CN212890969U - Flight control assembly and mobile device - Google Patents
Flight control assembly and mobile device Download PDFInfo
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- CN212890969U CN212890969U CN202021517374.8U CN202021517374U CN212890969U CN 212890969 U CN212890969 U CN 212890969U CN 202021517374 U CN202021517374 U CN 202021517374U CN 212890969 U CN212890969 U CN 212890969U
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Abstract
The utility model relates to an unmanned air vehicle technique field specifically discloses a fly accuse subassembly and mobile device. The flight control assembly comprises a shell, a connecting plate, a flight control plate and a vibration damping piece, wherein the shell is provided with an accommodating cavity; the vibration damping piece is provided with two vibration damping pieces at intervals in the accommodating cavity along the first direction; the connecting plate is clamped between the two vibration damping pieces, one side of the connecting plate is provided with a positioning boss, the vibration damping piece adjacent to the positioning boss is provided with a positioning hole, and the positioning boss is inserted into the positioning hole; the flight control panel is arranged on one side of the connecting plate, a containing hole penetrating along the first direction is formed in the vibration damping piece adjacent to the flight control panel, and the flight control panel is arranged in the containing hole. The connecting plate presss from both sides and locates between two damping pieces to for the connecting plate damping, because fly the control panel and connect on the connecting plate, and then can realize flying the damping of control panel. The flight control panel is located the accommodation hole, is convenient for the flight control panel heat dissipation to and make the thickness of flight control subassembly reduce. The positioning boss is inserted into the positioning hole, so that the positioning of the flight control panel can be realized.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to a fly accuse subassembly and mobile device.
Background
The unmanned aerial vehicle is often provided with the flight control subassembly, and the flight control board of flight control subassembly needs to take damping measures in order to reduce the influence of external vibration to the flight control board. Among the prior art, fly to control the subassembly and include the casing, set up flying control board and damping assembly in the casing, damping assembly includes two damping gaskets, and two damping gasket fixed connection are on flying control board's upper and lower surface to respectively with the interior upper wall and the interior lower wall butt of casing. The vibration reduction assembly isolates the flight control panel from the shell, and the purpose of reducing the vibration of the flight control panel is achieved.
Among the prior art, damping subassembly greatly increased the thickness of flying to control the subassembly to flying to control the board and pressing from both sides between two damping gaskets, making on the one hand fly to control the board and be difficult to the heat dissipation, on the other hand makes flying to control the board and be difficult to realize the location on the horizontal direction.
Therefore, a flight control assembly is needed to solve the above problems.
SUMMERY OF THE UTILITY MODEL
An object of the utility model is to provide a fly accuse subassembly and mobile device to reduce the thickness that flies the accuse subassembly, improve the radiating efficiency who flies the control panel, and realize the location that flies the control panel fast and effectively.
To achieve the purpose, the utility model adopts the following technical proposal:
a flight control assembly comprising:
a housing having an accommodating chamber;
the vibration damping piece is arranged in the accommodating cavity at intervals along a first direction, and the two vibration damping pieces are respectively abutted against the inner wall of the accommodating cavity;
the connecting plate is clamped between the two vibration damping pieces, a positioning boss is arranged on one side of the connecting plate, a positioning hole is formed in the vibration damping piece adjacent to the positioning boss, and the positioning boss is inserted into the positioning hole;
the flying control plate is arranged on one side, far away from the positioning boss, of the connecting plate, a containing hole penetrating along the first direction is formed in the vibration damping piece adjacent to the flying control plate, and the flying control plate is arranged in the containing hole.
Preferably, a distance is provided between the circumferential surface of the connecting plate and the inner side wall of the accommodating cavity.
Preferably, the housing has a through hole corresponding to the receiving hole.
Preferably, the vibration damping member is in a compressed state in the accommodating cavity, and an avoiding groove for avoiding the deformation of the vibration damping member is formed in the circumferential direction of the inner side wall of the accommodating cavity.
