CN210592492U - Microsatellite solar wing spreading mechanism - Google Patents

Abstract

The utility model relates to a microsatellite sun wing opens mechanism, include: the hinge comprises a male hinge and a female hinge which are connected through a rotating shaft, and an annular gasket, a T-shaped gasket, a torsion spring, a telescopic spring and a nut which are arranged on the rotating shaft. The solar wing spreading mechanism of the utility model has compact structure and small area of the cloth piece occupying the surface of the solar wing; the solar wing spreading mechanism provided by the utility model is provided with the annular gasket and the T-shaped gasket between the contact surfaces of the movable parts, thus effectively preventing the vacuum cold welding effect from generating; the utility model discloses set up expanding spring at the pivot both ends and can form the instantaneous impact of production when rotatory damping mechanism expandes.

Description

Microsatellite solar wing spreading mechanism

Technical Field

The utility model relates to a space satellite technical field, concretely relates to microsatellite sun wing opens mechanism.

Background

The solar wing is a device for collecting solar energy and supplying energy to the space satellite, and is an energy source of the space satellite. The space satellite is limited by a carrying space in a launching state, the solar wings are required to be folded and collected on the side walls of the satellite in a launching stage, and the solar wings of the satellite are unfolded into a plane shape after the satellite is separated from the rocket.

The unfolding mechanism of the satellite solar wing plays an important role in the launching and running processes of the satellite, the unfolding of the solar wing is a very important link for the satellite to enter a real working state, if the solar wing cannot be unfolded, the satellite loses working capacity due to gradual reduction of residual energy of a battery, and the service life of the satellite in orbit flight is further seriously influenced, so that the unfolding mechanism of the satellite solar wing is a key component for ensuring the normal running of the satellite.

The common solar wing spreading mechanisms at present are divided into two types: the active and passive solar wing mechanism is generally used as a repeatable folding and unlocking type solar wing mechanism, is applied to a large satellite more frequently, is driven by a motor generally, but consumes power resources and has a more complex structure.

For the microsatellite, the solar wing is usually unfolded by adopting passive driving, the solar wing is usually driven by a spring, the spring is pre-stressed to store potential energy of the spring during folding, and after the mechanism is unlocked, the spring releases the elastic potential energy to realize unfolding of the mechanism. The spring driving mode has the advantages of relative independence of the system and higher reliability. However, the driving force driven by the spring is not easy to control, and strong collision between adjacent solar wing panels is easily caused at the moment when the stretching is finished, so that the stretching process is not controllable, and the stability of the locking and releasing process is poor. Meanwhile, the vacuum cold welding effect exists in a vacuum environment, so that the moving part also needs to be provided with a means for preventing the vacuum cold welding.

Therefore, it is important to design a solar wing spreading mechanism with smooth spreading and releasing process and preventing the vacuum cold welding effect from generating for the microsatellite.

Disclosure of Invention

Therefore, the present invention has been made in view of the above problems, and an object of the present invention is to provide a solar wing spreading mechanism which is stable in the spreading and releasing process and has a function of preventing the vacuum cold welding effect from being generated, and the present invention is achieved by the following means.

A microsatellite solar wing opening mechanism comprising: the device comprises a male hinge, a female hinge, a rotating shaft, an annular gasket, a T-shaped gasket, a torsion spring, a telescopic spring and a nut;

the middle part of the back surface of the male hinge is provided with two hook-shaped reeds which are arranged in a splayed manner, the hook parts of the hook-shaped reeds are positioned on the side, close to the rotating shaft, of the male hinge, and the hook-shaped reeds are made of spring steel;

two convex parts with right-angled triangle sections are arranged in the middle of the back of the female hinge and close to the rotary shaft, and after the solar wing is unfolded in place, the hook-shaped reeds of the male hinge buckle the convex parts to lock the male hinge and the female hinge;

the torsion spring is sleeved in the middle of the rotating shaft, and the extension arms of the torsion spring respectively enter the limiting grooves of the female hinge and the male hinge;

the annular gasket is made of polytetrafluoroethylene and is arranged between the upper ear hole and the lower ear hole of the female hinge and the male hinge;

the rotating shaft penetrates through four coaxial ear holes formed by mutually matching the male hinge and the female hinge, and the middle section of the rotating shaft is sleeved with a cold welding prevention sleeve;

the number of the T-shaped gaskets is four, the T-shaped gaskets are all made of polytetrafluoroethylene, and two T-shaped gaskets are sleeved at two ends of the rotating shaft in a group;

the number of the telescopic springs is two, and the telescopic springs are respectively sleeved between two T-shaped gaskets at two ends of the rotating shaft;

the nuts are arranged at two ends of the rotating shaft, and the female hinge and the male hinge are prevented from sliding along the axial direction.

The utility model discloses beneficial effect:

the solar wing spreading mechanism of the utility model has compact structure and small area of the cloth piece occupying the surface of the solar wing;

the solar wing spreading mechanism provided by the utility model is provided with the annular gasket and the T-shaped gasket between the contact surfaces of the movable parts, thus effectively preventing the vacuum cold welding effect from generating;

the utility model discloses set up expanding spring at the pivot both ends and can form the instantaneous impact of production when rotatory damping mechanism expandes.

Drawings

Fig. 1 is a front view of a sun wing opening mechanism.

Fig. 2 is a rear view of the sun wing opening mechanism.

Fig. 3 is a view showing the structure of the rotary shaft.

Fig. 4 is a rear view of the sun wing spreading mechanism deployed 180 degrees.

Detailed Description

The preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings, which are easily implemented by those having ordinary skill in the art to which the present invention pertains. The invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. In addition, for the purpose of more clearly describing the present invention, parts not connected with the present invention will be omitted from the drawings.

As shown in fig. 1 to 4, a microsatellite solar wing opening mechanism includes: the hinge comprises a male hinge 100, a female hinge 200, a rotating shaft 300, an annular gasket 400, a T-shaped washer 500, a torsion spring 600, a telescopic spring 700 and a nut 800;

as shown in fig. 1 and 2, the male hinge 100 is of a U-shaped structure, the male hinge 100 is provided with an ear hole a101 and an ear hole B102 at the upper and lower parts, the ear hole a101 and the ear hole B102 are coaxial, a limiting groove is arranged below the ear hole a101, two hook-shaped reeds 103 arranged in a splayed shape are arranged in the middle of the back surface of the male hinge 100, hook parts of the hook-shaped reeds 103 are located at the outer side of the male hinge 100, the hook-shaped reeds 103 are made of spring steel, two through holes are arranged on the mounting surface of the male hinge 100 and used for being connected with a sun wing, and the male hinge 100 is made of aluminum;

as shown in fig. 1 and 2, the female hinge 200 is a U-shaped structure, the female hinge 200 is vertically distributed with an ear hole C201 and an ear hole D202, the ear hole C201 and the ear hole D202 are coaxial, a limiting groove is arranged above the ear hole D202, two inner side walls in the middle of the female hinge 200 are both provided with a convex part 203 with a right triangle cross section near the outer side, the inclined plane of the convex part 203 faces the outer side of the female hinge 200, the convex part 203 is higher than the back of the female hinge 200, two through holes are arranged on the mounting surface of the female hinge 200 for connecting with the sun wing, and the female hinge 200 is made of aluminum alloy;

as shown in fig. 1 and 3, two ends of the rotating shaft 300 are threaded sections, the diameter of the threaded sections is smaller than that of the middle section of the rotating shaft 300, a cold welding prevention sleeve 301 is sleeved on the middle section of the rotating shaft 300, and the cold welding prevention sleeve 301 is made of polytetrafluoroethylene;

as shown in fig. 1, the male hinge 100 is connected with the female hinge 200 through a rotating shaft 300, the rotating shaft 300 passes through the ear hole a101, the ear hole B102, the ear hole C201 and the ear hole D202, because the cold welding prevention sleeve 301 is arranged in the middle section of the rotating shaft 300, the contact part of the rotating shaft 300 and the male hinge 100 and the female hinge 200 cannot be subjected to cold welding, and the length of the middle section of the rotating shaft 300 is smaller than the length from the outer side of the ear hole C201 to the outer side of the ear hole D202 on the female hinge 200;

