A micro-nano satellite

Abstract

The present application relates to the field of aerospace equipment technology, and more specifically, to a micro-nano satellite, which includes a satellite body, a foldable solar wing, a clamping rod, and a locking mechanism; the locking mechanism is arranged on the satellite body; one end of the clamping rod is connected to the outermost substrate of the foldable solar wing, and the other end of the clamping rod passes through the other substrates of the foldable solar wing and cooperates with the locking mechanism; the locking mechanism is used to releasably lock the clamping rod to lock the foldable solar wing in a folded state. Compared with the destructive release method of releasing the foldable solar wing by cutting, fusing or blasting the clamping mechanism in the prior art, the solar wing, the clamping rod and the locking mechanism of the micro-nano satellite provided in the present application can be reused, thereby reducing the cost of the micro-nano satellite.

Description

Technical Field

[0001] The present application relates to the field of aerospace equipment technology, and in particular to a micro-nano satellite. Background Art

[0002] When launching a micro-nano satellite, its solar wings need to be folded together and then unfolded after entering orbit. Before unfolding, the solar wings of a micro-nano satellite are generally fixed to the satellite body by a clamping mechanism. When the solar wings need to be released, the clamping mechanism is cut, fused or exploded to release the solar wings. The clamping mechanism used in the existing micro-nano satellite and the fuse device connected to it lead to high cost of micro-nano satellites. Summary of the invention

[0003] The present application aims to provide a micro-nano satellite to solve the problem of high cost of micro-nano satellites in the prior art.

[0004] The embodiment of the present application is implemented as follows:

[0005] In one aspect, an embodiment of the present application provides a micro-nano satellite, which includes a satellite body, a foldable solar wing, a clamping rod, and a locking mechanism;

[0006] The locking mechanism is arranged on the satellite body;

[0007] One end of the clamping rod is connected to the outermost substrate of the foldable solar wing, and the other end of the clamping rod passes through the other substrates of the foldable solar wing and cooperates with the locking mechanism;

[0008] The locking mechanism is used to releasably lock the pressing rod to lock the foldable solar wing in a folded state.

[0009] The micro-nano satellite provided in the present application is provided with a locking mechanism on the satellite body, and a clamping rod is provided on the outermost substrate of the foldable solar wing. When the foldable solar wing is in a folded state, the clamping rod cooperates with the locking mechanism to press the foldable solar wing against the surface of the satellite body; when the foldable solar wing needs to be released, the locking mechanism releases the clamping rod to release the foldable solar wing. After the release, the clamping rod is connected to the outermost substrate of the foldable solar wing, so the clamping rod will not detach and float in the space. After the micro-nano satellite is recovered, its foldable solar wing can be folded repeatedly, and the clamping rod and the locking mechanism can be reused to cooperate in clamping the foldable solar wing, thereby reducing the cost of the micro-nano satellite.

[0010] Moreover, compared with the destructive release method in the prior art of releasing the foldable solar wing by cutting, melting or blasting the clamping mechanism, the prior method is prone to generate large vibrations at the moment of release. Such vibrations acting on the satellite body can easily have an adverse effect on the operating posture of the micro-nano satellite. The present application utilizes a locking mechanism to release the clamping rod, which has less vibration than the prior destructive release method and is not likely to affect the operating posture of the micro-nano satellite.

[0011] Optionally, in one embodiment of the present application, the micro-nano satellite also includes a clamping cover, a clamping spring and a pre-tightening nut, the clamping cover is fixed to the outermost substrate of the foldable solar wing, the clamping rod passes through the outermost substrate of the foldable solar wing and is threadedly connected to the pre-tightening nut, and the clamping spring is supported between the clamping cover and the pre-tightening nut.

[0012] By arranging a clamping cover on the outermost substrate of the foldable solar wing and arranging a pre-tightening nut at the end of the clamping rod, the clamping cover, the clamping spring and the pre-tightening nut cooperate to provide a pre-tightening force, and the pre-tightening force is borne and transmitted to the locking mechanism through the clamping rod, thereby clamping and locking the foldable solar wing.

[0013] Therefore, the clamping rod is configured to be slidably connected to the outermost substrate of the foldable solar wing along its axial direction, and the clamping rod will not slip off the outermost substrate of the foldable solar wing; and the magnitude of the pre-tightening force transmitted by the clamping rod is adjustable, and the magnitude of the pre-tightening force can also be adjusted by rotating the pre-tightening nut. The shorter the length of the clamping rod exposed outside the clamping cover by rotating the nut, the greater the pre-tightening force.