Preferably, the housing includes a first housing and a second housing disposed in the first direction;
the first shell is provided with a first accommodating groove, and the inner wall of the first accommodating groove is provided with a first half groove;
the second shell is provided with a second accommodating groove, and the inner wall of the second accommodating groove is provided with a second half groove;
the first shell is connected with the second shell, the first accommodating groove is formed by the second accommodating groove and the accommodating cavity, and the second half groove and the first half groove form the avoiding groove.
Preferably, an annular positioning protrusion protrudes from a side wall of the first half groove, and the annular positioning protrusion can be inserted into the second half groove; or the like, or, alternatively,
and an annular positioning bulge is protruded from the side wall of the second half groove and can be inserted into the first half groove.
Preferably, one of the side wall of the first shell and the side wall of the second shell is provided with a clamping groove, and the other is provided with a clamping part which can be clamped with the clamping groove.
Preferably, the side wall of the first housing and the side wall of the second housing are both provided with a fixing portion, the fixing portion is provided with a fixing hole, and the fixing hole of the first housing is connected with the fixing hole of the second housing through a connecting piece.
Preferably, the connecting plate is made of metal.
The utility model discloses still adopt following technical scheme:
a mobile device comprises the flight control assembly.
The utility model has the advantages that:
two damping pieces set up in holding the intracavity along upper and lower direction to respectively with the inner wall butt that holds the chamber, the connecting plate presss from both sides and locates between two damping pieces, thereby for the connecting plate damping, because fly the control panel and connect on the connecting plate, consequently, and then can realize flying the damping of control panel.
The damping piece adjacent to the flight control panel is provided with a containing hole penetrating along the first direction, and the flight control panel is positioned in the containing hole, so that the flight control panel is convenient to dissipate heat on one hand, and on the other hand, the thickness of the flight control assembly is reduced. The positioning boss is inserted into the positioning hole, so that the connecting plate can be quickly positioned, and the flight control plate is connected to the connecting plate, so that the positioning of the flight control plate can be realized.
Drawings
Fig. 1 is a schematic structural diagram of a flight control assembly provided in an embodiment of the present invention;
FIG. 2 is an exploded view of a flight control assembly provided by an embodiment of the present invention;
fig. 3 is a cross-sectional view of a flight control assembly provided by an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a second housing according to an embodiment of the present invention;
fig. 5 is a schematic structural diagram of a first housing according to an embodiment of the present invention.
In the figure:
10. a flight control module; 20. an interface board;
1. a housing; 11. a through hole; 12. an avoidance groove; 121. a first half-tank; 122. a second half-tank; 13. a first housing; 131. a fastening part; 132. an annular positioning bulge; 14. a second housing; 141. a card slot; 15. a fixed part; 151. a fixing hole;
2. a vibration damping member; 21. an accommodation hole; 22. positioning holes;
4. a connecting plate; 41. positioning the boss;
5. a flight control panel; 51. a circuit board; 52. and a functional module.
Detailed Description
The technical solution of the present invention is further explained by the following embodiments with reference to the accompanying drawings. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting of the invention. It should be further noted that, for the convenience of description, only some but not all of the elements related to the present invention are shown in the drawings.
The present invention is limited to certain orientation words, and when no opposite explanation is given, the used orientation words are "upper", "lower", "left", "right", "inner" and "outer", and these orientation words are adopted for easy understanding, and therefore do not constitute a limitation to the scope of the present invention.
In the present disclosure, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may comprise direct contact between the first and second features, or may comprise contact between the first and second features not directly. Also, the first feature being "on," "above" and "over" the second feature includes the first feature being directly on and obliquely above the second feature, or merely indicating that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature includes the first feature being directly under and obliquely below the second feature, or simply meaning that the first feature is at a lesser elevation than the second feature.
In the description of the present invention, unless expressly stated or limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, e.g., as meaning permanently connected, detachably connected, or integral to one another; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meaning of the above terms in the present invention can be understood in specific cases to those skilled in the art.
