CN213186961U

CN213186961U - Installation structure of spacecraft circuit board

Info

Publication number: CN213186961U
Application number: CN202022046793.4U
Authority: CN
Inventors: 陈鋆莹; 田小兰
Original assignee: Shenzhen Donghai Antai Industrial Co ltd
Current assignee: Shenzhen Donghai Antai Industrial Co ltd
Priority date: 2020-09-18
Filing date: 2020-09-18
Publication date: 2021-05-11
Anticipated expiration: 2030-09-18

Abstract

The utility model relates to a mounting structure of a spacecraft circuit board, which comprises a spacecraft shell, a mounting groove arranged inside the spacecraft shell, a mainboard and a supporting plate; through fixing the mainboard on the layer board, the layer board passes through the cross axle, first elastomeric element and second elastomeric element install in the mounting groove, thereby realize that the mainboard can move about in the mounting groove with elasticity, automatically controlled buckle is fixed the layer board side under the normal condition, thereby it is fixed with the mainboard, in case unmanned spacecraft and remote control equipment lose the antithetical couplet appear, the automatically controlled buckle of master control loosens, become elastic activity state with layer board and mainboard by the fixed state, unmanned spacecraft is when meetting violent collision, absorb energy and cushion by first elastomeric element and second elastomeric element, thereby guarantee that the mainboard is not impaired.

Description

Installation structure of spacecraft circuit board

Technical Field

The utility model relates to a field specifically is a mounting structure of spacecraft circuit board.

Background

In the use of unmanned vehicles, often can lead to unmanned vehicles to fall because unmanned vehicles loses the antithetical couplet with the remote controller at the flight in-process, unmanned vehicles often can lead to the mainboard impaired after falling to lead to the unable normal work of orientation module, make to be difficult to search the unmanned vehicles who falls according to unmanned vehicles's locating information, and the mainboard is whole unmanned vehicles' core, and the impaired maintenance cost that can lead to unmanned vehicles of mainboard is high.

SUMMERY OF THE UTILITY MODEL

In view of this, the utility model aims at providing a mounting structure of spacecraft circuit board can be when unmanned spacecraft and remote controller lose the antithetical couplet, the inside circuit board of automatic protection.

The utility model discloses a mounting structure of a spacecraft circuit board, which comprises a spacecraft shell, a mounting groove arranged in the spacecraft shell, a mainboard and a supporting plate; the supporting plate is in the same shape as the mounting groove and is mounted in the mounting groove, a cross shaft is fixedly arranged at the center of the bottom of the mounting groove, a first elastic part is fixedly arranged at the top of the cross shaft, the top of the first elastic part is fixedly connected with the center of the top of the supporting plate, and the edge of the supporting plate is connected with the edge of the bottom of the mounting groove through a plurality of second elastic parts; be equipped with a plurality of automatically controlled buckles that are used for fixed layer board on the lateral wall of mounting groove, mainboard fixed mounting is on the layer board, and automatically controlled buckle is connected with the control circuit electricity on the mainboard.

Further, automatically controlled buckle is including setting up horizontal spout, fixture block, spring and coil on the lateral wall of mounting groove, the coil is fixed to be set up in the spout bottom, and with control circuit on the mainboard connects, the fixture block setting in the spout and with spout sliding connection, the one end of spring and the bottom fixed connection of spout, the other end and the fixture block fixed connection of spring, the inside magnet that is equipped with of fixture block is equipped with the orientation on the fixture block the draw-in groove of layer board, the draw-in groove will the edge of layer board is fixed.

Further, the cross shaft comprises a first rotating piece and a second rotating piece, the first rotating piece is hinged with the center of the bottom of the mounting groove through a first axis, the second rotating piece is hinged with the top of the first rotating piece through a second axis, and the top of the second rotating piece is fixedly connected with the bottom end of the first elastic component; the first axis and the second rotating shaft are both in the horizontal direction, and the first axis is vertical to the second rotating shaft.

Further, the maximum rotatable amplitude of the first rotating member and the second rotating member does not exceed 15 °.

Further, the first elastic component and the second elastic component are both springs.

