CN105972151B - Pass through the main shaft and main rotor of the shimmy damping connection of block rubber - Google Patents
Pass through the main shaft and main rotor of the shimmy damping connection of block rubber Download PDFInfo
- Publication number
- CN105972151B CN105972151B CN201610571167.2A CN201610571167A CN105972151B CN 105972151 B CN105972151 B CN 105972151B CN 201610571167 A CN201610571167 A CN 201610571167A CN 105972151 B CN105972151 B CN 105972151B
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- China
- Prior art keywords
- main shaft
- main rotor
- wall
- shimmy
- pin hole
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- Expired - Fee Related
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- 238000013016 damping Methods 0.000 title claims abstract description 36
- 230000000149 penetrating effect Effects 0.000 claims description 3
- 230000005540 biological transmission Effects 0.000 description 3
- 238000009434 installation Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000002035 prolonged effect Effects 0.000 description 2
- 238000010586 diagram Methods 0.000 description 1
- 238000011900 installation process Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 230000001681 protective effect Effects 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
- F16F—SPRINGS; SHOCK-ABSORBERS; MEANS FOR DAMPING VIBRATION
- F16F15/00—Suppression of vibrations in systems; Means or arrangements for avoiding or reducing out-of-balance forces, e.g. due to motion
- F16F15/10—Suppression of vibrations in rotating systems by making use of members moving with the system
- F16F15/12—Suppression of vibrations in rotating systems by making use of members moving with the system using elastic members or friction-damping members, e.g. between a rotating shaft and a gyratory mass mounted thereon
- F16F15/121—Suppression of vibrations in rotating systems by making use of members moving with the system using elastic members or friction-damping members, e.g. between a rotating shaft and a gyratory mass mounted thereon using springs as elastic members, e.g. metallic springs
- F16F15/124—Elastomeric springs
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- Engineering & Computer Science (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Acoustics & Sound (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention discloses a kind of by the shimmy damping connection main shaft of block rubber and main rotor, the first pin hole is radially set in main shaft axis body top exterior walls, interior square set is set at the top of main shaft axis body and two the second pin holes is set in an opposing sidewalls, and main rotor combination is all provided with the 3rd pin hole on two side；First, second, and third pin hole is coaxially disposed, and pin can sequentially pass through the three, the second and first and pin hole and connect positioning；With setting screwed hole in the axially in parallel a pair of sidewalls of pin in interior square set, screwed hole can be passed through by the first bolt of rotation and be resisted against on the external wall of spindle shaft；The shimmy damping of block rubber is set on spindle shaft body, and inwall is fitted on the external wall of spindle shaft and outer wall is fitted on the endoporus inwall of main rotor combination lower section；Bottom face is provided with damping fixed plate, is set on main shaft axis body and closes main rotor combination lower section endoporus.Assembling simple and compact, in light weight, large carrying capacity, stable drive, wave that angle is small, the small advantage of noise.
Description
Technical Field
The invention relates to unmanned aerial vehicle parts, in particular to a main shaft and a main rotor which are connected through rubber block shimmy damping.
Background
The rotor head of the existing common unmanned helicopter is unreasonable or imperfect in structure, so that the rotor head is easy to generate a larger flapping angle when flapping, the instability of the unmanned helicopter is increased, the service life of blades is shortened, and the performance of the unmanned helicopter is greatly influenced.
Disclosure of Invention
The invention aims to provide a main shaft and a main rotor which are connected through a rubber block shimmy damping, and the main shaft and the main rotor have the advantages of simple and compact assembly, light weight, high bearing capacity, stable transmission, small flapping angle and low noise.
In order to achieve the purpose, the invention provides a main shaft and a main rotor wing which are connected through rubber block shimmy damping, and the main shaft and the main rotor wing comprise cylindrical main shaft bodies, inner square sleeves, main rotor wing combinations and rubber block shimmy damping;
a first pin hole penetrating through the main shaft body is radially arranged on the outer wall of the top of the main shaft body, an inner square sleeve is sleeved on the top of the main shaft body, two second pin holes are arranged on one opposite side wall of the inner square sleeve, and third pin holes are arranged on two side walls of the main rotor wing assembly;
the first pin hole, the second pin hole and the third pin hole are coaxially arranged, and the pin can sequentially penetrate through the third pin hole, the second pin hole and the first pin hole and is connected and positioned;
threaded holes are formed in a pair of side walls, parallel to the axial direction of the pin, of the inner square sleeve, and the first bolt can penetrate through the threaded holes and extend to abut against the outer wall of the spindle body by rotating the first bolt; wherein,
the rubber block shimmy damping sleeve is arranged on the spindle body, the inner wall of the rubber block shimmy damping is attached to the outer wall of the spindle body, and the outer wall of the rubber block shimmy damping is attached to the inner wall of the inner hole below the main rotor combination; and a damping fixing plate is arranged on the bottom end face of the rubber block shimmy damping, is sleeved on the spindle body and seals an inner hole below the main rotor wing combination through a second bolt.
Preferably, the outer wall of the bottom of the spindle body is radially provided with a plurality of flat key grooves, and the flat key grooves can be connected with the gear through flat keys; the bottom end surface part of the main shaft body is inwards sunken to form a cylindrical hollow structure.
Preferably, the upper part of the outer wall of the top part of the spindle shaft body is inwards recessed to form two mounting planes, and the two mounting planes are oppositely arranged in parallel and extend along the axis direction of the spindle shaft body.
Preferably, the edges of the two mounting planes extend outwards to form mounting wing plates matched with the mounting guide grooves on the main rotor combination.
Preferably, the first pin hole extends through from a surface of one mounting plane to a surface of the other mounting plane.
Preferably, the plurality of flat key grooves have different lengths and are arranged at intervals in the axial direction of the spindle shaft body.
Preferably, the bottom end surface of the spindle body protrudes outward to form a mounting convex ring.
According to the technical scheme, when the rotor head swings, the upper hole of the rotor head is used as a swinging center, the swinging angle of the rotor head is limited by the shimmy damping of the rubber block at the inner hole below the rotor head, the left and right lifting force can be balanced and the fatigue of the blade can be reduced when the rotor head swings in a small-range angle, and meanwhile, the shimmy damping of the rubber block material can reduce the vibration and reduce the possibility of resonance. The structure can ensure that the unmanned helicopter moves stably, has the characteristics of small flapping angle, reduced resonance, prolonged service life of the blades and the like, and has the advantages of simple and compact assembly, light weight, large bearing capacity, stable transmission and low noise.
Additional features and advantages of the invention will be set forth in the detailed description which follows.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the principles of the invention and not to limit the invention. In the drawings:
FIG. 1 is a cross-sectional view of a mast and a main rotor connected by bump shimmy damping in one embodiment provided in accordance with the present invention;
FIG. 2 is a schematic structural diagram of a mast and a main rotor coupled via a rubber block shimmy damping in accordance with an embodiment of the present invention;
FIG. 3 is a front view of a spindle body in one embodiment provided in accordance with the present invention; and
FIG. 4 is a side view of a spindle body in one embodiment provided in accordance with the present invention.
Description of the reference numerals
1-main shaft body 2-inner square sleeve
3-main rotor wing combination 4-third pin hole
5-Pin 6-first bolt
7-rubber block shimmy damping 8-damping fixing plate
9-second bolt 10-flat keyway
11-mounting plane 12-mounting wing plate
Detailed Description
The following detailed description of embodiments of the invention refers to the accompanying drawings. It should be understood that the detailed description and specific examples, while indicating the present invention, are given by way of illustration and explanation only, not limitation.
In the present invention, unless otherwise specified the terms "inwardly, outwardly, top, bottom" and the like are used in the terminology in an orientation that is usually used, or is colloquially understood by those skilled in the art, and should not be construed to limit the terminology.
Referring to fig. 1, the invention provides a main shaft and a main rotor which are connected through rubber block shimmy damping, comprising a cylindrical main shaft body 1, an inner square sleeve 2, a main rotor combination 3 and rubber block shimmy damping 7;
a first pin hole penetrating through the main shaft body 1 is formed in the outer wall of the top of the main shaft body 1 along the radial direction, the inner square sleeve 2 is sleeved on the top of the main shaft body 1, two second pin holes are formed in one opposite side wall of the inner square sleeve 2, and third pin holes 4 are formed in two side walls of the main rotor wing assembly 3;
the first pin hole, the second pin hole and the third pin hole 4 are coaxially arranged, and the pin 5 can sequentially penetrate through the third pin hole 4, the second pin hole and the first pin hole and is connected and positioned;
threaded holes are formed in a pair of side walls, parallel to the axial direction of the pin 5, of the inner square sleeve 2, and the first bolt 6 (shown in figure 2) can penetrate through the threaded holes and extend to abut against the outer wall of the spindle body 1 by rotating the first bolt 6; wherein,
the rubber block shimmy damper 7 is sleeved on the spindle body 1, the inner wall of the rubber block shimmy damper 7 is attached to the outer wall of the spindle body 1, and the outer wall of the rubber block shimmy damper 7 is attached to the inner wall of the inner hole below the main rotor combination 3; and a damping fixing plate 8 is arranged on the bottom end face of the rubber block shimmy damper 7, and the damping fixing plate 8 is sleeved on the spindle shaft body 1 and seals an inner hole below the main rotor wing assembly 3 through a second bolt 9.
