CN210761258U - Locking mechanical system and unmanned aerial vehicle cabin - Google Patents
Locking mechanical system and unmanned aerial vehicle cabin Download PDFInfo
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- CN210761258U CN210761258U CN201921644579.XU CN201921644579U CN210761258U CN 210761258 U CN210761258 U CN 210761258U CN 201921644579 U CN201921644579 U CN 201921644579U CN 210761258 U CN210761258 U CN 210761258U
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- 238000010586 diagram Methods 0.000 description 4
- 238000003825 pressing Methods 0.000 description 4
- 238000004026 adhesive bonding Methods 0.000 description 2
- 239000003292 glue Substances 0.000 description 2
- 238000011900 installation process Methods 0.000 description 2
- 230000006978 adaptation Effects 0.000 description 1
- 230000009931 harmful effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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Abstract
The utility model relates to an unmanned air vehicle technique field discloses a locking mechanical system and unmanned aerial vehicle cabin, and this locking mechanical system includes: the locking component comprises an operating rod and a lock pin fixed with the operating rod, the operating rod can drive the lock pin to rotate around the axial direction of the operating rod, the second fixing component is arranged on an axial extension line of the operating rod and is connected with the operating rod through the elastic component, a groove matched with the lock pin is formed in the bottom of the first fixing component, a notch is formed beside the groove, the width of the notch is larger than or equal to the outer diameter of the lock pin, and the groove and the notch are distributed in the circumferential direction of a rotating shaft of the locking component; this unmanned aerial vehicle includes this locking mechanical system. The locking mechanism and the unmanned aerial vehicle cabin provided by the embodiment of the utility model can not be separated independently when in an unlocking state, so as to prevent loss; and the height of the whole unlocking mechanism protruding out of the outer surface of the cabin is not more than 1 mm, so that the adverse effect on the pneumatic performance of the unmanned aerial vehicle is reduced.
Description
Technical Field
The utility model relates to an unmanned air vehicle technique field especially relates to a locking mechanical system and unmanned aerial vehicle cabin.
Background
At present combined material unmanned aerial vehicle cabin need set up the cabin cover, makes things convenient for the dismouting and the maintenance of equipment and power, and is mostly at locking means such as installation hasps on the hinge to the locking device of cabin cover casing at present. Under the trend that the preparation time requirement to unmanned aerial vehicle is more and more strict, can't satisfy the requirement that unmanned aerial vehicle takes off and land fast, locking device dismantles the back detached part and loses very easily when the field is tested. An unmanned aerial vehicle need be equipped with many sets of locking device, and the component consumption is big, and traditional locking mode is great at unmanned aerial vehicle surface part's occupation size, and it is great to unmanned aerial vehicle's aerodynamic performance influence, makes unmanned aerial vehicle's flying speed and wind resistance ability all reduce to some extent.
SUMMERY OF THE UTILITY MODEL
Technical problem to be solved
The utility model aims at providing a locking mechanical system and unmanned aerial vehicle cabin to the dismantlement back components and parts that the locking device who solves among the prior art exists at least lose easily, and the size of outstanding unmanned aerial vehicle organism is great, produces one of the technical problem of harmful effects to unmanned aerial vehicle pneumatic performance.
(II) technical scheme
In order to solve the above technical problem, an embodiment of the present invention provides a locking mechanism, including: the locking device comprises a first fixing piece, a second fixing piece, a locking part and an elastic part, wherein the locking part comprises an operating rod and a lock pin fixed with the operating rod, the operating rod can drive the lock pin to rotate around the axial direction of the operating rod, the second fixing piece is arranged on an axial extension line of the operating rod and is connected with the operating rod through the elastic part, a groove matched with the lock pin is formed in the bottom of the first fixing piece, a notch is formed beside the groove, the width of the notch is larger than or equal to the outer diameter of the lock pin, and the groove and the notch are distributed in the circumferential direction of a rotating shaft of the locking part.
