mechanism, so that the flexible solar wing is uniformly stressed, and the problem of excessive local pressure is avoided.

[0018] In addition, the compression release device of the flexible solar wing provided by the present disclosure realizes the multi-point compression effect of the first plate body and the second plate body through the two rotating mechanisms and the restraint assembly arranged between the two rotating mechanisms. In addition, the first plate body and the second plate body of the present disclosure have only two restraint points in the direction of the rotating shaft, and the long plate rotation release does not need to overcome the over-restraint resistance problem caused by multiple compression points on the axis. Whether the restraint assembly is on the rotating shaft does not affect the rotation release process, so that over-restraint of the compression points is avoided.

[0019] Other features of the present disclosure and its advantages will become apparent from the following detailed description of exemplary embodiments thereof, with reference to the drawings. BRIEF DESCRIPTION OF DRAWINGS

[0020] The accompanying drawings, which are incorporated in and constitute a part of the specification, illustrate embodiments of the present disclosure and, together with the description, serve to explain the principles of the present disclosure.

[0021] Figure 1 is a structural schematic diagram of the compression release device of the flexible solar wing when the plate body of the present disclosure is in the closed position; Figure 2 is a structural schematic diagram of the restraint assembly when the plate body of the present disclosure is in the closed position; Figure 3 is a sectional view of the restraint assembly when the plate body of the present disclosure is in the closed position. Figure 4 is a sectional view of the restraining assembly when the plate body of the present disclosure is in the open position; Figure 5 is a structural schematic view of the restraining assembly when the plate body of the present disclosure is in the open position; Figure 6 is a structural schematic view of the pressing releasing device when the plate body of the present disclosure is in the open position.

[0022] Figures 1 to 6 The one-to-one correspondence between the names of various components and the reference numerals in the following description is as follows: 1, first plate body; 2, second plate body; 3, rotating mechanism; 4, pressing releasing mechanism; 5, restraining assembly; 51, pressing member; 511, pressing portion; 512, matching portion; 513, connecting portion; 52, abutting member; 53, vertical surface; 54, abutting surface; 6, solar wing. DETAILED DESCRIPTION

[0023] Various exemplary embodiments of the present disclosure will now be described in detail with reference to the accompanying drawings. Note that the relative arrangement, numerical expressions, and numerical values of the components and steps set forth in these embodiments are not limiting to the scope of the present disclosure unless otherwise specifically stated.

[0024] The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way limiting to the scope of the disclosure and its applications or uses.

[0025] Techniques, methods, and apparatus known to those of ordinary skill in the relevant art can not be discussed in detail herein, but should be considered as part of the specification, where appropriate.

[0026] Note that similar reference numerals and letters indicate similar items in the following drawings, and thus, once an item is defined in one drawing, it need not be discussed further in subsequent drawings.

[0027] In this document, "upper", "lower", "front", "rear", "left", "right", and the like are used to describe relative positions between the relevant parts, and do not limit the absolute positions of the relevant parts.

[0028] In this document, "first", "second", and the like are used to distinguish between items, and do not indicate importance and order, and are not a prerequisite for each other.

[0029] In this document, "equal", "same", and the like are not strictly limited in the mathematical and / or geometric sense, but also include errors that can be understood by those skilled in the art and allowed in manufacturing or use, etc.

[0030] The compact release device of the flexible solar wing provided by the present disclosure can be applied to the compact release process of the solar wing. Before the spacecraft is launched, the solar wing needs to be folded and compactly accommodated in the compact release device, at this time, the compact release device is in the closed position, and the solar wing is in a non-working state to withstand the severe vibration in the launch process, ensuring the safety of the solar wing. The folded part of the solar wing is firmly locked by the plate body of the compact release device, preventing the folded part of the solar wing from sliding or colliding with other devices. When the spacecraft enters the predetermined orbit, the compact release device receives the release instruction, and the constraint on the solar wing is released, at this time, the compact release device is in the open position.