Through above-mentioned technical scheme, when the rotor head takes place to wave the motion, will regard as the center of waving with the last hole of rotor head, the angle that the rotor head waved will be restricted to the damping of shimmy of the block rubber of rotor head below inner bore department, when the rotor head takes place to wave in the angle of miniscope, can balance the lift about inhomogeneous, and reduce the fatigue of paddle, the damping of shimmy of block rubber material can reduce vibrations simultaneously, reduces the possibility of taking place resonance. The structure can ensure that the unmanned helicopter moves stably, has the characteristics of small flapping angle, reduced resonance, prolonged service life of the blades and the like, and has the advantages of simple and compact assembly, light weight, large bearing capacity, stable transmission and low noise.
In the present embodiment, in order to optimize the structure of the spindle shaft body 1, preferably, a plurality of flat key grooves 10 (as shown in fig. 3) are radially opened on the outer wall of the bottom of the spindle shaft body 1, and each of the flat key grooves 10 can be connected with a gear through a flat key; the bottom end surface part of the main shaft body 1 is inwards sunken to form a cylindrical hollow structure. Further, it is preferable that the upper portion of the top outer wall of the spindle shaft body 1 is recessed inwards to form two mounting planes 11, and the two mounting planes 11 are arranged in parallel relatively and extend along the axial direction of the spindle shaft body 1. Like this, solid flat shape above this main shaft axis body 1 can increase the area of contact of this main shaft axis body 1 and main rotor, reduces the stress with main rotor junction, has improved the working life of this main shaft.
In order to prevent the mechanical structure between the assembled main shaft body 1 and the main rotor from being loosened due to misalignment during the installation process, as shown in fig. 4, the edges of the two installation planes 11 are extended outward to form installation wing plates 12 which are matched with the installation guide grooves on the main rotor assembly 3.
Further, in order to facilitate the definition of the fitting position by the pin fitting with the first pin hole, it is preferable that the first pin hole extends through from the surface of one mounting plane 11 to the surface of the other mounting plane 11.
In order to expand the applicability of this high-speed rotatory main shaft subassembly of unmanned aerial vehicle for it can use and cooperate the use with the gear of a plurality of different specifications, preferably, the length of a plurality of flat key grooves 10 is different and sets up along the axial direction interval of main shaft axis body 1.
In the mounting process, in order to prevent the misoperation and increase the assembly speed to improve the production efficiency, it is preferable that the bottom end surface part of the main shaft body 1 protrudes outward to form a mounting convex ring.
The preferred embodiments of the present invention have been described in detail with reference to the accompanying drawings, however, the present invention is not limited to the specific details of the above embodiments, and various simple modifications can be made to the technical solution of the present invention within the technical idea of the present invention, and these simple modifications are within the protective scope of the present invention.
It should be noted that the various technical features described in the above embodiments can be combined in any suitable manner without contradiction, and the invention is not described in any way for the possible combinations in order to avoid unnecessary repetition.
In addition, any combination of the various embodiments of the present invention is also possible, and the same should be considered as the disclosure of the present invention as long as it does not depart from the spirit of the present invention.
Claims (7)
1. A main shaft and a main rotor wing connected through rubber block shimmy damping are characterized by comprising a cylindrical main shaft body (1), an inner square sleeve (2), a main rotor wing combination (3) and rubber block shimmy damping (8);
a first pin hole penetrating through the outer wall of the top of the spindle body (1) along the radial direction is formed in the outer wall of the top of the spindle body (1), an inner square sleeve (2) is sleeved on the top of the spindle body (1), two second pin holes are formed in one opposite side wall of the inner square sleeve (2), and third pin holes (4) are formed in two side walls of the main rotor wing assembly (3);
the first pin hole, the second pin hole and the third pin hole (4) are coaxially arranged, and the pin (5) can sequentially penetrate through the third pin hole (4), the second pin hole and the first pin hole and is connected and positioned;
threaded holes are formed in a pair of side walls, axially parallel to the pin (5), of the inner square sleeve (2), and the first bolt (6) can penetrate through the threaded holes and extend to abut against the outer wall of the spindle body (1) by rotating the first bolt (6); wherein,
the rubber block shimmy damper (7) is sleeved on the spindle body (1), the inner wall of the rubber block shimmy damper (7) is attached to the outer wall of the spindle body (1), and the outer wall of the rubber block shimmy damper (7) is attached to the inner wall of the inner hole below the main rotor combination (3); a damping fixing plate (8) is arranged on the bottom end face of the rubber block shimmy damper (7), the damping fixing plate (8) is sleeved on the spindle shaft body (1) and seals an inner hole below the main rotor wing combination (3) through a second bolt (9).