The middle part of the first fixing piece is provided with a first through hole for the second fixing piece to pass through.
Wherein a first platform is formed at the bottom of the first through hole, and the groove with a downward opening is formed on the lower surface of the first platform.
Wherein the second fixing member is configured with a second through hole through which the operation rod passes.
The top of the operating rod is a circular truncated cone, the bottom of the operating rod is a cylinder, the circular truncated cone is matched with the second through hole, the outer diameter of the cylinder is smaller than the second through hole, and the elastic part is arranged in a gap between the cylinder and the second through hole.
Wherein, the top surface of the round platform is provided with a straight-line-shaped groove or a cross-shaped groove.
The two ends of the first fixing piece are provided with positioning holes.
The second fixing piece comprises a second fixing piece body and a first boss arranged at the top of the second fixing piece body, and the outer diameter of the first boss is larger than that of the second fixing piece body.
The embodiment of the utility model provides a still disclose an unmanned aerial vehicle cabin, including cabin body, cabin cover and the locking mechanical system of the novel embodiment of faithful use, the cabin cover can open and shut the setting and be in on the cabin body, first mounting is fixed in the cabin body, the second mounting is fixed in the cabin cover.
(III) advantageous effects
An embodiment of the utility model provides a pair of locking mechanical system, operating personnel are through pressing down and rotatory action bars, and the action bars drives the lockpin for the lockpin switches between recess and breach, with locking and the unblock state between realization first mounting and the second mounting. The embodiment of the utility model provides an unmanned aerial vehicle cabin utilizes foretell locking mechanical system, is fixed in the cabin body with first mounting, and the second mounting is fixed in the cabin cover, through the locking and the unlocking state between first mounting and the second mounting in order to realize the locking and the unlocking state of cabin cover. When the locking mechanism and the unmanned aerial vehicle cabin provided by the embodiment of the utility model are in an unlocking state, the parts of the locking mechanism can not be separated independently, and are prevented from being lost; and the height of the whole unlocking mechanism protruding out of the outer surface of the cabin is not more than 1 mm, so that the adverse effect on the pneumatic performance of the unmanned aerial vehicle is reduced.
Drawings
Fig. 1 is a schematic structural diagram of a locking mechanism in a locked state according to an embodiment of the present invention;
fig. 2 is a schematic structural diagram of a locking mechanism in an unlocked state according to an embodiment of the present invention;
fig. 3 is a schematic structural view of a second fixing member according to an embodiment of the present invention;
fig. 4 is a schematic structural diagram of a first fixing member according to an embodiment of the present invention;
fig. 5 is a schematic structural view of an elastic member according to an embodiment of the present invention;
fig. 6 is a schematic structural diagram of a locking component according to an embodiment of the present invention.
Reference numerals:
1: a first fixing member; 101: positioning holes; 102: a first through hole; 103: a first platform; 104: a groove; 105: a notch; 2: a second fixing member; 201: a second through hole; 202: a second fixing member body; 203: a first boss; 3: an elastic member; 4: a locking member; 401: an operating lever; 411: a circular truncated cone; 421: a cylinder; 431: a straight-shaped groove; 402: and (4) locking pins.
Detailed Description
The following detailed description of the embodiments of the present invention is provided with reference to the accompanying drawings and examples. The following examples are intended to illustrate the invention, but are not intended to limit the scope of the invention.
In the description of the present invention, it is to be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; 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 the present invention can be understood in specific cases to those skilled in the art.
As shown in fig. 1 to 2, an embodiment of the present invention discloses a locking mechanism, including: first mounting 1, second mounting 2, locking part 4 and elastomeric element 3, locking part 4 includes action bars 401 and the lockpin 402 fixed with action bars 401, action bars 401 can drive the lockpin around its axial and rotate, second mounting 2 sets up on the axial extension line of action bars 401, and be connected with action bars 401 through elastomeric element, the bottom of first mounting 1 has the recess 104 with lockpin 402 looks adaptation, and be equipped with breach 105 in the next door of recess 104, the width of breach 105 is greater than or equal to the external diameter of lockpin 402, recess 104 and breach 105 distribute in the circumference of locking part 4 rotation axis.
