CN113895658B - Satellite sailboard unfolding mechanism and microsatellite - Google Patents
Satellite sailboard unfolding mechanism and microsatellite Download PDFInfo
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- CN113895658B CN113895658B CN202111359637.6A CN202111359637A CN113895658B CN 113895658 B CN113895658 B CN 113895658B CN 202111359637 A CN202111359637 A CN 202111359637A CN 113895658 B CN113895658 B CN 113895658B
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- 230000007246 mechanism Effects 0.000 title claims abstract description 52
- 108091092878 Microsatellite Proteins 0.000 title claims abstract description 14
- 230000000903 blocking effect Effects 0.000 claims description 17
- 230000009471 action Effects 0.000 claims description 5
- 238000000034 method Methods 0.000 abstract description 12
- 230000008569 process Effects 0.000 abstract description 12
- 238000012423 maintenance Methods 0.000 abstract description 7
- 230000008859 change Effects 0.000 abstract description 4
- 238000009434 installation Methods 0.000 description 7
- 238000010586 diagram Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 3
- 238000005381 potential energy Methods 0.000 description 2
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- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/42—Arrangements or adaptations of power supply systems
- B64G1/44—Arrangements or adaptations of power supply systems using radiation, e.g. deployable solar arrays
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64G—COSMONAUTICS; VEHICLES OR EQUIPMENT THEREFOR
- B64G1/00—Cosmonautic vehicles
- B64G1/22—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles
- B64G1/222—Parts of, or equipment specially adapted for fitting in or to, cosmonautic vehicles for deploying structures between a stowed and deployed state
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Abstract
The application relates to a solar wing hinge technical field especially relates to a satellite sailboard deployment mechanism and microsatellite, and satellite sailboard deployment mechanism includes: the fixed hinge is connected with the satellite body; the rotating hinge comprises a first hinge part and a connecting part connected with the first hinge part, the first hinge part is hinged to the fixed hinge, and the connecting part is connected with a satellite sailboard; the first fixing piece is arranged on the surface of the rotating hinge; the second fixing piece is arranged on the surface of the fixing hinge; one end of the driving piece is connected with the first fixing piece, and the other end of the driving piece is connected with the second fixing piece. The application provides a satellite sailboard deployment mechanism, driving piece assemble in whole deployment mechanism's outside as the power supply, when changing the driving piece, need not wholly carry out the dismouting to deployment mechanism, and the simple easy operation of change process of driving piece to effectively reduce the cost and the efficiency of holistic processing of deployment mechanism, maintenance.
Description
Technical Field
The application relates to the technical field of solar wing hinges, in particular to a satellite sailboard unfolding mechanism and a microsatellite.
Background
With the continuous enhancement of the functions of the microsatellite, the demand on energy is correspondingly improved, and the power consumption of the whole satellite cannot be met by only depending on the area of the body-mounted sailboard, so that the unfolded sailboard is widely applied. The key part for unfolding the sailboard is the unfolding mechanism, and the tiny satellites have strict requirements on size and weight, so the unfolding mechanism needs to have high reliability, simple structural form and small weight and size. In addition, due to the fact that the sizes and the weights of different satellite sailboards are different, the unfolding performance of the mechanism also needs to be designed in a customized mode.
At present, the power source of the microsatellite unfolding mechanism is usually a torsion spring, a volute spring, a leaf spring and the like. The torsion spring is usually embedded in the unfolding mechanism, the assembly process is relatively complicated, and the torsion spring needs to be integrally disassembled when replaced; the volute spring has a complex structure, high processing cost and long period.
Disclosure of Invention
An object of this application is to provide a satellite sailboard deployment mechanism and microsatellite to solve the current elastic component of solar wing hinge that exists among the prior art to a certain extent and inlay in among the deployment mechanism, the assembly process is loaded down with trivial details relatively, changes the torsional spring and needs whole dismantlement, leads to processing, high, the long technical problem of cycle cost of maintenance cost.
