CN111038742B

CN111038742B - A folding and unfolding mechanism, solar wing and micro-nano satellite

Info

Publication number: CN111038742B
Application number: CN201911424436.2A
Authority: CN
Inventors: 何宁泊; 高恩宇; 阎凯; 赵研博
Original assignee: Shaanxi Guoyu Space Technology Co Ltd
Current assignee: Beijing Weina Starry Sky Technology Co ltd
Priority date: 2019-12-31
Filing date: 2019-12-31
Publication date: 2025-03-04
Anticipated expiration: 2039-12-31
Also published as: CN111038742A

Abstract

The present application relates to the field of aerospace equipment technology, and specifically, to a folding and unfolding mechanism, a solar wing, and a micro-nano satellite. The folding and unfolding mechanism is used to connect the substrates of the solar wing and the satellite body of the micro-nano satellite. The folding and unfolding mechanism includes a first body, a second body; a rotating shaft, and the first body and the second body are pivotally connected by the rotating shaft; an elastic support member, which is used to drive the first body and the second body to rotate from a folded state to an unfolded state; a damping assembly, which is used to generate damping when the first body and the second body rotate, and the magnitude of the damping is adjustable. The folding and unfolding mechanism provided by the present application can adjust the magnitude of its unfolding force so that the required unfolding force is applied to different parts of the solar wing, so that the substrates of the solar wing are synchronously unfolded at the same angular velocity, thereby solving the problem that the existing folding and unfolding mechanism cannot unfold the solar wing in an orderly manner and reducing the adverse effects of the unfolding action of the solar wing on the satellite attitude.

Description

Folding and unfolding mechanism, solar wing and micro-nano satellite

Technical Field

The application relates to the technical field of aerospace equipment, in particular to a folding and unfolding mechanism, a solar wing and a micro-nano satellite.

Background

The existing solar wing folding and unfolding mechanism for large satellites is mainly connected with all the base plates through hinges, and the motor is used for driving a rope linkage system to enable all the base plates of the solar wings to be gradually unfolded to a specified position in an orderly mode. The micro-nano satellite is limited by the size of the micro-nano satellite and the energy source on the satellite, and the folding and unfolding movement is not easy to be carried out by adopting a motor-driven rope linkage system, so that the folding solar wing of the micro-nano satellite is generally connected with each substrate by adopting a rigid hinge, the unfolding force is provided by utilizing the compression energy of a self spring or a memory material, the unfolding action and locking are completed, the solar wing of the micro-nano satellite is mainly unfolded in disorder, the sequence of the sequential unfolding of a plurality of substrates cannot be predicted, the solar wing can be vibrated abnormally for a plurality of times by unfolding the plurality of substrates in a disorder mode, the satellite gesture is further adversely affected, and the functions and performances of the satellite are possibly damaged.

Disclosure of Invention

The application aims to provide a folding and unfolding mechanism and a micro-nano satellite solar wing, which are used for solving the problem that the folding and unfolding mechanism in the prior art cannot enable the solar wing to be unfolded orderly.

Embodiments of the present application are implemented as follows:

in a first aspect, embodiments of the present application provide a folding mechanism, including:

a first body and a second body;

the first body and the second body are pivotally connected through the rotating shaft;

an elastic support for driving the first body and the second body to rotate from a folded state to an unfolded state;

and the damping component is used for generating damping when the first body and the second body rotate, and the damping is adjustable in size.

Due to the material characteristics of the torsion springs and the memory materials and the specifications of the torsion springs or the memory materials which can be purchased in the market, the torsion springs or the memory materials with different specifications are selected to be configured to a folding and unfolding mechanism in a conventional setting mode, and finally, the obtained unfolding force is always a certain fixed value. That is, when a torsion spring of one specification is selected, the deployment force obtained by the folding mechanism has been determined as the supporting force that can be provided by the torsion spring, and since the specifications of torsion springs on the market are often established, it is difficult to obtain the required deployment force when the required deployment force does not coincide with the supporting force that can be provided by torsion springs of these established specifications. According to the folding and unfolding mechanism provided by the application, the first body and the second body can be relatively unfolded or relatively close to each other around the rotating shaft, the elastic supporting piece of the folding and unfolding mechanism is used for providing supporting force for relatively unfolding the first body and the second body, the damping component is used for generating damping when the first body and the second body are relatively unfolded, the damping is used for resisting the supporting force provided by the elastic supporting piece, and a part of supporting force after being counteracted by the damping is the unfolding force finally output by the folding and unfolding mechanism. The damping assembly is configured such that the magnitude of the damping is adjustable, and thus the magnitude of the deployment force.

The folding and unfolding mechanism provided by the application can adjust the unfolding force of the folding and unfolding mechanism so as to apply needed unfolding force on different parts of the solar wing, and solves the problem that the existing folding and unfolding mechanism can not enable the solar wing to be unfolded orderly.

Optionally, in an embodiment of the present application, a first friction surface is provided on the first body, a second friction surface is provided on the second body, and the damping assembly includes a damping portion, a first adjusting member and a second adjusting member, where the damping portion is respectively matched with the first friction surface and the second friction surface to generate damping, the first adjusting member is used for adjusting pressure between the damping portion and the first friction surface, and the second adjusting member is used for adjusting pressure between the damping portion and the second friction surface.

