CN106005397A - Multi-rotor machine blade, multi-rotor machine and method for improving static unbalance of blade - Google Patents
Multi-rotor machine blade, multi-rotor machine and method for improving static unbalance of blade Download PDFInfo
- Publication number
- CN106005397A CN106005397A CN201610554604.XA CN201610554604A CN106005397A CN 106005397 A CN106005397 A CN 106005397A CN 201610554604 A CN201610554604 A CN 201610554604A CN 106005397 A CN106005397 A CN 106005397A
- 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.)
- 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
- B64C27/46—Blades
- B64C27/473—Constructional features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/04—Helicopters
- B64C27/08—Helicopters with two or more rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a multi-rotor machine blade, a multi-rotor machine and a method for improving static unbalance of the blade. The multi-rotor machine blade comprises a plurality of blades mounted on a blade base, wherein one or more of the plurality of blades is/are equipped with a metal adjustment sheet pair; each metal adjustment sheet pair is mounted at the rear edge of the respective blade and comprises a first dynamic balance adjustment sheet and a second dynamic balance adjustment sheet.
Description
Technical field
The present invention relates to many gyroplanes field, particularly relate to a kind of many gyroplanes oar, to comprise this many gyroplanes oar many
Gyroplane and the method improving blade static unbalance.
Background technology
Currently, four rotors and many gyroplanes are the most more and more used, and the power as many gyroplanes comes
Source, 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, turning
After speed promotes, the difference of rotary shaft can cause blade aerodynamic power to produce difference, and rotor vibration strengthens, and then impact flies
Row device maneuverability so that flight is not sufficiently stable.
Therefore, in order to solve the problems referred to above, general rotor blade needs to carry out static balance and dynamic balancing examination before installation
Test.
At present, many rotorcraft blades static unbalance can be passed through at blade surface album leave adhesive tape or use sand papering
The modes such as blade surface carry out perfect.These methods, while have certain effect to improving dynamic balancing, but the most
Secondary Continuous pressing device for stereo-pattern destroys the profile of blade surface and easy covered with dust, and another aspect sand papering blade is same
The change of blade surface profile can be caused 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
The scheme of many rotorcraft blades static unbalance can be improved in the case of being used for multiple times.
Summary of the invention
Because the drawbacks described above of prior art, the technical problem to be solved is to provide one can be both
Will not destroy in the case of the profile of blade surface is capable of again being used for multiple times and improve the quiet injustice of many rotorcraft blades
The many gyroplanes oar weighed and the many gyroplanes comprising this many gyroplanes oar.
For achieving the above object, the invention 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 every
Individual metallic adjusted sheet is to being all arranged on the same side of respective blade, and each metallic adjusted sheet is to including that first is dynamic flat
Weighing apparatus metallic adjusted sheet and 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
Between dynamic balancing metallic adjusted sheet 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 chi that the first dynamic balancing metallic adjusted sheet and the second dynamic balancing metallic adjusted sheet highlight from blade surface
The very little 5%-15% for blade cross section chord length.
Preferably, the chi that the first dynamic balancing metallic adjusted sheet and the second dynamic balancing metallic adjusted sheet highlight from blade surface
Very little for the 10% of blade cross section chord length.
For achieving the above object, present invention also offers a kind of many gyroplanes including above-mentioned many gyroplanes oar.
For achieving the above object, present invention also offers a kind of method improving many rotorcraft blades static unbalance, bag
Include: manufacture above-mentioned many gyroplanes oar；When blade unbalance dynamic, it is folded upward at the gold of aerodynamic force bigger side blade
Belong to tab to or the metallic adjusted sheet pair of downward bending aerodynamic force less side blade, to realize many gyroplanes oar
The dynamic balancing of multi-disc blade.
Preferably, metallic adjusted sheet pair is configured at blade production period at blade.
In a word, many gyroplanes oar will not destroy outside the upper lower aerofoil of original blade according to the preferred embodiment of the invention
Shape, is suitable for various working and rotating speed, can be bent downwardly by tab in the case of blade lift is inadequate simultaneously
Promote lift.Thus, the present invention provides a kind of and not only can will not destroy the profile of blade surface but also be capable of many
The technical scheme of many gyroplanes oar of many rotorcraft blades static unbalance is improved in the case of secondary use.
Below with reference to accompanying drawing, the technique effect of design, concrete structure and the generation of the present invention is described further,
To be fully understood from the purpose of the present invention, feature and effect.
Accompanying drawing explanation
Fig. 1 is the general illustration of many gyroplanes oar according to the preferred embodiment of the invention.
Fig. 2 is the detailed view of the single paddle of many gyroplanes oar according to the preferred embodiment of the invention.
Fig. 3 is the dynamic balancing metal adjustment sheet of the blade installation of many gyroplanes oar according to the preferred embodiment of the invention
Detailed view.
It should be noted that accompanying drawing is used for illustrating the present invention, and the unrestricted present invention.Note, represent the attached of structure
Figure may be not necessarily drawn to scale.Further, in accompanying drawing, same or like element indicates same or like
Label.
Detailed description of the invention
Fig. 1 is the general illustration of many gyroplanes oar according to the preferred embodiment of the invention.Fig. 2 is according to the present invention
The detailed view of the single paddle of many gyroplanes oar of preferred embodiment.Fig. 3 is according to the preferred embodiment of the invention
The detailed view of the dynamic balancing metal adjustment sheet that the blade of many gyroplanes oar is installed.
As shown in Figure 1, Figure 2 and Figure 3, many gyroplanes oar includes according to the preferred embodiment of the invention: be arranged on
Multiple blades 20 on blade pedestal 10, the one or more blades 20 in wherein said multiple blades 20 are joined
It is equipped with metallic adjusted sheet pair；The most each metallic adjusted sheet is to being arranged on the same side of respective blade (such as, often
The individual metallic adjusted sheet trailing edge to being all arranged on respective blade), and each metallic adjusted sheet is to including that first is dynamic flat
Weighing apparatus 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, its
In between the first dynamic balancing metallic adjusted sheet 31 and the second dynamic balancing metallic adjusted sheet 32, there is space；And wherein,
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%
In the region of blade length.
Preferably, the first dynamic balancing metallic adjusted sheet 31 and the second dynamic balancing metallic adjusted sheet 32 are dashed forward from blade surface
The size gone out is the 5%-15% of blade cross section chord length, such as 10%.
According to another preferred embodiment of the invention, many gyroplanes of a kind of above-mentioned many gyroplanes oar are additionally provided.
In a word, in a particular embodiment, the present invention is at blade posterior segment (70%-80% opens up to position) posterior border position
Adding 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 is not suitable for installing additional after paddle molding owing to may destroy the profile of blade, thus typically produce at blade
Time use pre-buried method to configure；And sheet metal highlights trailing edge about 10% cross section chord length, every tab width
About 5% blade radius, has a small-gap suture between two panels tab, when blade unbalance dynamic, and can the most upwards
The tab of bending aerodynamic force bigger side blade or the tab of downward bending aerodynamic force less side blade, make
It reaches the dynamic balancing of multi-disc blade.The program changes blade two-dimensional section aerofoil profile mainly by the bending of sheet metal
Camber and the angle of attack, thus change aerodynamic force.Due to the aerodynamic force in single cross section can not change cause the most greatly along exhibition to
Aerodynamic force sudden change, can suitably bend second come perfect if first tab fails to reach effect.
Thus, the present invention actually additionally provides a kind of following method improving many rotorcraft blades static unbalance,
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, is folded upward at the metallic adjusted sheet pair of aerodynamic force bigger side blade
Or the metallic adjusted sheet pair of downward bending aerodynamic force less side blade, to realize the multi-disc blade of many gyroplanes oar
Dynamic balancing.
In a word, many gyroplanes oar will not destroy outside the upper lower aerofoil of original blade according to the preferred embodiment of the invention
Shape, is suitable for various working and rotating speed, can be bent downwardly by tab in the case of blade lift is inadequate simultaneously
Promote lift.Thus, the present invention provides a kind of and not only can will not destroy the profile of blade surface but also be capable of many
The technical scheme of many gyroplanes oar of many rotorcraft blades static unbalance is improved in the case of secondary use.
Described above illustrate and describes the preferred embodiments of the present invention, as previously mentioned, it should be understood that the present invention is not
It is confined to form disclosed herein, is not to be taken as the eliminating to other embodiments, and can be used for other groups various
Close, amendment and environment, and can be in invention contemplated scope described herein, by above-mentioned teaching or association area
Technology or knowledge are modified.And the change that those skilled in the art are carried out and change are without departing from the spirit of the present invention and model
Enclose, the most all should be in the protection domain of claims of the present invention.
Claims (10)
1. gyroplane oar more than a kind, it is characterised in that including: the multiple blades being arranged on blade pedestal, Qi Zhongsuo
State and be configured with metallic adjusted sheet pair on the one or more blades in multiple blade；The most each metallic adjusted
Sheet is to being all arranged on the same side of respective blade, and each metallic adjusted sheet is to including the first dynamic balancing gold
Belong to tab 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
Two dynamic balancing metallic adjusted sheets are arranged side by side, wherein the first dynamic balancing metallic adjusted sheet and the second dynamic balancing gold
Belong to, between tab, there is space；And wherein, the second dynamic balancing metallic adjusted sheet is dynamic flat relative to first
Weighing apparatus metallic adjusted sheet is 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 pacifying
It is contained in the trailing edge of respective blade.
Many gyroplanes oar the most as claimed in claim 1 or 2, it is characterised in that each metallic adjusted sheet is to pacifying
It is contained in the same position of respective blade.
Many gyroplanes oar the most as claimed in claim 1 or 2, it is characterised in that each metallic adjusted sheet is to pacifying
It is contained in the region with blade pedestal 70%-80% blade length apart of respective 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
The 5%-15% that size is blade cross section chord length highlighted from blade surface with the second dynamic balancing metallic adjusted sheet.
Many gyroplanes oar the most as claimed in claim 1 or 2, it is characterised in that the first dynamic balancing metallic adjusted sheet
With the second dynamic balancing metallic adjusted sheet 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.
9. the method improving many rotorcraft blades static unbalance, including: manufacture such as one of claim 1 to 7
Described many gyroplanes oar；When blade unbalance dynamic, it is folded upward at the gold of aerodynamic force bigger side blade
Belong to tab to or the metallic adjusted sheet pair of downward bending aerodynamic force less side blade, to realize many rotors
The dynamic balancing of the multi-disc blade of machine oar.
10. the method improving many rotorcraft blades static unbalance as claimed in claim 9, it is characterised in that at oar
Leaf production period configures metallic adjusted sheet pair at blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610554604.XA CN106005397A (en) | 2016-07-14 | 2016-07-14 | Multi-rotor machine blade, multi-rotor machine and method for improving static unbalance of blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610554604.XA CN106005397A (en) | 2016-07-14 | 2016-07-14 | Multi-rotor machine blade, multi-rotor machine and method for improving static unbalance of blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN106005397A true CN106005397A (en) | 2016-10-12 |
Family
ID=57118936
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610554604.XA Pending CN106005397A (en) | 2016-07-14 | 2016-07-14 | Multi-rotor machine blade, multi-rotor machine and method for improving static unbalance of blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106005397A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741857A (en) * | 2017-03-02 | 2017-05-31 | 南京那尔朴电子有限公司 | A kind of propeller that can be adjusted with thrust |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1215675A (en) * | 1957-10-21 | 1960-04-20 | Parsons Corp | Method for manufacturing and balancing helicopter rotor blades |
| GB1150123A (en) * | 1967-02-08 | 1969-04-30 | Westland Aircraft Ltd | Improvements in or relating to the Construction of Rotor Blades for Rotary Wing Aircraft |
| US3952601A (en) * | 1974-12-18 | 1976-04-27 | United Technologies Corporation | Helicopter rotor blade balancing method |
| US6196066B1 (en) * | 1998-07-17 | 2001-03-06 | Eurocopter | Rotor aircraft rotor blade with static and dynamic balancing device and balancing process of a blade |
| US6311924B1 (en) * | 1998-10-12 | 2001-11-06 | Eurocopter | Device and process for reducing the vibration generated on the structure of a rotary-wing aircraft, particularly a helicopter |
| US20050042109A1 (en) * | 2003-08-22 | 2005-02-24 | Kovalsky David A. | Braided spar for a rotor blade and method of manufacture thereof |
| CN203306224U (en) * | 2013-05-31 | 2013-11-27 | 深圳市大疆创新科技有限公司 | Propeller and aircraft provided with same |
| CN104340378A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Repair method of composite main paddle with hinge moment variance |
| CN205837194U (en) * | 2016-07-14 | 2016-12-28 | 上海未来伙伴机器人有限公司 | Many gyroplanes oar and many gyroplanes |
-
2016
- 2016-07-14 CN CN201610554604.XA patent/CN106005397A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1215675A (en) * | 1957-10-21 | 1960-04-20 | Parsons Corp | Method for manufacturing and balancing helicopter rotor blades |
| GB1150123A (en) * | 1967-02-08 | 1969-04-30 | Westland Aircraft Ltd | Improvements in or relating to the Construction of Rotor Blades for Rotary Wing Aircraft |
| US3952601A (en) * | 1974-12-18 | 1976-04-27 | United Technologies Corporation | Helicopter rotor blade balancing method |
| US6196066B1 (en) * | 1998-07-17 | 2001-03-06 | Eurocopter | Rotor aircraft rotor blade with static and dynamic balancing device and balancing process of a blade |
| US6311924B1 (en) * | 1998-10-12 | 2001-11-06 | Eurocopter | Device and process for reducing the vibration generated on the structure of a rotary-wing aircraft, particularly a helicopter |
| US20050042109A1 (en) * | 2003-08-22 | 2005-02-24 | Kovalsky David A. | Braided spar for a rotor blade and method of manufacture thereof |
| CN203306224U (en) * | 2013-05-31 | 2013-11-27 | 深圳市大疆创新科技有限公司 | Propeller and aircraft provided with same |
| CN104340378A (en) * | 2013-08-05 | 2015-02-11 | 哈尔滨飞机工业集团有限责任公司 | Repair method of composite main paddle with hinge moment variance |
| CN205837194U (en) * | 2016-07-14 | 2016-12-28 | 上海未来伙伴机器人有限公司 | Many gyroplanes oar and many gyroplanes |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106741857A (en) * | 2017-03-02 | 2017-05-31 | 南京那尔朴电子有限公司 | A kind of propeller that can be adjusted with thrust |
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| 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 |
Application publication date: 20161012 |
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| RJ01 | Rejection of invention patent application after publication |