The application provides a satellite sailboard deployment mechanism, includes:
the fixed hinge is used for being connected with the satellite body;
the rotating hinge comprises a first hinge part and a connecting part connected with the first hinge part, the first hinge part is hinged to the fixed hinge, and the connecting part is used for connecting a satellite sailboard;
the first fixing piece is arranged on the surface of the rotating hinge;
the second fixing piece is arranged on the surface of the fixing hinge;
one end of the driving piece is connected with the first fixing piece, and the other end of the driving piece is connected with the second fixing piece.
In the above technical solution, further, the fixed hinge includes:
the fixed platform is used for being connected with the satellite body;
the second hinge part is arranged on the fixed platform, and the first hinge part is hinged with the second hinge part.
In any of the above technical solutions, further, the satellite windsurfing board deployment mechanism further comprises a locking assembly, the locking assembly comprising:
a locking member, the second hinge portion being formed with a mounting portion, the locking member being provided to the mounting portion;
the elastic component, set up in the installation department, the locking piece with the elastic component is connected under the effect of elastic component, the locking piece has all the time and keeps away from the trend of installation department.
In any of the above technical solutions, further, the first hinge portion is formed with a locking portion, and when the rotating hinge rotates from an initial position to a deployed position with respect to the fixed hinge, a portion of the locking member is connected with the locking portion under the action of the elastic member so that the rotating hinge and the fixed hinge are locked at the deployed position.
In any one of the above technical solutions, the locking assembly further includes a blocking member, the blocking member is disposed on the mounting portion and connected to the second hinge portion to block the elastic member in the mounting portion, and one end of the elastic member is connected to the blocking member.
In any of the above technical solutions, further, the first fixing member protrudes relative to the first hinge portion, and the first fixing member is provided with a first fixing pin;
the second fixing piece is protruded relative to the second hinging part and is provided with a second fixing pin, one end of the driving piece is connected with the first fixing pin, and the other end of the driving piece is connected with the second fixing pin.
In any of the above technical solutions, further, the driving member is a tension spring, and when the rotating hinge is located at the initial position relative to the fixed hinge, the tension spring is in a stretched state; when the rotating hinge is located at the unfolding position relative to the fixed hinge, the tension spring is in a contracting state.
In any of the above technical solutions, further, the first hinge portion has a flat plate structure, and an end surface of the flat plate structure facing the second hinge portion is an arc surface;
the second hinge part is provided with a mounting groove, and the part of the flat plate structure of the first hinge part, which is provided with the cambered surface, is positioned in the mounting groove and is hinged with the second hinge part through a hinge shaft.
In any of the above technical solutions, further, the second hinge portion is provided with a limit baffle, and when the rotating hinge rotates to the unfolding position relative to the fixed hinge, the rotating hinge is blocked by the limit baffle.
The application also provides a microsatellite, including satellite body, satellite sailboard and the satellite sailboard deployment mechanism of above-mentioned arbitrary embodiment, satellite sailboard deployment mechanism's fixed hinge with this body coupling of satellite, the connecting portion of rotation hinge with the satellite sailboard is connected, has this satellite sailboard deployment mechanism's whole beneficial technological effects, here, no longer gives unnecessary details.
Compared with the prior art, the beneficial effects of this application do:
the application provides a satellite windsurfing board deployment mechanism includes: the fixed hinge is connected with the satellite body; the rotating hinge comprises a first hinge part and a connecting part connected with the first hinge part, the first hinge part is hinged to the fixed hinge, and the connecting part is connected with a satellite sailboard; the first fixing piece is arranged on the surface of the rotating hinge; the second fixing piece is arranged on the surface of the fixing hinge; one end of the driving piece is connected with the first fixing piece, and the other end of the driving piece is connected with the second fixing piece.
The application provides a satellite sailboard deployment mechanism, the driving piece assembles in whole deployment mechanism's outside as the power supply, can be according to the form of satellite sailboard, size, the reliable degree of driving piece is changed in order to ensure satellite sailboard deployment process and when the deployment position to the load that factors such as material correspond the difference, and overhaul, when needing to change the driving piece in the maintenance process, need not carry out the dismouting to deployment mechanism whole, the simple easy operation of change process of driving piece, need not carry out special treatment to other structures and the part of this satellite sailboard deployment mechanism, thereby effectively reduce the holistic processing of deployment mechanism, the cost and the efficiency of maintenance.