[0031] In order to solve the problems existing in the prior art, the present disclosure provides a compact release device of a flexible solar wing, which can be converted between an open position and a closed position, and at least includes a plate body and two rotating mechanisms, and a compact release mechanism. Wherein, the plate body includes a first plate body and a second plate body, the first plate body is hinged with the second plate body, and the first plate body and the second plate body can be relatively arranged as rectangular long plates. When the compact release device is in the closed position, the solar wing is located at the middle position of the first plate body and the second plate body, and the first plate body and the second plate body are used for clamping the solar wing. One side of the first plate body and the second plate body is hinged through the two rotating mechanisms, and the first plate body can rotate relative to the second plate body with the rotating shaft of the rotating mechanism as the rotation center. The rotating mechanism can be a hinge. When the compact release device is in the open position, the first plate body rotates relative to the second plate body, and the first plate body and the second plate body release the solar wing.

[0032] The conversion of the compact release device between the open position and the closed position is realized through the compact release mechanism, which is arranged on the first plate body and the second plate body, and is used for locking the first plate body and the second plate body when the first plate body and the second plate body are in the closed position, and unlocking the first plate body and the second plate body so that the first plate body and the second plate body are converted from the closed position to the open position.

[0033] When the first plate body and the second plate body are in the closed position, they can preliminarily compact the flexible solar wing and play a role of pre-fixing. The compact release mechanism locks the first plate body and the second plate body, so as to further compact the flexible solar wing and realize reliable compacting effect. The first plate body and the second plate body can balance the pressure from the compact release mechanism, so that the flexible solar wing is uniformly stressed, avoiding the problem of excessive local pressure.

[0034] In addition, the compression release device is provided with a constraint assembly, the constraint assembly is provided with at least one constraint assembly arranged between the two rotating mechanisms, and the constraint assembly is arranged on the same side of the first plate body and the second plate body as the rotating mechanisms. The constraint assembly comprises a compression piece fixed on the first plate body and an abutting piece arranged on the second plate body. When the first plate body and the second plate body are in the closed position, the compression piece abuts against the abutting piece, and the abutting piece provides a compression force to the first plate body in the direction of the second plate body through the compression piece, so as to realize the compression of the first plate body to the second plate body, thereby realizing the compression of the solar wing.

[0035] The compression release device of the flexible solar wing provided by the present disclosure realizes the multi-point compression effect of the first plate body and the second plate body through the two rotating mechanisms and the constraint assembly arranged between the two rotating mechanisms. In addition, the first plate body and the second plate body have only two constraint points in the direction of the rotation axis, and whether the constraint assembly is arranged on the rotation axis does not affect the rotation release process, so that the long plate rotation release does not need to overcome the over-constraint resistance problem caused by multiple compression points on the axis.

[0036] The specific embodiments of the present disclosure will be described below in combination with the drawings.

[0037] The present disclosure provides a compression release device of a flexible solar wing, as shown in Figure 1 、 Figure 3 and Figure 6 , the compression release device can be switched between an open position and a closed position, and the compression release device at least comprises: a plate body and a rotating mechanism 3, a compression release mechanism 4, and a constraint assembly 5. The plate body comprises a first plate body 1 and a second plate body 2, and the first plate body 1 is hinged to the second plate body 2. When the compression release device is in the closed position, the solar wing 6 is located in the middle position between the first plate body 1 and the second plate body 2, that is, the first plate body 1 and the second plate body 2 are used to clamp the solar wing 6. The first plate body 1 and the second plate body 2 can be relatively arranged rectangular long plates, the shapes of the first plate body 1 and the second plate body 2 can be the same, and the area of the second plate body 2 in contact with the solar wing 6 can be slightly larger than the area of the first plate body 1 in contact with the solar wing 6.

[0038] One of the side edges of the first plate body 1 and the second plate body 2 is hinged through two rotating mechanisms 3, and the first plate body 1 can rotate relative to the second plate body 2 with the rotating shaft of the rotating mechanism 3 as the rotation center. The rotating mechanism 3 can be a hinge, a knuckle bearing, or a mechanism that can rotate around the joint under the action of a spring. As shown in Figure 1 and Figure 6As shown, the rotation shaft of the rotation mechanism 3 is the axis A passing through the joint centers of the two rotation mechanisms 3. After the first plate body 1 starts to rotate relative to the second plate body 2, the compression release device is switched from the closed position to the open position, and when the compression release device is in the open position, the first plate body 1 releases the restriction on the solar wing 6, thereby releasing the solar wing 6.

