CN1064897C - Apparatus and method for assembling a helicopter main rotor blade subassembly - Google Patents
Apparatus and method for assembling a helicopter main rotor blade subassembly Download PDFInfo
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- CN1064897C CN1064897C CN988042304A CN98804230A CN1064897C CN 1064897 C CN1064897 C CN 1064897C CN 988042304 A CN988042304 A CN 988042304A CN 98804230 A CN98804230 A CN 98804230A CN 1064897 C CN1064897 C CN 1064897C
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
- B29D99/00—Subject matter not provided for in other groups of this subclass
- B29D99/0025—Producing blades or the like, e.g. blades for turbines, propellers, or wings
- B29D99/0028—Producing blades or the like, e.g. blades for turbines, propellers, or wings hollow blades
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
- B29L2031/082—Blades, e.g. for helicopters
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- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Wind Motors (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
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Abstract
An apparatus and method for assembling a helicopter main rotor blade subassembly which includes a lower airfoil skin, a core, an upper airfoil skin, and a spar assembly having a tip end and a root end, the apparatus comprising a lower assembly including a base having a contoured upper airfoil nest, wherein the contoured upper airfoil nest has a root end and a tip end, at least two guide ramps disposed proximal to the contoured upper airfoil nest, wherein at least one of the guide ramps is disposed proximal to the root end and at least one of the guide ramps is disposed proximal to the tip end, and a plurality of leading-edge pusher cams disposed proximal to the contoured upper airfoil nest. An upper assembly configured for mating with the lower assembly is provided, and comprises a support structure and a flexible impervious membrane supported by the support structure, wherein the flexible impervious membrane and the contoured upper airfoil nest define a molding cavity therebetween upon mating of the upper assembly to the lower assembly.
Description
Technical field
Relate generally to manufacturing equipment of the present invention and method in particular, relate to the equipment and the method for assembling helicopter main rotor blade subassembly.
Background technology
In aircraft industry, in various structural series and dynam apparatus, enlarge and use the tendency of composite material just growing.A kind of specific application scenario of composite material is a main rotor blades of making autogyro.
Seat section Bielski (Sikorsky) aircraft company had once developed a kind of parallel manufacture technology scheme that is used to produce the main rotor blades of autogyro, wherein, blade subassembly and leading-edge sheath are produced as independent member simultaneously, then, blade subassembly of making and leading-edge sheath are combined into one, become the main rotor blades that assembles.The main rotor blades that assembles is placed in the grab bucket, and maintenance in autoclave subsequently becomes the finished product main rotor blades.
In a kind of technological process of prior art of production main rotor blades, blade subassembly in the above-mentioned parallel manufacture technology scheme partly is with in the profiling plastics dimple that the assembly set of compound covering and cellular fuse is placed on the blade top airfoil, utilizes many tommys to reserve the position of spanwise and chordwise by hand then.A titanium system spar that has applied adhesive agent, the assembly set with covering and cellular fuse is bound up by hand, and is placed in cylindrical-conical inside in the cellular fuse.On cellular fuse, apply a layer binder then, again second composite skin is placed on the part of above-mentioned cellular fuse and spar, equally also utilize the tommy location.Then, the profiling vinyl cover of a blade lower aerofoil is placed on above-mentioned second composite skin, and on blade subassembly, applies thrust, it is cooperated with above-mentioned plastics dimple be bound up with many clampers.
The second portion of this production main rotor blades process program comprises leading-edge sheath is placed on the leading edge that comes out of blade subassembly.The shape that above-mentioned leading-edge sheath manufactures can not directly be inserted on the blade subassembly it.But must open the trailing edge of leading-edge sheath, could allow leading-edge sheath be inserted on the blade subassembly.Sheath of the prior art opens instrument and comprises plurality of segments bevelled stainless steel sheet metal claw, and these claws are arranged in spanwise, with the trailing edge connection of leading-edge sheath, contacts with its mold line (IML) surface (being made by composite material).Each section of prior art claw be all by means of side direction cam lever individually actuating, thereby open the trailing edge of leading-edge sheath.
Coated with adhesive on the leading edge of blade subassembly then rotates 90 to the blade fitter's tools and spends, and the leading edge that makes blade subassembly up.Then, with crane sheath is opened instrument and sling, put down again, be placed on the blade subassembly instrument, make leading-edge sheath be positioned at the top of blade subassembly leading edge.Then, utilize many screw rods that sheath is opened instrument and pull down, open instrument up to sheath and contact with the instrument block of being scheduled to towards this blade subassembly instrument.The process that this " leaving behind " sheath opens instrument can produce very big stress on leading-edge sheath.Then, the plate-shape metal claw unclamps the trailing edge of leading-edge sheath, makes leading-edge sheath be fixed on the leading edge of blade subassembly.
The disadvantage of this blade subassembly instrument that uses in technological process described above is, and is inappropriate by the thrust that clamper many and plastics dimple and lid associated working is applied on the blade subassembly.Specifically, thisly be applied to thrust on the blade subassembly, in the span of whole blade, distribute inhomogeneously, because each clamper only on the interrupted position of its spanwise, produces maximum thrust on blade subassembly by instrument.Experience with blade subassembly is shown, when forming gripping power with this clip, one when the blade of completion when taking out from this blade subassembly instrument, must be under thrust blade be put into grab bucket and autoclave half an hour, and whole blade is always become a useful person and can not got loose.
Except the thrust that forms in the whole span of blade subassembly is inappropriate, the chordwise that the blade subassembly instrument of prior art described above forms on blade subassembly to compress the service area also inappropriate.Because when opening instrument, above-mentioned blade subassembly instrument is still stayed on the blade subassembly at the operation sheath, thus this blade subassembly instrument can not full extension on the leading edge of blade subassembly.Therefore, the each several part that is positioned near the covering of the upper and lower aerofoil of blade subassembly leading edge is not directly compressed, thereby might not be fixed on the spar reliably.A shortcoming that not exclusively compresses is, when on the leading edge of leading edge sheath at blade subassembly when mobile, if whichever the covering of composite material is separated from spar, consequently one or two trailing edges of leading-edge sheath will be in the slip underneath of composite material skin, thereby between leading-edge sheath and blade subassembly, form bad interface, cause assembled blade to scrap.