[0014] Optionally, in one embodiment of the present application, the locking mechanism includes a lock body installed on the satellite body, the lock body is provided with a drive assembly and a first clamping piece, one end of the clamping rod is connected to a second clamping piece for cooperating with the first clamping piece; the drive assembly is used to drive the first clamping piece to move to separate from the second clamping piece, thereby releasing the clamping rod.

[0015] The existing destructive release methods, such as cutting, melting or blasting, are easily affected by temperature, materials and other external environmental factors. The present application realizes compression locking by setting a first clamping fixture and a second clamping fixture to cooperate with each other, and sets a driving component to move the first clamping fixture to unlock. The moving path of the first clamping fixture is determined, and the release method is stable and reliable, and is not prone to errors.

[0016] Optionally, in an embodiment of the present application, the locking mechanism further includes a reset member, a reset opening is provided on the lock body, and the reset member is used to move through the reset opening to move the first locking member, thereby making the first locking member cooperate with the second locking member.

[0017] By setting a reset port on the lock body, it is further convenient to compress and lock again after recovery, and the reset piece is extended into the lock body from the reset port to move the first clamping piece into place, so that the first clamping piece and the second clamping piece are locked in coordination.

[0018] Optionally, in an embodiment of the present application, the driving assembly includes a limiter and an elastic member, one end of the elastic member is connected to the lock body, and the other end is connected to the first clamping member, the limiter is movably arranged on the lock body, and the limiter has a working position and a release position;

[0019] The limiting member abuts against the first clamping member when in the working position so that the first clamping member and the second clamping member remain in cooperation; the limiting member is separated from the first clamping member when in the releasing position so that the first clamping member is away from the second clamping member under the action of the elastic member.

[0020] The first clamping member is kept in cooperation with the second clamping member by arranging the limiting member, and the elastic member is arranged to cooperate with the limiting member to realize driving the first clamping member. The overall structure is simple and the movement path of the first clamping member is clear.

[0021] Optionally, in an embodiment of the present application, the first clamping member is connected to the lock body via a rotating shaft, a hook body is formed on the first clamping member, and a groove body adapted to the hook body is formed on the second clamping member.

[0022] Optionally, in an embodiment of the present application, the limiting member includes a latch, and the locking mechanism further includes a pin puller connected to the lock body, and the pin puller is drivingly connected to the latch.

[0023] Optionally, in an embodiment of the present application, each substrate is respectively provided with a through hole for allowing the pressing rod to pass through, and a pressing bushing is provided in the through hole.

[0024] By providing a through hole with a compression bushing on each substrate, when the foldable solar wing is in a folded state, the compression bushings of adjacent substrates contact and are compressed with each other, forming a semi-rigid body from the outermost substrate of the foldable solar wing to the satellite body, which has the effect of transmitting pre-tightening force and further ensuring that the foldable solar wing is compressed.

[0025] Optionally, in an embodiment of the present application, a first pad and a second pad are formed at both ends of the compression sleeve, and when the foldable solar wing is in a folded state, the first pad and the second pad on two adjacent substrates abut against each other.

[0026] By forming a first liner and a second liner at both ends of the compression bushing, the contact area of ​​each compression bushing is increased, the cross-sectional area of ​​the semi-rigid body is increased, and the force transmission effect is good.

[0027] Optionally, in an embodiment of the present application, each substrate includes a first surface and a second surface, the first gasket is fixed to the first surface by a first screw, and the second gasket is fixed to the second surface by a second screw, and the positions of the first screw and the second screw are staggered.