[0039] The switching of the compression release device between the open position and the closed position is achieved by the compression release mechanism 4, which is arranged on the first plate body 1 and the second plate body 2, and is used to lock the first plate body 1 and the second plate body 2 when the compression release device is in the closed position, and is used to unlock the first plate body 1 and the second plate body 2 so that the first plate body 1 can rotate relative to the second plate body 2, thereby switching the compression release device between the closed position and the open position. The compression release mechanism 4 can be a device such as a pyrotechnic, a memory alloy tube, or a separation nut, which separates and releases the constraint on the first plate body 1 and the second plate body 2 when it is powered, heated, or ignited.

[0040] When the first plate body 1 and the second plate body 2 are in the closed position, they can preliminarily compress the solar wing 6 and play a role of pre-fixing, and the compression release mechanism 4 locks the first plate body 1 and the second plate body 2, thereby further compressing the solar wing 6 and achieving a reliable compression effect. The first plate body 1 and the second plate body 2 can balance the pressure from the compression release mechanism 4, so that the solar wing 6 is uniformly stressed and the problem of excessive local pressure is avoided.

[0041] In one embodiment of the present disclosure, as shown in Figure 1 and Figure 6 The first plate body 1 and the second plate body 2 can be rectangular, and when the first plate body 1 and the second plate body 2 are rectangular, the first plate body 1 and the second plate body 2 have opposite long sides and short sides. The rotation mechanism 3 can be arranged on the long side of one of the first plate body 1 and the second plate body 2, and the compression release mechanism 4 can be arranged on the other long side of the first plate body 1 and the second plate body 2 or on the two short sides of the first plate body 1 and the second plate body 2. In another embodiment of the present disclosure, the compression release mechanism 4 can be arranged on the other long side and the two short sides of the first plate body 1 and the second plate body 2.

[0042] The compact release mechanism 4 is arranged on the long side or short side of the first plate body 1 and the second plate body 2 respectively, which can improve the flexibility and adaptability of the structure of the compact release device, and make it suitable for different size or shape plate body combination requirements. Preferably, the compact release mechanism 4 can be arranged on the other long side and two short sides of the first plate body 1 and the second plate body 2, that is, the compact release mechanism 4 can be arranged on all sides of the first plate body 1 and the second plate body 2 which do not arrange the rotating mechanism 3, which can ensure that the force on each side of the first plate body 1 and the second plate body 2 is uniform when the compact release device is in the closed position, avoid structural deformation or local stress concentration caused by one-sided compacting, and at the same time enhance the stability and reliability of the overall structure, making the locking effect more firm.

[0043] The compact release device is also provided with a constraint assembly 5, as shown in Figure 2 、 Figure 3 and Figure 5 , the constraint assembly 5 is provided with at least one, and the constraint assembly 5 is arranged between the two rotating mechanisms 3, and the constraint assembly 5 is arranged on the same side of the first plate body 1 and the second plate body 2 as the rotating mechanism 3. When the constraint assembly 5 is arranged as one, the constraint assembly 5 can be arranged at the middle position of the two rotating mechanisms 3; when the constraint assembly 5 is arranged as at least two, the constraint assembly 5 can be evenly spaced at the middle position of the two rotating mechanisms 3.

[0044] As shown in Figure 2 , the constraint assembly 5 includes a compacting piece 51 fixed on the first plate body 1 respectively, and an abutting piece 52 arranged on the second plate body 2. When the first plate body 1 and the second plate body 2 are in the closed position, the compacting piece 51 abuts against the abutting piece 52, and the abutting piece 52 provides a compacting force to the first plate body 1 in the direction of the second plate body 2 through the compacting piece 51, so as to realize the compacting of the first plate body 1 to the second plate body 2, thereby realizing the compacting of the solar wing 6 clamped by the first plate body 1 and the second plate body 2.

[0045] The compacting piece 51 of the present disclosure can be fixedly connected with the first plate body 1 through a screw, and the abutting piece 52 can be fixedly connected with the second plate body 2 through a screw. When the first plate body 1 rotates in the direction of the closed position, the compacting piece 51 moves synchronously with the first plate body 1 until the free end of the compacting piece 51 abuts against the abutting piece 52; when the first plate body 1 continues to move in the direction of the closed position, the compacting piece 51 provides a compacting force to the first plate body 1 in the direction of the second plate body 2 through the abutting piece 52.

[0046] In the prior art, the rigidity of the plate body of the compression release device is low, and the length is large. In order to achieve uniform and effective compression of the solar wing 6, a rotating mechanism 3 is arranged on the side of the plate body, that is, a plurality of compression points need to be arranged on the rotating shaft for multi-point compression. When there are three or more compression points arranged on the side of the rotating shaft, each compression point will not be on a straight line due to the deformation of the plate body during compression or rotation. When the plate body needs to rotate around the axis, the three over-constrained points will become a large resistance during the release process, which can easily cause the plate body to be unable to rotate around the axis, and the solar wing 6 cannot be effectively released.

[0047] The compression release device provided by the present disclosure realizes the multi-point compression effect of the first plate body 1 and the second plate body 2 through the two rotating mechanisms 3 and the constraint assembly 5 located between the two rotating mechanisms 3. In addition, the first plate body 1 and the second plate body 2 of the present disclosure have only two constraint points in the direction of the rotating shaft, and the long plate does not need to overcome the over-constrained resistance problem caused by multiple compression points on the axis during rotation and release.

[0048] In one embodiment of the present disclosure, as shown in Figure 1 , when the first plate body 1 and the second plate body 2 are in the closed position, the planes where the first plate body 1 and the second plate body 2 are located are parallel to each other, and the direction of the compression force is perpendicular to the direction of the second plate body 2. The parallel arrangement of the first plate body 1 and the second plate body 2 in the closed state forms a symmetrical support, which can effectively resist external loads and reduce the risk of deformation or misplacement of the compression release device. The direction of the compression force being perpendicular to the direction of the second plate body 2 can reduce local wear and tear and prolong the service life of the compression release device.

[0049] In one embodiment of the present disclosure, as shown in Figure 1 , Figure 2 , and Figure 5 , when the first plate body 1 and the second plate body 2 move from the closed position to the open position, the compression piece 51 moves away from the abutting piece 52, thereby realizing the separation of the compression piece 51 and the abutting piece 52. When the first plate body 1 and the second plate body 2 move from the closed position to the open position, the compression piece 51 will move away from the abutting piece 52, thereby realizing the separation of the two. During this process, even if the first plate body 1 has a slight deformation during the previous compression process or the rotation process, since the two rotating mechanisms 3 have determined the rotation axis of the plate body, and the compression piece 51 and the abutting piece 52 have been separated, whether the compression piece 51 and the abutting piece 52 are on the rotation axis does not affect the rotation release process. Compared with the prior art which needs to increase the rotation torque of the first plate body 1, the design difficulty is reduced, and there is no need to control or measure the deformation of the first plate body 1 near each compression point, thereby improving the reliability of the compression and rotation release of the first plate body 1.

[0050] In one embodiment of the present disclosure, as shown in Figure 2 When the first plate body 1 and the second plate body 2 are in the closed position, the pressing member 51 and the abutting member 52 are in surface contact, and the surface where the two abut is the abutting surface 54. The abutting surface 54 can be a plane, a cylindrical surface, or other curved surface. Compared with point contact and line contact, surface contact can significantly improve the uniformity of the stress on the contact area, effectively disperse local stress, avoid material deformation or wear caused by concentrated load, thereby enhancing the stability and durability of the structure. At the same time, surface contact can also provide greater frictional resistance for the pressing member 51 and the abutting member 52, ensuring the stable connection of the pressing and releasing device in the closed state, preventing accidental loosening caused by vibration or external force, and further improving the sealing performance and overall reliability.

[0051] In one embodiment of the present disclosure, as shown in Figure 2 The abutting surface 54 is a plane, and the abutting surface 54 is parallel to the plane where the first plate body 1 is located. The abutting surface 54 is designed as a plane and remains parallel to the plane where the first plate body 1 is located. This structure can ensure that the pressing force is uniformly distributed on the entire contact area, avoiding structural deformation or wear caused by local stress concentration. Setting the abutting surface 54 parallel to the plane where the first plate body 1 is located is beneficial to maintaining the stability of the movement trajectory during the rotation of the first plate body 1, reducing the additional resistance caused by deflection friction, thereby improving the rotation smoothness and prolonging the service life of the pressing and releasing device.

[0052] In one embodiment of the present disclosure, as shown in Figure 3 The two rotating mechanisms 3 have collinear rotation axes, defining a vertical plane 53 perpendicular to the first plate body 1, and the rotation axes of the two rotating mechanisms 3 are located in the vertical plane 53; the abutting surface 54 and the first plate body 1 are located on opposite sides of the vertical plane 53. It should be noted that the vertical plane 53 is a plane defined for ease of understanding, and is not a physical structure. By setting the abutting surface 54 on the side of the vertical plane 53 away from the first plate body 1, the pressing member 51 and the abutting member 52 will not interfere with each other in the process of converting the pressing and releasing device of the flexible solar wing from the closed position to the open position, i.e., their movement paths do not conflict with each other, thereby avoiding the situation that the pressing and releasing device of the flexible solar wing cannot be converted from the closed position to the open position, and ensuring the normal operation of the solar wing 6 in subsequent work.

[0053] In one embodiment of the present disclosure, as shown in Figure 3 and Figure 4As shown, the pressing member 51 comprises a pressing portion 511, a matching portion 512, and a connecting portion 513 connecting the pressing portion 511 and the matching portion 512. The pressing portion 511 is fixedly connected with the first plate body 1, and the matching portion 512 abuts against the abutting member 52 when the first plate body 1 and the second plate body 2 are in the closed position. The fixed connection of the pressing portion 511 with the first plate body 1 can make the connection of the two more secure, and the transmission effect of the pressing force is better. The abutment of the matching portion 512 and the abutting member 52 can make the pressing member 51 and the abutting member 52 jointly act when the pressing release device is in the closed position, providing a restraining force for the first plate body 1 and the second plate body 2 clamping the solar wing 6, preventing it from sliding or colliding with other devices.

[0054] The connecting portion 513 of the pressing member 51 can be perpendicular to or at an angle with the pressing portion 511 and the matching portion 512. Preferably, the pressing portion 511 and the matching portion 512 are parallel, and the connecting portion 513 is perpendicular to the pressing portion 511 and the matching portion 512, respectively.

[0055] By designing the pressing portion 511 and the matching portion 512 as parallel structures and connecting them through the perpendicular connecting portion 513, the pressing member 51 can uniformly distribute the pressure when stressed, and will not concentrate on a certain point. In this way, the first plate body 1 and the second plate body 2 can be more tightly and stably attached together, and will not easily loosen or have gaps, making the closed state more secure and reliable. The parallel arrangement of the pressing portion 511 and the matching portion 512 helps to keep the force direction of the abutting member 52 consistent, avoiding local stress concentration or deformation caused by structural misalignment. The perpendicular connecting portion 513 enhances the rigidity and torsional resistance of the overall structure, ensuring that the pressing member 51 does not easily loosen or deform during the reverse opening and closing process. Designing the pressing portion 511 and the matching portion 512 as parallel structures and connecting them through the perpendicular connecting portion 513 not only improves the sealing performance and fixing strength in the closed state, but also reduces wear caused by long-term use, thereby improving the reliability and service life of the overall structure.

[0056] In one embodiment of the present disclosure, as shown in Figure 3 The side wall of the first plate body 1 is provided with a mounting groove, and the pressing portion 511 is configured to extend into the mounting groove and be fixedly connected with the first plate body 1. The mounting groove can be a blind groove formed on the inside of the side wall of the first plate body 1, and the opening direction of the mounting groove matches the shape of the pressing portion 511 extending into the first plate body 1, to ensure that the pressing portion 511 can be stably embedded in the mounting groove and fixedly connected, avoiding loosening or deviation of the pressing portion 511 when stressed, thereby enhancing the pressing effect on the solar wing 6. Figure 2 and Figure 3As shown, the pressing part 511 is fixedly connected with the first plate body 1 by a screw, and the source of the pressing force is the abutting member 52, which transmits the downward pressing force to the pressing part 511 by abutting with the matching part 512. Since the pressing part 511 partially extends into the mounting groove of the first plate body 1, the downward pressing force is thus transmitted to the first plate body 1, so that the first plate body 1 is pressed towards the second plate body 2. The abutting member 52 transmits the force through the transmission path, so that the first plate body 1 cooperates with the second plate body 2 to realize the stable pressing of the solar wing 6. This structure makes the long plate structure of the first plate body 1 the main force bearing component, thereby ensuring the pressing reliability of the pressing system under long-term stress working conditions.

[0057] In one embodiment of the present disclosure, as shown in Figure 3 As shown, when the first plate body 1 and the second plate body 2 are in the closed position, the connecting part 513 has a predetermined distance between the side surface adjacent to the first plate body 1 and the first plate body 1. The predetermined distance refers to the distance between the side surface adjacent to the first plate body 1 and the first plate body 1. The distance is about 1 / 5 to 2 / 5 of the distance between the rotation center of the rotating mechanism 3 and the edge thereof. If the predetermined distance is not provided, the pressing member 51 may interfere with the solar wing 6 clamped inside the first plate body 1 and the second plate body 2 during the rotation of the first plate body 1, affecting the subsequent normal operation of the solar wing 6. By providing the predetermined distance between the side surface adjacent to the first plate body 1 and the first plate body 1, the stable conversion of the pressing release device from the closed position to the open position can be ensured, and contact or interference with the clamped solar wing 6 can be avoided.

[0058] The present disclosure also provides a spacecraft comprising the aforementioned pressing release device of the flexible solar wing. Compared with the existing spacecraft, the pressing release device of the flexible solar wing in the spacecraft provided by the present disclosure comprises a first plate body 1 and a second plate body 2, which are hinged by two rotating mechanisms 3 and provide a binding point by a constraint assembly 5 located between the two rotating mechanisms 3, thereby realizing the multi-point pressing effect of the first plate body 1 and the second plate body 2. In addition, the first plate body 1 and the second plate body 2 of the pressing release device provided by the present disclosure have only two constraint points in the rotation axis direction, and the long plate rotation release does not need to overcome the over-constraint resistance problem caused by multiple pressing points on the axis, and the first plate body 1 and the second plate body 2 can balance the pressing force of the flexible battery array of the pressing device, and will not cause the problem of excessive local pressure.

[0059] Having described above several embodiments of the disclosure, any modifications and variations that fall within the scope of the described embodiments are also contemplated by the inventor(s). As such, the foregoing description is not intended to limit the scope of the disclosure, and it is recognized that modifications can be made by one of ordinary skill in the art without departing from the scope and spirit of the described embodiments. The word "comprising" is used herein to mean "including" but not necessarily "consisting of" or "composed of." The word "comprising" therefore should not be interpreted as being limited to the recited items information.

