CN101954972A - Be provided with the aircraft rotor of blade holding device - Google Patents
Be provided with the aircraft rotor of blade holding device Download PDFInfo
- Publication number
- CN101954972A CN101954972A CN2010102346523A CN201010234652A CN101954972A CN 101954972 A CN101954972 A CN 101954972A CN 2010102346523 A CN2010102346523 A CN 2010102346523A CN 201010234652 A CN201010234652 A CN 201010234652A CN 101954972 A CN101954972 A CN 101954972A
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- China
- Prior art keywords
- blade
- retainer
- rotor
- retaining hole
- spar
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/006—Safety devices
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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
- B64C27/48—Root attachment to rotor head
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/82—Rotorcraft; Rotors peculiar thereto characterised by the provision of an auxiliary rotor or fluid-jet device for counter-balancing lifting rotor torque or changing direction of rotorcraft
Abstract
The present invention relates to a kind of blade (10 that at least one is fixed to actuating device (2) that is provided with, 20) rotor (1), described rotor (1) comprises at least one retainer (50), described retainer is in case installation is in compressive state with regard to being applied with prestress, thereby described blade (10,20) is connected to actuating device (2).
Description
Technical field
The present invention relates to be provided with the aircraft rotor of blade holding device.
More particularly, the present invention relates to be used to keep the device of the blade of helicopter anti-torque rotor.
Background technology
According to the document, the free end of blade comprises first brace panel and second brace panel on first end that is clamped to slender member within it.Described first end then is fixed to first brace panel and second brace panel by clamp structure.
In addition, second end of slender member is outstanding with by the hub portion of bolt to rotor from the shell of blade.
In addition, this slender member can be made of a plurality of strips that keep together by adhesives.Because slender member is suitable for standing to reverse, and can reverse arm-type blade so this blade is called sometimes.
Will be understood that each blade is attached to the hub portion of rotor via slender member.Therefore, although may not take place, the fracture of slender member can cause blade to damage.
Also know second kind of afterbody blade, wherein, at least one pair of relative blade links together by the flexibility band, and this flexibility band portion ground is suitable for standing to reverse, described coilable flexible band constitute two relative blades public spar.
Be called " connecting band " or " perforation spar " when therefore, flexibility has by those skilled in the art.For for simplicity, use term " perforation spar " to be used as flexibility band spar, that can partly reverse of two relative blades hereinafter.
Different with first kind of rotor, the blade of rotor is fixed to actuating device in couples by their public spars.
In addition, each blade in a pair of blade has shell, the end that connects spar and the optional packing elements that is positioned at shell.
Therefore, two ends that connect spar are surrounded by first shell and second shell of first blade and second blade respectively.
These ends are suitable for standing to reverse, and the centre portion that extends between the shell of first blade that is associated and second blade, connect spar is a rigidity.In addition, centre portion is fixed to the rotor actuating device, specifically is fixed to rotor shaft.
In addition, each shell is equipped with the pitch hinge.When the aviator attempted to revise the pitch of blade, control stalk applied power on the pitch hinge, caused that thus the shell of blade rotates.Be suitable for torsional deflection owing to connect the end that is covered by shell of spar, so connect the rotation that spar does not hinder described blade shell.
Be connected to two securing devices of the rotor that constitutes by top board and base plate according to the centre portion of the perforation spar of 2 285 298, second kind of rotor of document FR.
Or rather, the bottom side that connects the centre portion of spar is placed to and is resisted against on the base plate that cooperates rotor shaft, the top board of rotor be pressed against on the top of the centre portion that connects spar and with bolt to rotor shaft.Therefore centre portion remains between base plate and the top board rigidly.
In addition, each shell gradually changes from its free end, thereby forms pullover at its root.The pullover flange that then covers with two flexible double-screw bolts, these two double-screw bolts are arranged on the both sides of the described plate of being installed, and every pair of double-screw bolt flexibly is connected to hub portion with flange.
As a modification,
Helicopter is also with trade name
And well-known, be provided with second kind of anti-torque rotor, this anti-torque rotor is provided with a pair of blade with the public perforation spar that can partly reverse.
On the helicopter, the pullover flange that comprises of each blade, this flange have the pitch hinge and are called the added mass of sinotype counterweight.
In addition, be positioned at the rotor metal base plate of the centre portion below of flexible band, connect the centre portion of spar, and the rotor metal top plate that is positioned at above the described centre portion can fit together:
Laminar first connection structure is arranged between flange and the base plate, and the external intensity member of first connection structure is fixed to flange, and the internal intensity member of first connection structure is fixed to base plate; And
Laminar second connection structure is arranged between flange and the top board, and the external intensity member of second connection structure is fixed to flange, and the internal intensity member of second connection structure is fixed to top board.
Base plate is then pierced through to be fixed to the crotch of rotor shaft by lifting shaft.Therefore rotor is called " lifting rotor ".
Rotor this rigidity or lifting is provided with a pair of blade by public perforation spar interconnection, thereby satisfactory.The size that connects spar is commonly used to guarantee not have an accident.
Yet, connect spar is fixed to the rotor securing device by the clamp structure of for example bolt and so on top board and base plate.According to the interval between the clamp structure, thereby have been found that in rare occasion crackle can take place causes the interface to be broken.
Therefore, when the perforation spar has the rotor shaft of passing its center, if be applied to the direction of power process between clamp structure and described axle on the spar, then can cause to connect spar at described clamp structure place and/or in the fracture at the interface of itself and rotor shaft, described clamp structure is used for the perforation spar is fixed to top board and base plate.
The infringement that connects the entity integrity of spar for the rotor of rotor craft can cause blade to radially slide.This causes excessive overbalance, can cause very violent vibration.For the anti-torque rotor of helicopter, this extent of vibration can cause the anti-torque rotor damage.
In addition, extreme is, this crackle can cause that blade scraps fully.
In addition, have been found that being difficult to observe the perforation spar has crackle.This causes potential inefficacy.
In this background technology, but also list of references DE 3 438 557 and US 4 373 862.
Summary of the invention
Therefore, an object of the present invention is to propose a kind ofly can overcome above-mentioned circumscribed aircraft rotor, no matter the spar of this aircraft rotor is to connect spar or other spar, can both prevent that blade from scrapping, and can also warn the damage of blade spar simultaneously.
According to the present invention, a kind of remarkable part with rotor of at least one blade that is fixed to actuating device is, this rotor comprises at least one retainer, and described retainer in a single day installation is in compressive state with regard to being applied with prestress, thereby blade is connected to actuating device.
Therefore, in normal work, promptly when blade is in good condition, retainer can absorption power, and regardless of these power., retainer is in compressive state because being applied with prestress, thus retainer generation deflection, and therefore its life-span can not shorten.
Yet if the spar of blade is impaired, blade will move radially under action of centrifugal force.
Therefore elongation and get back to its original-shape of the retainer that before had been applied with prestress and had been in compressive state, and prevent that blade from sliding.Blade keeps being attached to rotor, thereby implements its function and no longer include the risk that rotor damages.The performance of rotor in fact can deterioration, is equipped with means of delivery of the present invention but still be enough to avoid jeopardizing.
In addition, the motion of blade causes the rotor overbalance, and this rotor overbalance is subject to allowed value.
Just in case the spar of blade lost efficacy, then should be able to observe, retainer is not held in place blade, but limits its radial displacement.Therefore, aviator and being used to system's (if words that have) of monitoring the means of delivery vibration will detect the variation of means of delivery extent of vibration.
Therefore, the maintainer just can obtain notice then and there, and described maintainer can easily with the naked eye detect: retainer no longer be applied with prestress and therefore the spar of blade damage.