The embodiment provides a flight control assembly, which is arranged on a mobile device to reduce the thickness of the flight control assembly, improve the heat dissipation efficiency of a flight control panel 5, quickly and effectively realize the positioning of the flight control panel 5, and further improve the assembly efficiency of the flight control assembly.
Referring to fig. 1, the flight control assembly provided in this embodiment includes a flight control module 10. Preferably, the flight control assembly further includes an interface board 20, and the flight control module 10 is disposed on the interface board 20 and communicatively connected to the interface board 20.
As shown in fig. 1-3, flight control module 10 includes a housing 1, a connecting plate 4, a flight control plate 5, and a damping member 2. The casing 1 is used for fixing components such as a flight control panel 5; the flight control panel 5 is used for controlling the flight of the mobile equipment; the connecting plate 4 is used for connecting the flight control plate 5, so that the flight control plate 5 is conveniently fixed in the shell 1; the vibration damping piece 2 is used for realizing vibration damping of the flight control panel 5 and avoiding damage to the flight control panel 5.
Specifically, the housing 1 has an accommodating cavity, two vibration damping members 2 are arranged in the accommodating cavity at intervals along a first direction, and the two vibration damping members 2 are respectively abutted to the inner wall of the accommodating cavity. The connecting plate 4 is clamped between the two vibration dampers 2, one side of the connecting plate 4 is provided with a positioning boss 41, the vibration damper 2 adjacent to the positioning boss 41 is provided with a positioning hole 22, and the positioning boss 41 is inserted into the positioning hole 22. In the present embodiment, the positioning hole 22 is disposed through the damping member 2 along the first direction, but in other embodiments, the positioning hole 22 may be a blind hole, and the positioning hole 22 only needs to be capable of positioning the positioning boss 41. The flight control panel 5 is disposed on a side of the connecting plate 4 away from the positioning boss 41, the damping member 2 adjacent to the flight control panel 5 is provided with a receiving hole 21 penetrating along a first direction, and the flight control panel 5 is disposed in the receiving hole 21.
Two damping pieces 23 set up in holding the intracavity along upper and lower direction to respectively with the inner wall butt that holds the chamber, connecting plate 4 presss from both sides and locates between two damping pieces 2, thereby for connecting plate 4 damping, because it connects on connecting plate 4 to fly control panel 5, consequently, and then can realize flying control panel 5's damping.
The damping piece 2 adjacent to the flight control panel 5 is provided with an accommodating hole 21 penetrating along the first direction, and the flight control panel 5 is located in the accommodating hole 21, so that on one hand, the heat dissipation of the flight control panel 5 is facilitated, and on the other hand, the thickness of the flight control assembly is reduced, wherein the reduced thickness is the thickness of the flight control panel 5. The positioning boss 41 is inserted into the positioning hole 22, so that the connecting plate 4 can be quickly positioned, and the flight control plate 5 is connected to the connecting plate 4, so that the flight control plate 5 can be positioned.
As shown in fig. 2, the flight control board 5 preferably includes a circuit board 51 and a function module 52 provided on the circuit board 51 for implementing a predetermined function, and the circuit board 51 is connected to the connection board 4. The functional modules 52 may include a controller module, a processor module, a sensor module, and the like. Further, the sensor module may include an inertial measurement module, a temperature sensor module, a height sensor module, a distance sensor module, and the like. The inertial measurement module comprises an acceleration sensor and a gyroscope, and can measure flight attitude information of the mobile device. Since the specific structure and operation principle of the functional module 52 are the prior art and are not the improvement point of the present invention, the detailed description is omitted here.
Preferably, the connecting plate 4 is made of metal, and when the flight control plate 5 is connected, the flight control plate 5 can be used as a counterweight, so that the requirements of the functional module 52 on the parameters of the damping material, such as hardness and damping, are reduced, and a good damping effect can be achieved.
Preferably, the shore hardness of the damping part 2 is 30 to 40, so that the damping part 2 can damp both high-frequency vibrations and low-frequency vibrations.