The utility model has the advantages that: the utility model discloses a mounting structure of spacecraft circuit board, through fixing the mainboard on the layer board, the layer board passes through the cross, first elastomeric element and second elastomeric element are installed in the mounting groove, thereby realize that the mainboard can move about in the mounting groove with elasticity, automatically controlled buckle is fixed the layer board side under the normal condition, thereby it is fixed with the mainboard, in case unmanned spacecraft loses the antithetical couplet with remote control equipment appears, the automatically controlled buckle of master control loosens, become elastic activity state with layer board and mainboard by the stationary state, unmanned spacecraft is when meetting violent collision, absorb energy and buffering by first elastomeric element and second elastomeric element, thereby guarantee that the mainboard is not impaired.

Drawings

The invention will be further described with reference to the following figures and examples:

fig. 1 is a schematic structural view of the present invention;

fig. 2 is a schematic structural view of the cross shaft of the present invention.

The reference numbers are as follows: the device comprises a shell of the spacecraft, a mainboard 2, a supporting plate 3, an electric control buckle 4, a mounting groove 11, a cross shaft 12, a first elastic component 13, a second elastic component 14, a sliding groove 41, a clamping block 42, a spring 43, a coil 44, a first rotating component 121 and a second rotating component 122.

Detailed Description

As shown in fig. 1-2: the mounting structure of the spacecraft circuit board comprises a spacecraft shell 1, a mounting groove 11 arranged in the spacecraft shell 1, a main board 2 and a supporting plate 3; the shape of the supporting plate 3 is consistent with that of the mounting groove 11 and is mounted in the mounting groove 11, a cross shaft 12 is fixedly arranged at the center of the bottom of the mounting groove 11, a first elastic part 13 is fixedly arranged at the top of the cross shaft 12, the top of the first elastic part 13 is fixedly connected with the center of the top of the supporting plate 3, and the edge of the supporting plate 3 is connected with the edge of the bottom of the mounting groove 11 through a plurality of second elastic parts 14; be equipped with a plurality of automatically controlled buckles 4 that are used for fixed layer board 3 on the lateral wall of mounting groove 11, mainboard 2 fixed mounting is on layer board 3, and automatically controlled buckle 4 is connected with the control circuit electricity on the mainboard 2.

The utility model discloses a mounting structure of spacecraft circuit board, through fixing mainboard 2 on layer board 3, layer board 3 passes through cross 12, first elastomeric element 13 and second elastomeric element 14 are installed in mounting groove 11, thereby realize that mainboard 2 can move about in mounting groove 11 with elasticity, automatically controlled buckle 4 is fixed with layer board 3 side under the normal condition, thereby it is fixed with mainboard 2, in case unmanned spacecraft loses the antithetical couplet with remote control equipment appears, the automatically controlled buckle of master control 4 loosens, become elasticity activity state with layer board 3 and mainboard 2 by fixed state, unmanned spacecraft is when meetting violent collision, absorb energy and cushion by first elastomeric element 13 and second elastomeric element 14, thereby guarantee that mainboard 2 is not impaired.

In this embodiment, the electronic control buckle 4 includes a transverse sliding slot 41 disposed on the side wall of the mounting slot 11, a latch 42, a spring 43 and a coil 44, the coil 44 is fixedly disposed at the bottom of the sliding slot 41 and connected to the control circuit on the main board 2, the latch 42 is disposed in the sliding slot 41 and slidably connected to the sliding slot 41, one end of the spring 43 is fixedly connected to the bottom of the sliding slot 41, the other end of the spring 43 is fixedly connected to the latch 42, a magnet is disposed inside the latch 42, a slot facing the support plate 3 is disposed on the latch 42, the slot fixes the edge of the support plate 3, under normal conditions, the latch 42 extends out of the sliding slot 41 under the action of the spring 43 to fix the edge of the support plate 3, once the control chip on the main board 2 determines that the control chip is disconnected from the remote controller, the coil 44 is automatically energized through the control circuit, and magnetic force is generated after the coil 44 is energized to attract the, and the spring 43 is compressed, the first elastic component 13 at the center of the bottom of the supporting plate 3 drags up the supporting plate 3, so that the supporting plate 3 and the main plate 2 on the supporting plate 3 are converted into a movable state, and the hard landing of the main plate 2 when the unmanned spacecraft falls is prevented.