The microsatellite comprises the satellite sailboard unfolding mechanism, so that the sailboard of the microsatellite is unfolded relative to the satellite through the satellite sailboard unfolding mechanism, the overhauling and maintenance processes are convenient, and the sailboard can be locked in the unfolding position after being unfolded in place, and the stability is high.
Drawings
In order to more clearly illustrate the detailed description of the present application or the technical solutions in the prior art, the drawings needed to be used in the detailed description of the present application or the prior art description will be briefly introduced below, and it is obvious that the drawings in the following description are some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative efforts.
Fig. 1 is a schematic structural diagram of a satellite windsurfing board deployment mechanism provided in an embodiment of the present application in an initial position;
FIG. 2 is a schematic view of another configuration of a satellite windsurfing board deployment mechanism provided in accordance with an embodiment of the present application in an initial position;
FIG. 3 is a schematic structural view of a satellite windsurfing board deployment mechanism provided in an embodiment of the present application in a deployed position;
FIG. 4 is a schematic structural diagram of a satellite windsurfing board deployment mechanism provided in an embodiment of the present application;
FIG. 5 is a schematic structural diagram of a fixed hinge of a satellite windsurfing board unfolding mechanism provided by an embodiment of the present application;
fig. 6 is a schematic structural diagram of a rotating hinge of a satellite windsurfing board unfolding mechanism provided by an embodiment of the application.
Reference numerals are as follows:
1-rotating hinge, 101-first hinge part, 1011-arc surface, 102-connecting part, 103-first hinge hole, 104-locking part, 2-fixed hinge, 201-fixed platform, 202-second hinge part, 2021-first hinge arm, 2022-second hinge arm, 203-limit baffle, 204-mounting part, 3-driving part, 4-first fixing part, 401-first fixing pin, 5-second fixing part, 501-second fixing pin, 6-locking component, 601-locking part, 602-elastic part, 603-blocking component, 7-hinge shaft and 8-satellite sailboard.
Detailed Description
The technical solutions of the present application will be described clearly and completely with reference to the accompanying drawings, and it is to be understood that the described embodiments are only a part of the embodiments of the present application, and not all of the embodiments.
The components of the embodiments of the present application, generally described and illustrated in the figures herein, can be arranged and designed in a wide variety of different configurations. Thus, the following detailed description of the embodiments of the present application, presented in the accompanying drawings, is not intended to limit the scope of the claimed application, but is merely representative of selected embodiments of the application.
All other embodiments obtained by a person of ordinary skill in the art based on the embodiments in the present application without making any creative effort belong to the protection scope of the present application.
In the description of the present application, it should be noted that the terms "center", "upper", "lower", "left", "right", "vertical", "horizontal", "inner", "outer", and the like indicate orientations or positional relationships based on the orientations or positional relationships shown in the drawings, and are only for convenience of description and simplicity of description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus, should not be construed as limiting the present application. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present application, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in this application will be understood to be a specific case for those of ordinary skill in the art.
A satellite windsurfing board deployment mechanism and a microsatellite according to an embodiment of the present application are described below with reference to fig. 1 to 6.
Referring to fig. 1-6, embodiments of the present application provide a satellite windsurfing board deployment mechanism comprising: the satellite navigation system comprises a fixed hinge 2, a rotating hinge 1, a driving piece 3 and a locking assembly 6, wherein the fixed hinge 2 is hinged with the rotating hinge 1, the fixed hinge 2 is arranged on a satellite body, and the rotating hinge 1 is connected with a satellite sailboard 8; the surface of the rotating hinge 1 is provided with a first fixing part 4, the surface of the fixed hinge 2 is provided with a second fixing part 5, and the driving part 3 is respectively connected with the first fixing part 4 and the second fixing part 5, so that the rotating hinge 1 can rotate relative to the fixed hinge 2 under the action of the driving part 3, and the satellite sailboard 8 can be unfolded relative to the satellite body; in an initial state, the satellite sailboard 8 is close to the satellite body and is in a folded state, the rotating hinge 1 is at an initial position relative to the fixed hinge 2, after the rotating hinge 1 rotates relative to the fixed hinge 2 by a preset angle to reach a deployed position, the satellite sailboard 8 is deployed relative to the satellite body, and at the moment, the locking assembly 6 locks the rotating hinge 1 at a current position.
It should be noted that, the satellite sailboard 8 is provided with a pressing point (not shown in the drawings, the pressing and folding of the satellite sailboard 8 in an initial state is the prior mature technology, and will not be described herein too much), when in an initial position, the pressing point is in a locked state, so that the satellite sailboard 8 and the satellite body are in a folded state, at this time, the driving element 3 does not work, so that the satellite sailboard 8 and the satellite body can be maintained in the locked state, when the satellite sailboard 8 needs to be unfolded, the control system of the satellite body controls to release the pressing point, the locked state between the satellite sailboard 8 and the satellite body is cancelled, and at this time, the driving element 3 starts to work, and drives the satellite sailboard 8 to be unfolded relative to the satellite body.
Specifically, the fixed hinge 2 includes a fixed platform 201, the fixed platform 201 is formed with a second hinge portion 202, the second hinge portion 202 and the fixed platform 201 have an integrated structure, the fixed platform 201 has a flat plate structure, and the flat plate structure of the fixed platform 201 is formed with a hole structure for passing through a bolt, a screw, a pin or other fastener to connect the fixed platform 201 with the satellite body.
The second hinge portion 202 includes a first hinge arm 2021 and a second hinge arm 2022 disposed parallel to and facing each other, a limit stop 203 is disposed between the first hinge arm 2021 and the second hinge arm 2022, and preferably, both ends of the limit stop 203 are respectively connected to the first hinge arm 2021 and the second hinge arm 2022, so that the first hinge arm 2021, the second hinge arm 2022 and the limit stop 203 form a mounting groove for receiving and mounting the first hinge portion 101 and allowing the first hinge portion 101 to rotate above the fixed platform 201.
Further, the first hinge portion 101 has a flat plate structure, a portion of the first hinge portion 101 is disposed in the mounting groove, the first hinge portion 101 is formed with a first hinge hole 103, the first hinge arm 2021 is formed with a second hinge hole, the second hinge arm 2022 is formed with a third hinge hole, the first hinge portion 101 and the second hinge portion 202 are hinged by a hinge shaft 7, an end cap is disposed at one end of the hinge shaft 7, and the other end of the hinge shaft 7 sequentially passes through the second hinge hole, the first hinge hole 103 and the third hinge hole and is locked by a bolt to hinge the first hinge portion 101 and the second hinge portion 202.
Further, since the first hinge portion 101 has a flat plate structure, so that the first hinge portion 101 has a certain thickness, the first hinge portion 101 includes two surfaces facing each other and a side surface located between the two surfaces, preferably, the side surface includes an arc surface 1011 and planes located at two ends of the arc and naturally transited to the arc surface 1011, the end surface corresponding to the portion of the first hinge portion 101 located in the installation groove is the arc surface 1011, in a state where the first hinge portion 101 is located in the installation groove and in a process where the first hinge portion 101 rotates relative to the installation groove, the arc surface 1011 of the first hinge portion 101 can ensure the smoothness of the rotation of the first hinge portion 101 relative to the installation groove, ensure the smooth unfolding of the satellite windsurfing board 8, and when the first hinge portion 101 rotates in place, the plane of the first hinge portion 101 naturally transited to the arc surface 1011 contacts with the limit baffle 203, so that the limit baffle 203 limits the first hinge portion 101, the first hinge part 101, i.e. the rotating hinge 1, is blocked from further rotation, so that the satellite windsurfing board 8 stops in the current unfolded position, while the rotating hinge 1 and the fixed hinge 2 are locked in the current state by the locking assembly 6.
In addition, it should be noted that the rotation angle range of the first hinge part 101 relative to the installation groove can be adjusted by adjusting the distance between the limiting baffle plate 203 and the first hinge part 101, when the distance between the limiting baffle plate 203 and the first hinge part 101 is longer, the rotation angle between the rotating hinge 1 and the fixed hinge 2 is larger in the unfolding position, and at this time, the angle between the satellite sailboard 8 and the satellite body is a right angle or an obtuse angle; when the distance between the limit baffle 203 and the first hinge 101 is short, the rotation angle between the rotating hinge 1 and the fixed hinge 2 is large in the unfolded position, and at this time, the angle between the satellite windsurfing board 8 and the satellite body is a right angle or an acute angle.
Further, the first hinge portion 101 is connected to a plate-shaped connecting portion 102 for connecting the satellite windsurfing board 8, a plurality of hole structures are formed on the connecting portion 102, and after the connecting portion 102 is disposed to face the satellite windsurfing board 8, the connecting portion 102 is inserted into the hole structures on the connecting portion 102 by using screws, bolts, nuts or other types of fasteners to connect the connecting portion 102 with the satellite windsurfing board 8.
Further, the first fixing member 4 is disposed on a plane portion of a side surface of the first hinge portion 101 except for the arc surface 1011, the first fixing member 4 has a rod structure or a column structure and is protruded relative to the first hinge portion 101, and a first fixing pin 401 is detachably disposed on an end portion of the first fixing member 4 away from the first hinge portion 101; the second fixing piece 5 is arranged on a side wall surface of the limiting baffle plate 203 facing the outside of the mounting groove, the second fixing piece 5 also has a rod structure or a column structure and is convex relative to the limiting baffle plate 203, a second fixing pin 501 is detachably arranged at one end part of the second fixing piece 5 far away from the limiting baffle plate 203, one end of the driving piece 3 is connected with the first fixing pin 401, and the other end of the driving piece 3 is connected with the second fixing pin 501.
Further, the driving member 3 is specifically a tension spring, two ends of the tension spring are respectively provided with a hook, the hooks at two ends of the tension spring are respectively and fixedly connected with the first fixing pin 401 and the second fixing pin 501, in an initial state, that is, when the rotating hinge 1 is at an initial position relative to the fixing hinge 2, the tension spring is in a large-amplitude stretching state, and a certain elastic potential energy continues to be stored, after the pressing point of the satellite sailboard 8 is released, after the satellite sailboard 8 loses the binding effect of the satellite body on the satellite sailboard 8, the tension spring is stretched by itself and has the elastic potential energy to gradually recover to a shrinking state, in the process, the unfolding of the satellite sailboard 8 is completed until the satellite sailboard 8 is blocked by the limiting baffle 203 after rotating to the unfolding position along with the first hinge portion 101, and at this time, the arc surface 1011 of the first hinge portion 101 is just arranged facing the fixing platform 201.
Further, the locking assembly 6 comprises: the blocking member 601, the elastic piece 602 and the blocking member 603, preferably, an outer wall surface of the first hinge arm 2021, that is, a side wall surface facing away from the second hinge arm 2022 is provided with a mounting portion 204, the mounting portion 204 is specifically a groove body structure formed in the first hinge arm 2021, and a through hole is formed at a position where a groove bottom of the groove body structure is located in the middle so that the first hinge arm 2021 penetrates through the inside and the outside, the locking piece 601 is cylindrically penetrated in the through hole of the mounting portion 204, the elastic piece 602 is specifically a compression spring, the elastic piece 602 is located in the mounting portion 204, and one end of the elastic piece 602 is connected with one end of the locking piece 601 facing the outer wall surface of the first hinge arm 2021, the blocking member 603 is in a flat plate shape, and the blocking member 603 is in the same shape as the groove body structure of the mounting portion 204 so that the blocking member 603 can be embedded in the mounting portion 204.
Further, the blocking member 603 is formed with a hole structure, the number of the hole structures of the blocking member 603 is at least two, the at least two hole structures are arranged at intervals, a threaded hole is provided at a position where the groove bottom of the mounting portion 204 faces the two hole structures, the blocking member 603 is screwed with the threaded hole of the mounting portion 204 after penetrating the hole structure of the blocking member 603 with a bolt, so that the blocking member 603 can be fixed to the mounting portion 204, while an end of the elastic member 602 away from the locking member 601 is in contact with the blocking member 603 so that the elastic member 602 is pressed, so that the elastic member 602 can apply an elastic force to the locking member 601, the locking member 601 always has a tendency to protrude from the through hole toward the mounting groove (a partial space between the first hinge arm 2021 and the second hinge arm 2022), during rotation of the rotary hinge 1 relative to the fixed hinge 2 from an initial position toward a deployed position, an end of the locking member 601 is blocked by a wall surface of the first hinge portion 101, the elastic member 602 is always in a contracted state, so that the locking member 601 is retained in the through hole of the mounting portion 204.
Further, the first hinge hole 103 of the first hinge part 101 is formed near the center of the first hinge part 101, the locking part 104 is formed near the first hinge hole 103 of the first hinge part 101, the locking part 104 is formed as a through hole or a groove on one side surface of the first hinge part 101 facing the first hinge arm 2021, when the rotating hinge 1 rotates to the unfolded position, the locking part 601 just faces the locking part 104, and the locking part 601 enters the locking part 104 under the action of the elastic part 602, so that the rotating hinge 1 and the fixed hinge 2 are locked in the current state, further rotation of the rotating hinge 1 is avoided, and the impact force for unfolding to the right position is effectively reduced.
Further, after the locking member 601 and the locking portion 104 are inserted and locked with each other, the driving member 3 (the tension spring) still has an elastic margin, and does not completely contract to a natural state, and a certain elastic force is still applied to the first fixing member 4 and the second fixing member 5, so that the rotating hinge 1 and the fixed hinge 2 are ensured to be kept at the unfolding positions, and the reliability of unfolding the satellite sailboard 8 is improved.
To sum up, the satellite sailboard deployment mechanism that this application provided, the driving piece assembles in whole deployment mechanism's outside as the power supply, can be according to the form of satellite sailboard, size, the reliable degree of driving piece is changed in order to ensure satellite sailboard deployment process and when the deployment position to factors such as material correspond different loads, and overhaul, when the driving piece need be changed in the maintenance process, need not carry out the dismouting to deployment mechanism whole, the simple easy operation of change process of driving piece, need not carry out special treatment to other structures and the part of this satellite sailboard deployment mechanism, thereby effectively reduce the holistic processing of deployment mechanism, the cost and the efficiency of maintenance.
In addition, the satellite sailboard unfolding mechanism provided by the application is further provided with an automatic locking function, and the stability and the reliability of the satellite sailboard after being unfolded in place are further enhanced.
The embodiment of the application also provides a microsatellite which comprises the satellite sailboard unfolding mechanism in any one of the embodiments, so that the microsatellite has all the beneficial technical effects of the satellite sailboard unfolding mechanism, and the details are not repeated herein.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solutions of the present application, and not to limit the same; although the present application has been described in detail with reference to the foregoing embodiments, it should be understood by those of ordinary skill in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and these modifications or substitutions do not depart from the scope of the technical solutions of the embodiments of the present application.
Claims (6)
1. A satellite windsurfing board deployment mechanism comprising:
the fixed hinge is used for being connected with the satellite body;
the rotating hinge comprises a first hinge part and a connecting part connected with the first hinge part, the first hinge part is hinged to the fixed hinge, and the connecting part is used for connecting a satellite sailboard;
the first fixing piece is arranged on the surface of the rotating hinge;
the second fixing piece is arranged on the surface of the fixing hinge;
one end of the driving piece is connected with the first fixing piece, and the other end of the driving piece is connected with the second fixing piece;
the stationary hinge includes:
the fixed platform is used for being connected with the satellite body;
the second hinge part is arranged on the fixed platform, and the first hinge part is hinged with the second hinge part;
further comprising a locking assembly, the locking assembly comprising:
a locking member, the second hinge portion being formed with a mounting portion, the locking member being provided to the mounting portion;
the elastic piece is arranged on the mounting part, the locking piece is connected with the elastic piece, and the locking piece always has a tendency of being far away from the mounting part under the action of the elastic piece;
the first hinge part is formed with a locking part, and when the rotating hinge rotates relative to the fixed hinge from an initial position to a spreading position, part of the locking part is connected with the locking part under the action of the elastic part so that the rotating hinge and the fixed hinge are locked at the spreading position;
when the locking piece and the locking part are locked with each other, the driving piece has an elastic margin;
the driving piece is a tension spring, and when the rotating hinge is located at the initial position relative to the fixed hinge, the tension spring is in a stretching state; when the rotating hinge is located at the unfolding position relative to the fixed hinge, the tension spring is in a contracted state.
