CN205837194U - Many gyroplanes oar and many gyroplanes - Google Patents
Many gyroplanes oar and many gyroplanes Download PDFInfo
- Publication number
- CN205837194U CN205837194U CN201620742213.6U CN201620742213U CN205837194U CN 205837194 U CN205837194 U CN 205837194U CN 201620742213 U CN201620742213 U CN 201620742213U CN 205837194 U CN205837194 U CN 205837194U
- Authority
- CN
- China
- Prior art keywords
- blade
- adjusted sheet
- metallic adjusted
- oar
- dynamic balancing
- 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.)
- Expired - Fee Related
Links
Landscapes
- Laminated Bodies (AREA)
Abstract
The utility model discloses a kind of many gyroplanes oar and many gyroplanes.Include according to many gyroplanes oar of the present utility model: the multiple blades being arranged on blade pedestal, the one or more blades in wherein said multiple blades are configured with metallic adjusted sheet pair；The most each metallic adjusted sheet is to being arranged on the trailing edge of respective blade, and each metallic adjusted sheet is to including the first dynamic balancing metallic adjusted sheet and the second dynamic balancing metallic adjusted sheet.
Description
Technical field
This utility model relates to many gyroplanes field, particularly relates to a kind of many gyroplanes oar and comprises this many gyroplanes oar
Many gyroplanes.
Background technology
Currently, four rotors and many gyroplanes are the most more and more used, as the power resources of many gyroplanes,
The aeroperformance of blade affects the biggest for the overall performance of gyroplane.But, due to the restriction of manufacturing process and relevant
Foozle, each blade of rotor is not completely the same for its rotary shaft.Thus, after rotating speed promotes, rotary shaft
Difference can cause blade aerodynamic power to produce difference, and rotor vibration strengthens, and then affects aircraft control so that fly the most steady
Fixed.
Therefore, in order to solve the problems referred to above, general rotor blade needs to carry out static balance and dynamic balance running before installation.
At present, many rotorcraft blades static unbalance can be passed through at blade surface album leave adhesive tape or use sand papering leaf
The modes such as sheet surface carry out perfect.These methods, while have a certain effect to improving dynamic balancing, but on the one hand conducting repeated adhesion rubberizing
Band destroys the profile of blade surface and easy covered with dust, and another aspect sand papering blade can cause blade surface equally
The change of profile and be not suitable for being used for multiple times.
Therefore, those skilled in the art be devoted to develop a kind of can not only will not destroy blade surface profile but also can
The scheme of many rotorcraft blades static unbalance is improved in the case of being enough used for multiple times.
Utility model content
Because the drawbacks described above of prior art, technical problem to be solved in the utility model is to provide one can be
Many rotorcraft blades static unbalance was improved in the case of not only will not having destroyed the profile of blade surface but also be capable of being used for multiple times
Many gyroplanes oar and comprise many gyroplanes of this many gyroplanes oar.
For achieving the above object, this utility model provides a kind of many gyroplanes oar, including: it is arranged on blade pedestal
Multiple blades, the one or more blades in wherein said multiple blades are configured with metallic adjusted sheet pair；The most each metal
Tab is to being all arranged on the same side of respective blade, and each metallic adjusted sheet is to including the first dynamic balancing metallic adjusted sheet
With the second dynamic balancing metallic adjusted sheet.
Preferably, the first dynamic balancing metallic adjusted sheet and the second dynamic balancing metallic adjusted sheet are arranged side by side, and wherein first move
Between budget metals tab and the second dynamic balancing metallic adjusted sheet, there is space；And wherein, the second dynamic balancing metallic adjusted
Sheet relative to the first dynamic balancing metallic adjusted sheet closer to blade pedestal.
Preferably, each metallic adjusted sheet trailing edge to being arranged on respective blade.
Preferably, each metallic adjusted sheet same position to being arranged on respective blade.
Preferably, each metallic adjusted sheet to be arranged on respective blade with blade pedestal at a distance of 70%-80% blade
In the region of length.