Claims

1. A compact deployment device for a flexible solar wing, characterized in that The utility model relates to a solar wing folding mechanism, comprising: a first plate body (1) and a second plate body (2), the first plate body (1) and the second plate body (2) are hinged and are configured to clamp the flexible solar wing (6) in a closed position and release the solar wing (6) in an open position; two rotating mechanisms (3), one side of the first plate body (1) and the second plate body (2) is configured to be hinged by the two rotating mechanisms (3); the first plate body (1) is configured to rotate relative to the second plate body (2) with the rotating shaft of the rotating mechanism (3) as the rotating center; a pressing release mechanism (4) arranged on the first plate body (1) and the second plate body (2) and configured to lock the first plate body (1) and the second plate body (2) when the first plate body (1) and the second plate body (2) are in the closed position and unlock the first plate body (1) and the second plate body (2); at least one constraint assembly (5) arranged between the two rotating mechanisms (3); the constraint assembly (5) is arranged on the same side of the first plate body (1) and the second plate body (2) as the rotating mechanism (3); the constraint assembly (5) comprises a pressing piece (51) fixed on the first plate body (1) and an abutting piece (52) arranged on the second plate body (2); the first plate body (1) and the second plate body (2) are configured to be in the closed position, the pressing piece (51) is configured to abut against the abutting piece (52), and the abutting piece (52) is configured to provide a pressing force to the first plate body (1) in the direction of the second plate body (2) through the pressing piece (51).

2. A compact deployment device for a flexible solar wing according to claim 1, characterized in that When the first plate body (1) and the second plate body (2) move from the closed position to the open position, the pressing piece (51) is configured to move away from the abutting piece (52).

3. A compact deployment device for a flexible solar wing according to claim 1, characterized in that When the first plate body (1) and the second plate body (2) are in the closed position, the pressing piece (51) and the abutting piece (52) are in surface contact, and the surface abutting against each other is an abutting surface (54).

4. A compact deployment device for a flexible solar wing according to claim 3, characterized in that The abutting surface (54) is a plane, and the abutting surface (54) is parallel to the plane where the first plate body (1) is located.

5. The compact deployment apparatus of a flexible solar wing according to claim 3, wherein, A vertical plane (53) perpendicular to the first plate body (1) is defined, and the rotating axis of the rotating mechanism (3) is located in the vertical plane (53); the abutting surface (54) and the first plate body (1) are configured to be located on opposite sides of the vertical plane (53), respectively.

6. A compact deployment apparatus for a flexible solar wing according to claim 1, wherein, The pressing piece (51) comprises a pressing part (511), a matching part (512), and a connecting part (513) connecting the pressing part (511) and the matching part (512); the pressing part (511) is configured to be fixedly connected with the first plate body (1); and the matching part (512) is configured to abut against the abutting piece (52) when the first plate body (1) and the second plate body (2) are in the closed position.

7. A compact deployment apparatus for a flexible solar wing according to claim 5, wherein, The pressing part (511) is configured in parallel with the fitting part (512), and the connecting part (513) is configured in perpendicular to the pressing part (511) and the fitting part (512) respectively.

8. A compact deployment apparatus for a flexible solar wing according to claim 5, wherein, The side wall of the first plate body (1) is provided with a mounting groove, and the pressing part (511) is configured to extend into the mounting groove and be fixedly connected with the first plate body (1).

9. A compact deployment apparatus for a flexible solar wing according to claim 5, wherein, When the first plate body (1) and the second plate body (2) are in the closed position, the connecting part (513) adjacent to one side surface of the first plate body (1) is configured to have a predetermined distance from the first plate body (1).

10. A compact deployment apparatus for a flexible solar wing according to claim 1, wherein, When the first plate body (1) and the second plate body (2) are in the closed position, the planes where the first plate body (1) and the second plate body (2) are located are parallel to each other, and the direction of the pressing force is perpendicular to the direction of the second plate body (2).

11. A compact deployment apparatus for a flexible solar wing according to claim 1, characterized in that The first plate body (1) and the second plate body (2) are rectangular, the rotating mechanism (3) is arranged on a long side of one of the first plate body (1) and the second plate body (2), the pressing and releasing mechanism (4) is arranged on a long side of the other of the first plate body (1) and the second plate body (2), and / or the pressing and releasing mechanism (4) is arranged on both short sides of the first plate body (1) and the second plate body (2).

12. A spacecraft, characterized by, A pressing and releasing device of a flexible solar wing comprising any one of claims 1-11.

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