Specifically, the locking member 4 is connected to the second fixing member 2 through the elastic member 3, the locking member 4 includes an operating rod 401 and a lock pin 402 fixed perpendicular to the operating rod 401, the width of the notch 105 is greater than or equal to the outer diameter of the lock pin 402, so that the lock pin 402 can be smoothly released from the notch 105, and an operator can switch the lock pin 402 between the groove 104 and the notch 105 by pressing and rotating the operating rod 401.
For example: as shown in fig. 1, when the locking is required, when an operator presses and rotates the operating rod 401, the locking pin 402 is located at the position of the groove 104, due to the mutual buckling relation between the groove 104 and the locking pin 402, the relative fixing between the locking part 4 and the second fixing member 2 is ensured, and due to the connection between the locking part 4 and the second fixing member 2 through the elastic part 3, the elastic force is acted between the locking part 4 and the second fixing member, the elastic force is transmitted to the hatch cover through the second fixing member 2, so that the hatch cover and the cabin are buckled through the elastic force, and the hatch cover is in a locked state. As shown in fig. 5, the elastic member 3 in this embodiment may be a spring, one end of the spring is connected to the first fixing member 1, and the other end of the spring is connected to the operating rod 401.
As shown in fig. 2, when unlocking is required, when an operator presses and rotates the operating lever 401, the lock pin 402 is located at the position of the notch 105, so that the lock pin 402 can be completely disengaged from the notch 105, the locking member 4 and the second fixing member 2 are in an unlocked state, and the locking member 4 is connected with the first fixing member 1 through the elastic member 3, so that the first fixing member 1 and the second fixing member 2 are in an unlocked state, and the hatch cover is in an unlocked state.
In the embodiment, the first fixing member 1 is fixedly installed on the cabin, the second fixing member 2 is fixedly installed on the cabin cover, and the locking or unlocking of the cabin cover is realized by using the locking or unlocking relationship between the first fixing member 1 and the second fixing member 2. The locking mechanism can also be applied to a case or the like.
In the locking mechanism provided by the embodiment of the utility model, the operating personnel presses and rotates the operating rod, and the operating rod drives the lock pin, so that the lock pin is switched between the groove and the notch, and the locking and unlocking states between the first fixing piece and the second fixing piece are realized; the parts of the locking mechanism cannot be separated independently, so that the parts are prevented from being lost; and the height of the whole unlocking mechanism protruding out of the outer surface of the cabin is not more than 1 mm, so that the adverse effect on the pneumatic performance of the unmanned aerial vehicle is reduced.
As shown in fig. 4, the middle portion of the first fixing member 1 has a first through hole 102 through which the second fixing member 2 passes. Specifically, the first through hole 102 may be a circular arc hole.
Wherein, a first platform 103 is configured at the bottom of the first through hole 102, and the groove 104 with the downward opening is configured at the lower surface of the first platform 103. In order to enable the locking pin 402 to be smoothly clamped in the groove 104 and to be smoothly removed from the notch 105, the outer dimension of the first platform 103 in this embodiment is smaller than the inner diameter of the first through hole 102, so that the notch 105 is partially inside the bottom surface of the first through hole 102, and the locking pin 402 can pass through the notch 105 and be removed through the first through hole 102.
As shown in fig. 3, the second fixing member 2 is configured with a second through hole 201 through which an operation rod 401 passes. In this embodiment, the operating rod 401 can pass through the second through hole 201 in the second fixing member 2, so that the floor space of the locking mechanism is saved.