[0028] By staggering the positions of the first screw and the second screw, the first screw and the second screw are prevented from abutting against each other in the folded state, and the minimum spacing between adjacent substrates in the folded state is reduced, so that the foldable solar wing can be folded and compressed more compactly. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0030] Figure 1 A diagram of the unfolded state of a micro-nano satellite provided in an embodiment of the present application;

[0031] Figure 2 A diagram of the folded state of the micro-nano satellite provided in an embodiment of the present application;

[0032] Figure 3 A cross-sectional view of a micro-nano satellite in a folded state provided in an embodiment of the present application;

[0033] Figure 4 A schematic diagram of the three-dimensional structure of the locking mechanism provided in an embodiment of the present application;

[0034] Figure 5 A schematic diagram of the internal structure of the locking mechanism provided in an embodiment of the present application;

[0035] Figure 6 A schematic diagram of the structure of a clamping rod provided in an embodiment of the present application;

[0036] Figure 7 for Figure 1 A magnified view of part A;

[0037] Figure 8 for Figure 1 A magnified view of part B;

[0038] Fig. 9 for Figure 1 Enlarged view of part C;

[0039] Fig.10 for Figure 3 A magnified view of part D in the middle;

[0040] Fig.11 A schematic diagram of the cooperation between the rotation limiting block and the lock provided in the embodiment of the present application;

[0041] Fig.12 It is a schematic diagram of another embodiment of the rotation limiting block and the lock;

[0042] Fig.13 A schematic diagram of the structure of the first card firmware provided in an embodiment of the present application.

[0043] Icons: 10 - satellite body; 20 - solar wing; 21 - first base plate; 22 - second base plate; 23 - third base plate; 24 - through hole; 25 - clamping bushing; 251 - first gasket; 252 - second gasket; 261 - first screw; 262 - second screw; 30 - power hinge; 40 - clamping rod; 50 - locking mechanism; 41 - second clamping piece; 411 - groove body; 412 - rotation limit block; 42 - clamping cap; 43 - pre-tightening nut; 44 - clamping spring; 51 - lock body; 511 - lock mouth; 513 - reset mouth; 52 - first clamping piece; 521 - hook body; 522 - rotating shaft; 53 - limiting piece; 54 - elastic piece; 55 - pin puller. DETAILED DESCRIPTION

[0044] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

[0045] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application for which protection is sought, but merely represents selected embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0046] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0047] In the description of this application, it should be noted that if the terms "center", "up", "down", "left", "right", "vertical", "horizontal", "inside", "outside", etc. appear, the orientation or position relationship indicated is based on the orientation or position relationship shown in the drawings, or the orientation or position relationship in which the product of the application is usually placed when in use. It is only for the convenience of describing this application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operate in a specific orientation, and therefore cannot be understood as a limitation on this application. In addition, if the terms "first", "second", etc. appear in the description of this application, they are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0048] In addition, if the terms "horizontal" or "vertical" appear in the description of this application, it does not mean that the components are required to be absolutely horizontal or suspended, but can be slightly tilted. For example, "horizontal" only means that its direction is more horizontal than "vertical", and does not mean that the structure must be completely horizontal, but can be slightly tilted.

[0049] In the description of this application, it should also be noted that, unless otherwise clearly specified and limited, the terms "set", "install", "connect", and "connect" should be understood in a broad sense, for example, it can be a fixed connection, a detachable connection, or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection, or it can be indirectly connected through an intermediate medium, or it can be the internal connection of two components. For ordinary technicians in this field, the specific meanings of the above terms in this application can be understood according to specific circumstances.

[0050] Example

[0051] The present application provides a micro-nano satellite, which includes a satellite body 10 and a foldable solar wing 20 (hereinafter referred to as the solar wing 20). Figure 1 and Figure 2 A foldable solar wing 20 and a portion of a satellite body 10 connected to the foldable solar wing 20 are shown.

[0052] The solar wing 20 includes a first substrate 21, a second substrate 22 and a third substrate 23, which are hinged in sequence, wherein the third substrate 23 is the innermost substrate of the solar wing 20, and the third substrate 23 is hinged to the satellite body 10, and the first substrate 21 is the outermost substrate of the solar wing 20, and the first substrate 21 is far away from the satellite body 10.

[0053] The micro-nano satellite also includes a clamping rod 40 and a locking mechanism 50 . The locking mechanism 50 is disposed on the satellite body 10 . One end of the clamping rod 40 is connected to the first substrate 21 , and the other end of the clamping rod 40 can cooperate with the locking mechanism 50 .

[0054] When the multiple base plates of the solar wing 20 are in the folded state, the other end of the clamping rod 40 connected to the first base plate 21 cooperates with the locking mechanism 50, and the locking mechanism 50 is used to releasably lock the clamping rod 40 to lock the solar wing 20 in the folded state. When the solar wing 20 needs to be unfolded, the locking mechanism 50 releases the clamping rod 40, so that the solar wing 20 can be unfolded under the action of an external driving force.

