CN106494615A - Unmanned plane tail rotor - Google Patents
Unmanned plane tail rotor Download PDFInfo
- Publication number
- CN106494615A CN106494615A CN201610978616.5A CN201610978616A CN106494615A CN 106494615 A CN106494615 A CN 106494615A CN 201610978616 A CN201610978616 A CN 201610978616A CN 106494615 A CN106494615 A CN 106494615A
- Authority
- CN
- China
- Prior art keywords
- axle
- unmanned plane
- tail rotor
- oar folder
- oar
- 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.)
- Pending
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Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U10/00—Type of UAV
- B64U10/10—Rotorcrafts
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Remote Sensing (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of unmanned plane tail rotor, including rotating tailing axle, oar folder axle, damping material, oar folder, tail rotor head deep groove ball bearing, thrust bearing and fixture；Wherein, rotation tailing axle one end is vertically set in the tail-rotor fixed seat of unmanned plane, is mounted with tailspin wing head by fixture on the other end；Oar folder axle is arranged in tailspin wing head and vertical with the axial direction of rotation tailing axle, and damping material is arranged in tailspin wing head and is coordinated with oar folder axle outer wall installs fixation；The two ends of oar folder axle are connected to oar folder, are provided with deep groove ball bearing on oar folder, and thrust bearing is pressed from both sides by fastening screw on oar folder axle with oar.The unmanned plane tail rotor simple structure, easy to assembly, it is steady to enable to unmanned plane during flying, and can effectively extend unmanned plane service life.
Description
Technical field
The present invention relates to unmanned plane parts, in particular it relates to unmanned plane tail rotor.
Background technology
Oar folder axle is typically passed through steady pin on rotation tailing axle by conventional unmanned plane tail rotor at present, and oar presss from both sides axle
Mostly be with tailspin wing head and be rigidly connected, then blade is respectively mounted at the two ends of oar folder, during flying before unmanned plane, unmanned plane
Afterbody vibrations very big, the athletic meeting of tail rotor is had an impact, and oar folder axle is rigidly connected with tail rotor end to end and causes to shake
Vibrations will not be mitigated, then unmanned plane during flying can be caused unstable, and the parts depreciation speed on unmanned plane is accelerated, and is susceptible to revolve
Turn phenomenon of rupture between main shaft and blade connecting shaft, unmanned plane is difficult to the requirement for reaching precise control flight.
Therefore, urgent need will provide a kind of reasonable in design, and assembling is simple, cause unmanned plane during flying steady, and can be effectively
Extend the unmanned plane tail rotor of unmanned plane service life.
Content of the invention
It is an object of the invention to provide a kind of unmanned plane tail rotor, unmanned plane tail rotor simple structure, easy to assembly, the energy
Enough so that unmanned plane during flying is steady, and can effectively extend unmanned plane service life.
To achieve these goals, the invention provides a kind of unmanned plane tail rotor, the unmanned plane tail rotor includes rotating
Tailing axle, oar folder axle, damping material, oar folder, tail rotor head deep groove ball bearing, thrust bearing and fixture；Wherein,
Rotation tailing axle one end is vertically set in the tail-rotor fixed seat of unmanned plane, is installed by fixture and fix on the other end
There is tailspin wing head；
Oar folder axle is arranged in tailspin wing head and vertical with the axial direction of rotation tailing axle, and damping material is arranged on tail rotor
On head and coordinate to install with oar folder axle outer wall and fix；
The two ends of oar folder axle are connected to oar folder, are provided with deep groove ball bearing on oar folder, and thrust bearing and oar press from both sides by
Fastening screw is on oar folder axle.
Preferably, fixture includes backstop lid, the first steady pin, the second steady pin and backstop lid fixing bolt；Wherein,
First steady pin is engaged to be fixed on tailspin wing head with the pin-and-hole in tailspin wing head respectively with the second steady pin
On rotation tailing axle, and sell with pin-and-hole with being combined into interference fit；
Backstop lid is fixed in tailspin wing head by backstop lid fixing bolt.
