CN107161321A - A kind of folding mechanism and the aircraft using the mechanism - Google Patents
A kind of folding mechanism and the aircraft using the mechanism Download PDFInfo
- Publication number
- CN107161321A CN107161321A CN201710436944.7A CN201710436944A CN107161321A CN 107161321 A CN107161321 A CN 107161321A CN 201710436944 A CN201710436944 A CN 201710436944A CN 107161321 A CN107161321 A CN 107161321A
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- CN
- China
- Prior art keywords
- anglec
- engaging position
- fixing axle
- base stand
- folding mechanism
- Prior art date
- 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
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerials With Secondary Devices (AREA)
Abstract
The invention discloses the aircraft of a kind of folding mechanism and the use mechanism, including fixing axle, base stand location part, anglec of rotation part, elastic parts and fixture, base stand location part, anglec of rotation part, elastic parts and fixture are sequentially sleeved in fixing axle, elastic parts supports anglec of rotation part and fixture respectively, wherein, base stand location part is not set rotatably relative to fixing axle, and anglec of rotation part is rotatably set relative to fixing axle；Anglec of rotation part is circumferentially provided with the first engaging position and the first backstop position, the second backstop position that base stand location part is provided with the second engaging position for being adapted with the first engaging position and coordinated with the first backstop position, wherein the first engaging position with the first backstop on different circumference.The construction of fold mechanism is optimized, allows and is more stablized using the Flight Vehicle Structure of the folding mechanism.
Description
Technical field
The present invention relates to aircraft field, more particularly to a kind of folding mechanism and the aircraft using the mechanism.
Background technology
For convenience of transport, store, existing aircraft, which has, much all uses folded wing, and the machine of folded wing aircraft
Arm generally includes two parts, and Part I is fixedly connected with aircraft frame, and Part II is connected with propeller, Part I
Realized and be rotatably connected by a fold mechanism with Part II.
But the problem of folded wing aircraft has structural instability, specifically, horn Part II are easy to rotation
Excessively related to so as to cause horn Part II to be done something in disregard of obstacles with aircraft frame, scratch even damages the cause of aircraft frame side
Make aircraft frame side intensity decreases, and after aircraft frame side intensity decreases or damage, it is easy to cause aircraft to exist
Horn is separated with aircraft frame during flight, triggers unexpected.
The content of the invention
The technical problems to be solved by the invention are：A kind of new folding mechanism and the flight using the mechanism are provided
Device, the Flight Vehicle Structure is stable.
In order to solve the above-mentioned technical problem, the technical solution adopted by the present invention is：A kind of folding mechanism, including fixation
Axle, base stand location part, anglec of rotation part, elastic parts and fixture, base stand location part, anglec of rotation part, elastic parts and solid
Determine part to be sequentially sleeved in fixing axle, elastic parts supports anglec of rotation part and fixture respectively, wherein, base stand location part is relative
Do not set rotatably in fixing axle, anglec of rotation part is rotatably set relative to fixing axle；The anglec of rotation part is circumferentially disposed
Have the first engaging position and the first backstop position, base stand location part be provided with the second engaging position for being adapted with first engaging position with
And the second backstop position coordinated with first backstop position, wherein the first engaging position and the first backstop are on different circumference.
The present invention also uses following technical scheme：A kind of aircraft using the folding mechanism, including horn and machine
Body, the anglec of rotation part is fixedly connected with horn, and the base stand location part is fixedly connected with fuselage.
The beneficial effects of the present invention are：Set engaging position that anglec of rotation part can be made to consolidate with base stand location part relative position
Surely prevent the anglec of rotation part from unexpected rotate occur；Backstop position is set to prevent the anglec of rotation part from inordinate rotation occur and causing rotation
The object of gyration part connection occurs doing something in disregard of obstacles with the object that base stand location part is connected to be related to, and optimizes the construction of fold mechanism, allowing makes
More stablized with the product structure of the folding mechanism.
Brief description of the drawings
Fig. 1 is the structural representation of the aircraft of the embodiment of the present invention one (when horn is folded)：
Fig. 2 is the structural representation of the aircraft of the embodiment of the present invention one (when horn deploys)：
Fig. 3 for the embodiment of the present invention one aircraft in folding mechanism integrally-built schematic diagram；
Fig. 4 for the embodiment of the present invention one aircraft in folding mechanism explosive view；
Fig. 5 for the embodiment of the present invention one aircraft in folding mechanism in anglec of rotation part structural representation；
Fig. 6 for the embodiment of the present invention one aircraft in folding mechanism in base stand location part structural representation；
Fig. 7 for the embodiment of the present invention one aircraft in folding mechanism in elastic parts sectional view；
Fig. 8 for the embodiment of the present invention one aircraft in folding mechanism in anglec of rotation part top view；
Fig. 9 for the embodiment of the present invention one aircraft in folding mechanism in fixing axle front view；
Figure 10 for the embodiment of the present invention one aircraft in folding mechanism in fixing axle sectional view.
Label declaration：
1st, horn；2nd, fuselage；3rd, folding mechanism；4th, fixing axle；41st, flat position；
5th, base stand location part；51st, the second engaging position；52nd, the 4th engaging position；53rd, the second backstop position；
6th, anglec of rotation part；61st, the first engaging position；62nd, the 3rd engaging position；63rd, the first backstop position；
64th, the first engaging inclined-plane；65th, cylinder；7th, elastic parts；8th, fixture；9th, slipmat.
Embodiment
To describe technology contents, the objects and the effects of the present invention in detail, below in conjunction with embodiment and coordinate attached
Figure is explained.
The design of most critical of the present invention is：Backstop position is set, will be relative between anglec of rotation part and base stand location part
Rotation is limited in certain angular range.
Fig. 1 be refer to Figure 10, a kind of folding mechanism, including fixing axle 4, base stand location part 5, anglec of rotation part 6, bullet
Property component 7 and fixture 8, base stand location part 5, anglec of rotation part 6, elastic parts 7 and fixture 8 are sequentially sleeved at fixing axle 4
On, elastic parts 7 supports anglec of rotation part 6 and fixture 8 respectively, wherein, base stand location part 5 can not turn relative to fixing axle 4
Dynamic to set, anglec of rotation part 6 is rotatably set relative to fixing axle 4；The anglec of rotation part 6 is circumferentially provided with the first engaging position
61 and the first backstop position 63, base stand location part 5 be provided with the second engaging position 51 for being adapted with first engaging position 61 and
The the second backstop position 53 coordinated with first backstop position 63, wherein the first engaging position 61 and the first backstop 63 are in different circles
Zhou Shang.
The operation principle of the present invention is summarized as follows：Anglec of rotation part 6 is fixed on aircraft horn 1, base stand location part 5
It is fixed on aircraft fuselage 2, passes through the first engaging position 61 on anglec of rotation part 6 and the second engaging position 51 on base stand location part 5
Engaging so that the angle of aircraft horn 1 and fuselage 2 is relatively fixed；When needing that horn 1 is folded or deployed, only need by
Clockwise or counterclockwise rotation of the horn 1 along fixing axle 4, the first engaging position 61 is turned to second engaging position 51 in downstream
Interior (engaging position of fluted body has multiple), untill horn 1 is folded or deployed；When user misoperation is rotated further horn
When 1, the first backstop position 63 will be contacted so as to prevent horn 1 from being rotated further with the second backstop position 53, be effectively prevented from horn 1 and scraped
Wear bad fuselage 2 situation appearance.
Also, the number of engaging position, and can root along the anglec of rotation between the circumferentially disposed adjacent engaging position of fixing axle 4
Set according to the concrete condition of preceding horn and rear horn.For example, the first engaging position 61 on preceding horn anglec of rotation part 6 can be set
For three, the angle between adjacent first engaging position 61 is 50 degree；Then the first engaging position 61 on horn anglec of rotation part 6 can
With the angle that is set between two, two the first engaging positions 61 for 160 degree.
It was found from foregoing description, the beneficial effects of the present invention are：Engaging position is set to make anglec of rotation part and pedestal
Keeper relative position, which is fixed, prevents anglec of rotation part from unexpected rotate occur；Backstop position is set to prevent the anglec of rotation part from going out
The object that existing inordinate rotation causes anglec of rotation part to connect occurs doing something in disregard of obstacles with the object that base stand location part is connected to be related to, and optimizes folding
The construction of mechanism, is allowed and is more stablized using the product structure of the folding mechanism.
Further, the first engaging position 61 is provided with the first engaging inclined-plane 64 clockwise and counterclockwise.
Seen from the above description, set engaging inclined-plane to be conducive to the cooperation of the first engaging position and the second engaging position, separate, subtract
Few frictional dissipation between first engaging position and the second engaging position.
Further, anglec of rotation part 6 is circumferentially provided with the 3rd engaging position 62, and base stand location part 5 is provided with and the 3rd card
The 4th engaging position 52 that position 62 is adapted is closed, the 3rd engaging position 62 and the first engaging position 61 are on same circumference.
Further, the 3rd engaging position 62 is distributed on different semicircles from the first engaging position 61.
Seen from the above description, the structure of the 3rd engaging position and the first engaging position can be that identical can also be differed
, the preferably first engaging is located at the 3rd engaging bit architecture and differed.For example, the first engaging position is big by one compared to the 3rd engaging position
Point.
Further, the fixing axle 4 is symmetrically arranged with flat position 41 along central shaft, the anglec of rotation part 6 be provided with
The circular hole that fixing axle 4 is adapted, the base stand location part 5 is provided with the slotted hole being adapted with fixing axle 4.
Seen from the above description, fixing axle sets flat position, base stand location part to set slotted hole to be a kind of fixing axle and pedestal
The specific implementation that keeper is not set rotatably.Certain base stand location part is fixedly connected or is integrally formed with fixing axle
It is feasible.
Further, powder metallurgical technique shaping is respectively adopted in base stand location part 5 and anglec of rotation part 6.
Seen from the above description, base stand location part and anglec of rotation part construction are complicated, and a kind of nothing is cut when powder metallurgy is processed
Technique is cut, base stand location part and anglec of rotation part can be avoided the phenomenon of stress concentration occur, make base stand location part and the anglec of rotation
Degree part possesses good machinery, physical property, is conducive to further improving the stability of Flight Vehicle Structure.
Further, the fixture 8 is nut, and the nut is threadedly coupled and is welded and fixed with fixing axle 4.
Seen from the above description, after nut is tightened by thread and fixing axle, it is further added by welding procedure, it is ensured that collapsible
Mechanism will not loosen in multiple reciprocatory movement, be effectively guaranteed the flight stability of aircraft.
Further, in addition to the slipmat 9 that is set in fixing axle 4, the slipmat 9 is located at elastic parts 7 and rotation
Between gyration part 6, slipmat 9 is provided with multiple through holes.
Seen from the above description, slipmat designs multiple through holes, is conducive to strengthening slipmat and elastic parts and the anglec of rotation
Spend the friction of part.The shape of through hole is varied, can be circle, polygon etc..
Further, the elastic parts 7 includes multiple shell fragments mutually abutted, and the end face of the shell fragment is provided with depression
Portion.
Seen from the above description, being set on shell fragment has certain tension force after depressed part, compression.Certainly, the elastic parts
It is also feasible for spring.
The present invention also provides a kind of aircraft using above-mentioned folding mechanism, including horn 1 and fuselage 2, the rotation
Angle part 6 is fixedly connected with horn 1, and the base stand location part 5 is fixedly connected with fuselage 2.
Embodiment one
Fig. 1 to Figure 10 is refer to, embodiments of the invention one are：As shown in Figures 1 to 6, a kind of aircraft, including horn
1st, fuselage 2 and folding mechanism 3；The folding mechanism 3 includes fixing axle 4, base stand location part 5, anglec of rotation part 6, elasticity
Component 7 and fixture 8, base stand location part 5, anglec of rotation part 6, elastic parts 7 and fixture 8 are sequentially sleeved in fixing axle 4,
Elastic parts 7 supports anglec of rotation part 6 and fixture 8 respectively, wherein, base stand location part 5 is not set rotatably relative to fixing axle 4
Put, anglec of rotation part 6 is rotatably set relative to fixing axle 4；The anglec of rotation part 6 is circumferentially provided with the He of the first engaging position 61
First backstop position 63, base stand location part 5 be provided with the second engaging position 51 for being adapted with first engaging position 61 and with institute
The second backstop position 53 that the first backstop position 63 coordinates is stated, wherein the first engaging position 61 and the first backstop 63 are in different circumference
On, the anglec of rotation part 6 is fixedly connected with horn 1, and the base stand location part 5 is fixedly connected with fuselage 2.
Fig. 5 and Fig. 6 are referred to, further, first engaging position 61 is provided with first clockwise and counterclockwise
Engage inclined-plane 64, the second engaging position 51 is provided with the be adapted with the first engaging inclined-plane 64 clockwise and counterclockwise
Two engaging inclined-planes.
First engaging position 61 is the boss being arranged on the end face of anglec of rotation part 6, the first engaging inclined-plane 64
It is downwardly extending from the boss to the end slope of anglec of rotation part 6；Second engaging position 51 sets for the correspondence boss
The groove put, the second engaging inclined-plane is downwardly extending from the end face of angle locating piece to the groove slant.Or, institute
It is the groove being arranged on the end face of anglec of rotation part 6 to state the first engaging position 61, and the first engaging inclined-plane 64 is by the anglec of rotation
The end face of part 6 is downwardly extending to the groove slant；The boss that second engaging position 51 is set for the correspondence groove,
The end slope of second engaging inclined-plane from the boss to the angle locating piece is downwardly extending.In the present embodiment, fold
Formula mechanism 3 is exactly using second above-mentioned of set-up mode.
As a kind of preferred embodiment, the first backstop position 63 and the second backstop position 53 are respectively projection, wherein
There is a kind of backstop position provided with two, such as, the quantity of the first backstop position 63 is set to two, and the second backstop position 53 then can only be along two
Arc section activity between individual first backstop position 63, so as to reach spacing effect.
Fig. 5 and Fig. 6 are referred to, as a kind of fool-proof design, anglec of rotation part 6 is circumferentially provided with the 3rd engaging position 62, base
Seat keeper 5 is provided with the 4th engaging position 52 being adapted with the 3rd engaging position 62, the 3rd engaging position 62 and the first engaging position 61
On same circumference.It is preferred that, the 3rd engaging position 62 is distributed on different semicircles from the first engaging position 61.The present embodiment
In, the first engaging position 61 and the 3rd engaging position 62 are oppositely arranged (setting of 180 ° of interval), the 3rd engaging position 62 and the first engaging position
61 construction is identical but of different sizes.
Fig. 4 and Fig. 9 are referred to, specifically, the fixing axle 4 is symmetrically arranged with flat position 41, the rotation along central shaft
Angle part 6 is provided with the circular hole being adapted with fixing axle 4, and the base stand location part 5 is oval provided with what is be adapted with fixing axle 4
Hole.One end of the fixing axle 4 is provided with limiting platform, and the base stand location part 5 supports the limiting platform.
To improve the intensity and service life of base stand location part 5 and anglec of rotation part 6, base stand location part 5 and the anglec of rotation
Powder metallurgical technique shaping is respectively adopted in part 6.
Fig. 3 and Fig. 4 are referred to, the fixture 8 is nut, and the nut is threadedly coupled with fixing axle 4, to prevent horn
Fixture 8 is separated with fixing axle 4 after more than 1 rotation, and nut is welded and fixed after being spirally connected with fixing axle 4, is conducive to further
Improve the stability of Flight Vehicle Structure.
Also include the slipmat 9 being set in fixing axle 4, the slipmat 9 is located at elastic parts 7 and anglec of rotation part 6
Between, slipmat 9 is provided with multiple through holes, and the through hole is square opening.
Fig. 3, Fig. 4 and Fig. 7 are referred to, further, the elastic parts 7 includes multiple shell fragments mutually abutted, described
The end face of shell fragment is provided with depressed part, the present embodiment, and elastic parts 7 includes three shell fragments, the depressed part phase of two of which shell fragment
To setting, the depressed part of another shell fragment is against slipmat 9.In other embodiments, the elastic parts 7 can be spring.
As shown in figures 3 and 8, more stablize to allow horn 1 to be connected with anglec of rotation part 6, anglec of rotation part 6 is provided with court
The cylinder 65 extended away from the direction of base stand location part 5, the cylinder 65 has axially disposed internal thread, so that horn
1 with anglec of rotation part 6 when being connected, and attachment screw has longer effective fastening length.Similarly, can also on base stand location part 5
Carry out identical setting.The installation site of folding mechanism 3 is not differentiated between, anglec of rotation part 6 is provided with mark.
Fig. 9 and Figure 10 are referred to, preferably, be through hole in the middle of fixing axle 4, when finished product is assembled, motor lines, antenna can be from
Passed through at the hole, can effectively protect cable, prevent cable scratch, and wiring space can be reduced, while being effectively prevented line
Put chaotic and influence damping problem in road.
In summary, the present invention is provided folding mechanism and the aircraft using the mechanism, set engaging position to make
Anglec of rotation part is fixed with base stand location part relative position prevents anglec of rotation part from unexpected rotate occur；Set backstop position can be with
Prevent anglec of rotation part from the object appearance that inordinate rotation causes the object of anglec of rotation part connection to be connected with base stand location part occur
Do something in disregard of obstacles and relate to, optimize the construction of fold mechanism, allow and more stablized using the Flight Vehicle Structure of the folding mechanism.
Embodiments of the invention are the foregoing is only, are not intended to limit the scope of the invention, it is every to utilize this hair
The equivalents that bright specification and accompanying drawing content are made, or the technical field of correlation is directly or indirectly used in, similarly include
In the scope of patent protection of the present invention.
Claims (10)
1. a kind of folding mechanism, it is characterised in that：Including fixing axle, base stand location part, anglec of rotation part, elastic parts and solid
Determine part, base stand location part, anglec of rotation part, elastic parts and fixture are sequentially sleeved in fixing axle, and elastic parts is supported respectively
Hold anglec of rotation part and fixture, wherein, base stand location part is not set rotatably relative to fixing axle, anglec of rotation part relative to
Fixing axle is rotatably set；The anglec of rotation part is circumferentially provided with the first engaging position and the first backstop position, base stand location part
The the second backstop position coordinated provided with the second engaging position being adapted with first engaging position and with first backstop position, its
In the first engaging position and the first backstop position on different circumference.
2. folding mechanism according to claim 1, it is characterised in that：First engaging position is clockwise and counterclockwise
It is provided with the first engaging inclined-plane.
3. folding mechanism according to claim 1, it is characterised in that：Anglec of rotation part is circumferentially provided with the 3rd engaging
Position, base stand location part is provided with the 4th engaging position being adapted with the 3rd engaging position, and the 3rd engaging position is located at the first engaging position
On same circumference.
4. folding mechanism according to claim 3, it is characterised in that：3rd engaging position is distributed in not with the first engaging position
On same semicircle.
5. folding mechanism according to claim 1, it is characterised in that：The fixing axle is symmetrically arranged with along central shaft
Flat position, the anglec of rotation part is provided with the circular hole being adapted with fixing axle, and the base stand location part is provided with and mutually fitted with fixing axle
The slotted hole matched somebody with somebody.
6. folding mechanism according to claim 1, it is characterised in that：Base stand location part and anglec of rotation part are respectively adopted
Powder metallurgical technique is molded.
7. folding mechanism according to claim 1, it is characterised in that：The fixture is nut, and the nut is with consolidating
Dead axle is threadedly coupled and is welded and fixed.
8. folding mechanism according to claim 1, it is characterised in that：Also include the slipmat being set in fixing axle,
The slipmat is located between elastic parts and anglec of rotation part, and slipmat is provided with multiple through holes.
9. folding mechanism according to claim 1, it is characterised in that：The elastic parts includes multiple mutually abutting
Shell fragment, the end face of the shell fragment is provided with depressed part.
10. a kind of aircraft of the folding mechanism with described in any one in claim 1~9, it is characterised in that：Including
Horn and fuselage, the anglec of rotation part are fixedly connected with horn, and the base stand location part is fixedly connected with fuselage.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710436944.7A CN107161321A (en) | 2017-06-12 | 2017-06-12 | A kind of folding mechanism and the aircraft using the mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710436944.7A CN107161321A (en) | 2017-06-12 | 2017-06-12 | A kind of folding mechanism and the aircraft using the mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107161321A true CN107161321A (en) | 2017-09-15 |
Family
ID=59825135
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710436944.7A Pending CN107161321A (en) | 2017-06-12 | 2017-06-12 | A kind of folding mechanism and the aircraft using the mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107161321A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107672782A (en) * | 2017-11-01 | 2018-02-09 | 深圳市高巨创新科技开发有限公司 | A kind of rotating shaft mechanism and the aircraft with the rotating shaft mechanism |
| CN111422345A (en) * | 2020-05-13 | 2020-07-17 | 成都纵横大鹏无人机科技有限公司 | Rotating assembly |
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| JP2015051740A (en) * | 2013-09-09 | 2015-03-19 | ブリヂストンサイクル株式会社 | Folding type bicycle |
| CN205168886U (en) * | 2015-11-26 | 2016-04-20 | 深圳智航无人机有限公司 | Folding unmanned vehicles |
| CN106347623A (en) * | 2016-09-20 | 2017-01-25 | 深圳市高巨创新科技开发有限公司 | Aircraft rotation shaft and aircraft |
| CN205971800U (en) * | 2016-07-15 | 2017-02-22 | 深圳曼塔智能科技有限公司 | Unmanned aerial vehicle |
| CN206797701U (en) * | 2017-06-12 | 2017-12-26 | 深圳市高巨创新科技开发有限公司 | A kind of folding mechanism and the aircraft using the mechanism |
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2017
- 2017-06-12 CN CN201710436944.7A patent/CN107161321A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2015051740A (en) * | 2013-09-09 | 2015-03-19 | ブリヂストンサイクル株式会社 | Folding type bicycle |
| CN205168886U (en) * | 2015-11-26 | 2016-04-20 | 深圳智航无人机有限公司 | Folding unmanned vehicles |
| CN205971800U (en) * | 2016-07-15 | 2017-02-22 | 深圳曼塔智能科技有限公司 | Unmanned aerial vehicle |
| CN106347623A (en) * | 2016-09-20 | 2017-01-25 | 深圳市高巨创新科技开发有限公司 | Aircraft rotation shaft and aircraft |
| CN206797701U (en) * | 2017-06-12 | 2017-12-26 | 深圳市高巨创新科技开发有限公司 | A kind of folding mechanism and the aircraft using the mechanism |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107672782A (en) * | 2017-11-01 | 2018-02-09 | 深圳市高巨创新科技开发有限公司 | A kind of rotating shaft mechanism and the aircraft with the rotating shaft mechanism |
| CN107672782B (en) * | 2017-11-01 | 2024-05-14 | 深圳市高巨创新科技开发有限公司 | Rotating shaft mechanism and aircraft with same |
| CN111422345A (en) * | 2020-05-13 | 2020-07-17 | 成都纵横大鹏无人机科技有限公司 | Rotating assembly |
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