Further, as shown in fig. 6, the top of the operating rod 401 is a circular truncated cone 411, the bottom of the operating rod 401 is a cylinder 421, the circular truncated cone 411 is fitted with the second through hole 201, the outer diameter of the cylinder 421 is smaller than the second through hole 201, and the elastic component 3 is disposed in a gap between the cylinder 421 and the second through hole 201. The operating rod 401 in this embodiment is formed by an integral structure of the circular truncated cone 411 and the cylinder 421, the outer diameter of the circular truncated cone 411 is larger than the outer diameter of the cylinder 421, when the operating rod 401 is placed into the second through hole 201, a gap is formed between the cylinder 421 and the second through hole 201, and the elastic component 3 can be placed in the gap and connected between the outer side wall of the operating rod 401 and the inner side wall of the second through hole 201, so that the occupied area is further saved.
Wherein, the top surface of the round table 411 is provided with a straight groove 431 or a cross-shaped groove. An operator can press and rotate the straight-line-shaped groove 431 (or the cross-shaped groove) of the circular truncated cone 411 by using a corresponding straight-line screwdriver, and the operating rod 401 presses and rotates to drive the locking pin 402 to switch between the notch 105 and the groove 104.
Wherein, both ends of the first fixing member 1 are provided with positioning holes 101. In the present embodiment, the first fixing member 1 is fixed to the nacelle through the positioning hole 101 by using a fastener. Specifically, the positioning hole 101 is internally provided with threads, the nacelle is also internally provided with corresponding threaded holes, and screws are sequentially screwed into the positioning hole 101 and the threaded holes to fix the first fixing member 1 on the nacelle. The second fixing member 2 includes a second fixing member body 202 and a first boss 203 provided on the top of the second fixing member body 202, and the outer diameter of the first boss 203 is larger than that of the second fixing member body 202. The hatch is provided with a third through hole, the aperture of which is larger than the second fixing part body 202 and smaller than the first boss 203. In this embodiment, the second fixing member 2 can be fixed on the cover by gluing, so as to avoid falling off during pressing, and the structure of the first boss 203 is designed. In the installation process, the second fixing member body 202 can pass through the third through hole, and after the second fixing member body is in place, the first boss 203 is clamped at the third through hole, and then the second fixing member 2 is fixed on the cabin cover by using glue. The embodiment of the utility model provides a still disclose an unmanned aerial vehicle cabin, including cabin body, cabin cover and like the locking mechanical system of this embodiment, the cabin cover can open and shut and set up on the cabin body, and first mounting 1 is fixed in the cabin body, and second mounting 2 is fixed in the cabin cover.
The embodiment of the utility model provides an unmanned aerial vehicle cabin utilizes foretell locking mechanical system, is fixed in the cabin body with first mounting, and the second mounting is fixed in the cabin cover, through the locking and the unlocking state between first mounting and the second mounting in order to realize the locking and the unlocking state of cabin cover. When the locking mechanism and the unmanned aerial vehicle cabin provided by the embodiment of the utility model are in an unlocking state, the parts of the locking mechanism can not be separated independently, and are prevented from being lost; and the height of the whole unlocking mechanism protruding out of the outer surface of the cabin is not more than 1 mm, so that the adverse effect on the pneumatic performance of the unmanned aerial vehicle is reduced.
The second fixing member 2 includes a second fixing member body 202 and a first boss 203 disposed at the top of the second fixing member body 202, and the hatch cover is provided with a third through hole, and the aperture of the third through hole is larger than the second fixing member body 202 and smaller than the first boss 203. In this embodiment, the second fixing member 2 can be fixed on the cover by gluing, so as to avoid falling off during pressing, and the structure of the first boss 203 is designed. In the installation process, the second fixing member body 202 can pass through the third through hole, and after the second fixing member body is in place, the first boss 203 is clamped at the third through hole, and then the second fixing member 2 is fixed on the cabin cover by using glue.