Preferably, unmanned plane tail rotor also includes back-up ring, back-up ring the both sides that oar presss from both sides axle be symmetrical arranged and be arranged on tail
Damping material in the two side holes of rotor head connects.
Preferably, the material of damping material is neoprene.
Preferably, oar folder axle includes the first axle body of cylinder, and the two ends end face of the first axle body is respectively partly along axis side
The second axle body is formed to outwardly convex, the first axle body and the second axle body are coaxially disposed, also, the first axle body is with diameter greater than the second axle
The diameter of body；
The second axle body end face part caves inward in the axial direction and is formed with blind screw hole, and blind screw hole is along first
The central axial direction of axis body extends.
Preferably, 1.1-1.2 times of a diameter of the second axle body diameter of the first axle body.
Preferably, 1.2-1.4 times of a diameter of blind screw hole diameter of the second axle body.
Preferably, 1/10-1/8 of the depth of blind screw hole for the first axle body height.
Preferably, the first axle body and the second axle body are metal axis body.
Preferably, metal axis body is stainless steel axis body.
According to above-mentioned technical proposal, the present invention is provided with fixing hole, fixing hole and fixture phase interworking on rotation tailing axle
Close so that tailspin wing head be fixed on rotation tailing axle on, wherein, fixture include backstop lid, the first steady pin, the second steady pin and
Backstop lid fixing bolt, the two ends of first and second steady pin are provided with backstop lid, and backstop lid is arranged on tail rotor by bolt
On head, the first steady pin and the second steady pin are fixed on rotation tailing axle as interference fit, slurry folder axle piece axle of tail, are arranged on tail
It is to install with damping material on rotor head so that the vibrations of unmanned plane awing tail-rotor can damped material absorption one
Point, so as to increase the service life of tail-rotor part, slurry folder axle is arranged in tailspin wing head, because not by damping material and back-up ring
It is to be rigidly connected and for an axle, so that the cooperation of slurry folder axle and other parts is more preferably, the service life for increasing part is reduced
The damage of part, is the easier for installation of part, can effectively extend making for each connection member on unmanned plane tail rotor
With the life-span, and make aircraft be more easy to manipulate, fly more steady.
Other features and advantages of the present invention will be described in detail in subsequent specific embodiment part.
Description of the drawings
Accompanying drawing is for providing a further understanding of the present invention, and constitutes the part of specification, with following tool
Body embodiment is used for explaining the present invention together, but is not construed as limiting the invention.In the accompanying drawings：
Fig. 1 is the structural representation of the unmanned plane tail rotor in a kind of embodiment according to present invention offer；
Fig. 2 is the rearview of the unmanned plane tail rotor in a kind of embodiment according to present invention offer.
Description of reference numerals
1- oars press from both sides 2- damping materials
3- oars press from both sides axle 4- back-up rings
5- backstop lid 6- backstop lid fixing bolts
7- rotates tailing axle 8- tailspin wing heads
9- deep groove ball bearing 10- thrust bearings
The first steady pin of 11- fastening screws 12-
The second steady pins of 13-
Specific embodiment
The specific embodiment of the present invention is described in detail below in conjunction with accompanying drawing.It should be appreciated that this place is retouched
The specific embodiment that states is merely to illustrate and explains the present invention, is not limited to the present invention.
In the present invention, in the case where contrary explanation is not made, the noun of locality that " inside and outside " etc. is included in term is only represented
Orientation of the term under normal service condition, or be skilled artisan understands that be commonly called as, and be not construed as to the term
Restriction.
