CN218537152U - Solar wing locking and unfolding mechanism - Google Patents

Abstract

The utility model discloses a solar wing locking and unfolding mechanism, which comprises a solar wing substrate, a satellite main body and a satellite hinge, wherein the solar wing substrate is provided with a locking hook; a lock body is arranged on one side of the satellite main body facing the solar wing substrate, the lock body is provided with a clamping groove, and the locking clamping hook is locked in the clamping groove or released from the clamping groove; the satellite hinge comprises a fixed plate connected to the satellite main body, a rotating plate connected to the solar wing substrate and a connecting piece, wherein the rotating plate can be rotatably arranged relative to the fixed plate in an opening and closing mode through the connecting piece. The locking hook of the utility model is arranged on the solar wing substrate, has simple structure, and reduces the area of the solar battery plate; the mechanism is integrally arranged on the surface of the satellite, so that the internal space of the satellite is not occupied, and the space resource is saved for the whole satellite; the mechanism is rigidly locked and unfolded, can be repeatedly used and reduces the cost; the space occupation is small, the ultrathin design enables the folding state of the solar wings to be tightly attached to the satellite main body, and the emission volume of the whole satellite is reduced to the maximum extent.

Description

Solar wing locking and unfolding mechanism

Technical Field

The utility model relates to a satellite technology field, concretely relates to solar wing locking and deployment mechanism.

Background

The solar wing is an important component of the satellite, is a device for converting solar energy into electric energy, and is an electric energy source of the satellite. The solar wing is folded on the surface of the satellite in the satellite launching stage and unfolded after being in orbit, and the vibration environment in the launching process can damage the solar wing, so that the solar wing needs to be locked on the surface of the satellite in the launching stage to prevent damage of vibration.

The conventional solar wing unlocking and unfolding mechanism mainly comprises a pre-tightening rope combined hot knife mode, a compression nut compression mode, a micro hinge combined pin puller mode and the like, and the modes have the defects of complex structure, large occupied volume after compression, untight folding of the solar wing and a satellite main body and the like.

Specifically, the method comprises the following steps: 1. the hot knife mode of the pre-tightening rope has the defects of large volume, complex installation, small pre-tightening force and the like, and because the pre-tightening rope is made of a non-rigid material, the risk of loosing force exists in the use process. 2. The pressing nut mode is large in size and weight, large in occupied solar wing surface area and complex in installation steps, and the pressing mechanism of the pressing nut mode penetrates through the solar wing substrate 200, so that the solar cell piece area is occupied, the pressing step is complex, and the use is inconvenient. 3. The mode of miniature hinge combination pin puller, bulky and weight are big, and the pin puller needs to open a hole in satellite main part surface installation in addition, takes up the great problem of bringing to the internal space of star.

In view of the above, it is desirable to design a thinner and smaller solar wing locking and unfolding mechanism.

SUMMERY OF THE UTILITY MODEL

The utility model aims to solve the technical problem that there is the great problem of volume in present solar wing locking and deployment mechanism.

In order to solve the technical problem, the utility model provides a solar wing locking and deployment mechanism, include:

a solar wing locking and deployment mechanism, comprising:

the solar wing substrate is provided with a locking hook;

the locking hook is locked in the clamping groove or released from the clamping groove; and the number of the first and second groups,

the satellite hinge comprises a fixed plate connected with the satellite main body, a rotating plate connected with the solar wing substrate 200 and a connecting piece, wherein the rotating plate is rotatably arranged relative to the fixed plate through the connecting piece in an opening and closing manner.

In another preferred embodiment, the connecting member includes a rotating shaft and a hinge spring, the rotating shaft is disposed through the fixed plate and the rotating plate, the hinge spring is sleeved on the rotating shaft and is provided with a first foot end and a second foot end, the first foot end is limited on the fixed plate, and the second foot end is limited on the rotating plate.

Further, in the above embodiment, the fixing plate includes a strip-shaped first plate and two first bosses, first mounting holes for connecting the satellite main body are provided at two ends of the first plate, the first bosses are protruded along a length direction of the first plate, each of the first bosses is provided with a coaxial first through hole, and the rotating shaft penetrates through the first through holes.

Further, in the above embodiment, the rotating plate includes a second plate body and two second bosses, the second plate body is provided with a second mounting hole for connecting the solar wing substrate, the second bosses are convexly provided on the second plate body, each of the second bosses is provided with a coaxial second through hole, and the rotating shaft passes through the second through hole.

In another preferred embodiment, the lock body is rectangular, and the thickness of the lock body is smaller than the distance between the fixed plate and the rotating plate in the parallel state.

In another preferred embodiment, the lock body is provided with a working cavity mutually independent of the clamping groove, a locking piece which can be controllably slidably arranged is arranged in the working cavity, the locking piece comprises a pin puller, and the pin puller penetrates through the working cavity and is movably clamped with the locking clamping hook, so that the locking clamping hook is locked in the clamping groove or released from the clamping groove.

In another preferred embodiment, the locking member includes:

the first PCB is arranged statically and is arranged at one end far away from the pin puller;

the second PCB is movably arranged and is connected with the pin puller; and the number of the first and second groups,

and the memory alloy wire is connected with the first PCB and the second PCB.

In another preferred embodiment, the locking catch comprises:

the clamping part extends into the clamping groove and is clamped with the pin puller; and the number of the first and second groups,

the inserting part is provided with a mounting hole for connecting the solar wing, and the inserting part is higher than the clamping groove.

In another preferred embodiment, the lock body is provided with ejectors on both sides, which eject against the locking hooks.

In another preferred embodiment, the pin puller comprises:

the working cavity is provided with a through hole to be communicated with the clamping groove, and the pin head is movably arranged in the through hole in a penetrating way; and the number of the first and second groups,

the connecting part is arranged in the working cavity.

According to the technical scheme, the solar wing locking and unfolding mechanism has the advantages and positive effects that: compared with the prior art, the locking hook is arranged on the solar wing substrate, the structure is simple, and the area of the solar cell sheet occupied is reduced; the mechanism is integrally arranged on the surface of the satellite, so that the internal space of the satellite is not occupied, and the space resource is saved for the whole satellite; the mechanism is rigidly locked and unfolded, the unfolding time is controllable, the mechanism can be repeatedly used, and the cost is reduced; the space occupied is small, the folding state of the solar wings is tightly attached to the satellite main body due to the ultrathin design, and the solar wings are integrally arranged on the star surface and do not occupy the space in the star; the ultra-thin characteristic of the locking and unlocking device is fully utilized, the solar wing is tightly attached to the satellite main body, and the emission volume of the whole satellite is reduced to the greatest extent.

Drawings

The accompanying drawings, which are incorporated in and constitute a part of this specification, illustrate embodiments consistent with the invention and together with the description, serve to explain the principles of the invention.

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious for those skilled in the art that other drawings can be obtained according to the drawings without inventive exercise.

Fig. 1 is a schematic structural view of the solar wing substrate according to the present invention when it is unfolded;

fig. 2 is a schematic structural view of the solar wing substrate of the present invention when folded;

fig. 3 is a cross-sectional view of the solar wing substrate of the present invention when folded;

fig. 4 is a schematic view of the present invention when the cover is opened;

fig. 5 is a schematic view of the housing of the present invention when the guide cover is opened;

fig. 6 is a schematic view of a base of the present invention;

fig. 7 is a schematic structural view of a position limiting member according to the present invention;

fig. 8 is a schematic structural view of the connecting member of the present invention;

FIG. 9 is a schematic structural view of the pin puller of the present invention;

fig. 10 is a schematic structural view of the locking hook of the present invention inserted into the locking slot of the lock body;

fig. 11 is a schematic structural view of the locking hook popping out of the lock body slot of the present invention;

fig. 12 is a cross-sectional view of the locking hook of the present invention inserted into the locking slot of the lock body;

fig. 13 is a schematic view of the internal structure of the lock body of the present invention;

fig. 14 is a schematic structural view of the lock body lifting guide rail cover of the present invention;

fig. 15 is a schematic structural view of a base of the lock body of the present invention;

fig. 16 is a schematic structural view of a limiting member of the lock body of the present invention;

fig. 17 is a schematic structural view of the locking hook of the present invention;

fig. 18 is a schematic structural view of the pin puller of the present invention.

Note that: the corresponding relationship between the components and the reference numerals in the figures is as follows:

a satellite body 100;

a solar wing substrate 200;

the satellite hinge comprises a satellite hinge 300, a fixing plate 310, an installation body 3101, a connecting body 3102, a first installation hole 311, a first boss 312, a first through hole 3121, a first limit hole 313, a limit table 314, a first groove 315, a rotating plate 320, a second installation hole 321, a second boss 322, a second through hole 3221, a second limit hole 323, a second groove 324, a rotating shaft 330, a buckling groove 331, a hinge spring 340, a first foot end 341 and a second foot end 342;

the locking and unlocking device 400, the lock body 410, the working cavity 4101, the slot 4102, the boss 4103, the adjusting hole 41031, the adjusting screw 41032, the base 4104, the cover 4105, the wire guide 41051, the limit piece 411, the limit piece 4111, the slide rail 4112, the limit table 4113, the guide rail cover 412, the limit piece 4121, the eject piece 413, the locking hook 420, the clamping part 421, the plug part 422, the mounting hole 4221, the locking piece 430, the pin puller 431, the pin head 4311, the connecting part 4312, the first PCB 432, the second PCB 433, and the memory alloy wire 434.

Detailed Description

In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be clearly and completely described below with reference to the drawings in the embodiments of the present application, and it is obvious that the described embodiments are some embodiments of the present application, but not all embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. The utility model provides a solar wing locking and deployment mechanism has not only simplified the structure, has still reduced whole volume and quality, more is favorable to the technical development of space flight field especially satellite. The invention is described in detail below with reference to the drawings and the detailed description.

In order to overcome the problem of the large size and weight of the solar wing locking and unfolding mechanism in the prior art, referring to fig. 1, 2 and 3, the utility model provides a solar wing locking and unfolding mechanism, which comprises a satellite main body 100, a solar wing base plate 200 and a satellite hinge 300. The solar wing substrate 200 is provided with a locking hook 420. The side of the satellite body 100 facing the solar wing substrate 200 is provided with a lock body 410, the lock body 410 is provided with a slot 4102, and the locking hook 420 is locked in the slot 4102 or released from the slot 4102. The satellite hinge 300 includes a fixed plate 310 connected to the satellite body 100, a rotating plate 320 connected to the solar wing substrate 200, and a connector, and the rotating plate 320 is rotatably provided to be openable and closable with respect to the fixed plate 310 by the connector. Wherein, the lock body 410 and the locking hook 420 both belong to the unlocking device 400.

According to the above technical solution, in the solar wing locking and unfolding mechanism of the present application, the locking hook 420 drives the solar wing substrate 200 to controllably unfold or fold from the satellite main body 100, and the satellite hinge 300 provides a structural basis for the rotation of the solar wing substrate 200. The locking hook 420 and the lock body 410 are separated to be in an unfolded state, and the locking hook is locked in the locking groove 4102 of the lock body 410 to be in a folded state. The locking hook 420 is arranged on the solar wing substrate 200, so that the structure is simple, and the area of the solar cell sheet occupied is reduced; the mechanism is integrally arranged on the surface of the satellite, so that the internal space of the satellite is not occupied, and the space resource is saved for the whole satellite; the mechanism is rigidly locked and unfolded, the unfolding time is controllable, the mechanism can be repeatedly used, and the cost is reduced; the satellite hinge 300 comprises a fixed plate 310 and a rotating plate 320, the plate-shaped structure enables the occupied space of the satellite hinge 300 to be smaller, the ultrathin design enables the folded state of the solar wings to be tightly attached to the satellite main body 100, and the whole satellite hinge is arranged on the star surface and does not occupy the space in the star; the ultra-thin characteristic of the locking and unlocking device is fully utilized, the solar wing substrate 200 is tightly attached to the satellite main body 100, and the emission volume of the whole satellite is reduced to the greatest extent.