The present invention also can comprise one or more in the following supplementary features.
For example, retainer can be made of the band bundle that comprises a folded strip.Therefore, retainer is easy to adapt to various rotors.
By regulating the quantity of used band (for example metal tape), can regulate the tensile strength of retainer.In addition, be easy between intensity and ability to seek a kind of compromise, thereby when flexural deformation, can not pass by in time and damage.
In addition, retainer is provided with respectively first end and second end that is pierced through by first retaining hole and second retaining hole, when retainer does not have application of stress, therefore when promptly being in idle state neither compression be also unstressed, first retaining hole and second retaining hole separate first spacing, described first retaining hole and second retaining hole are suitable for respectively joining with the inferior hole association of at least one main aperture of the securing device of described actuating device and described blade, when described blade is fixed to described actuating device, first retaining hole and second retaining hole separate second spacing, and described first spacing is greater than described second spacing.
In this case, for fixed retainer, use for example clamp structure of bolt and so on, it passes first retaining hole and main aperture.Similarly, the clamp structure of screw bolt-type passes second retaining hole and time hole.
Because second spacing is less than first spacing, so retainer is applied prestress and is in compressive state.
Difference between first spacing and described second spacing can be less than or equal to 5% of first spacing, is advantageously located in the scope of 4%-5% of first spacing.
In addition, be applied with prestressed retainer and present an amount of deflection, described amount of deflection is less than or equal to 15% of first spacing, is advantageously located in the scope of 10%-12% of described first spacing.Should be able to observe, this amount of deflection represent retainer, specifically its center with comprise the maximum vertical displacement on the plane of first end and second end.
In addition, retainer is provided with respectively first end and second end that is pierced through by first retaining hole and second retaining hole, and described second end is fixed to the spar of blade.Second retaining hole is then alternatively assisted and is joined via passing wherein the concrete inferior hole with spar of bolt.
Therefore in first modification, each blade makes himself spar have to be fixed to via its second retaining hole its at least one retainer.The spar of each blade is coilable, and this spar is suitable for standing to reverse.
In second modification, rotor has first blade and second blade, each blade is provided with shell, first blade and second blade link together by public perforation spar, the centre portion of described public perforation spar is fixed to the securing device of actuating device, and each retainer of blade is fixed to centre portion and securing device.Connecting spar is the spar that can partly reverse, and the end that connects spar is contained in the shell being suitable for stands to reverse.
For example, the securing device that retainer is fixed to via its first retaining hole is fixed to the centre portion that connects spar via its second retaining hole, alternatively between the securing device of the shell of blade and actuating device.
Advantageously, rotor comprises first retainer and second retainer for each blade, first main aperture association of first retaining hole of first retainer and the securing device of actuating device joins, second main aperture association of first retaining hole of second retainer and the securing device of actuating device joins, and a same hole of second retaining hole of first retainer and second retainer and described blade is assisted and joined.
Therefore each blade is remained on 2 by the securing device of rotor.
Therefore, first main aperture and second main aperture are distributed in the both sides of the rotation axis of actuating device in equidistant mode, thereby optimize the maintenance for blade.
At last, rotor comprises first blade and second blade of alignment, and
Same first main aperture of first retaining hole of first retaining hole of first retainer of first blade and first retainer of second blade and actuating device is assisted and is joined;
Same second main aperture of second retaining hole of second retaining hole of second retainer of first blade and second retainer of second blade and actuating device is assisted and is joined;
A same hole of first retainer of first blade and second retaining hole of second retainer and first blade is assisted and is joined; And
A same hole of first retainer of second blade and second retaining hole of second retainer and second blade is assisted and is joined.