The above description is only a preferred embodiment of the present invention, and should not be taken as limiting the invention, and any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (9)
1. A locking mechanism, comprising: the locking device comprises a first fixing piece, a second fixing piece, a locking part and an elastic part, wherein the locking part comprises an operating rod and a lock pin fixed with the operating rod, the operating rod can drive the lock pin to rotate around the axial direction of the operating rod, the second fixing piece is arranged on an axial extension line of the operating rod and is connected with the operating rod through the elastic part, a groove matched with the lock pin is formed in the bottom of the first fixing piece, a notch is formed beside the groove, the width of the notch is larger than or equal to the outer diameter of the lock pin, and the groove and the notch are distributed in the circumferential direction of a rotating shaft of the locking part.
2. The locking mechanism of claim 1, wherein the middle portion of the first securing member has a first through hole through which the second securing member passes.
3. The lock mechanism according to claim 2, wherein a first land is formed at a bottom of the first through hole, and the groove having a downward opening is formed at a lower surface of the first land.
4. The locking mechanism of claim 1, wherein the second fixing member is configured with a second through hole through which the operating rod passes.
5. The locking mechanism of claim 4, wherein the top of the operating rod is a circular truncated cone and the bottom of the operating rod is a cylinder, the circular truncated cone fits into the second through hole, the outer diameter of the cylinder is smaller than the second through hole, and the elastic member is disposed in a gap between the cylinder and the second through hole.
6. The locking mechanism of claim 5, wherein the top surface of the circular table has a "straight" or "cross" shaped groove.
7. The locking mechanism of claim 1, wherein the first securing member has locating holes at both ends.
8. The locking mechanism of claim 1, wherein the second fastener includes a second fastener body and a first boss disposed on top of the second fastener body, the first boss having an outer diameter greater than an outer diameter of the second fastener body.
9. An unmanned aerial vehicle cabin, comprising a cabin body, a hatch, and the locking mechanism of any one of claims 1-8, wherein the hatch is openably and closably disposed on the cabin body, and wherein the first fastener is fixed to the cabin body and the second fastener is fixed to the hatch.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921644579.XU CN210761258U (en) | 2019-09-29 | 2019-09-29 | Locking mechanical system and unmanned aerial vehicle cabin |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201921644579.XU CN210761258U (en) | 2019-09-29 | 2019-09-29 | Locking mechanical system and unmanned aerial vehicle cabin |
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| Publication Number | Publication Date |
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| CN210761258U true CN210761258U (en) | 2020-06-16 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201921644579.XU Active CN210761258U (en) | 2019-09-29 | 2019-09-29 | Locking mechanical system and unmanned aerial vehicle cabin |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112125173A (en) * | 2020-09-02 | 2020-12-25 | 中联重科股份有限公司 | Locking device and engineering machinery |
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2019
- 2019-09-29 CN CN201921644579.XU patent/CN210761258U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112125173A (en) * | 2020-09-02 | 2020-12-25 | 中联重科股份有限公司 | Locking device and engineering machinery |
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Legal Events
| 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: Room 2607, No. 18 Yumin Road, Xicheng District, Beijing, 100029 (Desheng Park) Patentee after: China test Neville Technology (Beijing) Co.,Ltd. Patentee after: Beijing Sai Microelectronics Co.,Ltd. Address before: Room 2607, No. 18 Yumin Road, Xicheng District, Beijing, 100029 (Desheng Park) Patentee before: China test Neville Technology (Beijing) Co.,Ltd. Patentee before: Beijing Neville Technology Co.,Ltd. |
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| CP01 | Change in the name or title of a patent holder | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231102 Address after: Room 2607, No. 18 Yumin Road, Xicheng District, Beijing, 100029 (Desheng Park) Patentee after: Beijing Sai Microelectronics Co.,Ltd. Address before: Room 2607, No. 18 Yumin Road, Xicheng District, Beijing, 100029 (Desheng Park) Patentee before: China test Neville Technology (Beijing) Co.,Ltd. Patentee before: Beijing Sai Microelectronics Co.,Ltd. |
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| TR01 | Transfer of patent right |