CN102452480B - There is rotor and the production method thereof of all-in-one-piece tension torque transmitting element - Google Patents
There is rotor and the production method thereof of all-in-one-piece tension torque transmitting element Download PDFInfo
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- CN102452480B CN102452480B CN201010522380.7A CN201010522380A CN102452480B CN 102452480 B CN102452480 B CN 102452480B CN 201010522380 A CN201010522380 A CN 201010522380A CN 102452480 B CN102452480 B CN 102452480B
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Abstract
A kind of rotor with fiber reinforced composite design, this rotor comprises fibrage, in particular for the fibrage of the tail rotor of rotor craft, this rotor has rotor blade (1), tension torque transmitting element (3) and fibrage (42-47), this rotor blade (1) comprises blade top layer (40,50) and blade body (41-57), and this blade body comprises the effective profile of aerodynamics; This tension torque transmitting element (3) is connected to rotor, and is designed to one with rotor blade (1); These fibrages extend through tension torque transmitting element (3), and interlocking is in rotor blade (1), the improvement that this rotor has is: these fibrages (42-47) pass to blade body (41-57) from direct extension of tension torque transmitting element (3).In addition, a kind of method for the production of this rotor is described.
Description
Technical field
The present invention relates to a kind of rotor with fiber reinforced composite design, this rotor comprises fibrage, in particular for the fibrage of the tail rotor of rotor craft or autogyro.This rotor comprises rotor blade and tension torque transmitting element, this rotor blade has blade top layer and blade body, this blade body comprises the effective profile of aerodynamics, and this tension torque transmitting element is connected to this rotor blade, and is designed to one with rotor blade.Fibrage extends through tension torque transmitting element, and is included in rotor blade.The invention still further relates to the method for producing this rotor.
Background technology
Due to relevant to weight and cost, especially in aircraft construction, more and more attempt to utilize the parts carrying out producing with fiber reinforced composite design to substitute the element be made of metal.Due to their geometric configuration, thus these parts need to be suitable for this design.These parts are produced being placed with in fibrolaminar mould, these fibrages by synthesis fortified resin, under pressure and temperature effect force together.Have and have the so-called exhausting tail-rotor of the rotor of cover tail rotor, autogyro also can fiber reinforced composite design to produce.
Such as, DE69307856 discloses this rotor blade.This rotor blade comprises connecting device, and this connecting device is used for the hub of the driver element this rotor blade being attached to rotor.Rotor blade is configured to by outer rigid housing, and this outer rigid housing comprises aerodynamic profile, and this shell is along the whole length extension of the span of rotor, and extends by the tubulose blade base being connected to hub side.Described rotor blade also comprises durable bearer frame, and this framework at least in part lengthwise is contained in shell, and is connected to described shell.In addition, in the side being connected to hub, rotor blade ends at root, this root comprise blade at least one be rotatably connected bundle, wherein, this connection Shu Jiben extends along the longitudinal extension direction of shell, and can rotate on its longitudinal axis.Described connection bundle is also made up of fiber-reinforced material, and this fiber-reinforced material comprises following fiber substantially: these fibers extend along a direction, and is suppressed by the synthetic resin strengthened.This connection bundle is connected to this supporting frame, and extend in end regions through blade base at outer side, this end regions is designed to this connection bundle and rotor blade to be linked to hub.At end regions place, this connection bundle comprises strengthening head, the holding device of this strengthening head rest supporting hub.As an alternative, this is rotatably connected bundle except comprising end regions, can end at ring, can promote bolt for being connected to hub by this ring.Although the production of rotor blade, connection bundle especially in end regions seems simple, but, the rotor blade produced as the method, especially connect bundle and lack abrasion test and there is extremely short service life.Their burst was lost efficacy and not obvious, and was even not easily detected in inspection.Therefore, this rotor blade does not provide feasible solution.
Summary of the invention
Therefore, target of the present invention is: propose a kind of rotor blade, in particular for the rotor blade of exhausting tail-rotor rotor, although manufacture with fiber reinforced composite design, this rotor blade still has long service life and damage tolerance performance, has low maintainability and simple and easy as far as possible production.
In rotor described in the present invention, this target is that fibrage directly extends from tension torque transmitting element and passes to blade body.Therefore, the present invention avoids the rotor design of the independent bearer frame comprising stable shell and be connected to this shell.On the contrary, the present invention carries out the principle from supporting shell, thus makes independent bearer frame become unnecessary.Shell itself is enough stablized and is had enough rigidity, to absorb and all power be applied to it of removal.Substantially should comprise blade body from supporting shell, this blade body covered by thin blade top layer, and provides aerodynamics actv. shape for rotor blade.Blade body comprises fibrage, and these fibrages not only extend along whole blade body, and carries out transition or seamlessly carry out transition under without any the condition of interrupting, thus is combined in tension torque transmitting element straightly.Therefore, rotor blade comprises such fibrage, and these fibrages not only form blade body, and forms tension torque transmitting element.Like this, these fibrages can from the tip of rotor blade, to extend through tension torque transmitting element along the whole length of rotor blade, directly extend on the end relative with vane tip of tension torque transmitting element linkage section.By combination as the function of shell on the one hand and the function as bearer frame on the other hand, in single parts, namely in supporting blade body, the quantity of the quality and parts that can reduce rotor blade also reduces produces necessary production stage.In addition, no longer need to be provided as shell on the one hand and as the connection between bearer frame on the other hand, otherwise this connection needs are produced in independent production stage.Like this, get rid of possible error source, and reduce the production intensity relevant to rotor blade.
The load along the longitudinal direction of through fiber, because their directions along centnifugal force extend, therefore preferably load, centnifugal force mainly acts on when using rotor.Due to the aligning that this kind of fiber is corresponding with load, thus each fibrage has larger load-carrying capacity, thus needs less fibrage for realizing identical load-carrying capacity.This causes straight and saves space-efficient design, and in addition, this design makes the weight of rotor reduce.
According to the concrete geometric configuration in the profile region of rotor blade, give rotor with the so-called stagger angle relative to plane of rotation, described rotor in operation rotates in this plane of rotation.Stagger angle is pre-determined in order to aerodynamic reasons.Because rotor blade tilts with the stagger angle of maximum 20 ° in tail rotor, relative to its plane of rotation, thus each fibrage also rotates 20 ° at the most slightly.This rotation is quite little, to prevent from straining by cross directional stretch any stripping caused.In addition, Stability Analysis of Structures is to such degree: even peel off, and still can guarantee fibrolaminar load-carrying capacity.Specifically, because the fibrage of tension torque transmitting element not covered by other parts of such as control tube, thus can check the damage of rotor by simple visual inspection, especially check each fibrolaminar stripping.
According to a preferred embodiment of the present invention, these fibrages comprise the spar band be made up of unidirectional fiber material.These spar bands form each straight layer, and the fibre stream of these are straight layer extends along the direction of force flux, and the direction in other words along centnifugal force extends, and therefore these straight layers have the excellent load-carrying capacity along this direction.This specifically puts on tension torque transmitting element, and the Main Load of this tension torque transmitting element is caused by centnifugal force.The most important thing is, the design that tension torque transmitting element is made up of the unidirectional fiber material along load direction orientation means, more preferably and use these materials economically.This makes in parts, have minimum tension force, and rotor blade has long service life thus.This kind of simple structure comprises the risk reducing manufacturing errors, and makes rotor blade have the good reproducibility of same special quality.