Description of drawings
From the embodiment that provides in the explanation mode with reference to the accompanying drawings describes, will present the present invention and advantage thereof in more detail, in the accompanying drawings:
Fig. 1 is the first modification rotor that each blade is provided with a retainer;
Fig. 2 is the section that is in the retainer in the idle state;
Fig. 3 is applied with prestress and the section that is in the retainer in the compressive state;
Fig. 4 is the first modification rotor that each blade is provided with two retainers;
Fig. 5 is the diagrammatic top view of a pair of blade of each blade second modification rotor of being provided with a retainer;
Fig. 6 is the diagrammatic top view of a pair of blade of each blade preferable second modification rotor of being provided with two retainers; And
Fig. 7 is that each blade is provided with two retainers, is provided with the partial perspective view of the second modification rotor of two pairs of rotor blades.
The element that occurs in the above accompanying drawing of a width of cloth will be given each identical Reference numeral wherein.
The specific embodiment
Fig. 1 shows the rotor 1 of first modification, and this rotor 1 is provided with two blades 10,20, and each blade has the spar 40 of himself, and this spar is suitable for standing to reverse.Each spar radially extends, and the one end is inserted in the shell 11,21 of relevant blade 10,20, and the other end is outstanding from shell 11,21.
The outshot of spar 40 then is fixed to the securing device 30 of actuating device 2, specifically is fixed to axle drive shaft 33.Or rather, actuating device comprises base plate 31 and top board 32, and the spar 40 of each blade 10,20 is fixed between base plate 31 and the top board 32 by the main clamp structure 3 of screw bolt-type.
In an example shown, base plate 31 is by usual means, may be fixed to the skirt section of axle drive shaft 33 by being fitted to each other, and top board is with the plate of bolt to axle drive shaft 33.
Illustrate that therefore the rotor that illustrates is rigid rotor.
As a modification, top board 32 can be fixed to base plate, with base plate hinged to axle drive shaft 33, as
Such in the anti-torque rotor of helicopter.Therefore rotor is " lifting rotor ".
Similarly, base plate and top board can be connected to the ball and cocket joint that surrounds axle drive shaft 33.
In this case, when axle drive shaft 33 centered on rotation axis AX rotation by driving engine, axle drive shaft 33 caused blade 10 rotations via securing device 30 and spar 40.
In addition, rotor 1 has at least one retainer 50 for each blade, and specifically in modification shown in Figure 1, each blade has a retainer 50.50 of each retainers blade of will being correlated with is connected to the securing device 30 of the actuating device of rotor 1.
Referring to Fig. 2, retainer 50 is the blade bundles that comprise a folded strip 53, and the thickness of each strip 53 is about 0.1 millimeter.
These strips are made by metal or composite material, and the reinforcing phase of composite material is aromatic poly amide, carbon or glass fibre, and matrix is themoplasticity or thermosetting resin.
In addition, retainer 50 extends to second end 52 from first end 51, and two ends are pierced through by the corresponding first retaining hole O1 and the second retaining hole O2.When retainer is idle, promptly attempt to stretch or when compressing its stress, the first retaining hole O1 and the second retaining hole O2 separate the first spacing E1 without undergoing any when retainer.
Specifically referring to Fig. 3, retainer is fixed to the securing device 30 and the blade 10 of rotor respectively via first end 51 and second end 52.
Therefore, the first retaining hole O1 joins with at least one main aperture OP association of securing device at first end 51.Or rather, the first retaining hole O1 joins with base plate 31 that is formed on securing device 30 and the association of the main aperture OP in the top board 32 at first end 51.
Therefore, the main clamp structure 3 of screw bolt-type passes the first retaining hole O1 successively, is formed on main aperture OP in the top board 32 of securing device 30, the attachment apertures 41 of spar 40, is formed on the main aperture OP in the base plate 31 of securing device 30.
Therefore first end 51 of retainer 50 is fixed to the securing device 30 of axle drive shaft 33.
Similarly, the second retaining hole O2 assists at the inferior hole OS of second end 52 and blade and joins, and specifically joins with the retaining hole OS association that is arranged in the spar 40 via the inferior clamp structure 4 of for example bolt type.
Therefore, second end 52 of retainer 50 is fixed to blade 10, is fixed to its spar 40 or rather.
In addition, the inferior hole OS of main aperture OP and blade separates the second spacing E2, and inferior hole OS is associated with main aperture OP by retainer 50.
Because the second spacing E2 is less than the first spacing E1, so retainer is applied prestress and is in compressive state.Be arranged on the rotor, be applied with prestressed retainer and have amount of deflection FL, this amount of deflection FL is less than or equal to 15% of first spacing.
If spar 40 ruptures near main clamp structure 3 places or splits, then blade 10 will radially slide along the centnifugal force direction, as shown by arrow F.
When the second spacing E2 reached the value of the first spacing E1, retainer kept blade 10.
The first spacing E1 of retainer is specific as follows to be determined:
The overbalance that restriction blade 10 slides and produced;
The entity integrity that keeps rotor 1; And
Generation can be by aviator or the extent of vibration that is detected by the system that monitors the FLIGHT VEHICLE VIBRATION degree.
Although may be astonishing, advantageously allow extent of vibration to increase.By preventing infringement like this, just can warn the aviator that fault is arranged.
Can notify the maintainer then.The visual inspection rotor just is enough to see that retainer no longer is applied with prestress, this means that blade slides in mode improperly.
Referring to Fig. 4, can two retainers be set for each blade 10,20, rather than a retainer.
Therefore, first retaining hole 61 of first retainer 61 of first blade 10 ' join with at least one first main aperture OP1 association of the securing device 30 of axle drive shaft 33 via main clamp structure 3 is for example joined with two first main aperture associations of base plate 31 and top board 32.
In addition, second retaining hole 61 of first retainer 61 of first blade 10 " is assisted with inferior hole OS1 of first blade 10 and to be joined.
Similarly, first retaining hole 62 of first retainer 62 of first blade 10 ' join with at least one second main aperture OP2 association of the securing device 30 of axle drive shaft 33 via main clamp structure 3 is for example joined with two second main aperture associations of base plate 31 and top board 32.
Should be able to observe, the first main aperture OP1 and the second main aperture OP2 are equally spaced around the rotation axis AX of rotor 1, and rotation axis AX is positioned in the middle of the first main aperture OP1 and the second main aperture OP2.
In addition, second retaining hole 62 of second retainer 62 of first blade 10 " is assisted with inferior hole OS1 of first blade 10 and to be joined.
Advantageously, second retaining hole 61 of first retainer 61 of first blade and second retainer 62 ", 62 " with join with a hole OS1 association.
For being provided with two retainers, each blade is used for guaranteeing the tram of blade by limiting its aerodynamic drag.
Equally, second blade 20 has first retainer 63 and second retainer 64.
In these cases:
First retaining hole 61 of first retainer 61 of first blade 10 ' and first retaining hole 63 of first retainer 63 of second blade 20 ' with the same first main aperture OP1 of actuating device 2 is assisted and is joined;
Second retaining hole 62 of second retainer 62 of first blade 10 ' and second retaining hole 64 of second retainer 64 of second blade 20 ' with the same second main aperture OP2 of actuating device 2 is assisted and is joined;
The same hole OS1 association of first retainer 61 of first blade 10 and second retaining hole 61 of second retainer 62 ", 62 " and described first blade 10 joins; And
The same hole OS2 association of first retainer 63 of second blade 20 and second retaining hole 63 of second retainer 64 ", 64 " and described second blade 20 joins.
Fig. 5,6 and 7 shows the rotor 1 that is in the present invention's one preferable second modification.
Referring to Fig. 5 and 6, connect spar 100 and have first end 102 and the second end 103, first end 102 and the second end 103 are separately fixed in second shell 22 of first shell 12 of first blade 10 and second blade 20.First end 102 and the second end 103 are suitable for standing to reverse, thereby avoid hindering the motion of each shell around himself displacement axis.
In addition, the perforation spar 100 of a pair of blade 10,20 has the rigidity centre portion 101 between first end 102 and the second end 103.
The shell 12,22 of each blade 10,20 is provided with the flange 13,23 that is fixed to pitch hinge 14,24.
In addition, corresponding elastic connection structure is arranged on each flange and connects between the spar 100.Each elastic connection structure comprises elastomeric support, and this elastomeric support is provided with external intensity member 15,25, elastomeric elements 16,26, and internal intensity member 17,27.
In these cases, first elastomeric support is arranged between flange and the spar bottom surface, and the first external intensity member of this first supporting member is screwed on the flange, and the first internal intensity member of first supporting member is screwed on the described bottom surface.Similarly, second elastomeric support is arranged on flange 13,23 and connects between the end face FSUP of spar 100, the second external intensity member 15,25 of this second supporting member is screwed on the flange 13,23, and the second internal intensity member 17,27 of second supporting member is screwed on the described end face FSUP.
In addition, the centre portion 101 of the public perforation spar of a pair of blade 10,20 remains on by main clamp structure 3 between the base plate 31 and top board 32 of securing device 30 of axle drive shaft 33.For example, four bolts are fixed to base plate 31 and top board 32 with centre portion 101.
Should be able to observe, the counterpoise grounding of metal lining is arranged between each flange 13,23 and the securing device.
According to the present invention, at least one is applied with prestressed retainer and is fixed between the securing device of perforation spar 100 of blade and fastening described blade.
Advantageously, first end of each retainer is fixed to the securing device 30 that connects spar 100, and second end of retainer is fixed to the centre portion 101 that connects spar 100.
Because the second internal intensity member 17,27 of the elastic connection structure of blade 10,20 is outstanding from the shell 12,22 of described blade 10,20,, second end of retainer connects spar 100 so alternatively being fixed to via described outstanding internal intensity member 27.
Referring to Fig. 5, use the single retainer 81,82 of type shown in Figure 2 for each blade.
Therefore, at least one main aperture OP association of first retaining hole O1 of retainer first end and securing device joins.The main clamp structure 3 of screw bolt-type for example passes the first retaining hole O1 successively, be formed on main aperture OP in the top board 32 of securing device 30, the attachment apertures 41 of spar 100, be formed on the main aperture OP in the base plate 31 of securing device 30.
Therefore first end of retainer is fixed to the securing device 30 of axle drive shaft 33.
Similarly, the inferior hole OS of second retaining hole O2 of retainer second end and blade assists and joins, and promptly joins with the retaining hole OS association that is arranged in the centre portion 101 that connects spar 100 via the inferior clamp structure 4 of for example bolt type.
Therefore, second end 52 of retainer 50 is fixed to blade 10, and the internal intensity member via its elastic connection structure is fixed to the centre portion 101 that it connects spar 100 or rather.
In addition, the inferior hole OS of main aperture OP and blade separates second spacing, and inferior hole OS is associated with main aperture OP by retainer 50.
Because second spacing is less than first spacing, so retainer is applied prestress and is in compressive state.
Referring to Fig. 6 and 7, each blade advantageously has two retainers.
Therefore, first retaining hole 61 of first retainer 61 of first blade 10 ' and first retaining hole 63 of first retainer 63 of second blade 20 ' with the same first main aperture OP1 of actuating device 2 is assisted and is joined.Similarly, second retaining hole 62 of second retainer 62 of first blade 10 ' and second retaining hole 64 of second retainer 64 of second blade 20 ' with the same second main aperture OP2 of actuating device 2 is assisted and is joined.
In addition, the same hole OS1 association of first retainer 61 of first blade 10 and second retaining hole 61 of second retainer 62 ", 62 " and described first blade 10 joins, and the same hole OS2 association of first retainer 63 of second blade 20 and second retaining hole 63 of second retainer 64 ", 64 " and described second blade 20 joins.
Certainly, the present invention can have many modification aspect its embodiment.Although described some embodiment, understand easily, provide exhaustively might can not imagine by embodiment.Certainly can imagine with equivalent device and replace any in the described device and do not exceed scope of the present invention.
Claims (9)
1. a rotor (1), described rotor is provided with at least one blade (10 that is fixed to actuating device (2), 20), described rotor (1) is characterised in that, described rotor comprises at least one retainer (50), described retainer is in case installation is in compressive state with regard to being applied with prestress, thereby with described blade (10,20) be connected to described actuating device (2), described retainer (50) is provided with respectively by first retaining hole and the second retaining hole (O1, O2) first end that pierces through and second end (51,52), when described retainer does not have application of stress, described first retaining hole and second retaining hole separate first spacing (E1), described first retaining hole and the second retaining hole (O1, O2) be suitable for respectively at least one main aperture (OP) and described blade (10 with the securing device (30) of described actuating device (2), 20) inferior hole (OS) association joins, when described blade (10, when 20) being fixed to described actuating device (2), described first retaining hole and second retaining hole separate second spacing (E2), and described first spacing (E1) is greater than described second spacing (E2).
2. rotor as claimed in claim 1 is characterized in that, described retainer (50) is the band bundle that comprises a folded strip (53).
3. rotor as claimed in claim 1 is characterized in that, the difference between described first spacing (E1) and described second spacing (E2) is less than or equal to 5% of described first spacing (E1).
4. rotor as claimed in claim 1 is characterized in that, the described prestressed retainer (50) that is applied with presents an amount of deflection (FL), and described amount of deflection (FL) is less than or equal to 15% of described first spacing (E1).
5. rotor as claimed in claim 1 is characterized in that, described retainer (50) is provided with respectively by first retaining hole and the second retaining hole (O1, O2) first end that pierces through and second end (51,52), described second end (52) is fixed to described blade (10,20) spar (40,100).
6. rotor as claimed in claim 1, it is characterized in that, described rotor (1) has first blade and second blade (10,20), each blade is provided with shell (12,22), described first blade and second blade (10,20) link together by public perforation spar (100), the centre portion (101) of described public perforation spar (100) is fixed to the securing device (30) of described actuating device (2), each retainer (61,62 of blade (10,20), 63,64,81,82) be fixed to described centre portion (101) and described securing device (30).
7. rotor as claimed in claim 1, it is characterized in that, described rotor is for each blade (10,20) comprise first retainer and the second retainer (61-62,63-64), described first retainer (61, first retaining hole 63) (61 ', 63 ') join with first main aperture (OP1) association of the securing device (30) of described actuating device (2), described second retainer (62,64) first retaining hole (62 ', 64 ') is joined described first retainer and the second retainer (61-62 with second main aperture (OP2) association of the securing device (30) of described actuating device (2), (61 " 62 " of second retaining hole 63-64), 63 " 64 ") (OS1, OS2) association joins with the same hole of described blade (10,20).
8. rotor as claimed in claim 7 is characterized in that, (OP1 OP2) is distributed in the both sides of the rotation axis (AX) of described actuating device (2) in equidistant mode for described first main aperture and second main aperture.
9. rotor as claimed in claim 7 is characterized in that, described rotor (1) comprises first blade and second blade (10,20) of alignment, and:
First retaining hole (63 ') of first retaining hole (61 ') of described first retainer (61) of described first blade (10) and described first retainer (63) of described second blade (20) is joined with same first main aperture (OP1) of described actuating device (2) association;
Second retaining hole (64 ') of second retaining hole (62 ') of described second retainer (62) of described first blade (10) and described second retainer (64) of described second blade (20) is joined with same second main aperture (OP2) of described actuating device (2) association;
Described first retainer of described first blade (10) and described second retaining hole of second retainer (61,62) (61 ", 62 ") are joined with a same hole (OS1) association of described first blade (10); And
Described first retainer of described second blade (20) and described second retaining hole of second retainer (63,64) (63 ", 64 ") are joined with a same hole (OS2) association of described second blade (20).
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR0903445A FR2948097B1 (en) | 2009-07-15 | 2009-07-15 | AIRCRAFT ROTOR PROVIDED WITH A MEANS FOR RETAINING BLADES |
| FR09/03445 | 2009-07-15 |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101954972A true CN101954972A (en) | 2011-01-26 |
| CN101954972B CN101954972B (en) | 2014-04-16 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201010234652.3A Active CN101954972B (en) | 2009-07-15 | 2010-07-13 | Rotor for aerocraft provided with blade retainer device |
Country Status (2)
| Country | Link |
|---|---|
| CN (1) | CN101954972B (en) |
| FR (1) | FR2948097B1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104229135A (en) * | 2013-06-24 | 2014-12-24 | 空客直升机德国有限公司 | Rotor system of a rotary wing aircraft |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104683759B (en) * | 2015-01-23 | 2017-12-05 | 中国计量学院 | Inner wall of stack corrosion condition wireless video monitoring apparatus and method for based on aircraft |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1756264A1 (en) * | 1967-05-22 | 1970-03-19 | Sud Aviat Soc Nat De Const Aer | Screw or rotor with variable angle of attack |
| US4373862A (en) * | 1981-10-26 | 1983-02-15 | United Technologies Corporation | Rotor blade shaft integrity monitoring system |
| DE3438557A1 (en) * | 1984-10-20 | 1986-04-24 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Torsionally elastic connecting element which can be loaded in tension |
| EP0493145A1 (en) * | 1990-12-27 | 1992-07-01 | AEROSPATIALE Société Nationale Industrielle | Rotor hub for a rotorcraft |
| US5542818A (en) * | 1994-05-04 | 1996-08-06 | Eurocopter France | Ducted Anti-torque rotor with floating blades |
| CN1774366A (en) * | 2003-04-08 | 2006-05-17 | 欧洲直升机德国有限责任公司 | Rotor and gyrocopter with said rotor |
-
2009
- 2009-07-15 FR FR0903445A patent/FR2948097B1/en not_active Expired - Fee Related
-
2010
- 2010-07-13 CN CN201010234652.3A patent/CN101954972B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1756264A1 (en) * | 1967-05-22 | 1970-03-19 | Sud Aviat Soc Nat De Const Aer | Screw or rotor with variable angle of attack |
| US4373862A (en) * | 1981-10-26 | 1983-02-15 | United Technologies Corporation | Rotor blade shaft integrity monitoring system |
| DE3438557A1 (en) * | 1984-10-20 | 1986-04-24 | Messerschmitt-Bölkow-Blohm GmbH, 8000 München | Torsionally elastic connecting element which can be loaded in tension |
| EP0493145A1 (en) * | 1990-12-27 | 1992-07-01 | AEROSPATIALE Société Nationale Industrielle | Rotor hub for a rotorcraft |
| US5542818A (en) * | 1994-05-04 | 1996-08-06 | Eurocopter France | Ducted Anti-torque rotor with floating blades |
| CN1774366A (en) * | 2003-04-08 | 2006-05-17 | 欧洲直升机德国有限责任公司 | Rotor and gyrocopter with said rotor |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104229135A (en) * | 2013-06-24 | 2014-12-24 | 空客直升机德国有限公司 | Rotor system of a rotary wing aircraft |
| CN104229135B (en) * | 2013-06-24 | 2016-08-31 | 空客直升机德国有限公司 | The rotor system of rotor craft |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101954972B (en) | 2014-04-16 |
| FR2948097A1 (en) | 2011-01-21 |
| FR2948097B1 (en) | 2014-11-21 |
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