The application can generate friction damping with the damping part once the first body or the second body rotates by arranging the damping part which is respectively in friction fit with the first body and the second body, adjusts the unfolding force, is sensitive and effective in adjustment, and is convenient to adjust and easy to control by adjusting the pressure of the damping part and the first friction surface or the second friction surface to adjust the corresponding friction damping.

Optionally, in an embodiment of the present application, the damping part includes a damping washer sleeved on the rotating shaft, an outer circumferential surface of the damping washer is matched with the first friction surface, and one end surface of the damping washer is matched with the second friction surface.

By arranging the damping part as the damping gasket, the outer peripheral surface of the damping gasket is matched with the first friction surface, one end surface of the damping gasket is matched with the second friction surface, the position of the damping gasket is unchanged no matter how the first body and the second body rotate around the rotating shaft, and the positions of the outer peripheral surface and the end surface of the damping gasket are stable so as to be matched with the first friction surface and the second friction surface stably to generate damping.

Optionally, in one embodiment of the present application, the first body includes a first base and a clip, the first base and the second body are pivotally connected through the rotating shaft, the clip is connected to the first base, the clip is disposed on an outer peripheral surface of the damping washer, the first friction surface is an inner wall of the clip, and two ends of an opening of the clip are connected through the first adjusting member.

The first body is arranged to be the first base and the clamp, the clamp is arranged on the outer peripheral surface of the damping washer in a hooping mode, the clamp, the damping washer and the rotating shaft are coaxial, the clamp and the outer peripheral surface of the damping washer are always kept in contact no matter how the first body rotates around the rotating shaft, stable damping is guaranteed to be generated between the first body and the damping washer, the opening size of the clamp is adjusted through the first adjusting piece, pressure between the clamp and the damping washer is changed, and therefore size adjustment of damping is achieved.

Optionally, in an embodiment of the present application, the first adjusting member is an adjusting screw, and the clip is connected to the first base by the adjusting screw.

Through setting up first regulating part as adjusting screw to with the clamp through adjusting screw connection on the body, know easily, at the opening part, one side of clamp supports at first basal portion, and the another side of clamp supports on adjusting screw's nut, twists adjusting screw just can realize the opening size adjustment of clamp, and the mode of this kind of stepless regulation makes the regulation precision of spreading force high, obtains required spreading force easily, and adjusts simple structure reliably.

Optionally, in an embodiment of the present application, a thread is formed at one end of the rotating shaft, the second adjusting member is an adjusting nut matched with the thread of the rotating shaft, and the adjusting nut and the second friction surface are respectively located at two ends of the damping washer.

Through setting up the second regulating part as adjusting nut, rotate adjusting nut can adjust the pressure between damping washer and the second friction surface, the stepless damping size of adjusting between damping washer and the second friction surface, and adjusting structure is simple reliable, the regulation precision is high.

Optionally, in an embodiment of the present application, a shaft sleeve is formed on the second body, the rotating shaft is penetrating through the shaft sleeve, the elastic supporting piece is a torsion spring sleeved on the shaft sleeve, and the second friction surface is an end surface of the shaft sleeve.

The torsion spring and the second friction surface are arranged on the shaft sleeve through the shaft sleeve formed on the second body, so that the whole structure is compact, the size is small, the torsion spring can be applied to smaller satellites, and the torsion spring and the rotating shaft are not easy to interfere when the first body and the second body rotate, and the supporting force is not influenced.

Optionally, in an embodiment of the present application, the folding mechanism further includes a positioning assembly for locking the first body and the second body in the folded state.

In the prior art, the final unfolding position of the folding mechanism sometimes depends on a torsion spring or a memory material, when the torsion spring is unfolded to the final position, or when the memory material is unfolded to the final position, the folding mechanism reaches the final unfolding position, and the manner makes each substrate unstable after the solar wing is unfolded. The final unfolding position of the folding and unfolding mechanism is locked by the positioning assembly, so that the stability is improved.

Alternatively, in one embodiment of the present application, the positioning assembly includes a locking pin and a compression spring, the second body has a receiving hole formed therein to receive the locking pin and the compression spring, the first body has a pin hole formed therein, the locking pin is aligned with the pin hole when the first body and the second body are in the unfolded state, and the compression spring drives one end of the locking pin to be inserted into the pin hole.

Optionally, in an embodiment of the present application, the positioning assembly further includes a reset lever detachably connected to the locking pin, and a viewing port is provided on the second body, and the viewing port is used for allowing the reset lever to move through so as to pull the locking pin out of the pin hole.

Through setting up viewing aperture and reset lever, be convenient for with folding mechanism reset to the folded condition.

Optionally, in an embodiment of the present application, the first body is formed with a first limiting surface, the second body is formed with a second limiting surface, and when the first body and the second body are in a deployed state, the first limiting surface and the second limiting surface are in contact to limit a deployment angle of the first body and the second body.

The first limiting surface and the second limiting surface are matched to limit the maximum unfolding angle of the folding and unfolding mechanism, so that the folding and unfolding mechanism is prevented from being excessively unfolded.

Optionally, in an embodiment of the present application, the folding and unfolding mechanism further includes an in-place switch, where the in-place switch is installed on the first body, and when the first body and the second body relatively rotate to the unfolded state, the second body triggers the in-place switch.

