CN107662704B - Unmanned helicopter main rotor hub mechanism - Google Patents
Unmanned helicopter main rotor hub mechanism Download PDFInfo
- Publication number
- CN107662704B CN107662704B CN201710994234.6A CN201710994234A CN107662704B CN 107662704 B CN107662704 B CN 107662704B CN 201710994234 A CN201710994234 A CN 201710994234A CN 107662704 B CN107662704 B CN 107662704B
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- CN
- China
- Prior art keywords
- main rotor
- hub
- rotor hub
- bearing
- ball bearing
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Links
- 239000004519 grease Substances 0.000 claims abstract description 29
- 125000006850 spacer group Chemical group 0.000 claims abstract description 11
- 230000001050 lubricating effect Effects 0.000 abstract description 18
- 230000002035 prolonged effect Effects 0.000 abstract description 3
- 238000005461 lubrication Methods 0.000 abstract description 2
- 238000012423 maintenance Methods 0.000 description 5
- 238000005299 abrasion Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000003068 static effect 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
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/02—Hub construction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Rolling Contact Bearings (AREA)
Abstract
The invention provides a main rotor hub mechanism of an unmanned helicopter, which comprises a main rotor head, wherein the main rotor head is connected with a connecting shaft, the connecting shaft is connected with the main rotor hub, the connecting shaft penetrates through a lubricating grease cavity in the main rotor hub, a thrust bearing II and a ball bearing II are sequentially arranged on the left side of the lubricating grease cavity from right to left, a spacer sleeve II is arranged between the thrust bearing II and the ball bearing II, a thrust bearing I and a ball bearing I are sequentially arranged on the right side of the lubricating grease cavity from left to right, a spacer sleeve I is arranged between the thrust bearing I and the ball bearing I, a lubricating grease filling port communicated with the lubricating grease cavity is arranged on the main rotor hub, the main rotor hub is connected with a main blade, and a blade limit screw is arranged on the main rotor hub. The invention has the advantages that: the axial force born by the ball bearing is eliminated by changing the layout mode of the bearing in the hub, so that the service life of the ball bearing is prolonged; the grease cavity is formed inside the hub, and the grease filling part is added on the hub, so that the lubrication of the bearings in the hub is facilitated.
Description
Technical Field
The invention relates to an unmanned helicopter, in particular to a main rotor hub mechanism of the unmanned helicopter.
Background
At present, the interior of most unmanned helicopter hubs adopts a structural form of two pairs of ball bearings or a pair of ball bearings plus a thrust bearing, and after the bearing arrangement form applies pretightening force, the ball bearings are always in an axial force state under the static condition; after the rotor runs to the rated rotation speed, the ball bearing can also receive axial force, so that the abrasion degree of the bearing balls, the bearing inner ring and the bearing outer ring can be increased, and the service life of the bearing is reduced. Meanwhile, the hub has a complex inner structure, a large number of bearings and difficult assembly and disassembly. At present, most unmanned helicopter main hubs do not have a filling port for lubricating grease, the helicopter must be returned to a factory after working for a period of time, a hub assembly is disassembled, and lubricating grease is added to bearings in the hubs, so that the complexity of maintenance of the unmanned helicopter is increased. The service life of the inner bearing of the hub of the unmanned helicopter is prolonged, the maintenance procedure of the main rotor wing part is simplified, and favorable conditions are provided for popularization of the unmanned helicopter.
Disclosure of Invention
The invention provides a main rotor hub mechanism of an unmanned helicopter, which solves the problems of poor stress and complex maintenance of an inner bearing of the existing unmanned helicopter hub.
The technical scheme of the invention is realized as follows: the utility model provides an unmanned helicopter main rotor oar hub mechanism, includes main oar head, main oar head be connected with the connecting axle, the connecting axle is connected with main rotor oar hub, the connecting axle passes the inside lubricating grease chamber of main rotor oar hub, the left side in lubricating grease chamber is equipped with thrust bearing two and ball bearing two in proper order from right to left, be equipped with spacer sleeve two between thrust bearing two and the ball bearing two, the right side in lubricating grease chamber is from left to right equipped with thrust bearing one and ball bearing one in proper order, be equipped with spacer sleeve one between thrust bearing one and the ball bearing one, be equipped with the lubricating grease filler mouth with lubricating grease chamber intercommunication on the main rotor oar hub, main rotor oar hub is connected with main paddle, be equipped with paddle stop screw on the main rotor oar hub.