as shown in fig. 1, the number of the annular gaskets 400 is two, and the two annular gaskets 400 are made of teflon, and are respectively arranged between the ear hole a101 and the ear hole C201, and between the ear hole B102 and the ear hole D202, so as to prevent cold welding between the male hinge 100 and the female hinge 200;

as shown in fig. 1, the number of the T-shaped washers 500 is four, and the T-shaped washers 500 are made of polytetrafluoroethylene, and two of the T-shaped washers 500 are sleeved on the threaded sections at the two ends of the rotating shaft 300 in a group;

as shown in fig. 1, the torsion spring 600 is made of spring steel, two ends of the torsion spring 600 are provided with extending portions, a gap is left between coils of the torsion spring 600 to prevent cold welding, the torsion spring 600 is sleeved on the outer peripheral side of the cold welding releasing sleeve 301, the extending portions of the two ends of the torsion spring 600 are respectively located in limiting grooves formed in the male hinge 100 and the female hinge 200 to prevent the torsion spring 600 from being unstable;

as shown in fig. 1, the number of the extension springs 700 is two, and the two extension springs 700 are made of spring steel, and the two extension springs 700 are respectively sleeved on the threaded sections at the two ends of the rotating shaft 300 and are located between the T-shaped washers 500 arranged at the two ends of the rotating shaft 300 in pairs, so as to prevent cold welding between the extension springs 700 and the rotating shaft 300;

as shown in fig. 1, the number of the nuts 800 is two, and the nuts 800 are respectively installed in the thread sections at the two ends of the rotating shaft 300, and the nuts 800 apply a certain pressure to the extension spring 700 to generate rotational damping, so that the extension process of the torsion spring 600 is stable when the torsion spring is extended and no transient impact is formed;

as shown in fig. 4, after the torsion spring 600 is completely unfolded, a 180-degree included angle is formed between the male hinge 100 and the female hinge 200, and in the unfolding process, the hook-shaped spring plate 103 slides into the rear part of the protrusion 203 through the inclined surface of the protrusion 203 to hook the protrusion 203, so as to complete the locking function;

according to the present embodiment, the maximum deployment angle of the sun-wing deployment mechanism is 180 degrees.

According to this embodiment, the sun wing opening mechanism is installed between the two sun wings.

The foregoing is a more detailed description of the invention, taken in conjunction with the accompanying preferred embodiments, and it is not intended that the invention be limited to the specific embodiments described above. To the utility model belongs to the technical field of the ordinary technical personnel, do not deviate from the utility model discloses under the prerequisite of design, can also make a plurality of simple deductions or replacement, all should regard as belonging to the utility model discloses a protection scope.

Claims (2)

1. A microsatellite solar wing opening mechanism comprising: the device comprises a male hinge, a female hinge, a rotating shaft, an annular gasket, a T-shaped gasket, a torsion spring, a telescopic spring and a nut;

the method is characterized in that: the middle part of the back of the male hinge is provided with two splayed hook-shaped reeds, and hook parts of the hook-shaped reeds are positioned on the side, close to the rotating shaft, of the male hinge;

two convex parts with right-angled triangle sections are arranged in the middle of the back of the female hinge and close to the rotary shaft;

the torsion spring is sleeved in the middle of the rotating shaft, and the extension arms of the torsion spring respectively enter the limiting grooves of the female hinge and the male hinge;

the annular gasket is made of polytetrafluoroethylene and is arranged between the upper ear hole and the lower ear hole of the female hinge and the male hinge;

the rotating shaft penetrates through four coaxial ear holes formed by mutually matching the male hinge and the female hinge, and the middle section of the rotating shaft is sleeved with a cold welding prevention sleeve;

the number of the T-shaped gaskets is four, the T-shaped gaskets are all made of polytetrafluoroethylene, and two T-shaped gaskets are sleeved at two ends of the rotating shaft in a group;

the number of the telescopic springs is two, and the telescopic springs are respectively sleeved between two T-shaped gaskets at two ends of the rotating shaft;

the nuts are mounted at both ends of the rotating shaft.

2. A microsatellite solar wing opening mechanism according to claim 1 wherein: the hook-shaped reed is made of spring steel.

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