2. The main shaft and the main rotor wing connected through the rubber block shimmy damping according to claim 1 are characterized in that a plurality of flat key grooves (10) are radially formed in the outer wall of the bottom of the main shaft body (1), and the flat key grooves (10) can be connected with a gear through flat keys; the bottom end surface part of the main shaft body (1) is inwards sunken to form a cylindrical hollow structure.
3. The main shaft and the main rotor connected through the rubber block shimmy damping are characterized in that the upper part of the outer wall of the top of the main shaft body (1) is inwards sunken to form two mounting planes (11), and the two mounting planes (11) are arranged in parallel relatively and extend along the axial direction of the main shaft body (1).
4. A mast and main rotor connected by bump shimmy damping according to claim 3 characterized in that the edges of the two mounting planes (11) are extended outwards forming mounting wings (12) cooperating with mounting guide slots on the main rotor assembly (3).
5. Mast and main rotor connected by bump shimmy damping according to claim 4, characterized in that the first pin hole extends through from the surface of one mounting plane (11) to the surface of the other mounting plane (11).
6. The main shaft and the main rotor connected through the rubber block shimmy damping according to claim 2, characterized in that the plurality of flat key grooves (10) have different lengths and are arranged at intervals in the axial direction of the main shaft body (1).
7. The mast and main rotor connected by bump damping of claim 1, wherein the bottom end face of the mast body (1) is partially outwardly convex to form a mounting collar.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610571167.2A CN105972151B (en) | 2016-07-20 | 2016-07-20 | Pass through the main shaft and main rotor of the shimmy damping connection of block rubber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610571167.2A CN105972151B (en) | 2016-07-20 | 2016-07-20 | Pass through the main shaft and main rotor of the shimmy damping connection of block rubber |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105972151A CN105972151A (en) | 2016-09-28 |
| CN105972151B true CN105972151B (en) | 2018-03-13 |
Family
ID=56952732
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610571167.2A Expired - Fee Related CN105972151B (en) | 2016-07-20 | 2016-07-20 | Pass through the main shaft and main rotor of the shimmy damping connection of block rubber |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105972151B (en) |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106494615A (en) * | 2016-11-08 | 2017-03-15 | 芜湖万户航空航天科技有限公司 | Unmanned plane tail rotor |
Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2127061A5 (en) * | 1971-02-22 | 1972-10-13 | Arfina | |
| US5372478A (en) * | 1993-02-04 | 1994-12-13 | The Boeing Company | Helicopter rotor damper |
| CN1842463A (en) * | 2003-08-27 | 2006-10-04 | 贝尔直升机泰克斯特龙公司 | Soft in-plane rotor hub |
| CN1944185A (en) * | 2005-09-21 | 2007-04-11 | 欧洲直升机公司 | Rotor for rotorcraft with blades articulated in flap and drag |
| CN203698662U (en) * | 2014-01-24 | 2014-07-09 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN205387196U (en) * | 2016-03-21 | 2016-07-20 | 甄圣远 | Connection constructs in unmanned helicopter rotor head |
| CN106114849A (en) * | 2016-07-20 | 2016-11-16 | 芜湖万户航空航天科技有限公司 | The main shaft connected by interior square set and main rotor |
| CN205806325U (en) * | 2016-07-20 | 2016-12-14 | 芜湖万户航空航天科技有限公司 | The main shaft connected by the shimmy damping of block rubber and main rotor |
-
2016
- 2016-07-20 CN CN201610571167.2A patent/CN105972151B/en not_active Expired - Fee Related
Patent Citations (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR2127061A5 (en) * | 1971-02-22 | 1972-10-13 | Arfina | |
| US5372478A (en) * | 1993-02-04 | 1994-12-13 | The Boeing Company | Helicopter rotor damper |
| CN1842463A (en) * | 2003-08-27 | 2006-10-04 | 贝尔直升机泰克斯特龙公司 | Soft in-plane rotor hub |
| CN1944185A (en) * | 2005-09-21 | 2007-04-11 | 欧洲直升机公司 | Rotor for rotorcraft with blades articulated in flap and drag |
| CN203698662U (en) * | 2014-01-24 | 2014-07-09 | 兰州神龙航空科技有限公司 | Vertical take-off and landing rotary wing type unmanned aerial vehicle |
| CN205387196U (en) * | 2016-03-21 | 2016-07-20 | 甄圣远 | Connection constructs in unmanned helicopter rotor head |
| CN106114849A (en) * | 2016-07-20 | 2016-11-16 | 芜湖万户航空航天科技有限公司 | The main shaft connected by interior square set and main rotor |
| CN205806325U (en) * | 2016-07-20 | 2016-12-14 | 芜湖万户航空航天科技有限公司 | The main shaft connected by the shimmy damping of block rubber and main rotor |
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| Publication number | Publication date |
|---|---|
| CN105972151A (en) | 2016-09-28 |
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Granted publication date: 20180313 |