According to another preferred embodiment of the present invention, spar band especially comprises rectangular cross section in the region of tension torque transmitting element.This makes especially tension torque transmitting element have simply and the design of economy, and this design maintains such promise: reduce error risk and have high quality thus.
According to another preferred embodiment of the present invention, spar band on the one hand for the formation of the aerodynamic force profile of blade body, and forms tension torque transmitting element on the other hand, if these spar bands are arranged to multilayer and are needed to be arranged to be staggered.Therefore, even if rotor blade and tension torque transmitting element have extremely different cross-sectional profile, these through fibrages still can be produced, and without the need to significant cost.This can reduce the cost producing rotor.
According to another preferred embodiment of the present invention, spar band has different width according to their height and positions in tension torque transmitting element.Those spar bands being arranged on the zone line of tension torque transmitting element are designed to: the spar band being positioned at outside or top and bottom place than those is wider.Like this, tension torque element obtains its characteristic lateral section, and this cross-sectional plane is rectangle in principle and slightly swells in its narrow side or bend.
As everyone knows, tension torque transmitting element comprises the straight fibrage of a branch of stratification.Except carrying out the tensile force of the centnifugal force of the rotor blade of spinning, tension torque transmitting element must absorb moment of torsion.Therefore, this tension torque transmitting element must be designed to flexible torsional to a certain extent.The setting of this size by cross-sectional plane realizes.Such as, the rectangular cross section of rule can carry out size setting according to height and width and height to width ratio, thus obtains corresponding torsional stiffness.Substituting as rectangular cross section, if need to have the otch along the extension of centnifugal force direction or hollow space, to affect torsional stiffness, can select the modification of cross-like cross-section, ellipse, hexagon or octagon or these shapes.Therefore, tension torque transmitting element also such as can comprise pillar, and these pillars are flat and the setting that is laminated to each other, or the squarish pillar be arranged side by side each other, and the intrinsic curve of these pillars forms flat rectangular cross section.Comprise and somely substantially to extend and the cross-sectional plane of spaced stratification spar band is particularly advantageous in torsional stiffness along the bearing of trend of rotor, and especially involved production.The stratification spar band of some interconnection forms thin layer together, forms tension torque transmitting element by some thin layers.Adjacent thin layer separates by separate layer, thus under the condition of the cross sectional dimensions be applicable to, the torsional stiffness desired by tension torque transmitting element obtains.Separate layer between adjoining platelet makes these thin layers separated from one another, thus in the situation reversed, at least reduces the transmission of the shear strain between thin layer.This still can make tension torque transmitting element have design closely.
According to another preferred embodiment of the present invention, separate layer can be located between spar band in the form of a film.In addition, these films can suitably be applied.These films prevent spar band from sticking to each other, and also make each thin layer separated from one another completely, thus the transmission of shear strain can not occur the edge surface faced by them.For this reason, such as, can use so-called
film is as separate layer.This thin film coated has
and be especially suitable for having sufficient resistivity and good serviceability is provided.
According to still another embodiment of the invention, can form groove between thin layer, these grooves are provided as the air gap of separate layer.Therefore, in this region, the side faced by these thin layers contacts no longer each other; But comprise air gap among each other.Like this, any transmission of the shear strain between each thin layer is in fact got rid of.In addition, the disappearance of single partitioned film provides such advantage: the production of tension torque transmitting element is more simplified and more economical.Should keep noticing, separate layer due to the impact of temperature and humidity can stand aging, so that become fragile and expand.In addition, under the effect of bending load and torsional load, these separate layers can due to fibrage scouring and wearing and tearing each other.The thin layer separated also is associated with following advantage: these thin layers can carry out damage inspection individually.
In this kind is arranged, the size of the distance between the height of groove or thin layer should be set to: even if be tending towards in bending situation, these thin layers can not touch one another.Groove between each thin layer size setting in or in the design of thickness of thin layer, the centnifugal force acted in rotor operating process has positive role.This is because centnifugal force makes these thin layers stretch, and therefore stops any of these thin layers to touch.
In order to the cost and complexity that make production torque delivery element are low, the least possible thin layer quantity should be kept.Releasing by calculating, utilizing the thin layer of four about 1.13mm thickness can provide sufficient intensity and torsional stiffness.
Prevent the manipulation error of torque delivery element in installation process from being the design height of groove and the another standard of thin layer.In other words, these thin layers and being dimensioned to lamellate tension torque transmitting element: tension torque transmitting element can not be manually overflexing until exceed the twist angle of allowing; The situation of damage is had when preventing these parts from can maintain installation.Calculating for the design of tension torque transmitting element indicates such thin layer: have the length of the thickness of about 1.3mm, about 75mm and the better width of about 12mm.
According to another preferred embodiment of the present invention, in the linkage section of the tension torque transmitting element on the one hand on rotor blade, and on the other hand on blade connects, additional woven fabric layers can arrange the height of grooving.On the one hand, these woven fabric layers strengthen these linkage sections, and like this, these linkage sections can the load of any importing of removal, and if words applicatory can removal load deviation, and any damage can not be continued.On the other hand, these additional woven fabric layers provide space between thin layer, and to form separation trough, thus ought from the side, the lamellar fibrage of shape can extend through tension torque transmitting element with complete plane with linear fashion.Therefore, the unidirectional fiber layers preferably load of these thin layers, and the deviation of any extension in-plane along them caused by centnifugal force can not be stood, thus described fibrage can use minimum material to bear maximum load.
From unidirectional fiber layers to the failure-free load transfer of additional woven fabric layers, occur by launching unidirectional fiber layers, additional woven fabric layers is embedded between these fibrages.Due in addition, unidirectional fiber layers and additional woven fabric layers all very thin, thus produce multiple contact surface and adhesive surface between, the layers.Because load can be distributed in comparatively large regions, thus guarantee the load transfer that can't harm, thus each independent contact area can not transship, and therefore not have the danger producing crack.Therefore, for connecting expansion that these layers carry out and interlocking makes connection and whole rotor can have the performance of damage tolerance and the service life of abundance.
According to another preferred embodiment of the present invention, additional woven fabric layers has following fiber alignment: be about +/-45 ° relative to the main bearing of trend of rotor or its longitudinal axis.The angular deviation that can not cause the fiber alignment of any damage can have the tolerance of +/-10 ° of scopes, thus load is guided to and is dispensed to adjacent thin layer.
According to another preferred embodiment of the present invention, form continuous transition at the transition position of the separation trough of linkage section.Its objective is, in BENDING PROCESS, especially outside in thin layer, prevent larger flexure stress from producing, this flexure stress can caused by the rigidity step between end segments and thin layer.Like this, this continuous transition continues to improve torsional stiffnesses in torque delivery element, thus prevents the load peaks in flexure stress and especially for the damage of outer thin layer.Therefore, additional woven fabric layers is arranged to: in the lateral plan of tension torque transmitting element, the thickness of the thin layer in transition phase increases continuously, until these separation troughs of filling completely, and these thin layers similarly ankylose to form homogeneous blocks, i.e. linkage section.In other words, these additional woven fabric layers are arranged to be laminated to each other from the top of thin layer, in a step-wise manner.In addition, described layer also can change on width, and such as first and the longest additional woven fabric layers can be the widest, the tissue layer next thereupon arranged narrows with highly increase.Like this, between thin layer and linkage section, subcontinuous transition can be obtained.
And consider the fibrage in the linkage section of hub side is more accurately arranged, we also introduce the content of this patent application to form the theme of the application especially also with reference to European patent application EP 09400020.5.
According to another preferred embodiment of the present invention, the linkage section of rotor blade comprises connection eyelet dorsad, and rotor blade is by bolt, be attached to actuating device by this connection eyelet, and this bolt is basically perpendicular to the extension plane of rotor blade and extends.Therefore, in the situation simplified most, connect eyelet and can be designed to the round hole in linkage section.This connection eyelet penetrates each fibrage, and also perpendicular to these fibrolaminar extension planes.In operation, connect eyelet and form hole surface connection, this hole surface connects almost exclusively in fibrolaminar extension plane, and the fibrage of load linkage section and the fibrage of tension torque transmitting element, therefore this kind of load is best for these fibers.When carrying out power guiding by bolt, be connected in these fibrages by the hole surface connecting eyelet and can not produce power deviation, this power deviation can make fibrage peel off in linkage section.In addition, carrying fiber layer extends when almost not having tension force, between connection eyelet and rotor blade.This can also use minimum material, obtains maximum load-carrying capacity.This is of value to the economical production of rotor, long service life, little outside dimension and light weight.
Such parts are represented: these parts are not subject to the interference of fiber end or fiber abutment joint, and bolt force are preferably guided in rotor for the linkage section connecting eyelet that has by hole surface directed force.Complete interference-free parts have especially good load-carrying capacity, and can manufacture with less fault.Compared with the eyelet be located in traditional ring design, connect eyelet, at identical design height place, there is higher load-carrying capacity.The ratio of rim space and diameter should in the scope of 1.3 and 2.0, to guarantee preferably strength character.
In addition, compared with the prior art state made at ring in the situation of fibrage 90-degree bent, form connect eyelet fibre length substantially straightly, plane earth and in no case extending deviously.Therefore, the present invention points out such rotor design: do not consider the structure expedients connecting eyelet, this rotor design is without the need to any unfavorable bending fibrage.According to prior art state, fibrolaminar bending needs are very accurately located for each fibrage, and this location is expensive and be easy to make mistakes thus.In contrast, the design of load thin layer is significantly comparatively simple and more insensitive for production error.
In addition, according to prior art state, bend and need specific design length to form " ring of standing ".In contrast, it is bending unnecessary that " flat sleeping ring " makes, thus make rotor have especially compact size.In addition, " flat sleeping ring " under identical load ability condition makes linkage section have less design height, thus should " flat sleeping ring " can more easily be combined in exhausting tail-rotor.
According to another preferred embodiment of the present invention, connect eyelet and be only fully formed in the state of processed tension torque transmitting element.Such as, can mill out or get out connection eyelet, this connection eyelet can be produced afterwards in any case.This makes the hole surface of the conventional circular of connection eyelet have very straight and uniform edge designs, the production after can detecting undoubtedly thus.Due to interference-free edge designs, thus linkage section can be loaded to the edge connecting eyelet completely, thus preferably uses cross-sectional plane and make the size of linkage section minimum.Especially wish preferably to use cross-sectional plane on connection eyelet, this is because in exhausting tail-rotor, some linkage sections need to be disposed side by side on each other in little space, and wherein, the space needed for described linkage section should not have adverse effect to the size in exhausting tail-rotor.
Select about other of the torque delivery element of design tension torque transmitting element, linkage section and connection eyelet, we, with reference to the application with application 2008E00532, obviously also quote the content related to this of this application, to form theme of the present invention.
Another preferred embodiment of the present invention relates to following rotor: have the connecting section of rotor, independent control sleeve pipe or independent control tube and linkage section, the connecting section of rotor is between rotor blade and tension torque transmitting element, independent control sleeve pipe or independent control tube are used for regulating rotor along the longitudinal axis of rotor, and linkage section is used for control tube to be connected to rotor blade.According to the present invention, the connecting section of rotor blade and the linkage section of control tube comprise corresponding shape of cross section, for effectively locking the power transmission of the control effort between rotor blade and control tube.Independent control tube is attached to rotor by the linkage section and tension torque transmitting element with connection eyelet, and the control tube in connecting section is linked to rotor.By the corresponding shape of cross section in connecting section and connected section, under harmless condition, control effort can be guided to rotor, and without the need to using another Connection Element, this Connection Element such as extends past the bolt of the longitudinal axis of rotor.
It is preferred that the shape of cross section of connecting section and connected section not only make rotor peripherally line, be resisted against control tube in a linear fashion, and preferably with contact surface against.Can with simple and the mode of economy affects the power transmission between control tube and rotor utilizing this kind of simple measures to carry out, this is except the risk of saving parts and reducing assembly error, also with reduce expenses relevant with expendable weight.
Make the tension torque transmitting element extended along plane of rotation just in time rotate this stagger angle for meeting needed for aerodynamics, rotor relative to the stagger angle of plane of rotation, or stand to be just in time the twisting motion of this stagger angle.In any case, be in the situation of one-piece design at rotor blade and tension torque transmitting element, such region must be provided with: those fibrages forming two parts carry out twisting motion in this region.From the viewpoint considering load, these fibrolaminar twisting motions have secondary importance, until following degree: on the one hand, this twisting motion only covers the scope of 10 ° to 20 °, and on the other hand, this twisting motion extends beyond certain minor increment.In an experiment, pointed out that the length of 20 to 30mm is preferably.Usually, the twisting motion in this length does not cause the stripping caused by lateral pull, thus, still the extension of fibrage in torsion region can be considered to basic plane.
Such as, transitional region can be arranged in rotor blade, at the transition phase of the linkage section of tension torque transmitting element.According to another preferred embodiment of the present invention, the region of twisting motion be arranged in tension torque transmitting element, towards rotor blade or therebetween linkage section.By getting up near the linkage section of blade and the areas combine of twisting motion, due to the region without the need to providing independent twisting motion, thus rotor can be designed to shorter.Therefore, tail rotor can entirety less, thus cost can be saved significantly.
According to another preferred embodiment of the present invention, the twisting motion between rotor blade and tension torque transmitting element be arranged on rotor, with control sleeve pipe the interactional connecting section of connected section in.Like this, find or identified the region with sufficient length, thus fibrage excessive deflection in the region of twisting motion can not have been made.Because aerodynamics also imagines critical importance in the situation of the rotor blade of tail rotor, thus from fluid dynamic viewpoint, the connecting section directly not standing air-flow of rotor is more better than the transitional region directly standing air-flow.Usually, the region of twisting motion makes cross-sectional plane increase, such as transitional region, the region of this twisting motion in portion's section of standing air-flow can make resistance increase.In contrast, in connecting section, twisting motion by the control tube be located in exhausting tail-rotor close, on aerodynamics, therefore keep invalid.
In European Patent Application No. EP09400019.7, provide other embodiments, especially corresponding control tube, also introduces the content of this application especially to form the theme of the application.
Target described is in the description realized by a kind of like this method of producing rotor further, and this rotor has rotor blade and has the all-in-one-piece tension torque transmitting element being connected eyelet, and is made up of fiber-reinforced material, and the method comprises the following steps:
If a) need to rabbet interlayer, at least part of ready fibrage is placed in a mold, with producing shaped blank;
B) by pressurizeing and be heating and curing this moulded blank;
C) at least in some regions, milling is carried out for the moulded blank of having solidified of having deviate from from mould, thus give profile final with it.
Therefore, method of the present invention takes uncommon approach, wherein, there is fiber strengthen the parts of composite design and not exclusively to produce with its final profile, but at least in some regions, produce while there is remarkable surplus, and only its solid state just receive its final size.According to the program, only the rotor blade of rotor of the present invention is produced with its final size, and all-in-one-piece tension torque transmitting element is made longer and wider than its final size.This is because in the curing process, in the region of the moulded blank of tension torque transmitting element, the displacement caused by fibrage motion can occur, this displacement can make to produce quality loss in the moulded blank region of thin layer.Therefore, the Internal periphery of the mould being used for tension torque transmitting element can be selected to: wider than its net shape and longer.Only after being deviate from from mould by rotor, the outline for tension torque transmitting element carries out milling, thus gives its net shape.So, specifically, owing to subsequently any moulded blank region in process of production with interference effect being eliminated, thus obtain and there is suitable special quality tension torque transmitting element.Therefore, this kind of production method makes tension torque transmitting element have minimum reasonable size, thus uses material best.In addition, after curing molding blank, such as, also can carry out modification to the width of torque delivery element, like this, if the need arises, the torsional stiffness of torque delivery element can be changed.If make each fibrage get out surplus, then also can simplify their cutting technique, thus can preparation cost be reduced.
The fibrage (so-called prepreg) of dried fibres and pre-impregnated resin is all suitable for preparing fibrage.In order to improve the stability of moulded blank and rotor, especially stand in each section of load at rotor, in the region of the transition phase such as in the region of linkage section or between tension torque transmitting element and rotor blade, interlayer or filling bed can be rabbeted.These strengthening layers can comprise following size: or corresponding from those remaining fibrages or different and region only with to be strengthened is corresponding with those remaining fibrages.In addition, strengthening layer can have the fiber alignment identical with these fibrages, or they can have the fiber alignment different from these fibrages.Such as, described strengthening layer can extend with the angle of +/-45 ° to +/-90 °, thus improves the strength and stiffness of each section to be fortified.
According to preferred embodiment of the present invention, subsequently in steps d) in, get out or mill out the connection eyelet in tension torque transmitting element along the direction perpendicular to the extension plane of tension torque transmitting element.The thin layer connecting eyelet and surrounding is dimensioned to hole surface, and stands load.Owing to producing this connection eyelet afterwards, thus thin layer directly passes to this hole surface uninterruptedly.Also disclosing the production to connecting after eyelet, wherein, owing to holing to hole surface afterwards, thus not disturbing fibrage completely, these fibrages are laminated to each other compact placement.Therefore, due to without the need to there is lower load-carrying capacity and the fibrage be disturbed calculating surplus to any, thus tension torque transmitting element can be produced into the possible minimum size of tool.
Accompanying drawing explanation
With reference to accompanying drawing, explain principle of the present invention in more detail in a schematic way.The following drawings is shown:
Fig. 1 illustrates the birds-eye view of rotor;
Fig. 2 illustrates the cutaway view of rotor shown in Fig. 1;
Fig. 3 illustrates the partial longitudinal sectional figure of rotor;
Fig. 4 illustrates the model relevant to the fibrage for the production of rotor;
Fig. 5 illustrates the cutaway view of the blade sections of rotor;
Fig. 6 illustrates the birds-eye view having and fibrolaminar rotor is shown;
Fig. 7 illustrates the lateral plan of rotor;
Fig. 8 illustrates in rotor manufacturing process, the birds-eye view of rotor;
Fig. 9 illustrates the another birds-eye view of rotor;
Figure 10 illustrates the connection eyelet of the tension torque transmitting element with three thin layers;
Figure 11 illustrates the lateral plan of the tension torque transmitting element with four thin layers;
Figure 12 illustrates the partial view of rotor and control tube;
Figure 13 illustrates the rotor with manned control tube;
Figure 14 illustrates the sectional side elevation of Figure 13;
Figure 15 illustrates the part sectional view of Figure 14;
Figure 16 illustrates the part sectional view connecting eyelet; And
Figure 17 illustrates the device for the production of rotor.
Detailed description of the invention
Substantially rotor blade 1 and tension torque transmitting element 3 is comprised according to the rotor of Fig. 1.Tension torque transmitting element 3 makes rotor blade 1 be connected to the hub of actuating device (not shown).Rotor blade 1 and tension torque transmitting element 3 are with one-piece design, and wherein in hub side, blade transition section 7 connects after the blade sections 5 of rotor blade 1, also has moment of torsion pass segment 9 in hub side.Start from moment of torsion pass segment 9, tension torque transmitting element 3 is connected to blade-side linkage section 11, and this blade-side linkage section 11 specifically presents tapering transition significantly from birds-eye view, until significantly thinner rectangle torque delivery element 13.Torque delivery element 13 expands in hub side, and to form bar-shaped linkage section 15, this bar-shaped linkage section 15 holds circular connection eyelet 17, and this circle connects eyelet and extends vertically through described linkage section 15.Dotted line illustrates outline line 19, and this outline line 19 illustrates tension torque transmitting element 3 manufacture profile in the fabrication process.
According to the lateral plan of Fig. 3, torque delivery element 13 comprises four independent banded thin layers 21, and these thin layers extend parallel to each other and stacking, and these thin layers enclose the groove 23 with same nature.This torque delivery element 13 transits to the linkage section 15 of hub side with almost identical design height.In contrast, on that be arranged on blade side, relative linkage section 11, described torque delivery element 13 is widened, thus the linkage section 11 of blade side has taper as shown in the side view of figure 3.Described linkage section 11 is similar to diad or the basic axially symmetry of symmetrical plane A with relative linkage section 15, and in addition because thin layer 21 ends at wherein, thus linkage section 11 side direction fluting as may be appreciated in the cross-sectional view of figure 2.
As shown in Figure 5, blade sections 5 comprises the effective profile of aerodynamics on cross-sectional plane.Described profile is substantially elongated, and relative to diad or the basic axially symmetry of symmetrical plane B.Blade transition linkage section 7 (according to Fig. 1 and Fig. 7) is for determining the transition between the compact cross-sectional plane that the elongated profile of blade sections 5 and the moment of torsion of ellipse transmit linkage section 9.Because moment of torsion pass segment 9 is compacter significantly, in blade transition section 7, thus there is cross-sectional plane significantly change.
As shown in figure 12, rotor has the stagger angle of so-called about 16 °, and this stagger angle is the angle of its blade sections 5 (or its symmetrical plane B) relative to its plane of rotation (according to symmetrical plane A).Moment of torsion pass segment 9 one aspect is for mating the different extension plane of caused blade sections 5, and another aspect is for mating the different extension plane of tension torque transmitting element 3.In addition, moment of torsion pass segment 9 is also used as the contact surface of control tube 70 (according to Figure 12 to 15), is described in more detail below this control tube.
Have in the blade-side linkage section 11 of tapering greatly than moment of torsion pass segment 9 in design, between the moment of torsion pass segment 9 of ellipse and the tension torque transmitting element 3 of almost rectangle, carry out cross-section adaptation.Form the transition transitting to thin layer 21 for described section 11, these thin layers form torque delivery element 13, and have the cross-sectional plane of basic rectangle, and their elongated, belt-shaped shape leads to the linkage section 15 of hub side.
The form that rotor according to the present invention designs with fiber reinforced composite is produced.The linkage section 15 that single fibrage (according to Fig. 6) wherein comprises partly loose boss side extend through tension torque transmitting element 3, through moment of torsion pass segment 9, blade transition section 7, by blade sections 5 and until its vane tip 6.Owing to having extremely different shape of cross sections, especially between blade sections 5 and the linkage section 15 of hub side, thus also the fibrage of not all extends completely through whole rotor.But those fibrages forming thin layer 21 extend through whole rotor until the vane tip 6 of shown rotor from the linkage section 15 of hub side.They form the keystone configuration of rotor.
Fig. 4 illustrates the fibrolaminar constituent for the formation of rotor.Fibrage 40 to 48 leftward shown in side is arranged to be laminated to each other in couples, wherein they be associated with leading edge 25 in the future (with reference to Fig. 5) of rotor blade 1 in the face of side 401,411,421 etc., and their edge 402,412,422,432 etc. away form one another is correspondingly associated with the trailing edge 27 of rotor blade 1.These fibrages are arranged in rotor according to their position.From left-hand side, rectangular section a represents the manufacture profile 19 (Fig. 1 and 6) of tension torque transmitting element 3 together with b.Portion section b forms the part of the linkage section 11 by becoming blade side.The linkage section 15 of hub side does not illustrate separately in the diagram.Moment of torsion pass segment 9 is connected to tension torque transmitting element 3, and this moment of torsion pass segment 9 is corresponding with portion section c.Blade transition section 7 formed by the portion section d of fibrage 40 to 48.Finally, portion's section 5 of rotor formed with their portion section e and additional fibrage 50 and 51 by fibrage 40 to 48.
Remaining fibrage, i.e. fibrage 52 to 57, fibrage 60 to 62 and filling bed 63 to 69 are rabbeted between fibrage 40 to 57, and fibrage 52 to 57, fibrage 60 to 62 link together in the mode of pectination.
Fibrage 42 to 47 represents such fibrage, and these fibrages extend through whole rotor until the vane tip 6 of rotor from the linkage section 15 of the hub side of rotor.These fibrages comprise unidirectional fiber material, and this kind of unidirectional fiber material extends along the longitudinal extension direction of fibrage 42 to 47.At the horizontal direction of these fibre stream, these fibers chemically or by sewing up mechanically keep together.
Although fibrage 40,41 and 48 also comprises unidirectional fiber material, but they do not extend through whole rotor.Fibrage 50 to 57 and the fibrage shown in its right-hand side 63 to 69 (also can refer to Fig. 8) comprise multiaxis lamination coating, the machine direction of this kind of multiaxis lamination coating extends in the mode each other in right angle, but is not therefore parallel to or is orthogonal to their edge 502,512.Therefore, as shown in the figure, fibrage 50 to 57 rotates 45 ° relative to their end positions in rotor, and fibrage 60 to 62 is relative to they end position half-twists in rotor.These fibrages are mainly placed or are rabbeted between fibrage 40 to 48, thus extend between every two fibrages of at least one fibrage in the fibrage 40 to 48 with unidirectional fibre orientation, these fibrolaminar fibers are arranged to become the angle of +/-45 ° or 90 ° relative to unidirectional fibre.Fiber bag is made in this way, and therefore rotor also can obtain enough stability at horizontal direction.
Therefore, the portion section e of fibrage 40 to 48 forms the blade sections 5 of rotor blade 1.Corresponding with the position in future of the fibrage 40,41 in the profile of rotor etc., inner side 401,411,421 etc. facing each other almost extends through in portion section e with straight line.In contrast, the sidepiece 422,432,442 etc. be associated with the trailing edge 27 in future of rotor cuts, thus leave space for the foamed core 39 (with reference to Fig. 5) in rotor inside.Because the height of the profile of blade sections 5 reduces along the direction of its vane tip 6, thus fibrage 47,48 does not thoroughly extend and passes to vane tip 6.
Fibrage 40 forms blade top layer together with multiaxis fibrage 50, and this blade top layer encloses the whole profile of rotor blade 1.But they do not extend through whole rotor, therefore in rotor wing rotation process, they do not absorb any centnifugal force.Contrary with above-mentioned fibrage, through layer 42 to 47 participates in load and absorbs.These through layers are arranged to be laminated to each other to three layers with two-layer, and stable blade body is formed together with such as rabbeting the interlayer of fibrage 52 to 57 and filling bed 63 to 69 and so on, this blade body can not only guarantee the stability of profile forms, and can bear the load transfer of the longitudinal direction along rotor.Therefore they realize following functions as blade body: not only have stable shell, and have supporting frame, and this supporting frame has early stage rotor blade and constructs the load-carrying capacity had.
Also be the linkage section 11 that the fibrage 52 to 57 (also can refer to Fig. 6) of multilayer interlocking mainly forms blade transition section 7, moment of torsion pass segment 9 and blade side.These fibrages enter in the linkage section 11 of blade side with their rounding pleurapophysis, and at this, they form the area of space of the groove 23 between thin layer 21, and this space is retained in moment of torsion and transmits in Connection Element 13.Contrary with upper, the tip region 522,532,542,552 of fibrage 52 to 55 participates in the formation of blade transition section 7, and also directly charges in blade sections 5, terminates in foamed core 39 place in this this tip region.
Pectinate fibers layer 60,61,62 in linkage section 15 is corresponding with the rounding section 521,532,541 and 551 (Fig. 4) in the linkage section 11 of blade side.In these fibrolaminar incision, they are spaced, and on the left hand edge of portion section a, the interlocking of these fibrages is between the portion section a of fibrage 42 to 47.These fibrages form the linkage section 15 of hub side with the height of the groove 23 of torque delivery element 13.
Finally, be attached in filling bed 63 to 69 compound blade transition section 7 and moment of torsion pass segment 9, in basic region on the outside of fibrage 42 to 48, in other words in the below on the blade top layer of fibrage 40 and 50.These filling beds make the cross-sectional plane of blade transition section 7 and moment of torsion pass segment 9 increase, and without the need to making through fibrage 42 to 48 excessive deflection.These fibrages can lose the ability that straight line extends through in this kind of deflection, and when standing centnifugal force, this can cause excessive cross directional stretch strain in addition, and this cross directional stretch strain can cause single fibrage to be peeled off.In order to still obtain desired blade transition section 7 and the design height of moment of torsion pass segment 9, having and outwards subtracting undersized filling bed 63 to 69 and place to be similar to pyramidal mode, and only covered by the fibrage 40,50 forming blade top layer.
Fig. 5 illustrates the outline profile view of the rotor in the region of blade sections 5.This profile comprises leading edge or guide lug 25 and relative trailing edge 27, and in having the flat droplet profile at top 29 and bottom 31.Profile all comprises step 33 on top 29 and bottom 31, from the leading edge 25 of blade sections 5 to this step 33, is applied with the corrosion protection apparatus (not shown) be such as made of metal from the teeth outwards.The profile of blade sections 5 from outside to inner side formed by fibrage 40, and this fibrage encapsulates whole profile as blade top layer.This fibrage 40 abuts the leading edge 25 of blade sections 5.Below this fibrage 40, be connected to fibrage 50, this fibrage 50 also abuts in leading edge 25.Although the machine direction of the first position of fibers 40 is designed to the longitudinal direction along rotor, but the fiber of fibrage 50 is to extend with the angle of this longitudinal direction into about 45 °.Ensuing fibrage comprises unidirectional aligned fibers material, and this lamination coating is close to the lamination coating (being multiaxis again) of fibrage 51.Ensuing is other fibrage, and for each rotor, these fibrages not only can be used alone also capable of being combined use.These fibrages encapsulating foamed core 39, this foamed core is arranged to the trailing edge 27 closer to blade sections 5, thus the center of gravity of the profile of blade sections 5 is arranged in and has heavier fibrolaminar front region.
Fig. 6 illustrates the birds-eye view of the position in each fibrage 40 to 55 in a schematic way.The some fibre layer of the such as fibrage 40 and 50 in these fibrages reaches the degree covered completely each other, thus they only comprise an outline line.Because these fibrages are not designed to axial symmetry on the other hand, but specifically their trailing edge 421,422,432 etc. has the otch of different depth, thus be foamed core 39 leaving space, in figure 6 by fibrage 41,42,43 etc. that some outline line identifiable design are associated.
Fibrage 40 to 55 forms the part in the linkage section 11 of blade sections 5, blade transition section 7, moment of torsion pass segment 9 and blade side.In addition, fibrage 42 to 47 forms whole tension torque pass segment 3, and the manufacture profile 19 in this position.In this position, alternately laminated with the comb patterns shown in Fig. 4 with fibrage 60 to 62 in principle, this comb patterns is described relative to blade sections 5.In figure 6, because the symmetrical plane B of blade sections 1 is arranged to be parallel to blade plane, thus tension torque transmitting element 3 is shown as and tilts with stagger angle.
Fig. 7 illustrates the lateral plan of the part in rotor, i.e. the moment of torsion pass segment 9 of tension torque transmitting element 3 and rotor blade 1 and blade transition section 7.In this view, the position of the trailing edge 27 of blade sections 5 also illustrates stagger angle, and this stagger angle is the angle of described blade sections 5 relative to tension torque transmitting element 3.Fig. 7 illustrates the design of the thin layer 21 of tension torque transmitting element 3 particularly, and these thin layers are arranged to be laminated to each other, and is arranged to parallel with three grooves 23 be located at therebetween.These thin layers are formed by fibrage 42 to 47, and these fibrages are unidirectional and extend through whole rotor, and wherein in various scenarios, three fibrages in these fibrages 42 to 47 form a thin layer 21.Described fibrage 42 to 47 is derived from the linkage section 15 of hub side, and when without any deflection, completely straight and plane earth extends through torque delivery element 13, enters the linkage section 11 of blade side.These fibrages only necessarily deflected carry out transitting to the plane of blade sections 5 in blade transition section 7 before in moment of torsion pass segment 9, and the plane of this blade sections 5 tilts relative to tension torque transmitting element 3 stagger angle of about 16 °.This deflection to occur and very little along length of about 25mm, thus under the tensile load caused by centnifugal force even in operation, this deflection can not cause any damaging shearing force, and this shearing force can cause fibrage to be peeled off.
The thin layer 21 spaced by groove 23 of torque delivery element 13 forms uniform fiber bag in the linkage section 15 of hub side and in the linkage section 11 of blade side, and this fiber bag is higher than the fiber bag in torque delivery element 13.This obtained by with the fibrage 60 to 62 shown in the comb patterns in Fig. 4 on the one hand, and the rounding section 521,531 of another aspect fibrage 52,53 etc. etc. are on the linkage section of blade side.This in figures 10 and 11 more in detail and be clearly shown that.
Fig. 8 illustrates the detail region of linkage section 11 of blade transition section 7, moment of torsion pass segment 9 and blade side.In this region, rotor obtains the design height along the direction starting from torque delivery element 13.In order to fibrage 42 to 47 being guided through moment of torsion pass segment from torque delivery element 13 under stagger angle effect, with minimum possible deflection, design height desired by simultaneously obtaining, specifically, the cross-sectional plane of moment of torsion pass segment is supplemented by packed layer 63 to 69.This can produce the cross-sectional plane with sufficient size, thus specifically can install control tube (according to Figure 13) in moment of torsion pass segment.
Fig. 9 illustrates the cutaway view of the rotor roughly in its plane of symmetry B.So foamed core 39 (according to Fig. 5) is appreciiable, this foamed core extends through whole blade sections 5, enters in the linkage section 11 of blade side except vane tip 6.Described foamed core 39 for compensating the uneven region in fibrage, and prevents excess pressure to be in process of production applied on fibrage, and also prevents any displacement.In addition, the centroidal axis of rotor can be affected by its size design, this centroidal axis advantageously as far as possible near-earth extend to the leading edge 25 of blade sections.
Figure 10 illustrates the linkage section 15 of hub side, has the block diagram of the tension torque transmitting element 3 of three thin layers 21.The lateral plan of Figure 11 also illustrates the tension torque transmitting element with four thin layers, and these thin layers 21 transit to compact linkage section 15 gradually.This is realized by interlocking fibrage 60,61,62, and these fibrages 60,61,62 are placed between fibrage 42,43 or 44,45 or 46,47 (with reference to Fig. 4).So birds-eye view illustrates delta-shaped region, this delta-shaped region avoid the element 13 separating thin layer 21 as having on the one hand and as compact linkage section 15 on the other hand between produce rigidity step.Therefore, the flexure stress in thin layer 21 outside can be reduced significantly, otherwise the load peak of this flexure stress can destroy thin layer 21.In addition, rabbeting fibrage 60,61,62 makes the torsional stiffness between torque delivery element 13 and linkage section 15 continue to increase.Relative linkage section 11 is constructed similarly by interlocking fibrage 52 to 57.
Figure 12 illustrates before being screwed into or being placed on rotor blade 1 by tension torque transmitting element 3, the partial view of rotor blade 1 and control tube 70.Described control tube 70 comprises matrix 71, and this matrix is tubulose in principle, and comprises in rotor blade side and have the larger-diameter plate-like bearing section of setting 72 and comprise the similar plate-like bearing section of setting 74 with small diameter in hub side.Therebetween, control stalk 76 is triangular in shape axially away from matrix 71.Control tube 70 comprises oval threaded openings 80 (hiding in fig. 12) in blade side, in installation process, rotor 1 is inserting in this threaded openings foremost with tension torque transmitting element 3.Be provided with circular open 81 relative to threaded openings 80, in operational state, tension torque transmitting element 3 is outstanding from this circular open at least partly.
Figure 13 and 14 illustrates projection and the cutaway view of installing condition.Therefore, control tube 70 covers the linkage section 11 of moment of torsion pass segment 9 and blade side completely, and covers the torque delivery element 13 of about half.In the region of the bearing section of setting 72 of control tube 70, the inside near threaded openings 80 of control tube 70 comprises oval inner cone 82 (detailed view according in Figure 15), and it is also on oval moment of torsion pass segment 9 that this inner cone 82 is engaged in.This causes and contacts on the whole area on the generate surface of moment of torsion pass segment 9, and control tube 70 is bonded in rotor blade 1 in this generate surface.Therefore, moment of torsion pass segment 9 represents the connecting section between rotor blade 1 and control tube 70 simultaneously.
In order to make control tube 70 correctly feel relieved on rotor blade 1, in binder-treatment process, insert in the circular open 81 relative with threaded openings 80 by installation voussoir 84, this installation voussoir is supported by tension torque transmitting element 3.
Figure 16 illustrates the detailed view of the linkage section 15 of hub side.Connect eyelet 17 and comprise protection ring 86, these protection rings are arranged on the both sides of linkage section 15.Their protection linkage sections 15, fibrage on the fork-shaped clamped position of tension torque transmitting element 3 in exhausting tail-rotor.These protection rings comprise the special textile fabric with low friction drag, and provide for the good protection by the wearing and tearing caused that rub.
Figure 17 illustrates mould 90 or so-called FEMI process units, this mould 90 or so-called FEMI process units made of aluminum and for the production of rotor blade 1.Described mould 90 comprises backform 92, bed die 94, two side direction end plates 96, some slotted metal thin plates 98 and two slip into device 100, and bed die 94 has the stripping surface 95 of bed die 94, and slotted metal thin plate 98 has the edge 99 on band inclined-plane.They form the commutative parts of backform 92 and bed die 94.On the trailing edge 27 of rotor blade 1, resin storage tank 102 extends along the longitudinal direction of bed die 94.Use thru-bolt 104 auxiliary as location, thus especially make backform 92 accurately can locate relative to bed die 94.
In order to successfully remove rotor blade 1 from mould, the stripping surface between backform 92 and bed die 94 always must be resisted against the widest outline line of rotor blade 1, and Figure 17 only illustrates the stripping surface 95 of bed die 94.Due to the moment of torsion pass segment 9 between tension torque transmitting element 3 and blade sections 5, or due to the stagger angle of rotor blade 1, thus stripping surface 95 extends in two planes tilted relative to each other with stagger angle.This is the reason that mould 90 has geometric complexity.
As shown in Figure 4, blade sections 5, blade transition section 7 and moment of torsion pass segment 9 produce the final profile to them.Therefore, the fibrage 40-51 in corresponding region c, d and e gets out the net shape making rotor blade 1.In contrast, tension torque transmitting element 3 only obtains net shape by milling after removing from mould.
In the production process of rotor blade 1, the excess resin especially from torque delivery element 13 can flow out from mould 90, and is blocked or make it cementing.After this, only mould could be opened with sizable power.Therefore, in bed die 94, blade future trailing edge 27 region in, make resin storage tank 102 by milling, this resin storage tank 102 is collected excess resin and is provided enough collection spaces for flowing out resin.
After stripping surface mold release being applied to backform 92 and bed die 94, start to lay ready fibrage 40-69.Laid processes in bed die 94 is followed and certain is laid plan, and these fibrolaminar order and quantity are specified in this plan of laying.Finally, foamed core 39 is placed in position, and applies the fibrage being covered in foamed core 39.In order to obtain the laminate structure of torque delivery element 13, slotted metal thin plate 98 is placed on formed thin layer 21 fibrage 42-47 between.Their size is corresponding with the groove 23 in those future.On end, end plate 96 is arranged on mould 90, thus rotor will be heated equably from each side.
Blade sections 5 comprises the corrosion protection apparatus of integral production in its leading edge 25.For this reason, after being placed in mould 90 by fibrage 40-69 and after being closed by mould 90, removing and slip into device 100, this slips into the occupying device that device is used as corrosion protection apparatus up to now.After this, corrosion protection apparatus is applied to still soft fibrage 40-69, and mould 90 is closed when slipping into device (not shown) with other.Consider the corrosion protection apparatus inserted, and replacement slips into device 100.After this, rotor is cured under pressure and heat effects.Like this, the production of the corrosion protection apparatus originally produced separately can be combined in the production of rotor economically.In addition, due to the integrated design of corrosion protection apparatus, thus blade sections 5 has high aerodynamic performance.
Due to the temperature traverse in solidification treating process, thus aluminium-making mould or mould 90 extend to a greater degree than the fiber-reinforced material of rotor.In heat process, mould 90 especially extends longitudinally direction in length, stands sizable change, and the fiber of the rotor that preferably stretches.So especially unidirectional fiber layers is aimed at along the longitudinal direction of rotor, and therefore aim at along the direction of centnifugal force, and similarly under tension in advance by stress.Rotor is cured in this state.In cooling process subsequently, because rotor keeps its length to a great extent, thus mould 90 compresses.After this, must remove end plate 96, otherwise pressure can be applied on rotor, this pressure can destroy this rotor.
Because the rotor described in detail is above only an illustrative examples, described illustrative examples usually can by those skilled in the art, carry out modification largely under the prerequisite not departing from the scope of the invention.Specifically, specific cutting is carried out for fibrage to carry out to be different from form described herein with these fibrolaminar orders that arrange.Similar, if the needs of reason of having living space or the needs of design reasons, the mechanical attachment on the linkage section of hub side can with some other form designs.In addition, the possibility that character pair measurer has plural number is not got rid of in the use of indefinite article "a" or "an".
