CN107310721A - A kind of depopulated helicopter rotor oar clamp mechanism - Google Patents
A kind of depopulated helicopter rotor oar clamp mechanism Download PDFInfo
- Publication number
- CN107310721A CN107310721A CN201710580913.9A CN201710580913A CN107310721A CN 107310721 A CN107310721 A CN 107310721A CN 201710580913 A CN201710580913 A CN 201710580913A CN 107310721 A CN107310721 A CN 107310721A
- Authority
- CN
- China
- Prior art keywords
- rotor head
- oar
- interior axle
- rotor
- bearing
- 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
Links
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims abstract description 20
- 229910052802 copper Inorganic materials 0.000 claims abstract description 20
- 239000010949 copper Substances 0.000 claims abstract description 20
- 238000013016 damping Methods 0.000 claims description 12
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000009825 accumulation Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000005540 biological transmission Effects 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 238000004519 manufacturing process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000001338 self-assembly Methods 0.000 description 1
- 238000005728 strengthening Methods 0.000 description 1
- 230000032258 transport Effects 0.000 description 1
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)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The present invention is a kind of depopulated helicopter rotor oar clamp mechanism, interior axle is pressed from both sides including oar, the oar folder at interior axle two ends is pressed from both sides installed in oar, ecto-entad is arranged with the first radial bearing successively between the inner ring of oar folder and the outer ring of oar folder interior axle, bearing washer, thrust bearing, bearing stop collar and the second radial bearing, the end face of oar folder interior axle is tight by round nut and oar clamp lock, the outside of oar folder interior axle is provided with rotor head clamping plate, rotor head clamping plate presss from both sides interior axle by main shaft king-bolt and oar to be fixed, rotor head clamping plate includes rotor head train wheel bridge and rotor head lower plate, main shaft king-bolt runs through rotor head train wheel bridge and rotor head lower plate, copper backing and copper sheathing are arranged with main shaft king-bolt, one end of main shaft king-bolt is provided with stop nut, rotor head train wheel bridge and rotor head lower plate pass through screw lock.Rational in infrastructure, easy to assembly, precision of the invention is high, and shaft strength is uniform, it is good, easy to adjust to be driven, and can be good at resisting centrifugal force during blade flight.
Description
Technical field
The present invention relates to unmanned plane field, more particularly to a kind of depopulated helicopter rotor oar clamp mechanism.
Background technology
The normal method of existing aircraft field unmanned plane lifting airscrew oar clamp mechanism has many kinds, one of which
Mode is that the oar at two ends is drawn a bow to the full and connected by a transverse axis, and respectively there are 2 to 3 bearings left and right, and finally in left and right, outer rim utilizes screw
Transverse axis and oar are drawn a bow to the full and fix locking, usual this mode is that each screw lock is on same transverse axis around, and transverse axis is same
The heart is symmetrical, and oar, which is drawn a bow to the full, in flight course can not adjust so-called flapping hinge；Also a kind of mode is propeller hub and the right on the left side
Oar draw a bow to the full by middle central shaft, carried and be driven using needle bearing, is driven with tension-torsion piece, which for
Small-sized depopulated helicopter is desirable, but there is also the unstability due to centrifugal force, can be occurred when being impacted suddenly
Oar is drawn a bow to the full outbound dangerous situation.
The content of the invention
It is an object of the invention to provide a kind of constitutionally stable depopulated helicopter rotor oar clamp mechanism.
The present invention is achieved through the following technical solutions above-mentioned purpose：A kind of depopulated helicopter rotor oar clamp mechanism, including
Oar folder interior axle, the oar folder installed in oar folder interior axle two ends, between the inner ring of the oar folder and the outer ring of oar folder interior axle
Ecto-entad is arranged with the first radial bearing, bearing washer, thrust bearing, bearing stop collar and the second radial bearing, institute successively
The end face for stating oar folder interior axle is tight by round nut and the oar clamp lock, and the outside of the oar folder interior axle is provided with rotor head clamping plate, institute
State rotor head clamping plate interior axle pressed from both sides by main shaft king-bolt and the oar and fix, the rotor head clamping plate include rotor head train wheel bridge and
Rotor head lower plate, the main shaft king-bolt runs through the rotor head train wheel bridge and the rotor head lower plate, and the main shaft is big
Copper backing and copper sheathing are arranged with bolt, the copper backing and the copper sheathing are located at the rotor head train wheel bridge and the rotor head
Between lower plate, one end of the main shaft king-bolt, which is provided with stop nut, the rotor head train wheel bridge and the rotor head, to press from both sides
Plate passes through screw lock.
Further, first radial bearing, bearing washer, thrust bearing, bearing stop collar and the second radial bearing
Respective end face be adjacent to successively together.
Further, the copper backing is located at the inner side of the copper sheathing.
Further, the stop nut is located at the outside of the rotor head clamping plate.
Further, damping block, the damping are additionally provided between the rotor head train wheel bridge and the rotor head lower plate
Internal damping block is provided with block.
Compared with prior art, the beneficial effect of depopulated helicopter rotor oar clamp mechanism of the present invention is：Mechanism structure
Rationally, easy to assembly, precision is high, and shaft strength is uniform, it is good, easy to adjust to be driven, when can be good at resistance blade flight
Centrifugal force.
Brief description of the drawings
Fig. 1 is the structural representation of invention.
Fig. 2 is Fig. 1 A-A schematic cross-sectional views.
Fig. 3 is Fig. 1 C-C schematic cross-sectional views.
Fig. 4 is the structural representation of undercarriage wheel component.
Embodiment
Fig. 1 is referred to Fig. 4, a kind of depopulated helicopter rotor oar clamp mechanism, including oar press from both sides interior axle 1, installed in oar folder
The oar folder 7 at the two ends of interior axle 1, the first radial bearing 4, bearing washer are arranged between the inner ring of oar folder 7 and the outer ring of oar folder interior axle 1
5th, thrust bearing 3, the radial bearing 6 of bearing stop collar 2 and second.First radial bearing 4, bearing washer 5, thrust bearing 3, bearing
The ecto-entad of 2 and second radial bearing of stop collar 6 is set gradually.First radial bearing 4, bearing washer 5, thrust bearing 3, bearing
Together with stop collar 2 is adjacent to successively with the respective end face of the second radial bearing 6.
The end face of oar folder interior axle 1 is locked by round nut 16 and oar folder 7, and all bearings can be adjusted by round nut 16
End-play.
The outside of oar folder interior axle 1 is provided with rotor head clamping plate 8, and rotor head clamping plate 8 presss from both sides interior axle 1 by main shaft king-bolt 9 and oar
Fixed, rotor head clamping plate 8 includes rotor head train wheel bridge 81 and rotor head lower plate 82, and main shaft king-bolt 9 is pressed from both sides on rotor head
Copper backing 13 and copper sheathing 14 are arranged with plate 81 and rotor head lower plate 82, main shaft king-bolt 9, copper backing 13 and copper sheathing 14 are located at
Between rotor head train wheel bridge 81 and rotor head lower plate 82, copper backing 13 is located at the inner side of copper sheathing 14, one end of main shaft king-bolt 9
Provided with stop nut 11, stop nut 11 is located at the outside of rotor head clamping plate 8, rotor head train wheel bridge 81 and rotor head lower plate 82
Between be additionally provided with damping block 10, internal damping block 12 is provided with damping block 10, rotor head train wheel bridge 81 and rotor head lower plate 82 are logical
Screw 15 is crossed to lock.
Advantages of the present invention has：
1）Mechanism bearing internal external circle in terms of axial direction has circle to have a reliable positioning datum, and outer ring can eliminate bearing clearance, interior
Circle plays its double-deck effect for carrying out pretension and locking by round nut, and all shaft strengths are uniform, and transmission is good, adjustment side
Just.
2）The oar folder interior axle of mechanism is an integral structure component, instead of several parts of conventional structure, it is to avoid with
Toward the processing and the accumulation of assembly precision error of several parts, while strengthening rigidity and reducing machining and assembling hardly possible
Degree.
3）Mechanism is segmented into the oar clip assembly of left and right two, the component of inside and outside damping block formation and main shaft king-bolt and formed
Component, each self-assembly finishes, and will carry out integration assembling after the rotor head train wheel bridge on both sides and the positioning of rotor head lower plate, and help
In raising efficiency and quickening manufacturing cycle.
4）The oar clip assembly on mechanism both sides is clamping fixed by the oar of the right and left respectively, and both sides are formed into an entirety,
Centrifugal force when interior axle resists blade flight jointly is pressed from both sides with oar.
5）The damping link that mechanism provides inside and outside damping block formation is effectively reduced rushing during unmanned plane during flying
Hit, effectively extend the life-span of other structures part.
6）Mechanism is reasonable in design, is also convenient for repairing and transports.
7）Mechanism is rational in infrastructure, and reference plane is unified, and installation tool is unified, and auxiliary equipment quantity required is also greatly reduced,
Also reduce the use cost of UAS.
The general principle and principal character and advantages of the present invention of the present invention has been shown and described above, for people in the art
For member, it is clear that the invention is not restricted to the details of above-mentioned one exemplary embodiment, and without departing substantially from the spiritual or basic of the present invention
In the case of feature, the present invention can be realized in other specific forms.Which point therefore, no matter from the point of view of, it will all should implement
Example regards exemplary as, and is nonrestrictive, and the scope of the present invention is limited by appended claims rather than described above
It is fixed, it is intended that all changes fallen in the implication and scope of the equivalency of claim are included in the present invention.No
Any reference in claim should be considered as to the claim involved by limitation.
Moreover, it will be appreciated that although the present specification is described in terms of embodiments, not each embodiment is only wrapped
Containing an independent technical scheme, this narrating mode of specification is only that for clarity, those skilled in the art should
Using specification as an entirety, the technical solutions in the various embodiments may also be suitably combined, forms those skilled in the art
It may be appreciated other embodiment.