[0055] After release, the clamping rod 40 is connected to the first substrate 21 to ensure that the clamping rod 40 will not be separated from the first substrate 21 and float in space. After the micro-nano satellite is recovered, the solar wing 20 can be repeatedly folded, and the clamping rod 40 is passed through multiple substrates so that the locking mechanism 50 can releasably lock the clamping rod 40.

[0056] In the prior art, the clamping mechanism is often cut, melted or exploded to release the foldable solar wing 20. Specifically, an pyrotechnic is set in the clamping mechanism of the micro-nano satellite, and the high heat or blasting force generated by the pyrotechnic is used to destroy the clamping mechanism. In the warehouse, pyrotechnics require a special storage space and are managed by a dedicated person to ensure storage safety; on the micro-nano satellite, once the pyrotechnic is ignited or detonated, the clamping mechanism cannot be used again. The existing method is not only unsafe, but also the clamping mechanism cannot be reused.

[0057] Compared with the destructive release method of the prior art, the solar wing 20, the clamping rod 40 and the locking mechanism 50 of the micro-nano satellite provided in the present application can be reused, with low management costs, thereby reducing the cost of the micro-nano satellite.

[0058] Moreover, the existing method is prone to generate large vibrations at the moment of release, and such vibrations acting on the satellite body 10 are likely to have an adverse effect on the operating attitude of the micro-nano satellite. The impact load generated when detonating pyrotechnics may even affect the normal operation of precision instruments and equipment on the micro-nano satellite. The present application utilizes a locking mechanism 50 to release the clamping rod 40, which has less vibration than the existing destructive release method and is not likely to affect the operating attitude of the micro-nano satellite.

[0059] Since the existing destructive release method has the aforementioned problems of poor safety, non-reusability, and large impact load, the clamping mechanism has poor testability, and the clamping mechanism can only be set up based on the configuration experience obtained through repeated tests, which is not convenient for testing each clamping mechanism and solar wing 20 actually used on the micro-nano satellite. The micro-nano satellite provided in the embodiment of the present application can test the assembled micro-nano satellite as a whole on the ground, and can also test the solar wing 20, the clamping rod 40, and the locking mechanism 50 separately. It has strong testability and can effectively verify and evaluate the reliability of the micro-nano satellite.

[0060] The first substrate 21, the second substrate 22, and the third substrate 23 are respectively provided with through holes 24, and the number of through holes 24 on each substrate is the same and the positions are corresponding. Figure 1 Each substrate is provided with three through holes 24, and the three through holes 24 on each substrate are located at the same position on the corresponding substrate. Accordingly, the micro-nano satellite is provided with three clamping rods 40 and three locking mechanisms 50. The following is an example of any clamping rod 40 and its matching locking mechanism 50 for explanation.

[0061] A pressing bushing 25 is disposed in each through hole 24 . A first gasket 251 and a second gasket 252 are formed at both ends of the pressing bushing 25 . The first gasket 251 and the second gasket 252 are respectively attached to two surfaces of the corresponding substrate.

[0062] For ease of description, the side of each substrate facing the satellite body 10 after folding is the first surface, and the other side is the second surface. The first pad 251 is fixed to the first surface by the first screw 261, and the second pad 252 is fixed to the second surface by the second screw 262. When the solar wing 20 is folded, the first surface of the previous substrate is relatively close to the second surface of the next substrate. In order to control the minimum spacing between adjacent substrates in the folded state, the positions of the first screw 261 and the second screw 262 are staggered.

[0063] like Figure 7 As shown, the through hole 24 is rectangular, and eight screw holes are arranged at the edge of each through hole 24, four of which are located at the four corners of the rectangle, and the other four are located at the midpoints of the four sides of the rectangle. Figure 8 As shown, on the second surface of the second substrate 22, the second gasket 252 of the compression bushing 25 is fixed by second screws 262, and four second screws 262 are connected to the screw holes at the four corners of the corresponding through hole 24. Fig. 9 As shown, on the first surface of the first substrate 21, the first gasket 251 of the compression bushing 25 is fixed by the first screws 261, and the four first screws 261 are connected to the screw holes at the midpoints of the four sides of the box-shaped through hole 24. When the first substrate 21 and the second substrate 22 are folded, the first surface of the first substrate 21 approaches the second surface of the second substrate 22, and the compression bushings 25 on the first substrate 21 and the second substrate 22 are in contact with each other, and the first screws 261 and the second screws 262 do not interfere with each other.

[0064] The two ends of the aforementioned pressing rod 40 are respectively provided with threads, one end of which is connected to a pre-tightening nut 43, and the other end is connected to a second clamping member 41. Figure 6To facilitate the installation of the clamping rod 40, a perforated pad can be provided at the through hole 24 of the first substrate 21. The perforated pad can be separately covered and fixed at the through hole 24; the perforated pad can also be connected to the pre-tightening nut 43 as a whole; or the outer periphery of the pre-tightening nut 43 can extend outward to abut against the first surface of the first substrate 21.

[0065] A clamping cap 42 is fixed on the second surface of the first substrate 21, and the clamping cap 42 forms a receiving cavity on the second surface of the first substrate 21. One end of the clamping rod 40 passes through the hole 24 to connect the perforated pad and the pre-tightening nut 43, and extends into the receiving cavity.

[0066] A compression spring 44 is abutted between the compression cap 42 and the pre-tightening nut 43, and the compression spring 44 is sleeved on the outside of the compression rod 40. The compression spring 44 is used to press the pre-tightening nut 43 against the first substrate 21 through the perforated pad, so that the pre-tightening force is received and transmitted through the compression rod 40, so that the multiple substrates of the solar wing 20 are compressed and locked on the satellite body 10.

[0067] The clamping cap 42 and the clamping rod 40 are not directly against each other, but are indirectly against each other through the clamping spring 44 and the pre-tightening nut 43. There can be a margin of relative movement between the clamping rod 40 and the clamping cap 42, that is, the clamping rod 40 can move out or move in toward the clamping cap 42, so that the length of the clamping rod 40 exposed outside the clamping cap can be changed. When clamping, the size of the pre-tightening force can be adjusted by rotating the pre-tightening nut 43.

[0068] For example, Figure 3 and Fig.10 In the process, tighten the pre-tightening nut 43 to press down each substrate, so that the length of the clamping rod 40 exposed outside the clamping cap 42 is shortened and the pre-tightening force is increased; or loosen the pre-tightening nut 43 to increase the length of the clamping rod 40 exposed outside the clamping cap 42 and reduce the pre-tightening force.

[0069] After the solar wing 20 is released, the locking mechanism 50 is separated from the clamping rod 40 , and the clamping rod 40 remains fixed on the first substrate 21 under the action of the clamping cap 42 , the pre-tightening nut 43 and the clamping spring 44 .

[0070] The aforementioned locking mechanism 50 includes a lock body 51 mounted on the satellite body 10, such as Figure 4 and Figure 5 The first clamping member 52 is disposed in the lock body 51 , and a locking opening 511 is provided on the lock body 51 . The second clamping member 41 connected to the pressing rod 40 can pass through the locking opening 511 and connect with the first clamping member 52 to lock the pressing rod 40 .

[0071] A hook 521 is formed on the first clamping member 52 , and a groove 411 is formed on the second clamping member 41 . The hook 521 extends into the groove 411 to restrict the pressing rod 40 from axially escaping from the locking opening 511 .

[0072] In order to prevent the second clamping member 41 threadedly connected to the pressing rod 40 from being separated or loosened from the pressing rod 40, the second clamping member 41 further forms a rotation limiting block 412, and the lock opening 511 is configured to be in a shape that matches the rotation limiting block 412. When the second clamping member 41 on the pressing rod 40 extends from the lock opening 511 into the lock body 51, the rotation limiting block 412 is located at the position of the lock opening 511 to prevent the second clamping member 41 from rotating in the lock body 51.

[0073] When limiting the rotation of the second clamping piece 41 around the axis of the clamping rod 40, the rotation limit block 412 also needs to meet the requirements of the unfolding action of the solar wing 20. When the solar wing 20 is unfolded, the clamping rod 40 may not move out in a straight line, and at this time, the rotation limit block 412 may be tilted.