As shown in fig. 3, the circumferential surface of the connecting plate 4 and the inner side wall of the accommodating cavity are provided with intervals, so that the connecting plate 4 is prevented from contacting the inner wall of the accommodating cavity, and the vibration of the shell 1 is effectively prevented from being transmitted to the flight control plate 5.
Because damping piece 2 is the elastic component, for better fixed flight control panel 5, preferably, damping piece 2 is in compression state in holding the intracavity, for the convenience of damping piece 2 takes place deformation, holds the interior lateral wall in chamber and has offered the groove 12 of dodging that is used for dodging damping piece 2 and warp in the circumference.
As shown in fig. 3-5, the housing 1 includes a first housing 13 and a second housing 14 disposed along a first direction, the first housing 13 defines a first receiving groove, and an inner wall of the first receiving groove defines a first half-groove 121. The second housing 14 has a second receiving groove, the inner wall of the second receiving groove has a second half groove 122, the first housing 13 is connected to the second housing 14, the first receiving groove and the second receiving groove form a receiving cavity, and the second half groove 122 and the first half groove 121 form an avoiding groove 12. The housing 1 is formed by connecting a first housing 13 and a second housing 14, thereby facilitating assembly of the flight control assembly.
As shown in fig. 4 and 5, a fastening portion 131 is disposed on a side wall of the first housing 13, a fastening groove 141 is disposed on one side wall of the second housing 14, and the fastening portion 131 can be fastened with the fastening groove 141, so as to realize positioning and preliminary connection between the first housing 13 and the second housing 14. Of course, in other embodiments, the fastening portion 131 may be disposed on one of the side walls of the second housing 14, and the fastening groove 141 may be disposed on the side wall of the first housing 13.
In order to further improve the stability of the connection between the first casing 13 and the second casing 14, it is preferable that the fixing portions 15 are respectively disposed on the side wall of the first casing 13 and the side wall of the second casing 14, the fixing portions 15 are opened with fixing holes 151, and the fixing holes 151 of the first casing 13 and the fixing holes 151 of the second casing 14 are connected by a connecting member such as a bolt.
Specifically, the first housing 13 and the second housing 14 are formed in a substantially square configuration, and the fixing portions 15 are provided at four corners of the outer sides of the first housing 13 and the second housing 14, respectively. The first housing 13 is provided with two opposite sides with locking parts 131, and the second housing 14 is provided with a locking groove 141 at a position corresponding to the locking parts 131.
Preferably, in order to further improve the heat dissipation efficiency of the flight control panel 5, the housing 1 is opened with a through hole 11 corresponding to the receiving hole 21. The receiving hole 21 and the through hole 11 may have a square structure, a circular structure, or a polygonal structure, which is not limited herein. Furthermore, the housing 1 is also provided with a through hole 11 corresponding to the positioning hole 22.
Since the fixing hole 151 of the first housing 13 can be aligned with the fixing hole 151 of the second housing 14 only when the relative position between the first housing 13 and the second housing 14 is the predetermined position, the connecting members such as bolts can be connected to the two fixing holes 151. In order to improve the positioning efficiency between the first housing 13 and the second housing 14, it is preferable that an annular positioning protrusion 132 protrudes from a side wall of the first half groove 121, and the annular positioning protrusion 132 can be inserted into the second half groove 121 to realize the positioning between the first housing 13 and the second housing 14. Of course, in other embodiments, an annular positioning protrusion 132 may protrude from the sidewall of the second half-groove 122, and the annular positioning protrusion 132 may be inserted into the second half-groove 122.
The embodiment also provides a mobile device, which comprises the flight control assembly, so as to improve the heat dissipation efficiency and the assembly efficiency of the mobile device. Wherein, the mobile device can be an unmanned aerial vehicle, an unmanned ship, an unmanned vehicle and the like.
It is obvious that the above embodiments of the present invention are only examples for clearly illustrating the present invention, and are not intended to limit the embodiments of the present invention. Other variations and modifications will be apparent to persons skilled in the art in light of the above description. And are neither required nor exhaustive of all embodiments. Any modification, equivalent replacement, and improvement made within the spirit and principle of the present invention should be included in the protection scope of the claims of the present invention.