The specific structure of the satellite hinge 300 is described below:

referring to fig. 4, in another preferred embodiment, the connecting member includes a rotating shaft 330 and a hinge spring 340, the rotating shaft 330 penetrates through the fixing plate 310 and the rotating plate 320, the hinge spring 340 has a first foot end 341 and a second foot end 342, the first foot end 341 is limited on the fixing plate 310, the second foot end 342 is limited on the rotating plate 320, and the rotating plate 320 is rotatably disposed relative to the fixing plate 310. The rotating shaft 330 is driven by a power source such as a motor, and the hinge spring 340 is used for limiting the rotating position of the rotating plate 320, so that the rotating angle is prevented from being too large, and the rotating speed of the rotating plate 320 is also limited. The first leg end 341 passes through the first position-limiting hole 313 of the fixing plate 310, and the second leg end 342 passes through the second position-limiting hole 323 of the rotating plate 320.

In a preferred embodiment, the fixing plate 310 includes a first plate body in a bar shape and two first bosses 312. Wherein, both ends of the first plate body are provided with first mounting holes 311 for connecting the satellite main body 100, the satellite main body 100 is connected to both ends of the first plate body by connecting elements such as pins, and the first mounting holes 311 are preferably arranged in pairs. The first bosses 312 are protruded along the length direction of the first plate, each of the first bosses 312 is provided with a coaxial first through hole 3121, and the rotating shaft 330 passes through the first through hole 3121. Therefore, the rotating shaft 330 and the first plate body are arranged in parallel, the distance between the rotating shaft 330 and the first plate body is achieved by adjusting the position of the first through hole 3121, the penetrating direction of the rotating shaft 330 is perpendicular to the mounting direction of the first mounting hole 311, the assembling direction is crossed, and the looseness is not easy to occur.

Referring to fig. 5 and 6, in the above embodiment, the first plate body includes a connecting body 3102 and a mounting body 3101, the mounting body 3101 is disposed at both ends of the connecting body 3102, the first mounting hole 311 is disposed on the mounting body 3101, the first boss 312 is disposed on the connecting body 3102, and the thickness of the connecting body 3102 is greater than that of the mounting body 3101. The first plate body is provided with two parts with different functions, the thickness of the mounting body 3101 is smaller, the length of a pin used for mounting can be reduced, the mounting tightness is improved, the connecting body 3102 is used for assembling a connecting piece, and the rotating shaft 330 and the hinge spring 340 of the connecting piece are movably arranged, so the thickness of the connecting body 3102 is larger for improving the strength.

With continued reference to fig. 5 and 6, or further, in the above embodiment, the side surface of the first plate body is provided with a limiting platform 314, which is movably contacted with the side surface of the rotating plate 320 to limit the rotating angle of the rotating plate 320. The solar wing substrate 200 has a predetermined moving range during the rotation process, and the limiting table 314 is disposed at the limiting position to fit the shape of the side surface of the first plate, so that the limiting accuracy is improved.

Referring to fig. 7, in another preferred embodiment, the rotating plate 320 includes a second plate body and two second bosses 322, the second plate body is provided with a second mounting hole 321 for connecting the solar wing substrate 200, the second bosses 322 are convexly provided on the second plate body, each second boss 322 is provided with a coaxial second through hole 3221, and the rotating shaft 330 passes through the second through hole 3221. The second mounting hole 321 is used for connecting the solar wing substrate 200, and the rotating shaft 330 passes through the second through hole 3221, it is understood that the second through hole 3221 should be adapted to the height of the first through hole 3121 in the previous embodiment, and the first bosses 312 may be respectively disposed at the outer sides of the second bosses 322, or the first bosses 312 and the second bosses 322 may be disposed at intervals, in the embodiment shown in fig. 1, the first bosses 312 are disposed at the outer sides of the second bosses 322, and the rotating shaft 330 passes through the first through hole 3121, the second through hole 3221, and the first through hole 3121 in sequence.