[0074] Alternatively, if Fig.11 As shown, the structure of the rotation limit block 412 and the lock 511 can be: the rotation limit block 412 is rectangular, the lock 511 is also rectangular, a set of relative edges of the rotation limit block 412 is in contact with a set of relative edges of the lock 511 to limit the rotation of the second clamping member 41 around the axis of the clamping rod 40, and another set of relative edges of the rotation limit block 412 and another set of relative edges of the lock 511 are reserved with a gap so that the rotation limit block 412 can be smoothly moved out when it is rotated to be tilted relative to the lock 511.

[0075] Alternatively, if Fig.12 As shown, the structure of the rotation limit block 412 and the lock 511 can also be: the rotation limit block 412 has a protruding cylinder, and the side wall of the lock 511 has a strip groove. When the part where the groove body 411 of the second clamping member 41 is located is inserted into the lock 511, the cylinder on the rotation limit block 412 is inserted into the strip groove, thereby limiting the rotation of the second clamping member 41 around the axis of the clamping rod 40. When the clamping rod 40 is tilted and moved out, the cylinder on the rotation limit block 412 can rotate to ensure that the rotation limit block 412 is tilted along with the clamping rod 40. The strip groove can also be set as a trumpet-shaped groove, the width of which gradually increases from the inside to the outside, the narrower part of the trumpet-shaped groove close to the inside of the lock body 51 is adapted to the diameter of the cylinder, and the wider part of the trumpet-shaped groove close to the outside of the lock body 51 provides more margin for the limit block to be tilted out.

[0076] In this embodiment, the structures of the rotation limiting block 412 and the lock 511 are as follows: Fig.11 The structure shown.

[0077] The lock body 51 is also provided with a driving component for controlling the first clamping member 52 . The driving component can keep the first clamping member 52 in cooperation with the second clamping member 41 to lock the clamping rod 40 , and can also drive the first clamping member 52 to move away from the second clamping member 41 to release the clamping rod 40 .

[0078] The driving assembly includes a limiter 53 and an elastic member 54. The elastic member 54 is connected between the first clamping member 52 and the lock body 51, and has potential energy to move the first clamping member 52 along a predetermined path, which is a path for the hook body 521 to be away from the slot body 411. The limiter 53 is movably arranged on the lock body 51, and the limiter 53 has a working position against the first clamping member 52, and a release position separated from the first clamping member 52.

[0079] When the limiting member 53 is at the working position, it abuts against the first clamping member 52 to limit the first clamping member 52 from moving along the predetermined path. When the limiting member 53 moves to the releasing position, the first clamping member 52 moves along the predetermined path under the action of the elastic member 54, so that the hook body 521 is disengaged from the groove body 411 of the second clamping member 41.

[0080] In this embodiment, the limiting member 53 is a latch and the elastic member 54 is a spring.

[0081] The structure of the first clamping member 52 is as follows: Fig.13 As shown, it is L-shaped, wherein the hook body 521 is located at one end of the L-shape, and the spring is connected to the other end of the L-shape. A boss is formed on the inner wall of the lock body 51, and a groove is formed in the middle of the boss. The end of the rotating shaft 522 of the first clamping member 52 can be rotatably engaged in the groove. In this embodiment, the rotating shaft 522 is set at the corner position of the L-shape.

[0082] The lock body 51 is also connected to a pin puller 55, which is a linear drive device, such as a linear motor, a cylinder, an electromagnet, etc. Figure 4 The pin puller 55 is connected to the outside of the lock body 51. The lock body 51 is provided with a limit opening, and the limit member 53 is connected to the pin puller 55 through the limit opening. The pin puller 55 is used to drive the limit member 53 to extend into the lock body 51 from the limit opening, and can also be used to drive the limit member 53 to move out of the lock body 51 from the limit opening.

[0083] To further facilitate repeated compression, a reset port 513 is provided on the lock body 51. A reset member is inserted into the lock body 51 through the reset port 513 to overcome the pulling force of the elastic member 54 and to push the first clamping member 52, so that the hook 521 of the first clamping member 52 is inserted into the groove 411 of the second clamping member 41. Figure 5The shape of the reset opening 513 is further set to be an arc, and the reset member is a slender rod-shaped object, such as a screwdriver, a screwdriver, etc., which can be manually driven or driven by a cam motor to move the reset member downward along the arc path of the reset opening 513, thereby pressing down the first clamping member 52.