2. The satellite windsurfing board deployment mechanism of claim 1, wherein said locking assembly further comprises a blocking member arranged at said mounting portion and connected to said second hinge portion for blocking said elastic member in said mounting portion, said elastic member having one end connected to said blocking member.
3. The satellite windsurfing board deployment mechanism of claim 1 wherein said first stationary member is raised relative to said first hinged portion and wherein said first stationary member is provided with a first securing pin;
the second fixing piece is protruded relative to the second hinge portion and provided with a second fixing pin, one end of the driving piece is connected with the first fixing pin, and the other end of the driving piece is connected with the second fixing pin.
4. The satellite windsurfing board deployment mechanism of any one of claims 1 to 3 wherein said first hinged portion has a flat plate structure, an end surface of said flat plate structure facing said second hinged portion being an arc;
the second hinge part is provided with a mounting groove, and the part of the flat plate structure of the first hinge part, which is provided with the cambered surface, is positioned in the mounting groove and is hinged with the second hinge part through a hinge shaft.
5. A satellite windsurfing board deployment mechanism according to claim 1, wherein said second hinged portion is provided with a stop flap, said rotary hinge being stopped by said stop flap when said rotary hinge is rotated relative to said stationary hinge to said deployed position.
6. A microsatellite comprising a satellite body, a satellite windsurfing board and a satellite windsurfing board deployment mechanism as defined in any one of claims 1 to 5, wherein a fixed hinge of said satellite windsurfing board deployment mechanism is connected to said satellite body and a connecting portion of said rotating hinge is connected to said satellite windsurfing board.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111359637.6A CN113895658B (en) | 2021-11-17 | 2021-11-17 | Satellite sailboard unfolding mechanism and microsatellite |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202111359637.6A CN113895658B (en) | 2021-11-17 | 2021-11-17 | Satellite sailboard unfolding mechanism and microsatellite |
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| Publication Number | Publication Date |
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| CN113895658A CN113895658A (en) | 2022-01-07 |
| CN113895658B true CN113895658B (en) | 2022-07-26 |
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| CN202111359637.6A Active CN113895658B (en) | 2021-11-17 | 2021-11-17 | Satellite sailboard unfolding mechanism and microsatellite |
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| CN115447805B (en) * | 2022-11-09 | 2023-03-21 | 哈尔滨工业大学 | Unfolding device for sailboard of micro-nano satellite and micro-nano satellite |
| CN117154372B (en) * | 2023-10-31 | 2024-01-02 | 银河航天科技(南通)有限公司 | Satellite turns over board expansion device with angle modulation |
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| US3184743A (en) * | 1961-03-07 | 1965-05-18 | Bell Telephone Labor Inc | Antenna structures for communication satellites |
| CN206368632U (en) * | 2016-11-25 | 2017-08-01 | 胡国衡 | A kind of structure-improved of durable type oven hinge |
| CN109229433B (en) * | 2018-10-29 | 2020-04-28 | 浙江大学 | Fixing and separating device for satellite and rocket of pico-satellite |
| CN110707466B (en) * | 2019-11-12 | 2024-05-17 | 顺科智连技术股份有限公司 | Connector locking device |
| CN111038742A (en) * | 2019-12-31 | 2020-04-21 | 陕西国宇星空科技有限公司 | Folding and unfolding mechanism, solar wing and micro-nano satellite |
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