Preferably, the size that the first dynamic balancing metallic adjusted sheet and the second dynamic balancing metallic adjusted sheet highlight from blade surface
5%-15% for blade cross section chord length.
Preferably, the size that the first dynamic balancing metallic adjusted sheet and the second dynamic balancing metallic adjusted sheet highlight from blade surface
For blade cross section chord length 10%.
For achieving the above object, this utility model additionally provides a kind of many gyroplanes including above-mentioned many gyroplanes oar.
For achieving the above object, this utility model additionally provides a kind of method improving many rotorcraft blades static unbalance,
Including: manufacture above-mentioned many gyroplanes oar；When blade unbalance dynamic, it is folded upward at the metallic adjusted of aerodynamic force bigger side blade
Sheet to or the metallic adjusted sheet pair of downward bending aerodynamic force less side blade, to realize the dynamic of the multi-disc blade of many gyroplanes oar
Balance.
Preferably, metallic adjusted sheet pair is configured at blade production period at blade.
In a word, will not destroy according to many gyroplanes oar of this utility model preferred embodiment outside the upper lower aerofoil of original blade
Shape, is suitable for various working and rotating speed, can be bent downwardly by tab simultaneously and promote liter in the case of blade lift is inadequate
Power.Thus, this utility model offer is a kind of not only can will not destroy the profile of blade surface but also is being capable of nonexpondable
In the case of improve the technical scheme of many gyroplanes oar of many rotorcraft blades static unbalance.
Below with reference to accompanying drawing, the technique effect of design of the present utility model, concrete structure and generation is made furtherly
Bright, to be fully understood from the purpose of this utility model, feature and effect.
Accompanying drawing explanation
Fig. 1 is the general illustration of the many gyroplanes oar according to this utility model preferred embodiment.
Fig. 2 is the detailed view of the single paddle of the many gyroplanes oar according to this utility model preferred embodiment.
Fig. 3 is the dynamic balancing metal adjustment sheet of the blade installation of the many gyroplanes oar according to this utility model preferred embodiment
Detailed view.
It should be noted that accompanying drawing is used for illustrating this utility model, and unrestricted this utility model.Note, represent structure
Accompanying drawing may be not necessarily drawn to scale.Further, in accompanying drawing, same or like element indicates same or like mark
Number.
Detailed description of the invention
Fig. 1 is the general illustration of the many gyroplanes oar according to this utility model preferred embodiment.Fig. 2 is according to this practicality
The detailed view of the single paddle of many gyroplanes oar of novel preferred embodiment.Fig. 3 is according to this utility model preferred embodiment
The detailed view of dynamic balancing metal adjustment sheet installed of the blade of many gyroplanes oar.
As shown in Figure 1, Figure 2 and Figure 3, include according to many gyroplanes oar of this utility model preferred embodiment: be arranged on oar
Multiple blades 20 on phyllopodium seat 10, the one or more blades 20 in wherein said multiple blades 20 are configured with metallic adjusted
Sheet pair；(such as, each metallic adjusted sheet is to installing to the same side being arranged on respective blade for the most each metallic adjusted sheet
Trailing edge at respective blade), and each metallic adjusted sheet is to including the first dynamic balancing metallic adjusted sheet 31 and the second dynamic balancing
Metallic adjusted sheet 32.
Preferably, the first dynamic balancing metallic adjusted sheet 31 and the second dynamic balancing metallic adjusted sheet 32 are arranged side by side, Qi Zhong
Between one dynamic balancing metallic adjusted sheet 31 and the second dynamic balancing metallic adjusted sheet 32, there is space；And wherein, the second dynamic balancing
Metallic adjusted sheet 32 relative to the first dynamic balancing metallic adjusted sheet 31 closer to blade pedestal 10.
Wherein it is preferred to, each metallic adjusted sheet same position to being arranged on respective blade.
Preferably, each metallic adjusted sheet to be arranged on respective blade with blade pedestal 10 at a distance of 70%-80% oar
In the region of leaf length.
Preferably, the first dynamic balancing metallic adjusted sheet 31 and the second dynamic balancing metallic adjusted sheet 32 highlight from blade surface
The a size of 5%-15% of blade cross section chord length, such as 10%.
According to another preferred embodiment of the present utility model, additionally provide many gyroplanes of a kind of above-mentioned many gyroplanes oar.
In a word, in a particular embodiment, this utility model is at blade posterior segment (70%-80% opens up to position) posterior border position
Add two panels metallic adjusted sheet, owing to the paddle size of many gyroplanes is the least and trailing edge is relatively thin, therefore metallic adjusted sheet due to
The profile of blade may be destroyed and be not suitable for installing additional after paddle molding, thus typically use pre-buried blade produces when
Method configuration；And sheet metal highlights trailing edge about 10% cross section chord length, every tab width about 5% blade radius, two panels
There is a small-gap suture between tab, when blade unbalance dynamic, can suitably be folded upward at the tune of aerodynamic force bigger side blade
The tab of full wafer or downwards bending aerodynamic force less side blade so that it is reach the dynamic balancing of multi-disc blade.Program master
If the bending utilizing sheet metal changes camber and the angle of attack of blade two-dimensional section aerofoil profile, thus changes aerodynamic force.Due to single
The aerodynamic force in cross section can not change cause the most greatly along exhibition to aerodynamic force sudden change, can fit if first tab fails to reach effect
When bending second comes perfect.
Thus, this utility model actually additionally provides following a kind of side improving many rotorcraft blades static unbalance
Method, including:
First step: manufacture many gyroplanes oar as above；
Such as, metallic adjusted sheet pair is configured at blade production period at blade；
Second step: when blade unbalance dynamic, be folded upward at the metallic adjusted sheet of aerodynamic force bigger side blade to or
The metallic adjusted sheet pair of bending aerodynamic force less side blade downwards, to realize the dynamic balancing of the multi-disc blade of many gyroplanes oar.
In a word, will not destroy according to many gyroplanes oar of this utility model preferred embodiment outside the upper lower aerofoil of original blade
Shape, is suitable for various working and rotating speed, can be bent downwardly by tab simultaneously and promote liter in the case of blade lift is inadequate
Power.Thus, this utility model offer is a kind of not only can will not destroy the profile of blade surface but also is being capable of nonexpondable
In the case of improve the technical scheme of many gyroplanes oar of many rotorcraft blades static unbalance.
Described above illustrate and describes preferred embodiment of the present utility model, as previously mentioned, it should be understood that this practicality is new
Type is not limited to form disclosed herein, is not to be taken as the eliminating to other embodiments, and can be used for other groups various
Close, revise and environment, and can be in utility model contemplated scope described herein, by above-mentioned teaching or the technology of association area
Or knowledge is modified.And the change that those skilled in the art are carried out and change are without departing from spirit and scope of the present utility model, then
All should be in the protection domain of this utility model claims.
Claims (8)
1. gyroplane oar more than a kind, it is characterised in that including: the multiple blades being arranged on blade pedestal, wherein said multiple oars
It is configured with metallic adjusted sheet pair on one or more blades in leaf；The most each metallic adjusted sheet is to being arranged on respective blade
The same side, and each metallic adjusted sheet is to including the first dynamic balancing metallic adjusted sheet and the second dynamic balancing metallic adjusted sheet.
Many gyroplanes oar the most as claimed in claim 1, it is characterised in that the first dynamic balancing metallic adjusted sheet and the second dynamic balancing
Metallic adjusted sheet is arranged side by side, and wherein has sky between the first dynamic balancing metallic adjusted sheet and the second dynamic balancing metallic adjusted sheet
Gap；And wherein, the second dynamic balancing metallic adjusted sheet relative to the first dynamic balancing metallic adjusted sheet closer to blade pedestal.
Many gyroplanes oar the most as claimed in claim 1 or 2, it is characterised in that each metallic adjusted sheet is to being arranged on each
The trailing edge of blade.
Many gyroplanes oar the most as claimed in claim 1 or 2, it is characterised in that each metallic adjusted sheet is to being arranged on each
The same position of blade.
Many gyroplanes oar the most as claimed in claim 1 or 2, it is characterised in that each metallic adjusted sheet is to being arranged on each
In the region with blade pedestal 70%-80% blade length apart of blade.
Many gyroplanes oar the most as claimed in claim 1 or 2, it is characterised in that the first dynamic balancing metallic adjusted sheet and second moves
The 5%-15% that size is blade cross section chord length that budget metals tab highlights from blade surface.
Many gyroplanes oar the most as claimed in claim 1 or 2, it is characterised in that the first dynamic balancing metallic adjusted sheet and second moves
Budget metals tab from blade surface prominent size is blade cross section chord length 10%.
8. many gyroplanes of many gyroplanes oar that a kind includes as described in one of claim 1 to 7.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620742213.6U CN205837194U (en) | 2016-07-14 | 2016-07-14 | Many gyroplanes oar and many gyroplanes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620742213.6U CN205837194U (en) | 2016-07-14 | 2016-07-14 | Many gyroplanes oar and many gyroplanes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN205837194U true CN205837194U (en) | 2016-12-28 |
Family
ID=57618914
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201620742213.6U Expired - Fee Related CN205837194U (en) | 2016-07-14 | 2016-07-14 | Many gyroplanes oar and many gyroplanes |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN205837194U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005397A (en) * | 2016-07-14 | 2016-10-12 | 上海未来伙伴机器人有限公司 | Multi-rotor machine blade, multi-rotor machine and method for improving static unbalance of blade |
-
2016
- 2016-07-14 CN CN201620742213.6U patent/CN205837194U/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106005397A (en) * | 2016-07-14 | 2016-10-12 | 上海未来伙伴机器人有限公司 | Multi-rotor machine blade, multi-rotor machine and method for improving static unbalance of blade |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US20200018285A1 (en) | Airfoil with a vortex generator pair | |
| CN103270296B (en) | Wind turbine blade, wind power generation device provided with same, and design method for wind turbine blade | |
| Chica et al. | Design of a hydrokinetic turbine | |
| CN106536921B (en) | To extract wind energy and hydrokinetic turbine rotor | |
| CN107341288B (en) | Optimization method for controlling vibration of combined cycle unit by adjusting elevation of bearing | |
| Menet et al. | A comparative calculation of the wind turbines capacities on the basis of the L–σ criterion | |
| US8734084B1 (en) | Wind wing | |
| CN103671249B (en) | A kind of centrifugal fan impeller blade with local compliance structure | |
| Hara et al. | Predicting double-blade vertical axis wind turbine performance by a quadruple-multiple streamtube model | |
| KR20080112244A (en) | A method for installing blades of a vertical-shaft wind generator | |
| CN205837194U (en) | Many gyroplanes oar and many gyroplanes | |
| CN107061329A (en) | A kind of axial flow blower | |
| CN106089569A (en) | A kind of Miniature Wind Turbine Blades aerofoil profile being applicable to low reynolds number flow | |
| JP2620087B2 (en) | Rotary wing aircraft blade | |
| EP3431750B1 (en) | Method for determining arrangement position of vortex generator on wind turbine blade, method for producing wind turbine blade assembly, and wind turbine blade assembly | |
| CN107873066A (en) | For damping the device of bridge vibration of beam | |
| CN109441719B (en) | Film self-excitation vibration type vertical axis wind turbine blade | |
| CN105351248A (en) | High-performance airfoil for fan | |
| CN106005397A (en) | Multi-rotor machine blade, multi-rotor machine and method for improving static unbalance of blade | |
| CN103256251A (en) | Variable-curvature arc equal-thickness plate wing section for fan group | |
| Zhuang et al. | Numerical study on aerodynamic performances of the wind turbine rotor with leading-edge rotation | |
| CN205678058U (en) | A kind of engine flywheel | |
| CN107697284A (en) | A kind of two section type bionic flapping-wing unmanned plane wing | |
| CN110378068B (en) | Variable camber inlet guide vane and design method thereof | |
| JP2018119483A (en) | Blade and wind turbine using the same |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20161228 Termination date: 20200714 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |