CN107521657A - A kind of retaining mechanism of aircraft horn - Google Patents
A kind of retaining mechanism of aircraft horn Download PDFInfo
- Publication number
- CN107521657A CN107521657A CN201610459722.2A CN201610459722A CN107521657A CN 107521657 A CN107521657 A CN 107521657A CN 201610459722 A CN201610459722 A CN 201610459722A CN 107521657 A CN107521657 A CN 107521657A
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- CN
- China
- Prior art keywords
- horn
- aircraft
- retaining mechanism
- tapered end
- aircraft horn
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- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- B64C—AEROPLANES; HELICOPTERS
- B64C39/00—Aircraft not otherwise provided for
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- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Steering Controls (AREA)
- Details Of Aerials (AREA)
Abstract
The invention discloses a kind of retaining mechanism of aircraft horn, including aircraft horn and for connecting the horn mounting seat of aircraft horn and aircraft body, the retaining mechanism includes the pilot hole for being arranged inside and outside insertion on aircraft horn connection end, the tapered end slidably coordinated is provided with pilot hole, with be connected with tapered end and be arranged at the drawing pin on aircraft horn, the tapered end is with drawing pin to move along a straight line in pilot hole, and the tapered end front end and the clamping plate surface that is arranged in horn mounting seat are bonded and contacted or remote.The present invention solves the problems, such as that aircraft horn can freely stretch/reclaim, mainly utilized in the present invention and be connected with tapered end and be arranged at the drawing pin on aircraft horn, the tapered end moves along a straight line with drawing pin in pilot hole, and the tapered end front end contacts or remote with the clamping plate surface fitting being arranged in horn mounting seat, and realizes locking/unblock of aircraft horn.
Description
Technical field
The present invention relates to unmanned vehicle field, especially a kind of retaining mechanism of aircraft horn.
Background technology
At present, aircraft or unmanned plane are applied in social life more and more widely, are difficult to what is reached for people
Place is closely observed, or is carried out high-altitude and taken a crane shot, and then is provided convenience for observation, shooting.
Existing aircraft is often formed by aircraft fuselage and from the aircraft fuselage horn that surrounding stretches out laterally,
The outer end installation motor and propeller of horn, and then the flight of aircraft is driven, the bottom of aircraft is additionally provided with foot stool, with
It is easy to the landing of aircraft.
But in existing aircraft, the horn and foot stool that are stretched out all be with fuselage in a manner of being fixedly connected,
After use, arm exhibition is larger to cause high requirement of the aircraft to parking space, while needs loss of weight for aircraft itself
Consider, the structure of various pieces also designs relatively succinct in aircraft, and therefore, larger also result in of arm exhibition deposits improper led
The danger for being easy to lose caused.
Therefore, a kind of aircraft for being easy to storage when not in use is designed to become for an important research direction.Together
When in order to realize this aircraft, the skeleton mechanism of such as aircraft, the expansion that can realize aircraft horn and recovery fly
The locking drive mechanism of row device horn, the horn of aircraft and can realize aircraft foot stool expansion and recovery aircraft
Foot stool drive mechanism etc., be required to carry out new exploitation.
The content of the invention
The technical problem to be solved in the present invention is overcome the deficiencies in the prior art, there is provided a kind of locking of aircraft horn
Mechanism, using being connected with tapered end and being arranged at the drawing pin on aircraft horn, the tapered end does straight line with drawing pin in pilot hole
Motion, and the tapered end front end and the clamping plate surface fitting that is arranged in horn mounting seat contacts or remote, and realization is winged
Locking/unblock of row device horn.
In order to realize the purpose, the present invention adopts the following technical scheme that：A kind of retaining mechanism of aircraft horn, including fly
Row device horn and the horn mounting seat for connecting aircraft horn and aircraft body, the retaining mechanism are winged including being arranged at
The pilot hole of inside and outside insertion on row device horn connection end, the tapered end slidably coordinated is provided with pilot hole, and be connected with tapered end
And the drawing pin on aircraft horn is arranged at, the tapered end moves along a straight line with drawing pin in pilot hole, and before the tapered end
Hold and contacted or remote with the clamping plate surface fitting being arranged in horn mounting seat.
Specifically, there is one jiao between the retaining mechanism control aircraft horn and aircraft body of the aircraft horn
Degree and aircraft horn and aircraft body, which are drawn close or controlled substantially between horn and aircraft body, to be had an angle and flies
Row device horn is at least partially disposed within aircraft body.