In this embodiment, the cross 12 includes a first rotating member 121 and a second rotating member 122, the first rotating member 121 is hinged to the center of the bottom of the mounting slot 11 by a first axis, the second rotating member 122 is hinged to the top of the first rotating member 121 by a second axis, and the top of the second rotating member 122 is fixedly connected to the bottom of the first elastic component 13; the first axis and the second axis are both in the horizontal direction, and the first axis is perpendicular to the second axis, so that the rotation on the two axes is realized, the rotation in multiple directions is realized through the rotation fit on the two axes, and when the unmanned spacecraft lands, which part is specifically landed cannot be judged, so that the stress energy storage of the first elastic component 13 and the second elastic component 14 can be effectively realized through the cross shaft 12 no matter which part of the unmanned spacecraft is landed, and the soft landing of the mainboard 2 is realized.

In this embodiment, the maximum rotatable amplitude of the first rotating member 121 and the second rotating member 122 does not exceed 15 °, since the pallet 3 and the main board 2 do not need a large rotatable range, and at the same time, the main board 2 has many connecting lines, and since the main board 2 cannot be rotated by a large amplitude, the rotatable range is limited by the shapes of the first rotating member 121 and the second rotating member 122, and the side of the hinge joint of the first rotating member 121 and the second rotating member 122 is limited by a limited block, thereby limiting the rotatable range of the device.

In the present embodiment, the first elastic member 13 and the second elastic member 14 are both springs 43.

Finally, although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the present invention can be modified or replaced by other means without departing from the spirit and scope of the present invention, which should be construed as limited only by the appended claims.

Claims

1. A mounting structure of spacecraft circuit board is characterized in that: the spacecraft mounting structure comprises a spacecraft shell, a mounting groove arranged in the spacecraft shell, a main board and a supporting plate; the supporting plate is in the same shape as the mounting groove and is mounted in the mounting groove, a cross shaft is fixedly arranged at the center of the bottom of the mounting groove, a first elastic part is fixedly arranged at the top of the cross shaft, the top of the first elastic part is fixedly connected with the center of the top of the supporting plate, and the edge of the supporting plate is connected with the edge of the bottom of the mounting groove through a plurality of second elastic parts; be equipped with a plurality of automatically controlled buckles that are used for fixed layer board on the lateral wall of mounting groove, mainboard fixed mounting is on the layer board, and automatically controlled buckle is connected with the control circuit electricity on the mainboard.

2. A spacecraft circuit board mounting structure according to claim 1, wherein: automatically controlled buckle is including setting up horizontal spout, fixture block, spring and coil on the lateral wall of mounting groove, the coil is fixed to be set up in the spout bottom, and with control circuit on the mainboard connects, the fixture block setting in the spout and with spout sliding connection, the one end of spring and the bottom fixed connection of spout, the other end and the fixture block fixed connection of spring, the inside magnet that is equipped with of fixture block, be equipped with the orientation on the fixture block the draw-in groove of layer board, the draw-in groove will the edge of layer board is fixed.

3. A spacecraft circuit board mounting structure according to claim 1, wherein: the cross shaft comprises a first rotating piece and a second rotating piece, the first rotating piece is hinged with the center of the bottom of the mounting groove through a first axis, the second rotating piece is hinged with the top of the first rotating piece through a second axis, and the top of the second rotating piece is fixedly connected with the bottom end of the first elastic component; the first axis and the second rotating shaft are both in the horizontal direction, and the first axis is vertical to the second rotating shaft.

4. A spacecraft circuit board mounting structure according to claim 3, wherein: the maximum rotatable amplitude of the first rotating member and the maximum rotatable amplitude of the second rotating member do not exceed 15 degrees.

5. A spacecraft circuit board mounting structure according to claim 1, wherein: the first elastic part and the second elastic part are both springs.