CN106800090B - A kind of paddle blade structure for postponing stall flutter - Google Patents
A kind of paddle blade structure for postponing stall flutter Download PDFInfo
- Publication number
- CN106800090B CN106800090B CN201510846468.7A CN201510846468A CN106800090B CN 106800090 B CN106800090 B CN 106800090B CN 201510846468 A CN201510846468 A CN 201510846468A CN 106800090 B CN106800090 B CN 106800090B
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- China
- Prior art keywords
- trimmer
- big
- blade
- blade structure
- postponing
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Classifications
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- 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
Abstract
The invention belongs to helicopter blade field of structural design, and in particular to one kind can postpone the paddle blade structure of stall flutter.When carrying out big Speed Flight subject and taking a flight test, pitch-change-link load increased dramatically certain type machine, be presented periodic peaks phenomenon bigger than normal, therefore it may be concluded that the type machine in big Speed Flight Shi Facheng stall flutter phenomenon.The present invention only carries out local improvement to blade internal structure under the premise of not being modified to paddle molding mold, and propeller-blade section position of centre of gravity is made to move forward, and installs big rear trimmer component additional in blade prevailing lift face rear, adjusts blade aerodynamic center.
Description
Technical field
The invention belongs to helicopter blade field of structural design, and in particular to one kind can postpone the blade knot of stall flutter
Structure.
Background technique
When the big Speed Flight subject of progress is taken a flight test, pitch-change-link load increased dramatically certain type machine, and periodic peaks are presented
Phenomenon bigger than normal, therefore it may be concluded that the type machine in big Speed Flight Shi Facheng stall flutter phenomenon.
Document number is GB51083751's, and purpose adjusts the unbalanced rear trimmer of blade aerodynamic power；Document number is
The application of CN201010190251.2 discloses the driving method and driving device of trailing edge winglet of rotor blade of helicopter, in paddle
Leaf rear installs intelligent winglet, is moved by intellectual material driving mechanism come active control rear winglet pitching or displacement, thus
Change the aerodynamic loading distribution on blade lift face or generate Additional pneumatic power, reaches and delay retreating blade dynamic stall, improve
Helicopter flight speed, the purpose for reducing blade oscillating load, reducing rotor noise.Above two are directed to adjust using rear
Piece is adjusted blade aerodynamic power.
Summary of the invention
This technical problem to be solved: under the premise of not being modified to paddle molding mold, only to blade inside
Structure carries out local improvement, and propeller-blade section position of centre of gravity is made to move forward, and installs big rear tune additional in blade prevailing lift face rear
Full wafer component adjusts blade aerodynamic center.
The technical scheme is that a kind of paddle blade structure that can postpone stall flutter, for reducing the big speed of helicopter
Pull rod load when preceding winged, the paddle blade structure have small rear trimmer in lifting surface rear, and the paddle blade structure is in small rear tune
Also there are several big rear trimmer components on the outside of full wafer, and be distributed at 0.7R-0.9R rotor radius；Big rear trimmer group
The angle of part and horizontal plane is 8 °.
Further, the big rear trimmer component is made of upper tab and lower trimmer bonding, and is held at one
Portion has opening.
Further, in the upper and lower side laying shield of blade rear and gluing, shield is inserted into opening for big rear trimmer component
The interior simultaneously gluing of mouth.
Further, shield and big rear trimmer component pass through rivet interlacement.
Further, the material of upper tab and lower trimmer is duralumin.
Further, upper tab and lower trimmer first use Arnold's fourth to carry out the anodization of non-close complex acid, then by type
Number it is applied to tab surface for the glue film of DHS186-211.20, it is at least 0.5 hour dry in room temperature environment, then again 135
Solidify 10 minutes -1 hour 1 hour at a temperature of DEG C -145 DEG C.
Further, shield is glass cloth ECS2335.10.
Further, the quantity of the big rear trimmer component is 14.
Further, 1 ± 0.5mm of spacing dimension of the big rear trimmer component.
The beneficial effects of the present invention are: covering device installation is simple, and necessary surface treatment is carried out, use process should
Covering device can realize condition based maintenance；Solidify and the double insurance mounting means of rivet interlacement using bonding, guarantees that the covering device exists
It is not in the equal strength problem that falls off in blade use process；Trimmer is divided into 14 to install respectively, guarantees that it will not influence
The shimmy rigidity of blade avoids the variation for causing the shimmy intrinsic frequency of type machine rotor；Test flight data shows pull rod load reduction,
Occur when big Speed Flight without stall flutter phenomenon.The main blade mould structure of change is avoided, change cost is reduced.
Detailed description of the invention
Fig. 1 is the schematic diagram of rotor structure of the present invention；
Fig. 2 is the A-A cross-sectional view of Fig. 1；
Fig. 3 is the partial enlarged view of Fig. 2；
Fig. 4 is the bonding schematic diagram of the big rear trimmer component of the present invention.
Trimmer, 5- shield, 6- rivet under the big rear trimmer component of 1-, the small rear trimmer of 2-, 3- upper tab, 4-
Specific embodiment
1. upper tab 3 and lower trimmer 4:
As shown in figure 4, its material is duralumin (ASNA3044-8543).Being glued front surface treatment process is first to use Arnold
Fourth carries out the anodization of non-close complex acid, and then by glue film, model DHS186-211.20 is applied to tab surface, in room temperature
Environmental drying at least 0.5 hour, then solidify 10 minutes -1 hour 1 hour at a temperature of 135 DEG C -145 DEG C again.
2. big rear trimmer component 1
It is made of upper tab 3 and lower trimmer 4, by upper tab 3 and lower trimmer 4 alignment bonding, as shown in Figure 3.
Side alignment requirements tolerance is ± 0.1mm, smears glue film, model DHS172-292.20 being glued face, cure cycle is 125
Under the conditions of DEG C ± 5 DEG C, solidify 30 minutes -2 hours 2 hours.
3. rivet
As shown in fig. 3, rivet 6 is 21215DC2407J.
4. trimmer shield
As shown in figure 3, shield 5 is glass cloth ECS2335.10.
5. the installation (being made of 14 trimmer components) of big rear trimmer component 1
Blade rear at 0.7-0.9 rotor radius installs 14 big rear trimmer component (as shown in Figure 1), therebetween
Carpenters square cun 11 is 1 ± 0.5mm.
The laying shield 5 first on rear, the brush coating DBC37.5/2 on shield, then in shield 5 and big rear trimmer group
Brush coating DHS172-172.20 between part.
Condition of cure be under the conditions of 70 DEG C of -80 DEG C of temperature, solidification 2 hours 30 points -3 hours 30 points.
Last 6 assembly of riveter nail, and carry out anti-corrosion protection work.
In main blade prevailing lift face, rear (at about 0.7-0.9R rotor radius) increases big rear trimmer component (as schemed
In 1 shown in 1).
As Figure 2-3, blade chord length size L1 is 420mm, will after big rear trimmer component is mounted on blade
, to 8 ° of bending under lower aerofoil direction, the big specific blade rear of rear trimmer element end is 44.5mm apart from size L2 for it.
Claims (7)
1. one kind can postpone the paddle blade structure of stall flutter, pull rod load when Speed Flight big for reducing helicopter, the paddle
Impeller structure has small rear trimmer (2) in lifting surface rear, it is characterised in that: the paddle blade structure is in small rear trimmer (2)
Outside also has several big rear trimmer components (1), and the outer edge of big rear trimmer component (1) exceeds lifting surface rear,
And be distributed at 0.7R-0.9R, R is rotor radius；Big rear trimmer component (1) is to the bending of lower aerofoil direction and and horizontal plane
Angle be 8 °；Big rear trimmer component (1) is made of upper tab (3) and lower trimmer (4) bonding, and an end
With opening, blade rear is inserted into the opening, and the material of upper tab (3) and lower trimmer (4) is duralumin.
2. the paddle blade structure according to claim 1 for postponing stall flutter, it is characterised in that: upper and lower in blade rear
Side laying shield (5) and gluing, shield (5) is inserted into the opening of big rear trimmer component (1) and gluing.
3. the paddle blade structure according to claim 2 for postponing stall flutter, it is characterised in that: shield (5) and big rear
Trimmer component (1) is connected by rivet (6).
4. the paddle blade structure according to claim 1 for postponing stall flutter, it is characterised in that: upper tab (3) and under
Trimmer (4) first carries out the anodization of non-close complex acid using Arnold's fourth, then smears the glue film of model DHS186-211.20
It is at least 0.5 hour dry in room temperature environment in upper and lower tab surface, then solidify at a temperature of 135 DEG C -145 DEG C again 1 hour -
10 minutes 1 hour.
5. the paddle blade structure according to claim 2 for postponing stall flutter, it is characterised in that: shield (5) is glass cloth
ECS2335.10。
6. the paddle blade structure according to claim 1 for postponing stall flutter, it is characterised in that: the big rear trimmer
The quantity of component (1) is 14.
7. the paddle blade structure according to claim 1 for postponing stall flutter, it is characterised in that: the big rear trimmer
1 ± 0.5mm of spacing dimension of component (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510846468.7A CN106800090B (en) | 2015-11-26 | 2015-11-26 | A kind of paddle blade structure for postponing stall flutter |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510846468.7A CN106800090B (en) | 2015-11-26 | 2015-11-26 | A kind of paddle blade structure for postponing stall flutter |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106800090A CN106800090A (en) | 2017-06-06 |
| CN106800090B true CN106800090B (en) | 2019-10-18 |
Family
ID=58976947
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201510846468.7A Active CN106800090B (en) | 2015-11-26 | 2015-11-26 | A kind of paddle blade structure for postponing stall flutter |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106800090B (en) |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB880425A (en) * | 1957-10-21 | 1961-10-18 | Parsons Corp | Improvements in rotor blades for helicopters and the like |
| US6942455B2 (en) * | 2003-06-12 | 2005-09-13 | Sikorsky Aircraft Corporation | Strain isolated trim tab |
| CN105179407A (en) * | 2015-09-02 | 2015-12-23 | 哈尔滨飞机工业集团有限责任公司 | Glue-jointing tool for large regulating sheet of paddle |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20040118978A1 (en) * | 2002-12-24 | 2004-06-24 | Anning Bruce D. | Helicopter rotor and method of repairing same |
| US7083383B2 (en) * | 2004-04-26 | 2006-08-01 | The Boeing Company | Segmented rotor blade trim tab |
| US8192162B2 (en) * | 2008-07-29 | 2012-06-05 | Loftus Robert T | Field installable and removable helicopter rotor blade vibration and blade tracking device |
-
2015
- 2015-11-26 CN CN201510846468.7A patent/CN106800090B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB880425A (en) * | 1957-10-21 | 1961-10-18 | Parsons Corp | Improvements in rotor blades for helicopters and the like |
| US6942455B2 (en) * | 2003-06-12 | 2005-09-13 | Sikorsky Aircraft Corporation | Strain isolated trim tab |
| CN105179407A (en) * | 2015-09-02 | 2015-12-23 | 哈尔滨飞机工业集团有限责任公司 | Glue-jointing tool for large regulating sheet of paddle |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106800090A (en) | 2017-06-06 |
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