[0084] The compression and release principle of the solar wing 20 of the micro-nano satellite provided in this embodiment is as follows:

[0085] Before launch, the multiple substrates of the solar wing 20 are folded, and the clamping rod 40 passes through the multiple substrates, so that the second clamping member 41 at the end thereof enters the lock body 51, and the limiter 53 abuts on the first clamping member 52, and the hook body 521 of the first clamping member 52 cooperates with the groove body 411 of the second clamping member 41. Tighten the pre-tightening nut 43, and the tension is borne and transmitted by the clamping rod 40, and a certain tension is always maintained in the clamping rod 40 to ensure that the solar wing 20 is fixed and not loosened. At this time, the clamping bushings 25 of the adjacent substrates are in contact with each other, wherein the first liner 251 of the clamping bushing 25 of the third substrate 23 abuts on the lock body 51, and the second liner 252 of the clamping bushing 25 of the first substrate 21 abuts on the clamping cap 42. Under the action of the pre-tightening force, a semi-rigid body is formed from the lock body 51 to the clamping cap 42 (or from the first substrate 21 to the satellite body 10), and the semi-rigid body can also play a role in transmitting the pre-tightening force, further ensuring that the solar wing 20 is clamped. The pressing bushing 25 can be made of a wear-resistant elastic material such as rubber, so that the semi-rigid body can be compressed after being pressed to further reduce the distance between adjacent substrates.

[0086] After the micro-nano satellite is launched into the orbit, the pin puller 55 is activated, and the pin puller 55 drives the limiter 53 to move out of the lock body 51 from the limit opening, and the elastic member 54 pulls the first clamping member 52, and the first clamping member 52 rotates around the rotating shaft 522, and its hook body 521 moves out of the groove body 411 of the second clamping member 41, and the locking mechanism 50 completes the action of releasing the clamping rod 40. The solar wing 20 is unfolded under the action of the external driving force, and the clamping rod 40 sequentially withdraws from the lock body 51, the third substrate 23, and the second substrate 22.

[0087] After the micro-nano satellite is recovered, the solar wing 20 is folded, the second clamping member 41 on the clamping rod 40 enters the lock body 51 from the lock opening 511 again, the reset member is extended into the lock body 51 from the reset opening 513, and the L-shaped first clamping member 52 is moved to connect one end of the elastic member 54, so that the first clamping member 52 is rotated until its hook body 521 enters the groove body 411 of the second clamping member 41, and then the pin puller 55 is started to reset the limiter 53, so that the limiter 53 moves from the limit opening into the lock body 51 and remains in the working position, and the locking mechanism 50 completes the action of locking the clamping rod 40. Then, the pre-tightening nut 43 in the clamping cap 42 is tightened to clamp the solar wing 20.

[0088] Compared with large satellites, the advantages of micro-nano satellites are short development cycle and low cost. However, the clamping mechanism used in the existing micro-nano satellites and the fuse device connected thereto are relatively expensive and can only be used once. The micro-nano satellite provided in the embodiment of the present application has a locking mechanism 50 and a clamping rod 40 and other components provided on the solar wing 20 for clamping the solar wing 20. They have low manufacturing cost and can be reused, which can effectively reduce the cost of micro-nano satellites and further give play to the advantages of micro-nano satellites.

[0089] In order to further reduce the size and cost of the micro-nano satellite, the micro-nano satellite provided in the present application is pivoted by a power hinge 30, and the power hinge 30 includes a first hinge part and a second hinge part pivoted by a hinge shaft, and the two hinge parts are respectively connected to two adjacent substrates. A torsion spring is sleeved on the hinge shaft, and the two ends of the torsion spring are respectively abutted against the first hinge part and the second hinge part, so as to provide an external driving force to relatively unfold the two connected substrates when the locking mechanism 50 releases the clamping rod 40.

[0090] In order to make the clamping rod 40 stably move out of the lock body 51 after being released by the locking mechanism 50, a damping component is optionally provided on the hinge shaft of the power hinge 30, and the damping component is used to generate damping when the first hinge part and the second hinge part are relatively unfolded, so as to adjust the unfolding force required by different parts of the solar wing 20, thereby ensuring that the multiple substrates of the solar wing 20 are synchronously unfolded at the same angular velocity. At this time, the moving direction and moving speed of the clamping rod 40 are relatively stable, and it is not easy to interfere with the lock body 51 or the substrate, which is conducive to the stable unfolding of the solar wing 20. The damping component mentioned here can be a damping washer provided on the hinge shaft, and the damping washer contacts at least one of the first hinge part and the second hinge part. The magnitude of the friction damping is adjusted by adjusting the pressure on the contact surface, thereby adjusting the unfolding force actually output by the torsion spring.