The main rotor head is connected with the connecting shaft through the connecting pin, the connecting shaft is connected with the main rotor hub through the groove-shaped lock nut, and the main rotor hub is connected with the main blades through the blade fixing screws.
The invention has the advantages that: the axial force born by the ball bearing is eliminated by changing the layout mode of the bearing in the propeller hub, so that the bearing in the propeller hub is in a good working condition, and the service life of the bearing in the propeller hub is prolonged; the grease cavity is formed in the hub, and the grease filling part is added on the hub, so that the lubrication of the bearing in the hub is facilitated, and the maintenance steps of the bearing in the hub are simplified.
Drawings
In order to more clearly illustrate the embodiments of the invention or the technical solutions in the prior art, the drawings that are required in the embodiments or the description of the prior art will be briefly described, it being obvious that the drawings in the following description are only some embodiments of the invention, and that other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.
Fig. 1 is a plan view of the present invention.
Fig. 2 is a perspective view of the structure of the present invention.
In the figure: 1-a main blade head; 2-connecting pins; 3-connecting shaft; 4-ball bearing one; 5-thrust bearing one; 6-a lubricating grease filling port; 7-a main rotor hub; 8-blade limit screws; 9-blade set screws; 10-main blade; 11-groove lock nut; 12-ball bearing II; 13-a second spacer sleeve; 14-a second thrust bearing; 15-a first spacer sleeve.
Detailed Description
The following description of the embodiments of the present invention will be made clearly and completely with reference to the accompanying drawings, in which it is apparent that the embodiments described are only some embodiments of the present invention, but not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1-2, an unmanned helicopter main rotor hub mechanism comprises a main rotor head 1, the main rotor head 1 is connected with a connecting shaft 3, the connecting shaft 3 is connected with a main rotor hub 7, the connecting shaft 3 penetrates through a lubricating grease cavity inside the main rotor hub 7, a second thrust bearing 14 and a second ball bearing 12 are sequentially arranged on the left side of the lubricating grease cavity from right to left, a second spacer sleeve 13 is arranged between the second thrust bearing 14 and the second ball bearing 12, a first thrust bearing 5 and a first ball bearing 4 are sequentially arranged on the right side of the lubricating grease cavity from left to right, a first spacer sleeve 15 is arranged between the first thrust bearing 5 and the first ball bearing 4, a lubricating grease filling port 6 communicated with the lubricating grease cavity is arranged on the main rotor hub 7, the main rotor hub 7 is connected with a main blade 10, and a blade limit screw 9 is arranged on the main rotor hub 7.
The main rotor head 1 is connected with the connecting shaft 3 through the connecting pin 2, the connecting shaft 3 is connected with the main rotor hub 7 through the slotted lock nut 11, and the main rotor hub 7 is connected with the main blades 10 through the blade fixing screws 9.
The propeller hub is connected with the main propeller head of the helicopter through a connecting shaft, the first ball bearing and the second ball bearing are arranged at the outermost side, the first thrust bearing and the second thrust bearing are arranged at the inner side, the first ball bearing and the second thrust bearing are separated by a spacer sleeve, the connecting shaft penetrates through the inner ring of the bearing, and the outer side of the second ball bearing is screwed by a groove type nut. When the groove-shaped nut is given with certain pretightening force, the first thrust bearing is stressed by the axial force, the first ball bearing, the second ball bearing and the second thrust bearing are not stressed, when the main rotor of the helicopter runs, the hub is acted by the centrifugal force of the blade, a part of pretightening force is counteracted, when the blade rotates at a low speed, the pretightening force is larger than the centrifugal force, the first thrust bearing is stressed by the axial force, the first ball bearing and the second ball bearing bear radial force, when the speed of the blade of the helicopter reaches the rated rotating speed, the pretightening force is smaller than the centrifugal force, the second thrust bearing is stressed by the axial force, the first ball bearing and the second ball bearing are stressed by the radial force, and the thrust bearing is not stressed by the thrust bearing, so that the axial force is not acted by the ball bearing under any working condition, and the bearing is in a better working condition.
A grease cavity is formed between the first thrust bearing and the second thrust bearing, a grease filling nozzle is arranged at the position corresponding to the hub, and after the inner bearing of the hub works for a period of time, the grease can be filled into the inner bearing without disassembling the hub, so that the maintenance is convenient.
The foregoing description of the preferred embodiments of the invention is not intended to be limiting, but rather is intended to cover all modifications, equivalents, alternatives, and improvements that fall within the spirit and scope of the invention.
Claims (2)
1. Unmanned helicopter main rotor hub mechanism, including main oar head (1), its characterized in that: the main rotor head (1) is connected with the connecting shaft (3), the connecting shaft (3) is connected with the main rotor hub (7), the connecting shaft (3) penetrates through a grease cavity in the main rotor hub (7), a thrust bearing II (14) and a ball bearing II (12) are sequentially arranged on the left side of the grease cavity from right to left, a spacer sleeve II (13) is arranged between the thrust bearing II (14) and the ball bearing II (12), a thrust bearing I (5) and a ball bearing I (4) are sequentially arranged on the right side of the grease cavity from left to right, a spacer sleeve I (15) is arranged between the thrust bearing I (5) and the ball bearing I (4), a grease filling port (6) communicated with the main rotor hub (7) is arranged on the main rotor hub (7), a main rotor blade (10) is connected with a blade limit screw (8);
the connecting shaft (3) is connected with the main rotor hub (7) through a groove-shaped lock nut (11).
2. The unmanned helicopter main rotor hub mechanism of claim 1, wherein: the main rotor head (1) is connected with the connecting shaft (3) through the connecting pin (2), and the main rotor hub (7) is connected with the main blades (10) through the blade fixing screws (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710994234.6A CN107662704B (en) | 2017-10-23 | 2017-10-23 | Unmanned helicopter main rotor hub mechanism |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710994234.6A CN107662704B (en) | 2017-10-23 | 2017-10-23 | Unmanned helicopter main rotor hub mechanism |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN107662704A CN107662704A (en) | 2018-02-06 |
| CN107662704B true CN107662704B (en) | 2023-11-03 |
Family
ID=61098495
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710994234.6A Active CN107662704B (en) | 2017-10-23 | 2017-10-23 | Unmanned helicopter main rotor hub mechanism |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107662704B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| 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 |
| CN112046739B (en) * | 2020-08-06 | 2022-03-18 | 中国人民解放军总参谋部第六十研究所 | Rigid rotor hub of helicopter |
| CN113071664B (en) * | 2021-04-06 | 2021-12-14 | 清华大学 | Hub assembly for helicopter rotors |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB254377A (en) * | 1925-03-30 | 1926-06-30 | Bramson Mogens Louis | Improvements in or relating to variable pitch propellers |
| GB644336A (en) * | 1948-01-09 | 1950-10-11 | Hartzell Industries | Improvements in or relating to propeller or airscrew blade mounting |
| JPH05263824A (en) * | 1992-03-18 | 1993-10-12 | Fanuc Ltd | Bearing device for electric motor |
| JP2002021843A (en) * | 2000-07-06 | 2002-01-23 | Mitsubishi Heavy Ind Ltd | Thrust bearing device |
| CN203979136U (en) * | 2014-07-11 | 2014-12-03 | 湖北易瓦特科技有限公司 | Dual thrust bearing combined mechanism |
| 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 |
| CN207374654U (en) * | 2017-10-23 | 2018-05-18 | 郑州方达电子技术有限公司 | A kind of unmanned helicopter main rotor propeller hub mechanism |
-
2017
- 2017-10-23 CN CN201710994234.6A patent/CN107662704B/en active Active
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB254377A (en) * | 1925-03-30 | 1926-06-30 | Bramson Mogens Louis | Improvements in or relating to variable pitch propellers |
| GB644336A (en) * | 1948-01-09 | 1950-10-11 | Hartzell Industries | Improvements in or relating to propeller or airscrew blade mounting |
| JPH05263824A (en) * | 1992-03-18 | 1993-10-12 | Fanuc Ltd | Bearing device for electric motor |
| JP2002021843A (en) * | 2000-07-06 | 2002-01-23 | Mitsubishi Heavy Ind Ltd | Thrust bearing device |
| CN203979136U (en) * | 2014-07-11 | 2014-12-03 | 湖北易瓦特科技有限公司 | Dual thrust bearing combined mechanism |
| 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 |
| CN207374654U (en) * | 2017-10-23 | 2018-05-18 | 郑州方达电子技术有限公司 | A kind of unmanned helicopter main rotor propeller hub mechanism |
Also Published As
| Publication number | Publication date |
|---|---|
| CN107662704A (en) | 2018-02-06 |
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