Further, the retaining mechanism also includes being arranged on aircraft horn and is used to limit the work for drawing pin linear motion
Dynamic groove and the connecting portion for being arranged at tapered end rear end, described to draw pin one end to be fixedly connected with connecting portion, the other end runs through loose slot；
Wherein, with drawing pin to be moved along a straight line in pilot hole, forming the tapered end front end and grip block can stretch the tapered end
Contracting coordinates.
Further, the loose slot and drawing pin are arranged at the lower surface shell of aircraft horn.
Further, the retaining mechanism also includes elastic component and position limiting structure, and described position limiting structure is fixedly mounted on
On horn, described elastic component one end is connected with locking member, and the other end is connected with position limiting structure.
Further, the position limiting structure includes stopper slot and fixed part, and described stopper slot is integrated knot with fixed part
Structure, described fixed part are connected with horn；
Wherein, described stopper slot inwall is engaged with elastic component.
Further, the elastic component is connected with connecting portion；
Wherein, the connecting portion is provided with locating dowel with elastic component junction, and described locating dowel is in elastic component.
Further, at least one limited impression with drawing pin card conjunction, the limited impression are provided with the loose slot
It is arranged at the front end of loose slot, and/or the rear end of loose slot.
Further, the tapered end front end is provided with an inclined-plane away from grip block side.
Further, the tapered end is provided with least one groove.
After adopting the above technical scheme, the present invention has the advantages that compared with prior art：
1st, the retaining mechanism of aircraft horn of the present invention solves what aircraft horn can freely stretch/reclaim
Problem, mainly sold in of the invention using drawing and drive tapered end to be moved along a straight line in pilot hole, then aircraft horn is around horn
Mounting seat rotates, and then realizes between control aircraft horn and aircraft body there is an angle and aircraft horn
Drawing close or control substantially with aircraft body has an angle and aircraft horn between aircraft horn and aircraft body
The function being at least partially disposed within aircraft body.Be advantageous to flight/storage of aircraft, flight can not only be saved
The storage placement space of device, additionally it is possible to realize in inapplicable aircraft, to the defencive function of aircraft horn.
2nd, when the retaining mechanism of aircraft horn of the present invention solves aircraft flight process status, aircraft machine
The problem of arm steady operation, being formed in of the invention using the tapered end of retaining mechanism and the grip block of horn mounting seat can stably stretch
Contracting coordinates, and the retaining mechanism can stablize the position for keeping aircraft horn to be in setting, fly when ensure that aircraft flight
The stability of the propeller works set on row device horn, and then ensure that the flight safety of aircraft.
3rd, draw pin and tapered end to may be contained within aircraft horn in the retaining mechanism of aircraft horn of the present invention, draw
Pin is arranged on the inside of aircraft horn, by aircraft body side so that after the recovery of aircraft horn, ensure that aircraft egg type
The globality of outward appearance, the accommodation space of retaining mechanism is further saved, the locking of the aircraft horn described in the present embodiment
It is simple in construction, reliable in action and cost is low.
Brief description of the drawings
The structure chart of the retaining mechanism of aircraft horn in Fig. 1, the embodiment of the present invention；
B-B profile in Fig. 2, Fig. 1 of the present invention；
The explosive view of the retaining mechanism of aircraft horn in Fig. 3, the embodiment of the present invention；
The structure chart of horn mounting seat in Fig. 4, the embodiment of the present invention；
Wherein, 1, aircraft horn, 2, tapered end, 4, horn mounting seat, 5, grip block, 11, draw pin, 12, elastic component, 13,
Position limiting structure, 14, connecting portion, 101, substrate, 102, stiffener, 103, cavity, 105, hinge hole, 106, linking arm；107、
Reinforcement, 108, fixing hole.
Embodiment
In order to facilitate the understanding of the purposes, features and advantages of the present invention, it is below in conjunction with the accompanying drawings and specific real
Applying mode, the present invention is further detailed explanation.
Embodiment one
As shown in Figure 1 to Figure 3, a kind of retaining mechanism of aircraft horn of the present invention, including aircraft horn 1 and for even
The horn mounting seat 4 of aircraft horn 1 and aircraft body is connect, the retaining mechanism includes being arranged at the body of aircraft horn 1
The pilot hole of inside and outside insertion on connection end, the tapered end 2 coordinated with pilot hole on the body of aircraft horn 1 and slidably is arranged at,
Be connected with tapered end 2 and be arranged at the drawing pin 11 on aircraft horn 1, the tapered end 2 with draw pin 11 straight line is done in pilot hole
Motion, and the front end of the tapered end 2 and the surface of grip block 5 that is arranged in horn mounting seat 4 are bonded and contacted or remote.
Or retaining mechanism described in the present embodiment includes aircraft horn 1 and for connecting aircraft horn 1 and aircraft
The horn mounting seat 4 of main body, the aircraft horn 1 are spindle rotationally arranged in the horn mounting seat 4, the horn installation
Seat 4 have one close to the turning end of aircraft horn 1 grip block 5, the turning end of aircraft horn 1 also slidably sets including one
Put on aircraft horn 1 and contacted with the fitting of the surface of grip block 5 or remote tapered end 2, is provided with the aircraft horn 1
The eccentric actuation 3 for driving tapered end 2 to slide.
Specifically, there is one jiao between the retaining mechanism control aircraft horn and aircraft body of the aircraft horn
Degree and aircraft horn and aircraft body, which are drawn close or controlled substantially between horn and aircraft body, to be had an angle and flies
Row device horn is at least partially disposed within aircraft body.
Also, be arranged in aircraft body to the movable connection of the aircraft horn 1 or within, the aircraft
Horn 1 is rotatable and is fixed at least one first position and a second place；Described first position is：The aircraft
There is an angle, the described second place is between horn 1 and aircraft body：The aircraft horn 1 and aircraft body
Substantially draw close or aircraft horn 1 is at least partially disposed within aircraft body；Also, at the second place, institute
The free end of aircraft horn 1 is stated less than aircraft horn 1 and the connection end of aircraft body.
Further, the retaining mechanism, which also includes being arranged on aircraft horn being used to limit, draws what pin 11 moved along a straight line
Loose slot and the connecting portion 14 for being arranged at the rear end of tapered end 2, described drawing one end of pin 11 are fixedly connected with connecting portion 14, and the other end passes through
Wear loose slot；
Wherein, the tapered end 2 forms the front end of tapered end 2 and grip block 5 with drawing pin 11 to be moved along a straight line in pilot hole
Scalable cooperation.
Further, the loose slot and drawing pin 11 are arranged at the lower surface shell of aircraft horn.
Further, the retaining mechanism also includes elastic component 12 and position limiting structure 13, and described position limiting structure 13 is fixed
On horn, described one end of elastic component 12 is connected with locking member, and the other end is connected with position limiting structure 13.
Further, the position limiting structure 13 includes stopper slot and fixed part, and described stopper slot is integrated with fixed part
Structure, described fixed part are connected with horn；
Wherein, described stopper slot inwall is engaged with elastic component 12.
Further, the elastic component 12 is connected with connecting portion 14；
Wherein, the connecting portion 14 is provided with locating dowel with the junction of elastic component 12, and described locating dowel is located at elastic component
In 12.
Further, at least one limited impression engaged with drawing pin 11 is provided with the loose slot, it is described spacing recessed
Groove is arranged at the front end of loose slot, and/or the rear end of loose slot.
Further, the front end of tapered end 2 is provided with an inclined-plane away from the side of grip block 5.Improve tapered end 2 and grip block 5
Degree of cooperation.
Or the front end of tapered end 2 is provided with the inclined-plane corresponding with grip block 5 close to the side of grip block 5, further carries
The high stability of retaining mechanism.
Further, the tapered end 2 is provided with least one groove.
Specifically, described tapered end 2 is flat body structure, at least one groove is set in the upside of tapered end 2 or downside,
The upside is corresponding with the outside of aircraft horn, and the downside is corresponding with the inner side of aircraft horn, and the groove can
To be arranged on the same side of tapered end 2, or the both sides of tapered end 2 are arranged on, then or are uniformly arranged on the both sides of tapered end 2.This reality
Apply in example by setting groove in tapered end 2, mitigate the weight of the retaining mechanism of aircraft horn, it is stable to improve aircraft flight
Property.
In summary, the retaining mechanism of the aircraft horn described in the present embodiment has advantages below：
1st, the retaining mechanism of the aircraft horn described in the present embodiment solves aircraft horn 1 and can freely stretch/return
The problem of receipts, mainly using drawing pin 11 to drive tapered end 2 to be moved along a straight line in pilot hole in the present embodiment, then aircraft machine
Arm 1 rotates around horn mounting seat 4, and then realizes between control aircraft horn 1 and aircraft body there is an angle
And aircraft horn 1 and aircraft body are drawn close or controlled substantially between aircraft horn 1 and aircraft body with one jiao
Degree and aircraft horn 1 are at least partially disposed in the function within aircraft body.Be advantageous to flight/storage of aircraft, no
The storage placement space of aircraft can only be saved, additionally it is possible to realize the protection to aircraft horn in inapplicable aircraft
Function.
2nd, when the retaining mechanism of the aircraft horn described in the present embodiment solves aircraft flight process status, aircraft
The problem of 1 steady operation of horn, formed surely using the tapered end 2 of retaining mechanism and the grip block 5 of horn mounting seat 4 in the present embodiment
Surely scalable cooperation, the retaining mechanism, which can be stablized, keeps aircraft horn 1 to ensure that aircraft in the position of setting
The stability of the propeller works set during flight on aircraft horn 1, and then ensure that the flight safety of aircraft.
3rd, pin 11 and tapered end 2 is drawn to may be contained within aircraft horn in the retaining mechanism of the aircraft horn described in the present embodiment
It is interior, draw pin 11 to be arranged on the inside of aircraft horn, by aircraft body side so that after the recovery of aircraft horn, to ensure that winged
The globality of row device egg-shaped appearance, the accommodation space of retaining mechanism is further saved, the aircraft machine described in the present embodiment
The locking mechanism of arm is simple, reliable in action and cost is low.
Embodiment two
Retaining mechanism described in the present embodiment, which also includes being arranged on aircraft horn being used to limit, draws pin 11 to move along a straight line
Loose slot and be arranged at the connecting portion 14 of the rear end of tapered end 2, described drawing one end of pin 11 is fixedly connected with connecting portion 14, the other end
Through loose slot；
Wherein, the tapered end 2 forms the front end of tapered end 2 and grip block 5 with drawing pin 11 to be moved along a straight line in pilot hole
Scalable cooperation.
Further, the drawing pin 11 includes connecting shaft, resetting structure, described to draw pin 11 to pass through connecting shaft and tapered end 2
Connecting portion 14 is connected, and resetting structure is provided between pin 11 and connecting portion 14 drawing, and control, which is drawn between pin 11 and loose slot, to be had
There is an angle and draw pin 11 and loose slot to draw close or control substantially and draw between pin 11 and loose slot with an angle and drawing pin 11
It is at least partially disposed within loose slot.
Specifically, described loose slot coordinates with drawing pin 11, wherein the described loose slot limitation activity for drawing pin 11
Scope, and as the accommodation space for drawing pin 11.
Retaining mechanism described in the present embodiment can more save the space of aircraft horn, and cause unmanned plane
The profile of horn is more beautiful, and when draw pin 11 when not in use, protection draw pin 11 not by other factorses interference and then
Influence unblock/locking effect of aircraft horn.
Embodiment three
As shown in figure 4, horn mounting seat described in the present embodiment 4, for connecting aircraft horn and aircraft body, institute
Stating horn mounting seat 4 includes a substrate 101, and the both sides of substrate 101, which are respectively equipped with, to be upwardly extended to form two linking arms 106,
Aircraft horn 1 is rotationally connected between two linking arms 106, and the end that is rotatably connected of the aircraft horn 1 has a lock
First 2, the substrate 101 on the part between two linking arms 106 have upwardly extend and contacted with tapered end 2 and against folder
Plate 5 is held, the height of the grip block 5 is more than the distance between the top of 1 tapered end of aircraft horn 2 and substrate 101, less than aircraft machine
Distance between the rotating shaft of arm 1 and substrate 101, the grip block 5 is interior to have cavity 103.
Specifically, the horn mounting seat 4 includes a substrate 101, the both sides of substrate 101 are respectively equipped with what is upwardly extended
Linking arm 106, part of the substrate 101 between two linking arms 106, is upwardly extended as the grip block of horn mounting seat 4
5, clamp and coordinate with the aircraft horn 1 with clipping retaining mechanism, at least there is a cavity 103 in the grip block 5.
Further, the quantity at least two of cavity 103, and be arranged at intervals along the width of grip block 5, institute
The width for stating interval is less than the width of cavity 103.
Further, the cavity 103 is distributed along the bearing of trend of grip block 5, is shaped as square.
Further, the epimere of linking arm 106 is cranked arm for what is bent forward or backward.
Further, the linking arm 106 has reinforcement 107,107 liang of the reinforcement with the coupling part of substrate 101
End is fixedly connected with linking arm 106 and substrate 101 respectively.
Further, the grip block 5 contacted with tapered end 2 and against surface on be additionally provided with stiffener 102, it is described plus
Strong component 102 is set along the bearing of trend of grip block 5.
Or the overbending direction side of linking arm 106 in the plane of grip block 5, there is the several and plane of grip block 5
Vertically along the stiffener 102 of the bearing of trend of grip block 5.
Further, the quantity of stiffener 102 is two, is arranged at intervals along the width of grip block 5, described two
Spacing between stiffener 102 is not less than the width of tapered end 2.
Wherein, there is the spacing for being used for accommodating the tapered end 2 between described two stiffeners 102.
Further, the stiffener 102 includes two panels reinforcing plate, and described reinforcing plate one end is connected with substrate 101, separately
One end gradually reduces close to the top of grip block 5 and height.
Also, the reinforcing plate root is connected with substrate 101, each reinforcing plate length is identical and is less than the length of grip block 5.
Further, the both sides of substrate 101 are additionally provided with the fixed plate to the extension of the outside of linking arm 106, the fixed plate
Be provided with the bolt hole for being used for the substrate 101 of the horn mounting seat 4 being fixed in aircraft body.
Also, the fixed plate also has has a connecting plate, the company with what the wrap direction cranked arm extended in the same direction
Fishplate bar is provided with the bolt hole for being used for being fixed on the substrate 101 of the horn mounting seat 4 in aircraft body.
Meanwhile the substrate 101 has the faying face of extension in cranking arm for linking arm 106 on its projecting direction, with reference to
Face is provided with the bolt hole for being used for being fixed on the substrate 101 of the horn mounting seat 4 on aircraft body.
Further, it is inclined-plane that the end of grip block 5, which has the side opposite with the contact surface of aircraft horn 1,.
Further, the end of linking arm 106 is in circular shape, which is provided with the hinge hole for installing jointed shaft
105。
Further, the substrate 101 also includes fixing hole 108, wherein, the fixing hole 108 on the substrate 101 is with admittedly
Determine bolt with aircraft body to be connected.
Horn mounting seat 4 described in the present embodiment both can be when needing aircraft horn 1 to be moved relative to aircraft body
The corresponding free degree is provided, it is also ensured that need aircraft horn 1 fix when for aircraft horn provide fixation and it is firm
Connection, also need to take into full account loss of weight problem while requirements above is met.
Embodiment in above-described embodiment can be further combined or replace, and embodiment is only to the present invention's
Preferred embodiment is described, and not the spirit and scope of the present invention are defined, and is not departing from design philosophy of the present invention
Under the premise of, various changes and modifications that professional and technical personnel in the art make to technical scheme belong to this hair
Bright protection domain.
Claims (9)
1. a kind of retaining mechanism of aircraft horn, including aircraft horn and for connecting aircraft horn and aircraft body
Horn mounting seat, it is characterised in that：The retaining mechanism includes being arranged at leading for inside and outside insertion on aircraft horn connection end
Xiang Kong, the tapered end slidably coordinated is provided with pilot hole, and be connected with tapered end and be arranged at the drawing pin on aircraft horn, institute
Tapered end is stated with drawing pin to move along a straight line in pilot hole, and the tapered end front end and the grip block that is arranged in horn mounting seat
Surface fitting contact or remote.
A kind of 2. retaining mechanism of aircraft horn according to claim 1, it is characterised in that：The retaining mechanism also wraps
Include to be arranged at and be used to limit the loose slot for drawing pin linear motion and the connecting portion for being arranged at tapered end rear end, institute on aircraft horn
State drawing pin one end to be fixedly connected with connecting portion, the other end runs through loose slot；
Wherein, the tapered end is with drawing pin to move along a straight line in pilot hole, forms the tapered end front end and grip block is scalable matches somebody with somebody
Close.
A kind of 3. retaining mechanism of aircraft horn according to claim 2, it is characterised in that：The loose slot and drawing are sold
It is arranged at the lower surface shell of aircraft horn.
A kind of 4. retaining mechanism of aircraft horn according to any one of claims 1 to 3, it is characterised in that：The locking
Mechanism also includes elastic component and position limiting structure, and described position limiting structure is fixedly mounted on horn, described elastic component one end with
Locking member is connected, and the other end is connected with position limiting structure.
A kind of 5. retaining mechanism of aircraft horn according to claim 4, it is characterised in that：The position limiting structure includes
Stopper slot and fixed part, described stopper slot are structure as a whole with fixed part, and described fixed part is connected with horn；
Wherein, described stopper slot inwall is engaged with elastic component.
6. according to a kind of retaining mechanism of any described aircraft horn of claim 4 or 5, it is characterised in that：The elasticity
Part is connected with connecting portion；
Wherein, the connecting portion is provided with locating dowel with elastic component junction, and described locating dowel is in elastic component.
A kind of 7. retaining mechanism of aircraft horn according to claim 2, it is characterised in that：Set in the loose slot
There is at least one limited impression with drawing pin card conjunction, after the limited impression is arranged at front end, and/or the loose slot of loose slot
End.
A kind of 8. retaining mechanism of aircraft horn according to claim 1, it is characterised in that：The tapered end front end is remote
Grip block side is provided with an inclined-plane.
9. according to a kind of retaining mechanism of any described aircraft horn of claim 1 or 8, it is characterised in that：The tapered end
It is provided with least one groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610459722.2A CN107521657B (en) | 2016-06-22 | 2016-06-22 | Locking mechanism of aircraft horn |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610459722.2A CN107521657B (en) | 2016-06-22 | 2016-06-22 | Locking mechanism of aircraft horn |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107521657A true CN107521657A (en) | 2017-12-29 |
| CN107521657B CN107521657B (en) | 2021-06-29 |
Family
ID=60735449
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610459722.2A Active CN107521657B (en) | 2016-06-22 | 2016-06-22 | Locking mechanism of aircraft horn |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107521657B (en) |
Citations (9)
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| CN101004234A (en) * | 2007-01-15 | 2007-07-25 | 张建明 | Locking device for metal expansion pipe |
| CN101023857A (en) * | 2007-02-12 | 2007-08-29 | 邬永龙 | Telescopic dust-collecting |
| CN202850585U (en) * | 2012-09-06 | 2013-04-03 | 香港巴福魅力有限公司上海代表处 | Quick foldable tent and slide block locking mechanism |
| CN204548479U (en) * | 2015-03-24 | 2015-08-12 | 陈灵峰 | A kind of folded piece of Multi-axis aircraft |
| CN204979229U (en) * | 2015-07-20 | 2016-01-20 | 河南凌云科技文化发展有限公司 | Many rotors are from novel folding horn of quick installation of dynamic formula and automatic locking |
| CN205022841U (en) * | 2015-09-06 | 2016-02-10 | 长沙鸿浪自动化科技有限公司 | A horn folding device for aircraft |
| CN205059994U (en) * | 2015-09-06 | 2016-03-02 | 湖南云顶智能科技有限公司 | A horn folding device for aircraft |
| CN105539827A (en) * | 2016-01-26 | 2016-05-04 | 南京航空航天大学 | Arm folding device of multi-axial air vehicle |
| CN105584621A (en) * | 2015-12-25 | 2016-05-18 | 北京臻迪机器人有限公司 | Aircraft |
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2016
- 2016-06-22 CN CN201610459722.2A patent/CN107521657B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101004234A (en) * | 2007-01-15 | 2007-07-25 | 张建明 | Locking device for metal expansion pipe |
| CN101023857A (en) * | 2007-02-12 | 2007-08-29 | 邬永龙 | Telescopic dust-collecting |
| CN202850585U (en) * | 2012-09-06 | 2013-04-03 | 香港巴福魅力有限公司上海代表处 | Quick foldable tent and slide block locking mechanism |
| CN204548479U (en) * | 2015-03-24 | 2015-08-12 | 陈灵峰 | A kind of folded piece of Multi-axis aircraft |
| CN204979229U (en) * | 2015-07-20 | 2016-01-20 | 河南凌云科技文化发展有限公司 | Many rotors are from novel folding horn of quick installation of dynamic formula and automatic locking |
| CN205022841U (en) * | 2015-09-06 | 2016-02-10 | 长沙鸿浪自动化科技有限公司 | A horn folding device for aircraft |
| CN205059994U (en) * | 2015-09-06 | 2016-03-02 | 湖南云顶智能科技有限公司 | A horn folding device for aircraft |
| CN105584621A (en) * | 2015-12-25 | 2016-05-18 | 北京臻迪机器人有限公司 | Aircraft |
| CN105539827A (en) * | 2016-01-26 | 2016-05-04 | 南京航空航天大学 | Arm folding device of multi-axial air vehicle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107521657B (en) | 2021-06-29 |
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