[0091] It should be noted that:

[0092] The number of second substrates 22, the number of power hinges 30 between any two adjacent substrates, and the number of sets of clamping rods 40 and locking mechanisms 50 are set according to factors such as the solar circuit board area requirement of the micro-nano satellite, the deployment force requirement of the solar wing 20, and the locking degree requirement of the solar wing 20.

[0093] The second substrate 22 (ie, the substrate between the first substrate 21 and the third substrate 23 ) may not be provided, or may be provided in number of one, two, three or even more. In actual use, the specific number is set according to needs.

[0094] Every two adjacent base plates can be pivotally connected via one, two, three or even more power hinges 30 , and the specific number is set according to needs.

[0095] The pressing rod 40 and the locking mechanism 50 can be matched to be provided in multiple sets. The number can be set according to factors such as the size of the substrate in actual use, and can be one set, two sets, three sets or even more.

[0096] The above description is only the preferred embodiment of the present application and is not intended to limit the present application. For those skilled in the art, the present application may have various modifications and variations. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application shall be included in the protection scope of the present application.

Claims

1. A micro-nano satellite, characterized in that: It includes a satellite body, a foldable solar wing, a clamping rod and a locking mechanism; The locking mechanism is arranged on the satellite body; One end of the clamping rod is connected to the outermost substrate of the foldable solar wing, and the other end of the clamping rod passes through the other substrates of the foldable solar wing and cooperates with the locking mechanism; The locking mechanism is used to releasably lock the clamping rod to lock the foldable solar wing in a folded state; The micro-nano satellite also includes a clamping cover, a clamping spring and a pre-tightening nut, wherein the clamping cover is fixed to the outermost substrate of the foldable solar wing, the clamping rod passes through the outermost substrate of the foldable solar wing and is threadedly connected to the pre-tightening nut, and the clamping spring is supported between the clamping cover and the pre-tightening nut; The locking mechanism includes a lock body installed on the satellite body, the lock body is provided with a driving assembly and a first clamping piece, one end of the clamping rod is connected to a second clamping piece for cooperating with the first clamping piece; the driving assembly is used to drive the first clamping piece to move to separate from the second clamping piece, thereby releasing the clamping rod.

2. A micro-nano satellite according to claim 1, characterized in that: The locking mechanism further comprises a reset member, a reset opening is provided on the lock body, and the reset member is used to move through the reset opening to move the first locking member, so that the first locking member cooperates with the second locking member.

3. A micro-nano satellite according to claim 2, characterized in that: The driving assembly includes a limiting member and an elastic member, one end of the elastic member is connected to the lock body, and the other end is connected to the first clamping member, the limiting member is movably arranged on the lock body, and the limiting member has a working position and a release position; The limiting member abuts against the first clamping member when in the working position so that the first clamping member and the second clamping member remain in cooperation; the limiting member is separated from the first clamping member when in the releasing position so that the first clamping member is away from the second clamping member under the action of the elastic member.

4. A micro-nano satellite according to claim 3, characterized in that: The first clamping member is connected to the lock body via a rotating shaft, a hook body is formed on the first clamping member, and a groove body adapted to the hook body is formed on the second clamping member.

5. A micro-nano satellite according to claim 3, characterized in that: The limiting member includes a latch pin, and the locking mechanism also includes a pin puller connected to the lock body, and the pin puller is drivingly connected to the latch pin.

6. A micro-nano satellite according to claim 1, characterized in that: A through hole for allowing the pressing rod to pass through is respectively provided on each base plate, and a pressing bushing is provided in the through hole.

7. A micro-nano satellite according to claim 6, characterized in that: A first pad and a second pad are formed at both ends of the compression sleeve. When the foldable solar wing is in a folded state, the first pad and the second pad on two adjacent substrates abut against each other.

8. A micro-nano satellite according to claim 7, characterized in that: Each substrate includes a first surface and a second surface. The first gasket is fixed to the first surface by a first screw, and the second gasket is fixed to the second surface by a second screw. The positions of the first screw and the second screw are staggered.

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