Claims (10)
1. A flight control assembly, comprising:
a housing (1) having a receiving cavity;
the damping piece (2) is arranged in the accommodating cavity at intervals along a first direction, and the two damping pieces (2) are respectively abutted against the inner wall of the accommodating cavity;
the connecting plate (4) is clamped between the two vibration damping pieces (2), one side of the connecting plate (4) is provided with a positioning boss (41), the vibration damping piece (2) adjacent to the positioning boss (41) is provided with a positioning hole (22), and the positioning boss (41) is inserted into the positioning hole (22);
the flying control plate (5) is arranged on one side, away from the positioning boss (41), of the connecting plate (4), an accommodating hole (21) penetrating along the first direction is formed in the vibration damping piece (2) adjacent to the flying control plate (5), and the flying control plate (5) is arranged in the accommodating hole (21).
2. Flight control assembly according to claim 1, characterized in that the circumferential surface of the connection plate (4) is provided with a spacing from the inner side walls of the accommodation chamber.
3. The flight control assembly according to claim 1, wherein the housing (1) has a through hole (11) corresponding to the receiving hole (21).
4. The flight control assembly according to claim 1, wherein the damping member (2) is in a compressed state in the accommodating cavity, and an avoiding groove (12) for avoiding deformation of the damping member (2) is formed in the circumferential direction of the inner side wall of the accommodating cavity.
5. The flight control assembly according to claim 4, wherein the housing (1) comprises a first housing (13) and a second housing (14) arranged in the first direction;
the first shell (13) is provided with a first accommodating groove, and the inner wall of the first accommodating groove is provided with a first half groove (121);
a second accommodating groove is formed in the second shell (14), and a second half groove (122) is formed in the inner wall of the second accommodating groove;
the first casing (13) with second casing (14) are connected, first holding tank with the second holds the groove and forms hold the chamber, second half groove (122) with first half groove (121) form dodge groove (12).
6. The flight control assembly of claim 5,
an annular positioning projection (132) is projected from the side wall of the first half groove (121), and the annular positioning projection (132) can be inserted into the second half groove (122); or the like, or, alternatively,
an annular positioning projection (132) is projected from the side wall of the second half groove (122), and the annular positioning projection (132) can be inserted into the first half groove (121).
7. The flight control assembly according to claim 5, wherein a clamping groove (141) is formed in one of the side wall of the first housing (13) and the side wall of the second housing (14), and a clamping part (131) is formed in the other side wall of the first housing and the second housing, and the clamping part (131) can be clamped with the clamping groove (141).
8. The flight control assembly according to claim 5, wherein a fixing portion (15) is correspondingly arranged on each of the side wall of the first casing (13) and the side wall of the second casing (14), a fixing hole (151) is formed in each fixing portion (15), and the fixing hole (151) of the first casing (13) is connected with the fixing hole (151) of the second casing (14) through a connecting piece.
9. Flight control assembly according to any one of claims 1 to 8, characterized in that the connection plate (4) is made of metal.
10. A mobile device comprising the flight control assembly of any one of claims 1-9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021517374.8U CN212890969U (en) | 2020-07-28 | 2020-07-28 | Flight control assembly and mobile device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021517374.8U CN212890969U (en) | 2020-07-28 | 2020-07-28 | Flight control assembly and mobile device |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN212890969U true CN212890969U (en) | 2021-04-06 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202021517374.8U Active CN212890969U (en) | 2020-07-28 | 2020-07-28 | Flight control assembly and mobile device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN212890969U (en) |
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2020
- 2020-07-28 CN CN202021517374.8U patent/CN212890969U/en active Active
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 510000 Block C, 115 Gaopu Road, Tianhe District, Guangzhou City, Guangdong Province Patentee after: Guangzhou Jifei Technology Co.,Ltd. Address before: 510000 Block C, 115 Gaopu Road, Tianhe District, Guangzhou City, Guangdong Province Patentee before: Guangzhou Xaircraft Technology Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder |