CN110723273A - Arm locking device and aircraft - Google Patents
Arm locking device and aircraft Download PDFInfo
- Publication number
- CN110723273A CN110723273A CN201911044417.7A CN201911044417A CN110723273A CN 110723273 A CN110723273 A CN 110723273A CN 201911044417 A CN201911044417 A CN 201911044417A CN 110723273 A CN110723273 A CN 110723273A
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- locking device
- connecting part
- horn
- fixing hole
- pair
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- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008092 positive effect Effects 0.000 description 1
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/30—Parts of fuselage relatively movable to reduce overall dimensions of aircraft
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Lock And Its Accessories (AREA)
Abstract
The invention discloses an arm locking device and an aircraft, wherein a first connecting part connected with an arm is provided with a fixing hole, a second connecting part connected with an aircraft body is provided with a pair of first connecting pieces, a gap is formed between the pair of first connecting pieces, the pair of first connecting pieces are pressed through a knob switch and fixedly connected with the fixing hole on the first connecting part through the gap, and the first connecting part and the second connecting part are locked, so that the arm and the aircraft body are locked; the arm locking device is simple in structure, light in weight, low in cost and suitable for an aircraft with low requirement on weight.
Description
Technical Field
The invention belongs to the field of design of aircrafts, and particularly relates to a locking device for a horn and an aircraft comprising the locking device for the horn.
Background
A drone is an unmanned aerial vehicle that is operated using a radio remote control device and a self-contained program control device. The horn of unmanned aerial vehicle generally needs horn locking device to lock or unblock the horn.
At present, the locking device structure of the unmanned aerial vehicle horn is too complex, the product weight is heavy, and the product cost is correspondingly increased.
Disclosure of Invention
The invention aims to provide an arm locking device and an aircraft.
In order to solve the problems, the technical scheme of the invention is as follows:
an arm locking device, comprising:
the first connecting part is provided with a fixing hole, and one end of the first connecting part can be fixedly connected with the machine arm;
one end of the second connecting part is provided with a pair of first connecting pieces, a gap is formed between the pair of first connecting pieces, and the other end of the second connecting part can be fixedly connected with an external machine body;
the knob switch can be inserted into the gap and is fixedly connected with the fixing hole; the first connecting part and the second connecting part are locked;
and under the locking state of the horn locking device, the knob switch compresses the first connecting piece and penetrates through the gap to be fixedly connected with the fixing hole.
According to an embodiment of the present invention, a pair of parallel second connecting members extends outwards from the other end of the first connecting portion along the edge of the first connecting portion, and a slot is formed; the second connecting piece is perpendicular to the surface where the fixing hole is located;
and a third connecting piece is arranged at the lower end of the first connecting piece of the second connecting part, and is arranged in the groove body and is rotationally connected with the second connecting piece.
According to an embodiment of the invention, a through hole is formed in the center of the knob switch, and a fastener can penetrate through the through hole to be fixedly connected with the fixing hole.
According to an embodiment of the present invention, a limiting groove is disposed at a bottom end of the rotary switch, a limiting boss is disposed on the first connecting portion near the fixing hole, and the limiting groove is matched with the limiting boss.
According to an embodiment of the present invention, the upper surface of the first connecting member is provided with a fool-proof boss.
According to an embodiment of the present invention, the knob switch is T-shaped.
According to an embodiment of the present invention, a pair of the second connecting members are provided with a first pin hole, and the third connecting member is provided with a second pin hole, and the first pin hole and the second pin hole can be connected by a pin.
An aircraft comprises the horn locking device in one embodiment of the invention.
Due to the adoption of the technical scheme, compared with the prior art, the invention has the following advantages and positive effects:
in the horn locking device in one embodiment of the invention, the first connecting part connected with the horn is provided with the fixing hole, the second connecting part connected with the machine body is provided with the pair of first connecting pieces, a gap is formed between the pair of first connecting pieces, the pair of first connecting pieces are pressed through the knob switch and fixedly connected with the fixing hole on the first connecting part through the gap, and the first connecting part and the second connecting part are locked, so that the horn and the machine body are locked. The arm locking device is simple in structure, light in weight, low in cost and suitable for an aircraft with low requirement on weight.
Drawings
FIG. 1 is a schematic structural view of a horn locking device in an embodiment of the present invention;
FIG. 2 is an exploded view of the structure of the horn locking device in one embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a rotary switch in the arm locking device according to an embodiment of the present invention;
FIG. 4 is a cross-sectional view of the locking mechanism of the arm in one embodiment of the present invention;
FIG. 5 is a schematic view of the locking mechanism of the arm in an embodiment of the present invention;
fig. 6 is a schematic view of the locking device of the arm in an unlocked state according to an embodiment of the present invention;
fig. 7 is a schematic view of the folding state of the arm according to an embodiment of the present invention.
Description of reference numerals:
1: a first connection portion; 101: a fixing hole; 102: a limiting boss; 103: a second connecting member; 2: a second connecting portion; 201: a first connecting member; 2011: a fool-proof boss; 202: a third connecting member; 3: a knob switch; 301: a limiting groove; 4: a machine arm.
Detailed Description
The present invention provides an arm locking device and an aircraft, which will be described in detail below with reference to the accompanying drawings and specific embodiments. Advantages and features of the present invention will become apparent from the following description and from the claims.
Example one
As shown in fig. 1, the present invention provides a locking device for a horn, comprising: the first connecting part 1 is provided with a fixing hole 101, and one end of the first connecting part 1 can be fixedly connected with the horn 4; a pair of first connecting pieces 201 are arranged at one end of the second connecting part 2, a gap exists between the pair of first connecting pieces 201, and the other end of the second connecting part 2 can be fixedly connected with an external machine body; the knob switch 3 can be inserted into the gap and is fixedly connected with the fixing hole 101; used for locking the first connecting part 1 and the second connecting part 2; under the locking state of the arm locking device, the knob switch 3 compresses the first connecting piece 201 and penetrates through the gap to be fixedly connected with the fixing hole 101.
In practice, the rotary switch 3 is connected with the fixing hole 101 on the first connecting portion 1, the first connecting portion 1 is fixedly connected with the horn 4, and the second connecting portion 2 is connected with the first connecting portion 1 through a shaft. When the horn 4 needs to be locked, the horn 4 can be rotated to enable the knob switch 3 to be positioned in a gap between the pair of first connecting pieces 201, and then the knob switch 3 is rotated to enable the knob switch 3 to be in interference fit with the first connecting pieces 201, so that the locking effect is achieved.
Compress tightly first connecting piece 201 through rotary switch 3, pass the space and link firmly with the fixed orifices 101 on the first connecting portion 1, lock first connecting portion 1 and second connecting portion 2, just also lock horn 4 and organism, this horn locking device simple structure, light in weight, with low costs are applicable to on the aircraft that requires light in weight.
Specifically, as shown in fig. 2, one end of the first connecting portion 1 is fixedly connected to the horn 4, the upper surface of the first connecting portion 1 is a platform, the platform is provided with a fixing hole 101, and a limiting boss 102 is arranged beside the fixing hole 101. A pair of parallel second connecting pieces 103 extend outwards from the other end of the first connecting part 1 along the edge of the first connecting part 1, and the pair of second connecting pieces 103 and the first connecting part 2 form a groove body; the second connector 103 is perpendicular to the upper surface of the first connector 1. A first pin hole is formed in the pair of second connection members 103 at a position opposite to each other.
One end of the second connecting portion 2 is provided with a pair of first connecting pieces 201, a gap exists between the pair of first connecting pieces 201, and a fool-proof boss 2011 is arranged on the upper surface of the first connecting pieces 201, and when the horn locking device is locked, the fool-proof boss 2011 can prevent the knob switch 3 from being separated from the first connecting pieces 201, so that accidental unlocking of the horn locking device is avoided. The other end of the second connecting part 2 can be fixedly connected with an external machine body. The third connecting piece 202 is arranged at the lower end of the first connecting piece 201, the second pin hole is arranged on the third connecting piece 202, and when the third connecting piece 202 is positioned in the groove body in the first connecting part 1, the first pin hole on the second connecting piece 103 is connected with the second pin hole on the third connecting piece 202 through the pin, so that the first connecting part 1 is rotatably connected with the second connecting part 2, namely, the horn 4 is foldable.
In the locked state of the arm locking device, as shown in fig. 1 and 4. A pair of first connecting pieces 201 are positioned on the upper surface of the first connecting part 1, the fixing hole 101 and the limiting boss 102 can be seen from the gap of the pair of first connecting pieces 201, the knob switch 3 compresses the pair of first connecting pieces 201 and penetrates through the gap to enable the limiting groove 301 at the bottom end of the knob switch 3 to be positioned on the limiting boss 102 and to be in seamless fit; then, a fastener is used to penetrate through the through hole in the center of the rotary switch 3 and is fixedly connected with the fixing hole on the first connecting portion 1, and the fastener is tightened to make the upper surfaces of the rotary switch 3, the first connecting member 201 and the first connecting portion 1 tightly fit with each other, as shown in fig. 5.
When the arm 4 needs to be unlocked, the rotary switch 3 is turned so as not to press the first connecting member 201 any more, as shown in fig. 6. After the arm locking device is unlocked, the arm 4 can be folded by rotating the arm 4, as shown in fig. 7.
Example two
The invention also provides an aircraft which comprises the horn locking device in the first embodiment. Through this horn locking device, the horn of this aircraft can be locked, collapsible. Because this horn locking device simple structure, light in weight, be applicable to very much the unmanned aerial vehicle who has strict requirement to weight.
The embodiments of the present invention have been described in detail with reference to the accompanying drawings, but the present invention is not limited to the above embodiments. Even if various changes are made to the present invention, it is still within the scope of the present invention if they fall within the scope of the claims of the present invention and their equivalents.
Claims (8)
1. An arm locking device, comprising:
the first connecting part is provided with a fixing hole, and one end of the first connecting part can be fixedly connected with the machine arm;
one end of the second connecting part is provided with a pair of first connecting pieces, a gap is formed between the pair of first connecting pieces, and the other end of the second connecting part can be fixedly connected with an external machine body;
the knob switch can be inserted into the gap and is fixedly connected with the fixing hole; the first connecting part and the second connecting part are locked;
and under the locking state of the horn locking device, the knob switch compresses the first connecting piece and penetrates through the gap to be fixedly connected with the fixing hole.
2. The horn locking device of claim 1 wherein the other end of said first link extends outwardly along the edge of said first link to form a pair of parallel second links and form a channel; the second connecting piece is perpendicular to the surface where the fixing hole is located;
and a third connecting piece is arranged at the lower end of the first connecting piece of the second connecting part, and is arranged in the groove body and is rotationally connected with the second connecting piece.
3. The horn locking device of claim 1, wherein said knob switch has a through hole at the center thereof, and is fastened to said fixing hole by a fastening member passing through said through hole.
4. The horn locking device according to claim 3, wherein a limit groove is formed at a bottom end of the rotary switch, a limit boss is formed on the first connecting portion near the fixing hole, and the limit groove is matched with the limit boss.
5. The horn locking assembly of claim 1 wherein said first connector has a fool-proof boss on an upper surface thereof.
6. The horn lock of claim 1, wherein said knob switch is T-shaped.
7. The horn locking device of claim 2 wherein a pair of said second connecting members each have a first pin hole and said third connecting member has a second pin hole, said first and second pin holes being adapted to be connected by a pin.
8. An aircraft comprising an arm locking device according to any one of claims 1 to 7.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2019105894785 | 2019-07-02 | ||
| CN201910589478 | 2019-07-02 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN110723273A true CN110723273A (en) | 2020-01-24 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201911044417.7A Pending CN110723273A (en) | 2019-07-02 | 2019-10-30 | Arm locking device and aircraft |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN110723273A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021243502A1 (en) * | 2020-06-01 | 2021-12-09 | 深圳市大疆创新科技有限公司 | Arm assembly and unmanned aerial vehicle |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2233393A2 (en) * | 2009-03-23 | 2010-09-29 | Gregor Schnoell | Locking system |
| CN203681871U (en) * | 2013-12-20 | 2014-07-02 | 深圳市大疆创新科技有限公司 | Engine arm assembly and stander device of aircraft and aircraft |
| CN106081058A (en) * | 2016-06-30 | 2016-11-09 | 辽宁猎鹰航空科技有限公司 | Unmanned plane pretension folded piece |
| CN205707292U (en) * | 2016-04-28 | 2016-11-23 | 杭州启飞智能科技有限公司 | A kind of collapsible horn pipe clamping device of plant protection unmanned plane |
| CN207617956U (en) * | 2017-11-02 | 2018-07-17 | 西安太极航空科技有限公司 | High speed multi-rotor aerocraft |
| CN108883823A (en) * | 2017-08-31 | 2018-11-23 | 深圳市大疆创新科技有限公司 | Horn locking mechanism and aircraft |
| CN208515811U (en) * | 2017-10-12 | 2019-02-19 | 四川尚航智能科技有限公司 | A kind of foldable six rotor wing unmanned aerial vehicle |
-
2019
- 2019-10-30 CN CN201911044417.7A patent/CN110723273A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP2233393A2 (en) * | 2009-03-23 | 2010-09-29 | Gregor Schnoell | Locking system |
| CN203681871U (en) * | 2013-12-20 | 2014-07-02 | 深圳市大疆创新科技有限公司 | Engine arm assembly and stander device of aircraft and aircraft |
| CN205707292U (en) * | 2016-04-28 | 2016-11-23 | 杭州启飞智能科技有限公司 | A kind of collapsible horn pipe clamping device of plant protection unmanned plane |
| CN106081058A (en) * | 2016-06-30 | 2016-11-09 | 辽宁猎鹰航空科技有限公司 | Unmanned plane pretension folded piece |
| CN108883823A (en) * | 2017-08-31 | 2018-11-23 | 深圳市大疆创新科技有限公司 | Horn locking mechanism and aircraft |
| CN208515811U (en) * | 2017-10-12 | 2019-02-19 | 四川尚航智能科技有限公司 | A kind of foldable six rotor wing unmanned aerial vehicle |
| CN207617956U (en) * | 2017-11-02 | 2018-07-17 | 西安太极航空科技有限公司 | High speed multi-rotor aerocraft |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2021243502A1 (en) * | 2020-06-01 | 2021-12-09 | 深圳市大疆创新科技有限公司 | Arm assembly and unmanned aerial vehicle |
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Application publication date: 20200124 |