reference numerals list
1 rotor blade
3 tension torque transmitting elements
5 blade sections
6 vane tipes
7 blade transition sections
9 moment of torsion pass segments
The linkage section of 11 blade sides
13 torque delivery element
The linkage section of 15 hub sides
17 connect eyelet
19 manufacture profile
21 thin layers
23 grooves
25 leading edges
27 trailing edges
29 tops
Bottom 31
33 steps
39 foam core
40 to 48 unidirectional fiber layers
401, the leading edges such as 411
402, the trailing edges such as 412
50 to 57 multiaxis fibrages
521, the rounding sections such as 531
522, the sharp-pointed sections such as 532
60 to 62 pectinate fibers layers
63 to 69 packed layers
70 control tubes
71 matrixes
The bearing section of setting of 72 blade sides
The bearing section of setting of 74 hub sides
76 control stalks
78 discharge orifices
80 threaded openings
81 openings
82 cones
84 install voussoir
86 protection rings
90 moulds
92 backforms
94 bed dies
95 stripping surfaces
96 end plates
98 slotted metal thin plates
99 edges
100 slip into device
102 resin storage tanks
104 thru-bolts
In a to e fibrage 40 to 48 each section
A, B diad or symmetrical plane
Claims (18)
1. have a rotor for fiber reinforced composite design, described rotor comprises fibrage, and described rotor has:
-rotor blade (1), described rotor blade comprises blade top layer (40,50) and blade body (41-57), and described blade body comprises the effective profile of aerodynamics;
-tension torque transmitting element (3), described tension torque transmitting element (3) is connected to described rotor blade (1), and is designed to one with described rotor blade (1);
-fibrage (42-47), described fibrage extends through described tension torque transmitting element (3), and is included in described rotor blade (1),
It is characterized in that, described fibrage (42-47) passes to described blade body (41-57), to form tension torque transmitting element (3) and described blade body (41-57) from direct extension of described tension torque transmitting element (3).
2. rotor as claimed in claim 1, it is characterized in that, described fibrage comprises spar band (42-47), and described spar band is made up of unidirectional fiber material.
3. rotor as claimed in claim 2, it is characterized in that, described spar band (42-47) has basic rectangular cross section.
4. rotor as claimed in claim 2, it is characterized in that, described spar band (42-47) has stratification and staggered layout, thus forms aerodynamic blade profile.
5. rotor as claimed in claim 4, is characterized in that, described spar band (42-47), according to they height and positions in described tension torque transmitting element (3), has different width.
6. as rotor in any one of the preceding claims wherein, it is characterized in that, described tension torque transmitting element (3) is formed by thin layer (21) and separate layer, described thin layer is made up of stacking spar band (42-47), and described separate layer is arranged between the adjoining platelet (21) in the region of torque delivery element (13).
7. rotor as claimed in claim 6, it is characterized in that, film is as the described separate layer between described spar band (42-47).
8. rotor as claimed in claim 6, it is characterized in that, in order to form groove (23) between described spar band (42-47), then in the region of described torque delivery element (13), described spar band (42-47) is arranged to have clearance envelope each other.
9. rotor as claimed in claim 8, described rotor has linkage section (15) in hub side, it is characterized in that, at the At The Height of described groove (23), the described linkage section (11 between described spar band (42-47); 15) extra play (52-57) be made up of textile fabric is comprised.
10. rotor as claimed in claim 9, is characterized in that, described additional fabric layer (52-57) has ± and the fiber alignment of 45 °.
11. rotors according to any one of claim 8 to 10, it is characterized in that, described groove (23) ends at described linkage section (11 obliquely; 15) place.
12. rotors according to any one of claim 1 to 5, it is characterized in that, connection eyelet (17) in described tension torque transmitting element (3) is for being attached to actuating device by bolt by described rotor blade (1), and the plane that described bolt is basically perpendicular to described rotor blade extends.
13. rotors as claimed in claim 12, is characterized in that, described connection eyelet (17) is only formed in the tension torque transmitting element (3) solidified.
14. rotors according to any one of claim 1 to 5, described rotor has:
The connecting section (9) of-described rotor, described connecting section (9) is between described rotor blade (1) and described tension torque transmitting element (3); And
-independent control tube (70), described independent control tube is used for control effort to be passed to described rotor, and described control tube (70) to have also be almost circular linkage section (71), described linkage section (71) is for being linked to described rotor blade (1) by described control tube (70)
It is characterized in that, the described connecting section (9) of described rotor and the described linkage section (71) of described control tube (70) comprise corresponding shape of cross section, for effectively locking the power transmission of the control effort between described rotor blade (1) and described control tube (70).
15. rotors as claimed in claim 14, it is characterized in that, moment of torsion pass segment (9) is arranged in the described connecting section between described rotor blade (1) and described tension torque transmitting element (3).
16. rotors as claimed in claim 1, is characterized in that, described fibrage is used for the tail rotor of rotor craft.
17. 1 kinds of methods for the production of rotor, described rotor is formed by rotor blade (1) and all-in-one-piece tension torque transmitting element (3) and is made up of fiber-reinforced material, said method comprising the steps of:
A) by interlayer (52-69) is rabbeted in described tension torque transmitting element (3) and described rotor blade (1), the fibrage (40-51) getting out profile is placed in mould (90);
B) by pressurizeing and be heating and curing moulded blank;
C) milling is carried out for the moulded blank of having solidified of deviating from from described mould, thus give described moulded blank with final profile.
18. methods as claimed in claim 17, is characterized in that, the steps d subsequently) in, in described tension torque transmitting element (3), get out/mill out connection eyelet (17).
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201010522380.7A CN102452480B (en) | 2010-10-15 | 2010-10-15 | There is rotor and the production method thereof of all-in-one-piece tension torque transmitting element |
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| CN201010522380.7A CN102452480B (en) | 2010-10-15 | 2010-10-15 | There is rotor and the production method thereof of all-in-one-piece tension torque transmitting element |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2131373A (en) * | 1982-12-03 | 1984-06-20 | Messerschmitt Boelkow Blohm | Rotor blade of fibre-reinforced plastics material |
| CN1030893A (en) * | 1987-07-30 | 1989-02-08 | 联合工艺公司 | The helicopter swashplate of composite material |
| US5383767A (en) * | 1992-12-23 | 1995-01-24 | Eurocopter France | Blade-hub linkage device with a laminate attachment |
| US6227805B1 (en) * | 1998-03-23 | 2001-05-08 | Eurocopter | Composite material variable pitch blade for helicopter rotor and manufacturing process of such a blade |
| CN101428686A (en) * | 2008-12-23 | 2009-05-13 | 北京航空航天大学 | Method for structural design of coaxal helicopter composite material blade |
| CN101456451A (en) * | 2007-12-14 | 2009-06-17 | 尤洛考普特公司 | Rotorcraft blade, rotorcraft rotor equipped with said blade and method of manufacturing this blade |
-
2010
- 2010-10-15 CN CN201010522380.7A patent/CN102452480B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2131373A (en) * | 1982-12-03 | 1984-06-20 | Messerschmitt Boelkow Blohm | Rotor blade of fibre-reinforced plastics material |
| CN1030893A (en) * | 1987-07-30 | 1989-02-08 | 联合工艺公司 | The helicopter swashplate of composite material |
| US5383767A (en) * | 1992-12-23 | 1995-01-24 | Eurocopter France | Blade-hub linkage device with a laminate attachment |
| US6227805B1 (en) * | 1998-03-23 | 2001-05-08 | Eurocopter | Composite material variable pitch blade for helicopter rotor and manufacturing process of such a blade |
| CN101456451A (en) * | 2007-12-14 | 2009-06-17 | 尤洛考普特公司 | Rotorcraft blade, rotorcraft rotor equipped with said blade and method of manufacturing this blade |
| CN101428686A (en) * | 2008-12-23 | 2009-05-13 | 北京航空航天大学 | Method for structural design of coaxal helicopter composite material blade |
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