Still referring to fig. 7, in the above embodiment, the second plate body is in a trapezoid shape, the second mounting holes 311 are also arranged in a trapezoid shape, and the second bosses 322 are sequentially arranged along the long side of the trapezoid. The shape of the second plate body is related to the structure and shape of the solar wing substrate 200, and the number of the first mounting holes 311 is four, so that the mounting strength can be improved by multi-point mounting. The second bosses 322 are disposed along the long sides of the second mounting holes 321, so that the rotating plate 320 and the fixing plate 310 are more compact in structure on the premise of ensuring the stability of the axis of the rotating shaft 330.

Referring to fig. 4 and 9, in another preferred embodiment, the wrap spring 340 includes a pair of left-hand wrap springs and a pair of right-hand wrap springs. The hinge springs 340 are arranged in pairs and are respectively arranged as a left-handed hinge spring and a right-handed hinge spring, so that the force on two sides can be balanced, and the whole stress balance is kept. Specifically, the left-handed and right-handed hinges are symmetrically disposed along the center of the rotation shaft 330.

Referring to fig. 6, in another preferred embodiment, a side of the fixing plate 310 facing away from the rotating shaft 330 is provided with a first groove 315, and the first leg end 341 penetrates the fixing plate 310 and enters the first groove 315. The first leg end 341 is limited on the fixing plate 310, and the first groove 315 can limit the first leg end 341, so as to prevent the first leg end 341 from sliding freely, provide a space for deformation of the first leg end 341, and prevent the hinge spring 340 from interfering with an adjacent component.

Referring to fig. 7, in another preferred embodiment, the side of the rotating plate 320 facing away from the rotating shaft 330 is provided with a second groove 324, and the second foot end 342 passes through the rotating plate 320 and enters the second groove 324. The second foot 342 is limited on the rotating plate 320, the second groove 324 has the same function as the first groove 315, and the first groove 315 is matched with the second groove 324 in position.

Referring to fig. 8, in another preferred embodiment, both ends of the rotating shaft 330 are provided with catching grooves 331 adapted to catching means to limit the rotation angle of the rotating shaft 330. Since the angle of the solar wing substrate 200 to be unfolded needs to be precisely controlled, in addition to the limit table 314 for positioning at the limit position, a fastening device needs to be disposed on the rotating shaft 330, so that the solar wing substrate 200 is kept relatively stationary at a predetermined angle, and therefore, a fastening groove 331 needs to be reserved on the rotating shaft 330 to install the fastening device.

The unlocking apparatus 400 includes a lock body 410 and a locking hook 420, and the structure of the unlocking apparatus 400 is described as follows:

referring to fig. 10 and 11, in another preferred embodiment, the lock body 410 has a rectangular parallelepiped shape, and the thickness of the lock body 410 is smaller than the distance between the fixed plate 310 and the rotating plate 320 in the parallel state. The lock body 410 adopts a brand-new cuboid structure, the use thickness is controlled within 9mm, the solar wing substrate 200 is attached to the satellite main body 100 more closely, and the emission volume of the whole satellite is effectively reduced. Due to the smaller volume, the system can adapt to more scenes and has less application limitation.

Referring to fig. 12, in another preferred embodiment, the lock body 410 is provided with a working chamber 4101 independent from the card slot 4102, a controllable slidably-arranged locking member 430 is arranged in the working chamber 4101, the locking member 430 is controllably slidably arranged in the working chamber 4101, the locking member 430 comprises a pin puller 431, and the pin puller 431 passes through the working chamber 4101 and is movably engaged with the locking hook 420, so that the locking hook 420 is locked in the card slot 4102 or released from the card slot 4102. The locking member 430 is disposed in the working chamber 4101 of the lock body 410, the locking member 430 is slidably disposed by itself, the locking hook 420 is locked or released by the linear sliding of the locking member 430, and the movable state of the locking member 430 is completely fitted to the rectangular hole space of the lock body 410, thereby making full use of the horizontal space.

Referring to fig. 13, in another preferred embodiment, the lock body 410 includes a base 4104 and a cover 4105, the base 4104 and the cover 4105 are fixed by bolts and form a working chamber 4101, the cover 4105 is provided with a wire guide 41051, and a cable is connected to the locking member 430 through the wire guide 41051. The base 4104 and the lock body 410 are configured to facilitate assembly of the lock body 410. Specifically, when viewing the figures, the base 4104 is configured to have three sides that close one side of the opening to facilitate installation of the locking member 430, and the cover 4105 is configured to close one side of the opening of the base 4104 to complete the closure of the lock body 410. In addition, the mounting screws of the base 4104 and the cover 4105 are fixed in two perpendicular directions, ensuring that the lock body 410 does not become loose. The cover 4105 is made of metal to protect internal components and fix the locking member 430 inside, and the cover 4105 and the base 4104 are fixed to each other. The base 4104 is made of metal and has four mounting ears designed to engage the top cover and hold the locking member 430 in place on either side of the structure.

Referring to fig. 14, in another preferred embodiment, the lock body 410 is provided with the pop-up member 4115 at both sides thereof, and the pop-up member 4115 abuts against the locking hook 420. The ejecting member 4115 tightly pushes the locking hook 420 in the working process to pre-tighten the solar wing substrate 200 during locking, so as to prevent the solar wing substrate 200 from being damaged due to vibration. When the locking hook 420 needs to be released, the pin puller 431 is in contact with the locking hook 420 for limiting, and then the locking hook 420 is ejected out by the elastic force of the ejection member 4115, so that smooth unlocking of the solar wing substrate 200 is ensured, the pretightening force is controllable, and the ejection is assisted, so that the unlocking is more reliable. Specifically, a spring or other similar element is attached to the bottom of the eject member 4115. The ejection members 4115 are symmetrically disposed on both sides, so that the locking hooks 420 are uniformly stressed in the ejection direction, and the locking hooks 420 are prevented from being jammed. Specifically, the base 4104 is provided with two rectangular ears with a hole in the center to house the ejection member 4115.

With continued reference to fig. 14, the locking member 430 includes a first PCB 432, a second PCB 433, and a memory alloy wire 434. The first PCB 432 is statically disposed and is disposed at an end away from the pin puller 431. The second PCB 433 is movably disposed and connected to the pin puller 431. The memory alloy wire 434 is a titanium-nickel alloy wire, and can be an alloy material capable of automatically restoring the self-deformation to the original shape at a specific temperature. The memory alloy wire 434 connects the first PCB 432 and the second PCB 433. The memory alloy wire 434 deforms under the control of current, and the second PCB 433 moves under the deformation, so that a pulling force is generated on the pin puller 431, and the pin puller 431 is movably connected with the locking hook 420 in a clamping manner. The traditional column pin puller 431 is threaded only after the PCB is installed, so that the space is small and the operation is difficult. And the utility model discloses can carry out the PCB earlier when the assembly and wear the silk, assembling, greatly reduced the threading technology degree of difficulty, simple structure is compact, and the assembly degree of difficulty is low, has also guaranteed product uniformity and reliability.

Referring to fig. 14, fig. 15 and fig. 16, further, in the above embodiment, a boss 4103 is disposed in the working chamber 4101, a limiting member 411 is disposed in the working chamber 4101, and the limiting member 411 is provided with a limiting member 4111, a sliding rail 4112 and a limiting table 4113. The stopper 4111 abuts against the boss 4103. The boss 4103 provides a stop and also provides a location for securing the lock body 410 itself. The second PCB 433 is slidably disposed in the slide rail 4112. The slide rail 4112 is made of a non-metal insulating material and functions as a guide rail for the second PCB 433. When the device is powered on, the memory alloy wire 434 deforms and contracts, the second PCB 433 moves along the sliding rail 4112, and then the pin puller 431 is driven to move, so that the locking hook 420 is pulled out of the clamping groove 4102, and then the locking hook 420 is unlocked. Spacing platform 4113 is located the both sides of slide rail 4112, and first PCB board 432 is arranged in between spacing platform 4113 and lock body 410, and spacing platform 4113 and lock body 410 have limited the installation space of first PCB board 432, adjust specific position as required when the installation.

Referring to fig. 14, further, in the above embodiment, a side of the limiting block 4111 close to the pin puller 431 is provided with a pre-tightening member, the pre-tightening member abuts against the pin puller 431, and the memory alloy wire 434 generates a pulling force after being powered on, so as to overcome the pressure of the pre-tightening member and pull the pin puller 431. Specifically, the pretensioning element is a spring, two holes are designed in the front end of the limiting block 4111 and used for installing a pretensioning spring, and the pretensioning spring pretensions the pin puller 431, so that the device is automatically locked in a non-unlocking state.

With reference to fig. 14, or, further, in the above embodiment, the limiting member 411 further includes a rail cover 412, the rail cover 412 is provided with a plurality of limiting portions 4121, and each limiting portion 4121 is pressed against the pin puller 431 and the first PCB 432, respectively. The guide rail cover 412 is made of a non-metal insulating material, and the first PCB 432 and the second PCB 433 fixing the memory alloy wire 434 and the memory alloy wire 434 are pressed by the limiting portion 4121 to limit the locking member 430.

Referring to fig. 15, or, further, in the above embodiment, an adjusting hole 41031 is disposed on a side of the boss 4103 facing the second PCB 433, the adjusting screw 41032 is screwed into the adjusting hole 41031, and the adjusting screw 41032 abuts against the second PCB 433, so as to adjust the initial distance between the first PCB 432 and the second PCB 433 according to the screwing depth of the adjusting screw 41032. The length of the memory alloy wire 434 of the existing pin puller 431 is fixed after the first assembly, but the device is aged and abraded due to multiple times of use in the using process, so that the pretightening force can not be recovered, the device is scrapped, the assembling difficulty of the product is increased, and the pretightening force is difficult to control and the consistency of the pretightening force is ensured. And the utility model relates to a pretightning force dynamic adjustment device, can adjust the pretightning force of pin puller 431 at any time, adjust the initial distance of first PCB board 432 and second PCB board 433 through the length that changes adjusting screw 41032 and stretch out to control pin puller 31's pretightning force, this problem of having avoided the device testing process to appear tired power of letting out owing to long-time repetitious usage has prolonged product life, also further reduces the assembly degree of difficulty, has increased the accommodation of product.

Referring to fig. 17, in another preferred embodiment, the locking hook 420 includes a hooking portion 421 and a mating portion 422. The engaging portion 421 extends into the engaging groove 4102, and engages with the pin remover 431. The plug part 422 is provided with a mounting hole 4221 for connecting the solar wing substrate 200, and the plug part 422 is higher than the card slot 4102. The locking hook 420 is made of metal, the top surface of the locking hook is connected with and fixed to the solar wing substrate 200, and in a locking state, the pin puller 431 extends into the slot 4102 and abuts against the plug-in part 422, so that the solar wing substrate 200 and the satellite body 100 are locked and pre-tightened. When the pin puller 431 is pulled out, the locking hook 420 can be freely ejected, so that the solar wing substrate 200 is unlocked and unfolded. Specifically, the insertion part 422 is provided with a non-penetrating circular groove or a penetrating circular hole, so that the pin puller 431 can be conveniently inserted.

Referring to fig. 18, in another preferred embodiment, the pin puller 431 includes a pin head 4311 and a connection portion 4312. The working chamber 4101 is provided with a through hole to communicate with the engaging groove 4102, and the pin head 4311 is movably inserted into the through hole. The connection portion 4312 is provided in the working chamber 4101. The pin puller 431 is made of metal, one end of the pin puller extends out of the pin head 4311 to be matched and locked with the inserting part 422 of the locking hook 420, the connecting part 4312 and the second PCB 433 are fixedly locked through a pin, and when the device is powered on, the second PCB 433 can be pulled by the memory alloy wire 434 to drive the pin head 4311 to be pulled out of the clamping groove 4102, so that unlocking is achieved.

It is noted that, in this document, relational terms such as "first" and "second," and the like, are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Also, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising a … …" does not exclude the presence of another identical element in a process, method, article, or apparatus that comprises the element.

The foregoing are merely exemplary embodiments of the present invention, which enable those skilled in the art to understand or practice the present invention. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the invention. Thus, the present invention is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims (10)

1. A solar wing locking and deployment mechanism, comprising:

the solar wing substrate is provided with a locking hook;

the locking hook is locked in the clamping groove or released from the clamping groove; and the number of the first and second groups,

the satellite hinge comprises a fixed plate connected with the satellite main body, a rotating plate connected with the solar wing substrate and a connecting piece, wherein the rotating plate is rotatably arranged relative to the fixed plate through the connecting piece in an opening and closing mode.

2. The solar wing locking and unfolding apparatus as claimed in claim 1, wherein said connecting member comprises a rotating shaft and a hinge spring, said rotating shaft is disposed through said fixed plate and said rotating plate, said hinge spring is sleeved on said rotating shaft and has a first foot end and a second foot end, said first foot end is limited on said fixed plate, said second foot end is limited on said rotating plate.

3. The solar wing locking and unfolding mechanism according to claim 2, wherein the fixing plate comprises a strip-shaped first plate and two first bosses, first mounting holes are formed at two ends of the first plate and used for connecting the satellite main body, the first bosses are arranged in a protruding manner along the length direction of the first plate, each first boss is provided with a coaxial first through hole, and the rotating shaft penetrates through the first through holes.

4. The solar wing locking and deployment mechanism of claim 2, wherein said rotating plate comprises a second plate body and two second bosses, said second plate body having a second mounting hole for connecting said solar wing base plate, said second bosses being protrudingly provided on said second plate body, each of said second bosses having a second coaxial through hole, said rotating shaft passing through said second through hole.

5. The solar wing locking and deployment mechanism of claim 1, wherein said lock body is rectangular in shape, said lock body having a thickness less than the distance between said fixed plate and said rotating plate in a parallel configuration.

6. The solar wing locking and deployment mechanism of claim 1, wherein said lock body has a working chamber independent of said slot, said working chamber having a locking member slidably disposed therein, said locking member including a pin puller, said pin puller passing through said working chamber and being movably engaged with said locking hook to lock or unlock said locking hook in or from said slot.

7. The solar wing lock and deployment mechanism of claim 6, wherein the locking member comprises:

the first PCB is arranged in a static manner and is arranged at one end far away from the pin puller;

the second PCB is movably arranged and is connected with the pin puller; and the number of the first and second groups,

and the memory alloy wire is connected with the first PCB and the second PCB.

8. The solar wing locking and deployment mechanism of claim 6, wherein the locking catch comprises:

the clamping part extends into the clamping groove and is clamped with the pin puller; and the number of the first and second groups,

the inserting part is provided with a mounting hole used for connecting the solar wing, and the inserting part is higher than the clamping groove.

9. The solar wing locking and deployment mechanism of claim 1, wherein said lock body is provided with ejectors on both sides, said ejectors bearing against said locking catches.

10. The solar wing locking and deployment mechanism of claim 6, wherein the pin puller comprises:

the working cavity is provided with a through hole to be communicated with the clamping groove, and the pin head is movably arranged in the through hole in a penetrating way; and the number of the first and second groups,

the connecting part is arranged in the working cavity.

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