Claims (5)
1. a kind of depopulated helicopter rotor oar clamp mechanism, it is characterised in that：Interior axle is pressed from both sides including oar folder interior axle, installed in the oar
The oar folder at two ends, ecto-entad is arranged with the first centripetal axle successively between the inner ring of the oar folder and the outer ring of oar folder interior axle
Hold, bearing washer, thrust bearing, bearing stop collar and the second radial bearing, the end face of the oar folder interior axle by round nut with
The oar clamp lock is tight, and the outside of the oar folder interior axle is provided with rotor head clamping plate, the rotor head clamping plate by main shaft king-bolt with
The oar folder interior axle is fixed, and the rotor head clamping plate includes rotor head train wheel bridge and rotor head lower plate, the main shaft king-bolt
Through the rotor head train wheel bridge and the rotor head lower plate, copper backing and copper sheathing are arranged with the main shaft king-bolt, institute
State copper backing and the copper sheathing is located between the rotor head train wheel bridge and the rotor head lower plate, the main shaft king-bolt
One end is provided with stop nut, and the rotor head train wheel bridge and the rotor head lower plate pass through screw lock.
2. depopulated helicopter rotor oar clamp mechanism according to claim 1, it is characterised in that：The first centripetal axle
Hold, the respective end face of bearing washer, thrust bearing, bearing stop collar and the second radial bearing is adjacent to together successively.
3. depopulated helicopter rotor oar clamp mechanism according to claim 1, it is characterised in that：The copper backing is located at institute
State the inner side of copper sheathing.
4. depopulated helicopter rotor oar clamp mechanism according to claim 1, it is characterised in that：The stop nut is located at
The outside of the rotor head clamping plate.
5. depopulated helicopter rotor oar clamp mechanism according to claim 1, it is characterised in that：The rotor head train wheel bridge
It is additionally provided between the rotor head lower plate in damping block, the damping block and is provided with internal damping block.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710580913.9A CN107310721A (en) | 2017-07-17 | 2017-07-17 | A kind of depopulated helicopter rotor oar clamp mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710580913.9A CN107310721A (en) | 2017-07-17 | 2017-07-17 | A kind of depopulated helicopter rotor oar clamp mechanism |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107310721A true CN107310721A (en) | 2017-11-03 |
Family
ID=60178184
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710580913.9A Pending CN107310721A (en) | 2017-07-17 | 2017-07-17 | A kind of depopulated helicopter rotor oar clamp mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107310721A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108956081A (en) * | 2018-06-14 | 2018-12-07 | 南京航空航天大学 | A kind of experimental rig for warship face rotor starting process |
| CN109279010A (en) * | 2018-10-12 | 2019-01-29 | 必扬星环（北京）航空科技有限公司 | A kind of main paddle clamping structure |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4257738A (en) * | 1977-03-23 | 1981-03-24 | Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung | Rotor mounting assembly for rotary wing aircraft |
| GB2059897A (en) * | 1979-10-02 | 1981-04-29 | Messerschmitt Boelkow Blohm | Helicopter rotor blade-to-hub connections |
| CN104908976A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Simple rotor mechanism of coaxial dual-rotor helicopter test stand |
| CN205418096U (en) * | 2016-03-21 | 2016-08-03 | 甄圣远 | First structure of unmanned helicopter rotor |
| CN207106880U (en) * | 2017-07-17 | 2018-03-16 | 飞瑞航空科技（江苏）有限公司 | A kind of depopulated helicopter rotor oar clamp mechanism |
-
2017
- 2017-07-17 CN CN201710580913.9A patent/CN107310721A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4257738A (en) * | 1977-03-23 | 1981-03-24 | Messerschmitt-Bolkow-Blohm Gesellschaft Mit Beschrankter Haftung | Rotor mounting assembly for rotary wing aircraft |
| GB2059897A (en) * | 1979-10-02 | 1981-04-29 | Messerschmitt Boelkow Blohm | Helicopter rotor blade-to-hub connections |
| CN104908976A (en) * | 2015-05-19 | 2015-09-16 | 北京航空航天大学 | Simple rotor mechanism of coaxial dual-rotor helicopter test stand |
| CN205418096U (en) * | 2016-03-21 | 2016-08-03 | 甄圣远 | First structure of unmanned helicopter rotor |
| CN207106880U (en) * | 2017-07-17 | 2018-03-16 | 飞瑞航空科技（江苏）有限公司 | A kind of depopulated helicopter rotor oar clamp mechanism |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108956081A (en) * | 2018-06-14 | 2018-12-07 | 南京航空航天大学 | A kind of experimental rig for warship face rotor starting process |
| CN109279010A (en) * | 2018-10-12 | 2019-01-29 | 必扬星环（北京）航空科技有限公司 | A kind of main paddle clamping structure |
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|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| WD01 | Invention patent application deemed withdrawn after publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20171103 |