By setting the in-place switch, the ground is informed of the information of the expansion in place.

Optionally, in an embodiment of the present application, the folding mechanism is used for connecting a first substrate and a second substrate, a first mounting hole for connecting the first substrate is formed on the first body, and a second mounting hole for connecting the second substrate is formed on the second body, and positions of the first mounting hole and the second mounting hole are staggered relatively.

The first base body and the second base body can be base plates of solar wings or satellite main bodies, when the folding and unfolding mechanism is applied to other equipment, the first base body and the second base body can be of other structures, through staggering the mounting holes in the first base body and the second base body, when the folding and unfolding mechanism is folded, anchoring pieces or connecting pieces arranged in the mounting holes are not interfered with each other, and the space between the first base body and the second base body can be folded to be smaller.

In a second aspect, an embodiment of the present application provides a solar wing, which includes at least two substrates and the aforementioned folding mechanism, and two adjacent substrates are connected by the folding mechanism.

The folding and unfolding mechanism is used for connecting the base plates of the solar wings, so that required unfolding forces are conveniently applied to different positions of the solar wings, the problem that the solar wings cannot be orderly unfolded by the existing folding and unfolding mechanism is solved, corresponding unfolding forces can be obtained for each base plate of the solar wings and different positions of each base plate, the rotating angular speeds of the base plates are consistent, and orderly unfolding of each base plate is ensured.

In a third aspect, an embodiment of the present application provides a micro/nano satellite, which includes a satellite main body and the solar wing, where one substrate of the solar wing is connected to the satellite main body through the folding mechanism.

In general, when the solar wings are unfolded out of order, each substrate generates vibration when being unfolded in place, the vibration is inevitably transmitted to a satellite main body connected with the solar wings, the pressure of the attitude and orbit control subsystem is obviously increased, and the solar cells on the substrates are also adversely affected.

By using the solar wing, the solar wing and the satellite main body are connected by using the folding and unfolding mechanisms, the unfolding force of each folding and unfolding mechanism is adjusted, the unfolding force of each folding and unfolding mechanism is matched with the unfolding force required by the position of each folding and unfolding mechanism, so that each substrate is synchronously unfolded, the unfolding time of each substrate in place is consistent, the satellite main body only receives once vibration, and the influence of the unfolding action of the solar wing on the posture of the satellite main body is reduced to be as small as possible.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are needed in the embodiments will be briefly described below, it being understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and other related drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a view of a folded state of a solar wing provided by an embodiment of the present application;

FIG. 2 is a view showing an unfolded state of a solar wing according to an embodiment of the present application;

FIG. 3 is a view illustrating a folded state of the folding mechanism according to the embodiment of the present application;

fig. 4 is a folding state diagram of the folding mechanism according to the embodiment of the present application under another view angle;

FIG. 5 is a view showing an unfolded state of the folding mechanism according to the embodiment of the present application;

FIG. 6 is a view showing an unfolded state of the folding mechanism according to the embodiment of the present application at another view angle;

FIG. 7 is a cross-sectional view of a folding and unfolding mechanism according to an embodiment of the present application;

FIG. 8 is an exploded view of a folding and unfolding mechanism according to an embodiment of the present application;

fig. 9 is a schematic structural diagram of a first body according to an embodiment of the present application under a view angle;

fig. 10 is a schematic structural diagram of the first body according to the embodiment of the present application under another view angle;

Fig. 11 is a schematic structural diagram of a first body according to an embodiment of the present application under a view angle;

fig. 12 is a schematic structural diagram of the first body according to another embodiment of the present application.

The icons are 10-satellite body, 20-solar wing, 21-first base plate, 22-second base plate, 23-third base plate, 30-folding mechanism, 40-pressing rod, 50-locking mechanism, 100-first body, 110-first base, 111-first mounting face, 112-first supporting face, 120-first connecting portion, 121-pin hole, 122-first limiting face, 130-clamp, 131-first friction face, 200-second body, 210-second base, 211-second mounting face, 212-second supporting face, 220-second connecting portion, 221-containing hole, 222-second limiting face, 230-sleeve, 231-second friction face, 240-limiting cover, 241-viewing port, 300-rotating shaft, 400-elastic support, 500-damping assembly, 510-damping washer, 520-first adjusting member, 530-second adjusting member, 600-positioning assembly, 610-locking pin, 620-compression spring, 700-in-position switch.

Detailed Description

For the purpose of making the objects, technical solutions and advantages of the embodiments of the present application more apparent, the technical solutions of the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present application, and it is apparent that the described embodiments are some embodiments of the present application, but not all embodiments of the present application. The components of the embodiments of the present application generally described and illustrated in the figures herein may be arranged and designed in a wide variety of different configurations.

Thus, the following detailed description of the embodiments of the application, as presented in the figures, is not intended to limit the scope of the application, as claimed, but is merely representative of selected embodiments of the application. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

It should be noted that like reference numerals and letters refer to like items in the following figures, and thus once an item is defined in one figure, no further definition or explanation thereof is necessary in the following figures.

In the description of the present application, it should be noted that, if the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", etc. indicate an azimuth or a positional relationship based on that shown in the drawings, or an azimuth or a positional relationship in which a product of the application is conventionally put in use, it is merely for convenience of describing the present application and simplifying the description, and it is not indicated or implied that the referred device or element must have a specific azimuth, be constructed and operated in a specific azimuth, and thus should not be construed as limiting the present application. Furthermore, the terms "first," "second," and the like in the description of the present application, if any, are used for distinguishing between the descriptions and not necessarily for indicating or implying a relative importance.

Furthermore, the terms "horizontal," "vertical," and the like in the description of the present application, if any, do not denote a requirement that the component be absolutely horizontal or overhang, but rather may be slightly inclined. As "horizontal" merely means that its direction is more horizontal than "vertical", and does not mean that the structure must be perfectly horizontal, but may be slightly inclined.

In the description of the present application, it should also be noted that, unless explicitly stated or limited otherwise, the terms "disposed," "mounted," "connected," and "connected" should be construed broadly, and may be, for example, fixedly connected, detachably connected, integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected through an intermediate medium, or in communication between two elements. The specific meaning of the above terms in the present application will be understood in specific cases by those of ordinary skill in the art.

Examples

The mode of a motor-driven rope linkage system is adopted on a large satellite, and the mode can realize ordered unfolding of a plurality of substrates to a great extent, but the micro-nano satellite is limited in size and energy, and is not suitable or easy to adopt, so that the multi-folded solar wings of the general micro-nano satellite are unfolded unordered. When the solar wings are unfolded in disorder, each part of each substrate can be unfolded in place to generate one-time abnormal vibration, so that multiple times of abnormal vibration can be generated in the whole process of completing the unfolding of the solar wings, the satellite attitude is adversely affected, and even the function and performance of the satellite can be damaged. To achieve orderly unfolding, the angular speed of unfolding of each substrate is generally controlled by selecting torsion springs or memory materials.

The material properties of the torsion spring and the memory material make this fitting work difficult. The specifications of torsion springs or memory materials commonly available in the market are generally established, and in order to achieve orderly deployment, researchers choose to use multiple torsion springs, but the stiffness coefficient, torsion force and energy of each torsion spring are discrete and intermittent, so the supporting force provided by the torsion springs with the established specifications is often inconsistent with the required deployment force.

Taking two adjacent substrates as an example, two or more hinge parts of the two substrates may be used, the required unfolding force of each hinge part may be different, and taking two hinge parts as an example, through calculation of research personnel, according to the corresponding unfolding force requirement, when the stiffness coefficient of a torsion spring of one hinge is 5.0Nmm/deg, the stiffness coefficient of the torsion spring of the other hinge can realize orderly unfolding if and only if the stiffness coefficient of the torsion spring of the other hinge is 7.6 Nmm/deg. At this time, it is highly possible that 7.6Nmm/deg torsion springs are not available on the market, even if specifically tailored, because the tailoring is limited by factors such as torsion spring wire diameter, outer diameter, number of turns, support angle, etc., the stiffness coefficient of the torsion springs cannot be specified under size constraints. This is also the case where only two base plates are hinged at only two points, which in practice tends to be more complex, and torsion springs to match each hinge point of each base plate to a particular stiffness coefficient tend to be more difficult.

The embodiment of the application provides a folding and unfolding mechanism 30, a solar wing 20 with the folding and unfolding mechanism 30, and a micro-nano satellite with the solar wing 20.

The deployment mechanism 30 provided by the embodiments of the present application is capable of providing an actual deployment force that matches the deployment force requirements. The solar wing 20 is arranged, the solar wing 20 and the satellite main body 10 are also connected through the folding and unfolding mechanism 30, and the satellite main body 10 is only subjected to one vibration from the beginning of the unfolding of the solar wing 20 to the completion of the unfolding operation, so that the influence of the unfolding operation of the solar wing 20 on the satellite main body 10 is greatly reduced.

Fig. 1 shows a folded state diagram of a micro-nano satellite provided by an embodiment of the present application, and fig. 2 shows an unfolded state diagram of a micro-nano satellite provided by an embodiment of the present application. As shown in fig. 1 and 2, the micro-nano satellite includes a satellite body 10 (part) and a solar wing 20. The solar wing 20 includes a first substrate 21, a second substrate 22 and a third substrate 23 hinged in sequence, wherein the third substrate 23 is the innermost substrate of the solar wing 20, the third substrate 23 is hinged with the satellite main body 10, the first substrate 21 is the outermost substrate of the solar wing 20, the first substrate 21 is far away from the satellite main body 10, the second substrate 22 between the first substrate 21 and the third substrate 23 may not be provided, or may be provided in one or more, and the embodiment is exemplified by taking the number of the second substrates 22 as one.

The first base plate 21, the second base plate 22, the third base plate 23, and the satellite body 10 are hinged by the folding mechanism 30, respectively, so that the solar wing 20 can have an unfolded state and a folded state.

The folded state of the solar wing 20 means that the first substrate 21, the second substrate 22, the third substrate 23, and the satellite body 10 are all in a parallel state as shown in fig. 1. To maintain the folded state, a pressing release mechanism is generally provided to press the plurality of substrates of the solar wing 20 against the surface of the satellite body 10. As shown in fig. 1 and 2, the hold-down release mechanism includes a lock mechanism 50 provided on the satellite body 10, and a hold-down lever 40 connected to the first base plate 21, the hold-down lever 40 being connected to the lock mechanism 50 through the second base plate 22 and the third base plate 23. When the locking mechanism 50 releases the hold-down bar 40, the solar wing 20 is unfolded by the folding mechanism 30.

The unfolded state of the solar wing 20 means that the first substrate 21, the second substrate 22, the third substrate 23, and the satellite body 10 are all unfolded at a certain angle. In fig. 2, for convenience of observation, the solar wing 20 is shown in a state that a plurality of substrates are unfolded at 180 degrees, which is only for convenience of observation, and does not mean that the solar wing 20 provided by the present application must be unfolded at the 180 degrees, but the solar wing 20 may be configured to be unfolded at other angles, such as 90 degrees, 180 degrees, 270 degrees, etc. In the present embodiment, the solar wing 20 is unfolded at 90 degrees, that is, the angle between the first substrate 21 and the second substrate 22, the angle between the second substrate 22 and the third substrate 23, and the angle between the third substrate 23 and the satellite body 10 are respectively at 90 degrees.

In the folded state of the solar wing 20, the folding mechanism 30 is in the folded state as shown in fig. 3 and 4, and in the unfolded state of the solar wing 20, the folding mechanism 30 is in the unfolded state as shown in fig. 5 and 6.

The folding and unfolding mechanism 30 includes a first body 100, a second body 200, a rotating shaft 300, an elastic support 400, and a damping assembly 500.

The first body 100 and the second body 200 are pivotally connected through a rotation shaft 300, two adjacent base plates (or the satellite main body 10 and the third base plate 23) are respectively connected to the first body 100 and the second body 200, the elastic support 400 is used for providing a supporting force to drive the first body 100 and the second body 200 to rotate from a folded state to an unfolded state, the damping assembly 500 is used for generating damping when the first body 100 and the second body 200 rotate, and the generated damping is adjustable in size. The actual deployment force of the first body 100 and the second body 200 is the supporting force minus the damping, and the actual deployment force is adjusted by adjusting the magnitude of the damping.

The damping assembly 500 includes a damping portion, a first adjusting member 520 and a second adjusting member 530, a first friction surface 131 is disposed on the first body 100, a second friction surface 231 is disposed on the second body 200, the first friction surface 131 and the second friction surface 231 are respectively used for being matched with the damping portion, and once the first body 100 or the second body 200 rotates, the corresponding friction surfaces can be matched with the damping portion to generate friction damping. The first adjuster 520 is used for adjusting the pressure between the first friction surface 131 and the damping portion, thereby adjusting the magnitude of damping generated between the first friction surface 131 and the damping portion, and the second adjuster 530 is used for adjusting the pressure between the second friction surface 231 and the damping portion, thereby adjusting the magnitude of damping generated between the second friction surface 231 and the damping portion.

The damping part includes a damping washer 510 sleeved on the rotation shaft 300, an outer circumferential surface of the damping washer 510 is matched with the first friction surface 131, and one end surface of the damping washer 510 is matched with the second friction surface 231. The part of the first body 100 protrudes toward the outer circumferential surface of the damping portion to form a first friction surface 131, and the part of the second body 200 protrudes toward one end surface of the damping portion to form a second friction surface 231.

The first body 100 includes a first base 110, the first base 110 being for coupling to the substrate or satellite body 10, a yoke 130 being coupled to the first base 110, the yoke 130 being for being coupled to an outer circumferential surface of the damping washer 510, the first friction surface 131 being configured as an inner wall of the yoke 130, a first adjusting member 520 being provided at an opening of the yoke 130 to adjust a degree of tightening of the damping washer 510 by the yoke 130, the first base 110 being formed with the first coupling portion 120.

The second body 200 includes a second base 210 and a boss 230, the second base 210 being for coupling with a substrate or at the satellite body 10, the boss 230 being flanged at one end to couple with the second base 210, a second friction surface 231 being formed on one end surface of the boss 230, the second base 210 being formed with a second coupling portion 220.

The rotating shaft 300 passes through the first connecting portion 120, the second connecting portion 220 and the shaft sleeve 230 to rotatably connect the first body 100 with the second body 200, the damping washer 510 is sleeved on the rotating shaft 300, the second adjusting member 530 is an adjusting nut in threaded connection with the rotating shaft 300, the adjusting nut is used for pressing the damping washer 510 to the second friction surface 231 on the shaft sleeve 230, and the pressure between the damping washer 510 and the second friction surface 231 can be adjusted by screwing the adjusting nut.

The elastic support 400 may be a spring plate or a spring, etc. that is abutted between the first base 110 and the second base 210, and in this embodiment, the elastic support 400 is a torsion spring, and the torsion spring is sleeved on the sleeve 230 to drive the first body 100 and the second body 200 to relatively expand.

By the above-mentioned cooperation of the first body 100, the second body 200, the rotation shaft 300, the elastic support 400 and the damping assembly 500, the folding and unfolding mechanism 30 has a supporting force for relatively unfolding the first body 100 and the second body 200, and also has two kinds of friction damping which can be respectively adjusted, namely, the friction damping between the first body 100 and the damping assembly 500 and the friction damping between the second body 200 and the damping assembly 500, so that the folding and unfolding mechanism 30 capable of adjusting the actual unfolding force by adjusting the damping magnitude is formed.

Further, since friction damping is provided between the first friction surface 131, the second friction surface 231 and the damping washer 510, respectively, the respective developing speeds of the first body 100 and the second body 200 are slowed down, respectively, and vibrations generated when the first body 100 and the second body 200 are developed in place are reduced.

As shown in fig. 9 and 10, the first body 100 has two staggered recesses on two surfaces of the first base 110, the two recesses are different in surface and staggered, a first mounting surface 111 for connecting the substrate or the satellite body 10 is formed at one of the recesses, a first abutting surface 112 for abutting against the torsion spring is formed at the other recess, and the first connecting portion 120 is disposed on the same side as the first abutting surface 112.

As shown in fig. 11 and 12, the second body 200 has two staggered recesses on two surfaces of the second base 210, the two recesses are different and staggered, a second mounting surface 211 for connecting the substrate or the satellite body 10 is formed at one recess, a second abutting surface 212 for abutting against the torsion spring is formed at the other recess, and the boss 230 and the second connecting portion 220 are disposed on the same side as the second abutting surface 212.

The thickness of the substrate is the same as the recess depth of the first mounting surface 111 and the second mounting surface 211, and the recess depth is exactly complemented when the substrate is connected to the first mounting surface 111 or the second mounting surface 211. The first and second abutment surfaces 112 and 212 are recessed to be spaced apart from the boss 230, respectively, to form a gap for mounting the torsion spring and the damping washer 510, as shown in fig. 5 and 8.

The base plate is attached to the first attachment surface 111 or the second attachment surface 211 by an anchor such as a screw. The first mounting surface 111 is provided with a first mounting hole penetrating the first base 110, and the second mounting surface 211 is provided with a second mounting hole penetrating the second base 210, and the first and second mounting holes are used for being matched with anchors such as screws. The first mounting holes and the second mounting holes are staggered, so that when the first body 100 and the second body 200 are in the folded state shown in fig. 1, anchors such as screws arranged in the mounting holes of the first body 100 and the second body 200 are not interfered with or abutted against each other, and the first body 100 and the second body 200 can be folded to be closer to each other when folded.

For weight reduction, alternatively, as shown in fig. 10, a recess is provided at a position where the first mounting surface 111 is not provided with the first mounting hole, as shown in fig. 12, a recess is provided at a position where the second mounting surface 211 is not provided with the second mounting hole, and the first base 110 and the second base 210 are thinner at the recess positions to reduce the weight of the folding mechanism 30. The recess can also be provided as hollow out, if the structural strength permits.

The first connection part 120 is inserted into a gap between the second connection part 220 and the shaft housing 230, and the rotation shaft 300 sequentially passes through the second connection part 220, the first connection part 120, the shaft housing 230, the damping washer 510, and the adjustment nut. The torsion spring is sleeved on the shaft sleeve 230, and two ends of the torsion spring are respectively abutted on the first abutting surface 112 and the second abutting surface 212.

The first adjusting member 520 is an adjusting screw that passes through the open position of the yoke 130 and is coupled to the first base 110. At the opening of the clamp 130, one side of the clamp 130 abuts against the first base 110, the other side of the clamp 130 abuts against the nut of the adjusting screw, and the adjusting screw is screwed to adjust the opening size of the clamp 130, so that the magnitude of friction damping between the first friction surface 131 and the damping washer 510 is adjusted steplessly. While screwing the adjusting nut is to realize stepless adjustment of the magnitude of the friction damping between the second friction surface 231 and the damping washer 510.

In the prior art, the final unfolding position of the folding mechanism 30 is sometimes dependent on the torsion spring or the memory material, when the torsion spring is unfolded to the final position after the stress is released, or when the memory material is unfolded to the final position, the folding mechanism 30 completes the unfolding, which makes the substrates not stable enough after the solar wing 20 is unfolded. Therefore, the inventor configures the first body 100 and the second body 200 to have a structure with limiting surfaces respectively, and when the two limiting surfaces are abutted, the first body 100 and the second body 200 cannot be further unfolded relatively, so as to control the maximum unfolding angle of the folding and unfolding mechanism 30.

Referring to fig. 8 again, the first connecting portion 120 of the first body 100 is a cylinder, a right-angle portion is formed on the circumferential surface of the cylinder, two planes forming the right angle are tangential planes of the circumferential surface, one plane is a first limiting surface 122, and the first limiting surface 122 is parallel to the first mounting surface 111. Referring to fig. 5, 8 and 11, a second limiting surface 222 is formed at a gap between the second connecting portion 220 of the second body 200 and the sleeve 230, and the second limiting surface 222 is perpendicular to the second mounting surface 211. When the first body 100 and the second body 200 are relatively unfolded to 90 degrees, the first limiting surface 122 abuts against the second limiting surface 222 to limit the first body 100 and the second body 200 to be further unfolded. In this embodiment, the maximum expansion angle is 90 degrees, and other settings may be made on the first limiting surface 122 and the second limiting surface 222 to set the maximum expansion angle to other values.

The deployment mechanism 30 is also provided with an in-place switch 700, the in-place switch 700 being configured to send deployment in-place information to the ground when the deployment mechanism 30 reaches a deployed state (i.e., when deployed to a maximum deployment angle). The in-place switch 700 is provided on the first body 100, and when the in-place switch 700 is unfolded, the second body 200 contacts the trigger portion of the in-place switch 700 to trigger the in-place switch 700.

A groove body is formed on the right angle part of the first connecting part 120 of the first body 100 and the other surface perpendicular to the first limiting surface 122, the in-place switch 700 is installed in the groove body, the triggering part of the in-place switch 700 faces the first limiting surface 122, and when the second limiting surface 222 abuts against the first limiting surface 122, the second limiting surface 222 contacts the triggering part of the in-place switch 700.

To further ensure stability after deployment, a positioning assembly 600 is disposed in the deployment mechanism 30, where the positioning assembly 600 is used to lock the first body 100 and the second body 200 in the deployed state.

The positioning assembly 600 includes a locking pin 610 and a compression spring 620, the locking pin 610 is mounted to the second body 200, and the compression spring 620 is connected to one end of the locking pin 610 to eject the other end of the locking pin 610 toward the first body 100, and a pin hole 121 is formed in the first body 100. The compression spring 620 pushes the locking pin 610 into the first body 100 when the first body 100 and the second body 200 are rotated to the unfolded state, thereby restricting the relative rotation of the first body 100 and the second body 200. To facilitate the retraction of the locking pin 610 to facilitate the return of the folding mechanism 30 to the folded state, a detachably connected reset lever is provided on the locking pin 610.

As shown in fig. 7, a receiving hole 221 is formed in the second connection portion 220 of the second body 200, a pin hole 121 is formed in the first connection portion 120 of the first body 100, and a locking pin 610 and a compression spring 620 are disposed in the receiving hole 221. When the first body 100 and the second body 200 are not in the unfolded state, the locking pin 610 and the compression spring 620 are blocked in the receiving hole 221, and when the first body 100 and the second body 200 are in the unfolded state, the receiving hole 221 is opposite to the pin hole 121, and the compression spring 620 ejects the locking pin 610 toward the pin hole 121.

To facilitate pulling out the locking pin 610 from the pin hole 121 so that the folding and unfolding mechanism 30 can be restored to the folded state, a viewing port 241 is provided on the second body 200, and a restoring rod (restoring rod is not shown in the drawing) can be movably connected to the locking pin 610 through the viewing port 241 to pull out the locking pin 610 from the pin hole 121.

As shown in fig. 11 and 12, a limiting cover 240 is disposed at one end of the second connecting portion 220 away from the first connecting portion 120, the accommodating hole 221 is a through hole, the limiting cover 240 covers the accommodating hole 221, two ends of the compression spring 620 respectively prop against between the locking pin 610 and the limiting cover 240, and the observation port 241 is opened on the limiting cover 240. The observation port 241 corresponds to the position of the accommodation hole 221, the caliber of the observation port 241 is smaller than the inner diameter of the accommodation hole 221, and the caliber of the observation port 241 is smaller than the inner diameter of the compression spring 620. The reset lever can be coupled to the locking pin 610 through the viewing port 241. Optionally, a reset lever is threadably coupled to the locking pin 610. The reset rod is a screw rod, one end of the locking pin 610, which faces the limit change, is provided with a threaded hole, the reset rod passes through the observation port 241 to be in threaded connection with the locking pin 610, and the reset rod is pulled backwards to pull the locking pin 610 out of the pin hole 121.

In other embodiments, the viewing port 241 may be disposed on the peripheral surface of the second connecting portion 220 and extend in a direction parallel to the rotation axis 300, and the restoring rod extends from the viewing port 241 into the receiving hole 221 and is connected to the peripheral surface of the locking pin 610, where the connection manner may be a threaded connection, a plugging connection, a clamping connection, or the like, and pulls the restoring rod along the viewing port 241 to pull the locking pin 610 out of the pin hole 121.

The solar wing 20 provided in this embodiment is connected by the aforementioned folding mechanism 30. As mentioned above, the solar wing 20 comprises at least two substrates, i.e. the solar wing 20 comprises at least a first substrate 21 and a third substrate 23. The folding and unfolding mechanism 30 is used for connecting two adjacent substrates.

In this embodiment, the solar wing 20 has a first substrate 21, a second substrate 22 and a third substrate 23, the first substrate 21 and the second substrate 22 are connected by three folding mechanisms 30, and the second substrate 22 and the third substrate 23 are connected by three folding mechanisms 30.

The damping size of the damping component 500 of each folding mechanism 30 is adjusted so that the actual unfolding force provided by each folding mechanism 30 meets the unfolding force requirement of the position of each folding mechanism, and therefore each substrate of the solar wing 20 and different parts of each substrate can obtain corresponding unfolding force, the rotation angular speed of each substrate is ensured to be consistent, and each substrate can be unfolded orderly. The time of the relative unfolding of the first substrate 21 and the second substrate 22 and the time of the relative unfolding of the second substrate 22 and the third substrate 23 are synchronous, that is to say, the first substrate 21, the second substrate 22 and the third substrate 23 are synchronously unfolded in place, and the vibration of unfolding in place is reduced due to the effect of the damping component 500 that the unfolding speed is slowed down, so that the unfolding action of the solar wing 20 only brings about small vibration, and the influence of the unfolding action of the solar wing 20 on the satellite attitude is greatly reduced.

The satellite main body 10 of the micro-nano satellite provided in this embodiment is connected to the third substrate 23 of the solar wing 20 through the three folding mechanisms 30, and the actual folding force of each folding mechanism 30 is adjusted according to the requirement of the folding force, so that the folding speed of the first substrate 21 relative to the satellite main body 10 is synchronous with other substrates, further ensuring that the folding action of the solar wing 20 is only once, and reducing the influence of the folding action of the solar wing 20 on the satellite attitude.

It should be noted that:

The number of the second substrates 22, the number of the folding and unfolding mechanisms 30 of any two adjacent substrates, the number of the pressing rods 40 and the number of the locking mechanisms 50 are respectively set according to factors such as the solar circuit board area requirement of the micro-nano satellite, the unfolding force requirement of the solar wing 20, the locking degree requirement of the solar wing 20 and the like.

The second substrate 22 (i.e., the substrate between the first substrate 21 and the third substrate 23) may not be provided, or may be provided in one, two, three or even more, and in actual use, the specific number is provided as needed.

Every two adjacent base plates can be pivoted by one, two, three or even more folding and unfolding mechanisms 30, and the specific number is set according to the requirement.

The pressing rod 40 and the locking mechanism 50 may be provided in a plurality of sets, and the number may be set according to factors such as the size of the substrate in actual use, and may be one set, two sets, three sets or more.

The above description is only of the preferred embodiments of the present application and is not intended to limit the present application, but various modifications and variations can be made to the present application by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the protection scope of the present application.

Claims

1. A folding and unfolding mechanism, comprising:

a first body;

A second body;

the damping assembly is used for generating damping when the first body and the second body rotate, and the damping is adjustable in size;

The damping assembly comprises a damping part, a first adjusting piece and a second adjusting piece, wherein the damping part is matched with the first friction surface and the second friction surface respectively to generate damping, the first adjusting piece is used for adjusting the pressure between the damping part and the first friction surface, and the second adjusting piece is used for adjusting the pressure between the damping part and the second friction surface;

the folding and unfolding mechanism further comprises a positioning assembly, wherein the positioning assembly is used for locking the first body and the second body in the unfolded state.

2. The folding and unfolding mechanism according to claim 1, wherein the damping portion includes a damping washer sleeved on the rotating shaft, an outer peripheral surface of the damping washer is matched with the first friction surface, and one end surface of the damping washer is matched with the second friction surface.

3. The folding and unfolding mechanism according to claim 2, wherein the first body comprises a first base and a clamp, the first base and the second body are pivotally connected through the rotating shaft, the clamp is connected to the first base, the clamp is arranged on the outer peripheral surface of the damping washer, the first friction surface is the inner wall of the clamp, and two ends of the opening of the clamp are connected through the first adjusting piece.

4. A folding and unfolding mechanism as claimed in claim 3, characterized in that the first adjusting member is an adjusting screw, and the clamp is connected to the first base by means of the adjusting screw.

5. The folding and unfolding mechanism according to claim 2, wherein one end of the rotating shaft is provided with threads, the second adjusting piece is an adjusting nut matched with the threads of the rotating shaft, and the adjusting nut and the second friction surface are respectively positioned at two ends of the damping washer.

6. The folding and unfolding mechanism according to claim 5, wherein a shaft sleeve is formed on the second body, the rotating shaft penetrates through the shaft sleeve, the elastic supporting piece is a torsion spring sleeved on the shaft sleeve, and the second friction surface is one end surface of the shaft sleeve.

7. The folding and unfolding mechanism as claimed in claim 1, characterized in that the positioning assembly comprises a locking pin and a compression spring, a receiving hole for receiving the locking pin and the compression spring is formed on the second body, a pin hole is formed on the first body, the locking pin is aligned with the pin hole when the first body and the second body are in the unfolded state, and one end of the locking pin is driven by the compression spring to be inserted into the pin hole.

8. The folding and unfolding mechanism of claim 7, wherein the positioning assembly further comprises a reset lever detachably connected to the locking pin, and wherein a viewing port is provided on the second body for allowing the reset lever to move through to pull the locking pin out of the pin hole.

9. The folding and unfolding mechanism of claim 1, wherein the first body is formed with a first limiting surface, the second body is formed with a second limiting surface, and the first limiting surface and the second limiting surface abut to limit an unfolding angle of the first body and the second body when the first body and the second body are in an unfolded state.

10. The folding and unfolding mechanism of claim 1 further comprising an in-place switch mounted to the first body, the second body triggering the in-place switch when the first body and the second body are relatively rotated to the unfolded state.

11. The folding and unfolding mechanism according to claim 1, wherein the folding and unfolding mechanism is used for connecting a first base body and a second base body, a first mounting hole used for connecting the first base body is formed in the first base body, a second mounting hole used for connecting the second base body is formed in the second base body, and the positions of the first mounting hole and the second mounting hole are staggered relatively.

12. A solar wing comprising at least two base plates and a folding and unfolding mechanism according to any one of claims 1 to 11, wherein two adjacent base plates are connected by the folding and unfolding mechanism.

13. A micro-nano satellite, comprising a satellite body and the solar wing of claim 12, wherein one substrate of the solar wing is connected with the satellite body through the folding mechanism.