Referring to Fig. 1, a kind of unmanned plane tail rotor of the invention, unmanned plane tail rotor include rotating tailing axle 7, oar folder axle 3, damping
Material 2, oar folder 1,8 deep groove ball bearing 9 of tailspin wing head, thrust bearing 10 and fixture；Wherein,
7 one end of rotation tailing axle is vertically set in the tail-rotor fixed seat of unmanned plane, is installed by fixture solid on the other end
Surely there is tailspin wing head 8；
Oar folder axle 3 is arranged in tailspin wing head 8 and vertical with the axial direction of rotation tailing axle 7, and damping material 2 is arranged on tail
On rotor head 8 and coordinate to install with oar 3 outer wall of folder axle and fix；
The two ends of oar folder axle 3 are connected to oar folder 1, are provided with deep groove ball bearing 9 on oar folder 1, and thrust bearing 10 with
Oar folder 1 is pressed from both sides on axle 3 installed in oar by fastening screw 11.
By above-mentioned technical proposal, the present invention is provided with fixing hole, fixing hole and fixture phase interworking on rotation tailing axle 7
Close so that tailspin wing head 8 is fixed on rotation tailing axle 7, wherein, fixture includes that backstop lid 5, the first steady pin 12, second are solid
Rationed marketing 13 and backstop lid fixing bolt 6, the two ends of first and second steady pin are provided with backstop lid 5, and backstop lid 5 is set by bolt
Put in tailspin wing head 8, the first steady pin 12 and the second steady pin 13 are fixed on rotation tailing axle 7 as interference fit, slurry folder axle
Piece axle of tail, being arranged in tailspin wing head 8 is installed with damping material 2 so that the vibrations of unmanned plane awing tail-rotor
The damped material 2 of meeting absorbs a part, and so as to increase the service life of tail-rotor part, slurry folder axle is by damping material 2 and gear
Circle 4 is arranged in tailspin wing head 8, because not being to be rigidly connected and being an axle, so that the cooperation of slurry folder axle and other parts is more
Good, the service life for increasing part reduces the damage of part, makes the easier for installation of part, can effectively extend nobody
The service life of each connection member on tail rotor, and make aircraft be more easy to manipulate, fly more steady.
In the present embodiment, in order to optimize the structure of fixture, as shown in Figure 2, it is preferable that fixture includes backstop lid
5th, the first steady pin 12, the second steady pin 13 and backstop lid fixing bolt 6；Wherein,
First steady pin 12 and the second steady pin 13 are engaged with the pin-and-hole in tailspin wing head 8 respectively with by tailspin wing head 8
It is fixed on rotation tailing axle 7, and sells with pin-and-hole with being combined into interference fit；
Backstop lid 5 is fixed in tailspin wing head 8 by backstop lid fixing bolt 6.
In order to avoid being rigidly connected between each part of unmanned plane tail rotor and rigidity friction, it is preferable that the unmanned tail
Rotor also includes back-up ring 4, back-up ring 4 the both sides that oar presss from both sides axle 3 be symmetrical arranged and with the resistance being arranged in the two side holes of tailspin wing head 8
Damping material 2 connects.
Above-mentioned damping material 2 can be made of common any flexible material in this area, but from being easy to draw materials
From the point of view of control cost, it is preferable that the material of damping material 2 is neoprene.
Additionally, pressing from both sides the structure of axle 3 in order to optimize oar, preferably oar folder axle 3 includes the first axle body of cylinder, the first axle body
Partly outwardly convex forms the second axle body to two ends end face in the axial direction respectively, and the first axle body and the second axle body are coaxially disposed, and
And, diameter of the first axle body with diameter greater than the second axle body；
The second axle body end face part caves inward in the axial direction and is formed with blind screw hole, and blind screw hole is along first
The central axial direction of axis body extends.So, the purpose of design of tail-rotor of the invention folder axle the second axle body structure is in order in tail
Step is formed on oar folder axle, for the fixed end face with its mating parts, while bolt presss from both sides the company of the screwed hole on axle with tail-rotor
Connect and can fix the other end for changing part, so as to ensure that axial workpiece presss from both sides the axial restraint on axle in tail-rotor, it is achieved that will
Tail-rotor folder axle rotation output to tail-rotor rotation, balance because main rotor rotate produce reaction torque, it is ensured that body steady
Fixed.
In the present embodiment, in order to optimize the connection of the first axle body and the second axle body and improve the mechanical strength of junction
Prevent deformation, it is preferable that 1.1-1.2 times of a diameter of the second axle body diameter of the first axle body.
For prevent blind screw hole diameter value excessive cause the second axle body lower thickness and cause overall become fragile easy to break, excellent
Select a diameter of blind screw hole diameter of the second axle body 1.2-1.4 times.
Likewise, for preventing, blind screw hole depth value is excessive to be caused the first axle body lower thickness and causes overall becoming fragile
Easy to break, it is preferable that 1/10-1/8 of the depth of blind screw hole for the first axle body height.
Additionally, for the mechanical strength for improving the unmanned plane tail-rotor folder, it is preferable that the first axle body and the second axle body are gold
Category axis body.
Above-mentioned metal axis body can be made of common any metal material in this area, such as iron, copper etc., but from
It is easy to angle consideration of drawing materials and increase the service life, preferably metal axis body is stainless steel axis body.
The preferred embodiment of the present invention is described in detail above in association with accompanying drawing, but, the present invention is not limited to above-mentioned reality
The detail in mode is applied, in the range of the technology design of the present invention, multiple letters can be carried out to technical scheme
Monotropic type, these simple variants belong to protection scope of the present invention.
It is further to note that each particular technique feature described in above-mentioned specific embodiment, in not lance
In the case of shield, can be combined by any suitable means, in order to avoid unnecessary repetition, the present invention to various can
The combination of energy is no longer separately illustrated.
Additionally, can also be combined between a variety of embodiments of the present invention, as long as which is without prejudice to this
The thought of invention, its should equally be considered as content disclosed in this invention.
Claims (10)
1. a kind of unmanned plane tail rotor, it is characterised in that the unmanned plane tail rotor include rotating tailing axle (7), oar folder axle (3),
Damping material (2), oar folder (1), tailspin wing head (8) deep groove ball bearing (9), thrust bearing (10) and fixture；Wherein,
Described rotation tailing axle (7) one end is vertically set in the tail-rotor fixed seat of unmanned plane, passes through the fixture on the other end
It is mounted with tailspin wing head (8)；
Oar folder axle (3) is arranged on described tailspin wing head (8) above and vertical with the axial direction of rotation tailing axle (7), institute
State damping material (2) to be arranged on described tailspin wing head (8) above and coordinate installation to fix with oar folder axle (3) outer wall；
The two ends of oar folder axle (3) are connected to oar folder (1), are provided with deep groove ball bearing on oar folder (1)
(9), and the thrust bearing (10) and oar folder (1) by fastening screw (11) on oar folder axle (3).
2. unmanned plane tail rotor according to claim 1, it is characterised in that the fixture include backstop lid (5), first
Steady pin (12), the second steady pin (13) and backstop lid fixing bolt (6)；Wherein,
First steady pin (12) are engaged to incite somebody to action with the second steady pin (13) respectively with the pin-and-hole on tailspin wing head (8)
Tailspin wing head (8) are fixed on rotation tailing axle (7), and the pin and pin-and-hole are with being combined into interference fit；
Described backstop lid (5) are fixed on tailspin wing head (8) by backstop lid fixing bolt (6).
3. unmanned plane tail rotor according to claim 1, it is characterised in that the unmanned plane tail rotor also includes back-up ring
(4), back-up ring (4) the oar press from both sides axle (3) both sides be symmetrical arranged and with the two side holes for being arranged on tailspin wing head (8)
The interior damping material (2) connects.
4. unmanned plane tail rotor according to claim 1, it is characterised in that the material of damping material (2) is neoprene
Rubber.
5. unmanned plane tail rotor according to claim 1, it is characterised in that oar folder axle (3) includes the of cylinder
One axis body, outwardly convex forms the second axle body in the axial direction for part respectively for the two ends end face of the first axle body, and described first
Axis body and the second axle body are coaxially disposed, also, the first axle body is with diameter greater than the diameter of the second axle body；
The second axle body end face part caves inward in the axial direction and is formed with blind screw hole, the blind screw hole edge
The central axial direction of the first axle body extends.
6. unmanned plane tail rotor according to claim 5, it is characterised in that a diameter of second axle of the first axle body
1.1-1.2 times of body diameter.
7. unmanned plane tail rotor according to claim 6, it is characterised in that a diameter of internal thread of the second axle body
1.2-1.4 times of blind hole diameter.
8. unmanned plane tail rotor according to claim 5, it is characterised in that the depth of the blind screw hole is described the
The 1/10-1/8 of one axis body height.
9. unmanned plane tail rotor according to claim 5, it is characterised in that the first axle body and the second axle body are gold
Category axis body.
10. unmanned plane tail rotor according to claim 9, it is characterised in that the metal axis body is stainless steel axis body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610978616.5A CN106494615A (en) | 2016-11-08 | 2016-11-08 | Unmanned plane tail rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610978616.5A CN106494615A (en) | 2016-11-08 | 2016-11-08 | Unmanned plane tail rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106494615A true CN106494615A (en) | 2017-03-15 |
Family
ID=58323304
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610978616.5A Pending CN106494615A (en) | 2016-11-08 | 2016-11-08 | Unmanned plane tail rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106494615A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200951832Y (en) * | 2006-09-20 | 2007-09-26 | 雷虎科技股份有限公司 | Tail rotor wing double push-pull angle attacking controlling structure |
| US20130195662A1 (en) * | 2012-01-26 | 2013-08-01 | Ta Sen Tu | Transmission structure of main propeller clamping seat and swashplate of remote-controlled helicopter |
| CN104029815A (en) * | 2014-06-18 | 2014-09-10 | 江苏泓雅集文化传播有限公司 | Adjustable tail variable pitch structure of helicopter for aerial photography |
| CN104097769A (en) * | 2014-06-27 | 2014-10-15 | 天津三爻航空航天科技发展有限公司 | Helicopter rotor head propeller clamping device |
| CN204310040U (en) * | 2014-10-27 | 2015-05-06 | 湖南农业大学 | A kind of single rotor unmanned helicopter main rotor system |
| CN205221108U (en) * | 2015-10-22 | 2016-05-11 | 上海龙云铝业有限公司 | Tail -rotor device is waved to small -size unmanned helicopter flexibility |
| CN105972151A (en) * | 2016-07-20 | 2016-09-28 | 芜湖万户航空航天科技有限公司 | Main shaft and main rotors connected through block rubber shimmy damping |
-
2016
- 2016-11-08 CN CN201610978616.5A patent/CN106494615A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN200951832Y (en) * | 2006-09-20 | 2007-09-26 | 雷虎科技股份有限公司 | Tail rotor wing double push-pull angle attacking controlling structure |
| US20130195662A1 (en) * | 2012-01-26 | 2013-08-01 | Ta Sen Tu | Transmission structure of main propeller clamping seat and swashplate of remote-controlled helicopter |
| CN104029815A (en) * | 2014-06-18 | 2014-09-10 | 江苏泓雅集文化传播有限公司 | Adjustable tail variable pitch structure of helicopter for aerial photography |
| CN104097769A (en) * | 2014-06-27 | 2014-10-15 | 天津三爻航空航天科技发展有限公司 | Helicopter rotor head propeller clamping device |
| CN204310040U (en) * | 2014-10-27 | 2015-05-06 | 湖南农业大学 | A kind of single rotor unmanned helicopter main rotor system |
| CN205221108U (en) * | 2015-10-22 | 2016-05-11 | 上海龙云铝业有限公司 | Tail -rotor device is waved to small -size unmanned helicopter flexibility |
| CN105972151A (en) * | 2016-07-20 | 2016-09-28 | 芜湖万户航空航天科技有限公司 | Main shaft and main rotors connected through block rubber shimmy damping |
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| C06 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20170315 |