Another part of parallel production decision described above is to be used for the sheath that leading-edge sheath and blade subassembly link into an integrated entity is opened instrument.Claw of the prior art when opening the trailing edge of leading-edge sheath, apply shear force to the IML surface of leading-edge sheath.The shear force that claw of the prior art applied may form crackle and peeling off in the composite material of leading-edge sheath, thereby can cause scrapping and doing over again of parts.In addition, in the working process of prior art claw, claw may pollute the bonding surface of leading-edge sheath cleaning.In addition, each section claw individually moves in order, therefore, open whole leading-edge sheath, must carry out repeated operating process.This is not only a kind of heavy duplication of labour, and time-consuming, the expense height, and also this process also can produce unnecessary stress in the trailing edge of leading-edge sheath.
In U.S. Patent No. 5,528,828 " making the method for helicopter main rotor blade " and No.5,570, (these two patents have all transferred United Technologies, hereinafter are referred to as " ' 828 patent " and " ' 631 patent " respectively) discloses the method for another kind of manufacturing main rotor blades in 631 " making the device of helicopter main rotor blade ".As illustrated in fig. 1 and 2, disclosed device comprises a compressing fixture 10 that is used to assemble and compress blade subassembly 24 in ' 828 patents and ' 631 patents, with one be used for that in clamping process leading-edge sheath 22 is opened and be inserted into the sheath that blade subassembly 24 gets on and open/insert device 50, wherein, blade subassembly 24 is by a top airfoil covering 12,18, one fuses 14 of a lower aerofoil covering and a spar assembly 16 are formed.
Above-mentioned compressing fixture 10 comprises a bottom assembly 26 and a top assembly 32, the bottom assembly has the top airfoil dimple 28 of a profiling of combining with a supporting member 30, the top assembly has a pressure bag 34 on the backboard 36 that is fixed on profiling with the leak free connection mode, and above-mentioned backboard 36 is fixedly connected on the structure support framework 38.The top airfoil dimple 28 of profiling comprises and manyly is used for top airfoil covering 12 location and aims at the top airfoil dimple 28 that is connected profiling, and many back walls promotion pins 39, be used for aiming at spar assemblies 16 at the top airfoil dimple 28 of above-mentioned profiling in chordwise.The spar pillar 40 that is fixed on the supporting frame 38 is aimed at spar assembly 16 in the top airfoil dimple 38 of spanwise in profiling. Top assembly 32 and 26 lockings of bottom assembly are bound up,, the parts 12,14,16,18 of the blade subassembly that assemble are compressed so pressure bag 34 just is under pressure.
Above-mentioned sheath opens/inserts device 50 and comprises: a pillar 52 movably; Be bound up with pillar 52 and be mounted to the upper and lower long stent member 54,56 that can be synchronized with the movement; And be mounted to the many rows suction hood 58,60 that is bound up with support element 54,56. Air cylinder 61,62 is arranged between pillar 52 and each the corresponding support element 54,56.The pressurization of air cylinder 61,62 makes that upper and lower support element 54,56 can be at a disengaged position, an engage position, and same moved further between control position, wherein, in the time of on disengaged position, above-mentioned leading-edge sheath 22 can insert row and arrange between the suction hood 58,60 down, in the time of on engage position, corresponding outer loft (0ML) surface is close to and contacts on above-mentioned suction hood and the leading-edge sheath 22, in the time of on control position, above-mentioned leading-edge sheath 22 opens, so that be inserted on the blade subassembly 24 in the process that compresses.A vacuum source 64 is connected on the above-mentioned suction hood 58,60, so that on contact position, in suction hood, produce suction, make suction hood 58,60 contact with corresponding 0ML surface on the leading-edge sheath 22, thereby make upper and lower support element 54,56 during with moved further, allow leading-edge sheath 22 open to control position subsequently.Movably the motion of pillar 52 makes the leading-edge sheath 22 after opening be positioned at when compressing on the blade subassembly 24.
When using blade subassembly instrument described above, a shortcoming of disclosed method and apparatus is in above-mentioned ' 828 patent and ' 631 patent, and compressing fixture 10 can not form suitable thrust between spar assembly 16 and position are near the each several part of the composite material skin 12,18 of the leading edge 42 of blade subassembly 24.As shown in Figure 2, because movably pillar 52 is in the process of pressurization leading-edge sheath 22 to be placed on the blade subassembly 24, so around the leading edge of blade subassembly 24 enough spaces must be arranged, allowing movably, in fact pillar 52 can move to suitable position by along continuous straight runs.Therefore, pressure bag 34 does not cover the leading edge of blade subassembly 24 fully, thereby the composite material skin 12,18 of upper and lower aerofoil also just can not suitably be pressed on the spar assembly 16 in that zone.Found that the leading edge of these two composite material skin 12,18 is also referred to as " interface ", may have in this leading edge zone and lift, leave the tendency of spar assembly 16.These interfaces respectively form one " step ", and leading-edge sheath 22 must be overlapping with corresponding composite material skin 12,18 on this step, so that a suitable interface is arranged between leading-edge sheath 22 and blade subassembly 24.Leave spar assembly 16 if these interfaces lift, so leading-edge sheath 22 just can be in the process of installing in the slip underneath of interface, thereby between leading-edge sheath 22 and blade subassembly 24 formation bad with inferior-quality interface.
In addition, disclosed sheath opens/inserts device 50 shortcoming structurally in ' 828 patent and ' 631 patent, also may further increase in the installation process possibility at the bad interface of formation between the leading-edge sheath 22 and blade subassembly 24.Specifically, when leading edge sheath 22 is positioned between two row's suction hoods 58,60, and upper and lower support element 54,56 is when being on the control position, and the weight of leading-edge sheath 22 just can arranged the downward power of generation on suction hood 60 and the lower bracket member 56 down.Have been found that the pressure that the downward power that acts on the lower bracket member 56 can not be infeeded down air cylinder 62 offsets, therefore, the lower bracket member is with regard to having along with 22 weight and the tendency that offsets downward.In addition, because the bellows of rubber is arranged in the suction hood 58,60, the weight of leading-edge sheath 22 also can be flattened down the bellows in row's suction hood 60, and elongates the bellows in the row's of going up suction hood 58.Act on the downward power on the support element 56, combine, just make that 22 trailing edge is crooked downwards with the flattening of following suction hood 60 tendency, to such an extent as between leading-edge sheath 22 and blade subassembly 24 situation of generation misalignment.The phenomenon of this misalignment can be such, promptly, when support 52 along continuous straight runs move, and when leading edge sheath 22 during near the leading edge of blade subassembly 24, the crooked trailing edge that may make leading-edge sheath 22 tops of leading-edge sheath 22 on the lower aerofoil that is stuck in composite material skin 18 below the interface, thereby form bad interface.
With this problem mix together be the following fact, promptly, in the time of near pillar 52 is positioned at compressing fixture 10, compressing fixture 10 and sheath open/insert the trailing edge that device 50 has blocked leading-edge sheath 22, make that the operator is difficult to differentiate with range estimation, whether the trailing edge of leading-edge sheath 22 is on the appropriate location of installation.Remedying this probabilistic way for one is, when aiming at the trailing edge of leading-edge sheath 22, open the trailing edge of leading-edge sheath 22 greatlyyer (greater than the optimum value 1.27cm (0.5in.) of each side displacement), so that the trailing edge of its side is not easy to block below an interface.Yet, each side of trailing edge open surpass 1.27cm (0.5in) shortcoming be that composite material in the leading-edge sheath 22 and temperature booster surface layer are probably owing to open the undue stress that produces and be more prone to scrap and do over again.
Disclosure of an invention
Therefore, an object of the present invention is to provide a kind of helicopter main rotor blade subassembly that is used to assemble, can apply the equipment and the method for thrust in the whole chordwise of blade subassembly and spanwise.
Another object of the present invention provides a kind of helicopter main rotor blade subassembly that is used to assemble, and can make the stress on the parts that are applied to helicopter main rotor blade subassembly be reduced to minimum equipment and method.
Another purpose of the present invention provides a kind of helicopter main rotor blade subassembly that is used to assemble, and can reduce lifting, transportation and the accurately equipment and the method for the hand labour intensity that spent of locating blades branch unit parts.
In the present invention, above-mentioned these and other some purposes are to be finished by a kind of equipment that assembles helicopter main rotor blade subassembly, above-mentioned blade subassembly comprises: a lower aerofoil covering, a fuse, a top airfoil covering, and spar assembly with a top and a butt, the said equipment has a bottom assembly, this assembly comprises a base that has the profiling dimple of top airfoil, wherein, the profiling dimple of above-mentioned top airfoil has a butt and a top, be arranged near the oblique rail of first and second guiding of profiling dimple of this top airfoil, wherein, the oblique rail of above-mentioned first guiding is arranged near the above-mentioned butt, and the oblique rail of above-mentioned second guiding is arranged near the above-mentioned top, and near many frontal advance cams of profiling dimple that is arranged on above-mentioned top airfoil.
Also be provided with one and be designed to the top assembly that matches with above-mentioned down assembly, it has a supporting member and one by above-mentioned supporting members supports, flexible fluid-tight diaphragm, wherein, the fluid-tight diaphragm of above-mentioned flexibility and above-mentioned top airfoil profiling dimple are between the two, when top assembly and bottom assembly are combined together, surround a die cavity.
In the present invention, above-mentioned these purposes are also reached by a kind of method of making helicopter main rotor blade subassembly, above-mentioned blade subassembly comprises: a lower aerofoil covering, one within it portion form cylindrical-conical fuse, a top airfoil covering, and a spar assembly with a top and a butt.
Said method comprises provides a blade pinch device, the bottom assembly that this device has a shape and top assembly to match.This bottom assembly comprises: a base that has the profiling dimple of top airfoil, and above-mentioned dimple has a butt and a top; Near at least two oblique rails of guiding of profiling dimple that are arranged on above-mentioned top airfoil, wherein, the oblique rail of above-mentioned guiding portion within it forms taper shape, and, wherein at least one oblique rail that leads is arranged near the above-mentioned butt, and at least one oblique rail that leads is arranged near the above-mentioned top, and near the frontal advance cam many profiling dimples that is arranged on above-mentioned top airfoil.
Above-mentioned top assembly comprises a supporting member that is supporting the waterproof diaphragm of a flexibility, wherein, between the fluid-tight diaphragm of above-mentioned flexibility and the profiling dimple of above-mentioned top airfoil, when top assembly and bottom assembly are combined together, surrounds a die cavity.
Said method also comprises the following steps: the profiling dimple of above-mentioned top airfoil covering and fuse and above-mentioned top airfoil is combined; One roots and tops supporting plug is connected with the top of above-mentioned spar assembly combines; End bearing plug one by one is connected with the butt of above-mentioned spar assembly combines, wherein, above-mentioned top supporting plug and butt supporting plug all have and are designed for guide surface and the ways combined with the oblique rail of above-mentioned guiding.Then, by means of at least one above-mentioned guide surface being leaned against on above-mentioned at least one oblique rail that leads, above-mentioned spar assembly is aimed in spanwise be positioned in the profiling dimple of above-mentioned top airfoil.By means of above-mentioned ways being advanced in the taper shape of the oblique rail of above-mentioned guiding with the frontal advance cam, and above-mentioned spar assembly is advanced in the taper shape of above-mentioned fuse, above-mentioned spar assembly is aimed in chordwise be positioned in the profiling dimple of above-mentioned top airfoil.Then, above-mentioned lower aerofoil covering and above-mentioned fuse and spar combination of components are got up, form the blade subassembly of autogyro, and then top assembly and bottom assembly are assembled together.Then, the air extraction in the above-mentioned die cavity is come, result, the vacuum behind the air extraction make the fluid-tight diaphragm of above-mentioned flexibility be applied to thrust on the blade subassembly of above-mentioned autogyro.
From the following detailed description, will make other purposes of the present invention and advantage for those skilled in the art, become fairly obvious.To preferred embodiments more of the present invention be described to realize best mode of the present invention in the following detailed description.Be readily appreciated that the present invention can be under the prerequisite that does not break away from inventive concept of the present invention, improve aspect different at each.Therefore, accompanying drawing and can only think illustrative to the description of accompanying drawing, rather than restrictive.
The accompanying drawing summary
Fig. 1 is the block diagram that a kind of compressing fixture and sheath of prior art opens/insert device;
Fig. 2 is the partial plan layout of the one type of prior art syringe among Fig. 1;
Fig. 3 A is the top view of the main rotor blades of H-60 autogyro as an example;
Fig. 3 B is the cross-sectional view along the main rotor blades of the 3B-3B line among Fig. 3 A;
Fig. 3 C is the partial perspective view after the amplification of the leading-edge sheath among Fig. 3 B;
Fig. 3 D is the partial perspective view after the amplification of spar assembly of the main rotor blades shown in Fig. 3 A;
Fig. 4 is the block diagram that has comprised the blade pinch device of characteristics of the present invention;
Fig. 5 is along the schematic partial cross sectional of the blade pinch device of 5-5 line, comprising the cross-sectional view of the main rotor blades among Fig. 3 B among Fig. 4;
Fig. 6 be among Fig. 4 along the cross-sectional view of the blade pinch device of 6-6 line, comprising the cross-sectional view of the main rotor blades among Fig. 3 B, shown that wherein the top assembly cooperates the situation that connects with the bottom assembly;
Fig. 7 has comprised characteristics of the present invention, the planar view of the bearing set of the spar assembly among supporting Fig. 3 D;
Fig. 8 is the planar view after the spar assembly among Fig. 7 falls with supporting plug partial cut;
Fig. 9 is the planar view that has comprised the leading-edge sheath erecting device of characteristics of the present invention;
Figure 10 is the scheme drawing that has shown air cylinder, suction hood, pipeline, vacuum pump and the vacuum reservoir etc. of the leading-edge sheath erecting device among Fig. 9;
Figure 11 is the planar view of the leading-edge sheath erecting device among Fig. 9, has shown that wherein the leading edge of blade subassembly is just being inserted in the leading-edge sheath;
Figure 12 is that explanation has comprised characteristics of the present invention, makes the diagram of circuit of the method for blade subassembly; And
Figure 13 is that explanation comprises characteristics of the present invention, leading-edge sheath is installed in the diagram of circuit of the method on the blade subassembly.
Implement optimal mode of the present invention
Equipment that will describe in further detail and method have below comprised the manufacture technology scheme part of the main rotor blades of the H-60 autogyro of making the manufacturing of Bielski aircraft company of seat section.But, should be appreciated that equipment and method described in this specification sheets can be used for making general main rotor blades.
Main rotor blades
A H-60 main rotor blades 100 is illustrated among Fig. 3 A-3D, and it comprises: a leading edge 102 and a trailing edge 104, leading edge and trailing edge combine and form the wing chord of main rotor blades 100; And a butt 106 and a top 108, the span (overhead guard 109 of main rotor blades 100 is to make separately, is connected on the top 108 of main rotor blades 100) that the two combines and forms main rotor blades 100.Main rotor blades 100 has upper and lower aerofoil covering 110,112, and the two forms the upper and lower aerodynamic surface of blade 100 respectively; A fuse 114; A spar assembly 116, and a leading-edge sheath 120.The above-mentioned lower aerofoil covering 110,112 of going up, fuse 114 and spar assembly 116 combine becomes a blade subassembly 132.
In described embodiment, upper and lower aerofoil covering 110,112 all is the composite material with several layers those skilled in the art known semi-solid preparation, for example, is clipped in the prefabricated components that the glass fiber material of the braiding in the suitable resin matrix is made.Many corresponding trailing edge instruments contact pin 130 extends out from the trailing edge of upper and lower aerofoil covering 110,112, wherein, and in each trailing edge instrument contact pin 130 all porose 131.Below with more detailed discussion, above-mentioned trailing edge instrument contact pin 130 facilities upper and lower aerofoil covering 110,112 in the blade fitting process in the correct location of spanwise and chordwise.
In described embodiment, fuse 114 is with normally used cellular material in the space flight equipment, NOMEX for example, (NOMEX is that E.I.Du Pont Company is the trade mark of aramid fiber or fabric registration) of making, its effect are as a kind of composition of lightweight additional strengthening between upper and lower aerofoil covering 110,112.The leading edge shape of fuse 114 is the taper shape 121 that the trailing edge with spar assembly 116 matches.The knock hole 134 that many alignings are arranged on top airfoil covering 110, lower aerofoil covering 112 and the fuse 114 will be so that the location of spar assembly 116 in blade pinch device 200 will describe in further detail hereinafter to this.After assembling main rotor blades 100, repair knock hole 134 with composite material, so that top airfoil covering 110 and lower aerofoil covering 112 have surface smooth on the aerodynamics.
Spar assembly 116 comprises: a spar 117, one or more counterweights 118, and some rear wall cushion blocks 119.Spar 117 plays the main components of main rotor blades 100, various dynamic loadings such as in the autogyro operation process, opposing produces in main rotor blades 100 reverses, crooked, shearing and centnifugal force.Spar 117 usefulness titaniums in the present embodiment are made, and but, in alternative embodiment, above-mentioned spar 117 can be made with other metals, also can make with the composite of composite material or above these materials.
Counterweight 118 is used for balance main rotor blades 100 on statics and dynam.In the present embodiment, from butt 106 to the top 108 spanwise, above-mentioned counterweight 118 can be used from lower density to highdensity various materials, for example, being respectively foamed plastic, tungsten and lead etc. makes, forming needed weight distribution, so that make main rotor blades 100 reach balance on statics and the dynam.Counterweight 118 manufactures and comprises some hard spots 136, and these hard spots have formed substantial the contact between the mold line (IML) of counterweight 118 and leading-edge sheath 120.Counterweight 118 is to be bonded on the leading edge of spar 117 with adhesive agent like this, that is, make counterweight 118 after the bonding between the leading edge of leading-edge sheath 120 and spar 117.
Rear wall cushion block 119 is bonded in adhesive agent on the trailing edge of spar 117 on the position of the knock hole 134 corresponding interruptions on several and top airfoil covering 110 and the fuse 114.Because knock hole 134 has been arranged, above-mentioned rear wall cushion block 119 has made things convenient for the location of spar assembly 116 in blade pressure device 200, and this point will be described in more detail below.
In the present embodiment, leading-edge sheath 120 (having represented these parts in Fig. 3 C in detail) is the prefabricated hybrid component made from composite material and abrasive resistant material.Sheath 120 is the U font on the whole, has surrounded the leading edge 102 of main rotor blades 100.Sheath 120 comprises: one or more layers semi-solid preparation composite material 122, for example, be clipped in the fiberglass braided material in the suitable resin matrix, and it has formed the mold line (IML) of leading-edge sheath 120; Article one, first wear-resistingly be with 124; And one second wear-resistingly be with 126.This leading-edge sheath 120 provides wear-resistant protection for the leading edge 102 of main rotor blades 100, has controlled the aerofoil tolerance of main rotor blades 100, and holds the ice removal assembly (not shown) of main rotor blades.
Be used for making the method for main rotor blades 100, comprise blade pinch device 200, the using method of bearing set 300 and leading-edge sheath erecting device 400 will be described hereinafter more all sidedly.
The blade pinch device
See also Fig. 4, the bottom assembly 202 that the blade pinch device 200 among the figure has its shape and top assembly 250 to match.Bottom assembly 202 comprises a base 206, this base has the profiling dimple 208 of a top airfoil, wherein, the shape of the profiling dimple 208 of this top airfoil and the top airfoil of blade subassembly 132 match, and have one with the butt 106 corresponding medial extremitys 210 of blade subassembly 132 and one top 108 corresponding external side ends 212 with blade subassembly 132.Article two, the guiding oblique rail 214,216 be arranged on top airfoil profiling dimple 208 near, promptly, the oblique rail 214 that leads is arranged near the medial extremity 210 of profiling dimple 208 of top airfoil, and the oblique rail 216 that leads is arranged near the external side end 212 of profiling dimple 208 of top airfoil.On each oblique rail 214,216 that leads an inclined-plane 218 is arranged all, this inclined-plane terminates on conical 222.In addition, on each bar leads oblique rail 214,216 bolt 224 is housed all, when rotating this root bolt 224, it just can cross inclined-plane 218, moves towards conical 222.
The pit 226 of plate promotion pin after three is arranged in the profiling dimple 208 of top airfoil, and its position in spanwise and chordwise is corresponding with the knock hole 134 in the blade subassembly 132.As shown in Figure 5, plate promotion pin 228 is to be used for combining with the pit 226 of knock hole 134 and back plate promotion pin after three, can use as various tool in the process of making blade subassembly 132 so that can make the back plate promote pin 228, this point will more fully be described hereinafter.In addition, near the leading edge of the profiling dimple 208 of top airfoil, be provided with three frontal advance cams 230, a cam face 232 is arranged on each cam, make each frontal advance cam 230 all be arranged on the spanwise and promote on the pit 226 corresponding positions of pin with above-mentioned back plate.The shape of frontal advance cam 230, can make cam face 232 promote pin 228 along chordwise towards the back plate and advance when leading edge advances cam 230 actions according to the known common mode design of this technical field.
See also Fig. 4 and Fig. 6, be provided with a vacuum source 234 on base 206, from this vacuum source many pipelines 236 that extend out, corresponding hole 238 places of the terminal of each root pipeline 236 wherein on base 206.In the present embodiment, above-mentioned vacuum source 234 comprises the vacuum pump that a Daepori is logical, and two rows are lined up in these holes 238, and a row position is near the leading edge of the profiling dimple 208 of top airfoil, and another row's position is near the trailing edge of the profiling dimple 208 of top airfoil.In addition, in chordwise and spanwise, on 131 corresponding positions, hole in the trailing edge instrument contact pin 130 of blade subassembly 132, near the profiling dimple 208 of top airfoil, be provided with five the spring loaded instrument contact pin of usefulness pins 240 that are arranged in a row.
See also Fig. 4 and Fig. 6, top assembly 250 comprises a supporting member 252 that is supporting the fluid-tight diaphragm 254 of a flexibility.In the present embodiment, the many hinges 256 of above-mentioned supporting member 252 usefulness are connected on the base 206, and make supporting member 252 to turn to the second place from primary importance, on primary importance, the fluid-tight diaphragm 254 of above-mentioned flexibility does not cover the profiling dimple 208 of top airfoil, on the second place, the fluid-tight diaphragm 254 of above-mentioned flexibility has covered the profiling dimple 208 of top airfoil.Above-mentioned supporting member 252, flexible fluid-tight diaphragm 254, the profiling dimple 208 and the base 206 of top airfoil are designed to link together like this, promptly, when supporting member 252 is on the second place, the fluid-tight diaphragm 254 of above-mentioned flexibility just covers the profiling dimple 208 of top airfoil, has formed gas tight seal between supporting member 252 and base 206.In addition, when above-mentioned supporting member 252 was in the second place, the fluid-tight diaphragm 254 of above-mentioned flexibility and the profiling dimple 208 of top airfoil surrounded a die cavity 258 between them.In the present embodiment, the hole 238 on the base 206 is such design-calculateds, that is, when vacuum source 234 starts, this vacuum source 234 air in the die cavity 258 of just finding time, thereby the profiling dimple 208 that flexible fluid-tight diaphragm 254 is inhaled to top airfoil.
Bearing set
See also Fig. 3 A-3D, Fig. 4 and Fig. 7, bearing set 300 is in making the process of blade subassembly 132 and blade pinch device 200 combines and uses.Bearing set 300 comprises: the butt supporting plug 302 on butt 106 that is designed for being connected spar 117; Top supporting plug 304 on top 108 that is designed for being connected spar 117; A top gear case 306 that is connected on the top supporting plug 304; A top gear case 308 that is connected on the butt supporting plug 302; And hoisting device 338 that is used to support butt and top gear case 308,306.As shown in Figure 8, for present embodiment, above-mentioned butt supporting plug 302 comprises a base 310, and it has a pair of member that extends out from it 312,314, and the shaped design of this a pair of member becomes can insert in the butt 106 of spar 117.Member in the member 312 has two to extend out from it, and spring-loading jaw 316 is used for being connected with corresponding pair of holes 117A on the spar 117, and its effect is butt to be supported plug 302 be fixedly connected on the spar 117.Supporting plug 304 in top has the inclined flange 320 in the top 108 of some insertion spars 117, and many holes 322 are arranged on these flanges, and the hole on the top 108 of these holes and spar 117 is corresponding, is used for overhead guard 109 is fixed on blade subassembly 132.Also be provided with many screws 324, be used for being connected, thereby top supporting plug 304 is located and is fixed on the spar 117 with above-mentioned hole 322.
See also Fig. 6 and Fig. 8, each supports plug 302,304 and also comprises two wayss 326,328, these two wayss extend to spanwise from it, the one end is connected on the gear case connecting panel 329 so that the supporting plug 302,304 be connected with they corresponding gears case 308,306 on.In the present embodiment, are columniform rollers near the ways 328 of the rear end of spar assembly 116, be used for the oblique rail 214,216 of guiding on inclined-plane 218 engagements.In addition, each gear case connecting panel 329 all has one to be positioned at this connecting panel 329 1 sides, near the guide surface 330 of ways 326,328.Above-mentioned ways 326,328 and guide surface 330 all are used for combining with the oblique rail 214,216 that leads, so as in to make the process of blade subassembly 132 location wing beam assembly 116 correctly.
See also Fig. 7 and Fig. 8, above-mentioned top gear case 306 and butt gear case 308 are designed to common gear system separately, make each gear case 306,308 can both be on the direction of perpendicular mobile spar assembly 116, and spar assembly 116 is rotated around its general axis 123.In the present embodiment, gear case 306,308 is provided with rotating crank 334,336 separately, with manual mode to vertical direction and/or rotation direction drive spar assembly 116 on one side.In alternative embodiment, can be connected with gear case 306,308 with electrical motor, so that spar assembly 116 is made perpendicular movement and/or rotatablely moved.
Above-mentioned hoisting device 338 has a common overhead traveling crane known in the art, is used for making the on-the-spot material that promotes.In the present embodiment, jacking system 338 comprises and each gear case 306,308 bonded assembly hoisting cables 340 that like this, jacking system 338 just can be at vertical and/or horizontal direction traveling gear case 306,308.
The erecting device of leading-edge sheath
See also Fig. 9,10 and 11, the erecting device 400 of leading-edge sheath comprises a bottom assembly 402 that is connected on the top assembly 450.
In the present embodiment, bottom assembly 402 also comprises four vacuum pumps 416 that are communicated with four vacuum reservoirs 418, and wherein, these vacuum reservoirs 418 utilize many corresponding pipelines 422 to be connected with many suction hoods 414.The effect that vacuum pump 416 and vacuum reservoir 418 combine is to provide suction for above-mentioned many suction hoods 414.In the present embodiment, these many suction hoods 414 and their corresponding pipelines 422 are divided into four loops, and each bar loop is connected with a vacuum reservoir 418.Many valves 424 are connected on the above-mentioned pipeline 422, and its effect is that the vacuum pressure that provides to many suction hoods 414 is provided.Vacuum reservoir 418 adopts common design, and the design-calculated predetermined volumes can provide the vacuum pressure between 676.73kPa-84.66kPa (20 in.Hg-25 in.Hg) greatly to each suction hood 414 rapidly.Between two opposite rows suction hood 414, be provided with the profiling dimple 420 of a leading-edge sheath, be used to support leading-edge sheath 120.In alternative embodiment, in order to meet the action need of those embodiment, different in the quantity in vacuum pump 416, vacuum reservoir 418 and loop and the present embodiment.
Top assembly 450 comprises five pillars 452, and these five pillars vertically extend out from base 404 basically, and the position of its spanwise is corresponding with the position of the trailing edge instrument contact pin 130 of blade subassembly 132.All connecting a profiling clamper 454 on each root pillar 452, wherein, each profiling clamper 454 comprises 456, one pivotally attached stationary members 458 of a contoured surface and an instrument contact pin pin 460.Above-mentioned contoured surface 456 and pivotally attached stationary member 458 are used for blade subassembly 132 is clamped in the middle of them, and wherein, the effect of instrument contact pin pin 460 is to be connected with the instrument contact pin 130 of blade subassembly 132, so that correct locating blades branch unit 132.In the present embodiment, each profiling clamper 454 can both be in an open state and a state that closes up, under open state, the position of pivotally attached stationary member 458 is away from contoured surface 456, and under the state that closes up, the close contoured surface 456 in the position of pivotally attached stationary member 458, and play a part stationary blade branch unit 132.In addition, top assembly 450 also is included in the cross-over connection member (not shown) that three rear walls that form on the above-mentioned contoured surface 456 advance the groove 451 of pin and/or extension between adjacent profiling clamper 454, and corresponding with the knock hole 134 on the blade subassembly 132 in the position of spanwise and chordwise.
Above-mentioned profiling clamper 454 is to be connected like this on the pillar 452, that is, these profiling clampers 454 can move with respect to the profiling dimple 420 of leading-edge sheath.In the present embodiment, in common gear system, be provided with a rotation hand wheel 462 and differentiator 464, and they and profiling clamper 454 connect, move as straight line with respect to profiling dimple 420 so that promote profiling clamper 454 by hand.In alternative embodiment, above-mentioned straight line moves and can utilize electrical motor and/or hydraulic efficiency gear to finish.
Make the method for blade subassembly
Below, with reference to the blade subassembly of in Fig. 3 A-D and 4-8, describing 132, blade pinch device 200, and bearing set 300, and, describe the method for making above-mentioned blade subassembly 132 in detail with reference to the diagram of circuit among Figure 12.
In step 500, top airfoil covering 110 and fuse 114 are placed on the top airfoil dimple 208.In the present embodiment, top airfoil covering 110 and fuse 114 bonded together with adhesive agent before being placed on top airfoil dimple 208, so that shorten the time of making.In step 502, the fabricate block of top airfoil covering 110 and fuse 114 is by means of being enclosed within the hole 131 in the trailing edge instrument contact pin 130 with on the spring loaded instrument contact pin pin 240, and all has been positioned on the top airfoil dimple 208 in spanwise and chordwise.In addition, back plate promotion pin 228 passes the knock hole 134 on fuse 114 and the top airfoil covering 110, inserts in the back plate pushing pin pit 226.
In the present embodiment, be used for the spar of blade is bonded on covering/fuse fabricate block, the adhesive agent (not shown) well known in the art was coated in before carry out step 504 on the spar assembly 116.In step 504, butt supporting plug 302 is connected on the butt 106 of spar 117, and top supporting plug 304 is connected on the top 108 of spar 117.In step 506 and 508, butt supporting plug 302 is connected on the butt gear case 308, top supporting plug 304 is connected on the top gear case 306, and then two gears case 306,308 are connected with hoisting rope 340, so that spar assembly 116 is supported by hoisting device 338.
In step 510, spar assembly 116 usefulness hoisting device 338 are sling, and locate in the following manner, promptly, butt supporting plug 302 is at the oblique rail 214 of the close guiding in medial extremity 210 places of top airfoil profiling dimple 208, and supporting plug 304 in top is then at the oblique rail 216 of the close guiding in external side end 212 places of top airfoil profiling dimple 208.In step 512, both wayss 326,328 of above-mentioned butt supporting plug 302 and top supporting plug 304 all contact with inclined surface 218 in the oblique rail 214,216 of guiding.Then, by means of making guide surface 330 on the top supporting plug 304 be close to the oblique rail 216 of guiding on the external side end 212 of top airfoil profiling dimple 208, spar assembly 116 is located in spanwise.In step 514, butt gear case 308 and butt supporting plug 302 are thrown off, and top gear case 306 and top supporting plug 304 are thrown off.
In step 516, by means of ways 326,328 being pushed in the inclined-plane 218 with bolt 224, trailing edge up to ways 328 spar assembly 116 around all approaching taper shape 222 in each inclined-plane 218 is correctly located the butt 106 of spar assembly 116 and top 108 in chordwise.The butt 106 of spar assembly 116 and the correct location on top 108 might not guarantee that the remainder of spar assembly 116 all correctly aims in spanwise.For whole spar assembly 116 is correctly located in chordwise, in step 518, drive leading edge actuating cam 230, cam face 232 contact with hard spot 136 on the spar assembly 116, and the back plate block 119 that drives spar assembly 116 leans against on the pin 228 of plate promotion afterwards.Should be appreciated that on such position, that is, back plate block 119 correctly is placed in the taper shape 121 that is surrounded by fuse 114 with the trailing edge that has guaranteed spar assembly 116 that contacts that the back plate promotes between the pin 228 above-mentioned back plate promotion pin 228 in chordwise.Lag behind in spar assembly 116 correct location, the adhesive agent (not shown) is coated on fuse 114 and the spar assembly 116, prepare to accept lower aerofoil covering 112.
In step 520, lower aerofoil covering 112 is placed on fuse 114 and the spar assembly 116, and utilizes the trailing edge instrument contact pin 130 of lower aerofoil covering 112 to be connected and in spanwise and chordwise location with spring loaded instrument contact pin pin 240.In step 522, cover (see figure 6) on blade subassembly 132 with a polishing plate 242 so that in compaction process by means of the fluid-tight diaphragm 254 of flexibility, distribute the thrust that is applied on the blade subassembly 132 equably.In step 524, a glass fibre ventilation bag 244 is covered (see figure 6) on polishing plate 242, one side helps the air extraction between the fluid-tight diaphragm 254 that is captured in polishing plate 242 and flexibility is come in compaction process, and the friction between the fluid-tight diaphragm 254 of minimizing blade subassembly 132 and flexibility.
In step 256, supporting member 252 is turned to the second place and be fixed on this position, make flexible fluid-tight diaphragm 254 cover blade subassembly 132 and top airfoil profiling dimple 208, thereby between the two, form air tight die cavity 258.In step 528, start vacuum source 234, in die cavity 258, deflate.In the present embodiment, the vacuum pressure that is provided by vacuum source 234 approximates 44.02kPa (13in.Hg) greatly.Come from die cavity 258 inside air extraction, just make flexible fluid-tight diaphragm 254 be pulled to top airfoil profiling dimple 208, thereby on the member of blade subassembly 132, applied thrust.In the present embodiment, when the pneumatics power of taking seriously approximates 44.02kPa (13in.Hg) greatly,, can provide suitable thrust for blade subassembly 132 about 30 minutes compressing in the phase.
In step 530, stop vacuum source 234, rotating support member 252 is got back to primary importance then, so flexible fluid-tight diaphragm 254 no longer covers blade subassembly 132.Prepare for the blade subassembly 132 after compressing is unloaded down from blade pinch device 200, will promote pin 228 to ventilation bag 244, polishing plate 242, leading edge actuating cam 230 and back plate earlier and all unload down.In step 532 and 534, again butt supporting plug 302 is connected on the butt gear case 308, top supporting plug 304 is connected on the top gear case 306, again two gears case 306,308 are reconnected on hoisting rope 340, so that blade subassembly 132 is supported by hoisting device 338.
In step 536, unclamp bolt 224, so ways 326,328 just slides into the outside of oblique track surface 218, make butt supporting plug 302 and top supporting plug 304 no longer be subjected to the constraint of blade pinch device 200.Then, with bearing set 300 blade subassembly 132 is transported on the leading-edge sheath erecting device 400 from blade pinch device 200.
The method of leading-edge sheath is installed
Below, consult blade subassembly 132, bearing set 300 and leading-edge sheath erecting device 400 among Fig. 3 A-3D and Fig. 7-11, describe the diagram of circuit of the installation method that leading-edge sheath 120 and the blade subassembly 132 that compresses are combined among Figure 13 in detail.
In step 600, preparing leading-edge sheath 120 in leading-edge sheath erecting device 400 when mobile, check the relative suction hood 414 of two rows earlier, to guarantee that suction hood 414 is on the appointed positions, at this moment, the distance that separates of the relative suction hood 414 of two rows is greater than the width W les (seeing Fig. 3 C) of leading-edge sheath 120.In step 602, leading-edge sheath 120 is placed in the profiling dimple 420 of leading-edge sheath, and leans against on the instrument block (not shown) by means of top it is located in spanwise leading-edge sheath 120.In step 604, make the relative suction hood 414 of two rows move to a contact position by means of air cylinder 406, make each suction hood 414 all surperficial near contacting with the corresponding outer loft (OML) of leading-edge sheath 120 trailing edges.
In step 606, start vacuum pump 416, so in each corresponding vacuum reservoir, just stored vacuum pressure.In step 608, open valve 424, for each suction hood 414 provides the vacuum pressure that is stored in the vacuum reservoir 418, thereby between the OML surface of each suction hood 414 and leading-edge sheath 120, produce suction.In the present embodiment, suction hood 414 all is the structure of bellows form, and when valve 424 was opened, the part of the bellows form of each suction hood 414 was crushed, thereby makes the OML surface of leading-edge sheath 120 trailing edges be pulled to relative support element 412.In the present embodiment, the structure of suction hood 414 is such, promptly, when the pneumatics power of taking seriously approximately reaches between 67.73kPa and the 84.66kPa (20 in.Hg and 25 in.Hg), the part of the bellows form of each suction hood 414 has been flattened about 1.27cm (0.5in.), so the width W les of leading-edge sheath 120 has approximately increased 2.54cm (1in.).In interchangeable embodiment, the structure of suction hood 414 be applied to suction hood 414 on suction size can with present embodiment in different, to increase or to reduce leading-edge sheath 120 open width.In addition, air cylinder 406 can be used for moving the relative suction hood 414 of two rows mutually away from so that leading-edge sheath 120 can open extraly.
Before blade subassembly 132 is combined in leading-edge sheath erecting device 400, can be on the leading edge 133 of blade subassembly 132 the adhesive stripe-coating (not shown), for use in leading-edge sheath 120 is bonded on the blade subassembly 132.In step 610, adjust the butt and the top gear case 306,308 of bearing set 300, be on the vertical direction basically with assurance blade subassembly 132, and the leading edge 133 of blade subassembly 132 is towards the below.In step 612, back plate in the top assembly 450 of back plate promotion pin 228 insertion leading-edge sheath erecting devices 400 is promoted in the pin pit 451, and profiling clamper 454 is in the shape of opening, so that pivotally attached stationary member 458 is on the remote location that leaves contoured surface 456.In step 614, blade subassembly 132 is moved on the profiling clamper of opening 454 with bearing set 300, and put into wherein, make back plate promotion pin 228 pass the knock hole 134 on the top airfoil covering 110, and make instrument contact pin pin 460 pass corresponding instrument connecting piece perforation 131, thereby guarantee blade subassembly 132 correct aligning in the erecting device 400 of leading-edge sheath.In step 616, it is close-shaped that the profiling clamper is in, and makes pivotally attached stationary member 458 be in lower aerofoil covering 112 with blade subassembly 132 near on the position contacting, thereby blade subassembly 132 is fixed in the profiling clamper 454.
In step 618, make butt 308 break away from butt supporting plug 302, and make top gear case 306 break away from top supporting zine plate 304.In step 620, utilize rotation hand wheel 462 that profiling clamper 454 is moved down, make the leading edge 133 of blade subassembly 132 insert in the open leading-edge sheath 120.In step 622, leading edge 133 and leading-edge sheath 120 with visual inspection blade subassembly 132, correctly insert in the leading-edge sheath 120 with the leading edge 133 that guarantees blade subassembly 132, and the trailing edge of leading-edge sheath 120 is overlapped on top airfoil covering 110 and the lower aerofoil covering 110.Specifically, step 622 is one and checks step, can not cause separation between top airfoil covering 110 or lower aerofoil covering 112 and the spar assembly 116 with the trailing edge that guarantees leading-edge sheath 120.
In step 624, close and be arranged to the valve 424 that links together with pipeline 422, cut off supply, thereby leading-edge sheath 120 is enclosed within on the leading edge 133 of blade subassembly 132 to the vacuum pressure of many suction hoods 414.In step 626, utilize rotation hand wheel 462 that profiling clamper 454 is moved up, make the main rotor blades 100 that assembles leave the relative suction hood 414 of two rows.In step 628 and 630, again butt supporting plug 302 is connected on the butt gear case 308, top supporting plug 304 is connected on the top gear case 306, then, again two gears case 306,308 are reconnected on hoisting rope 340, so main rotor blades 100 is just supported by hoisting device 338.
In step 632 and 634, open profiling clamper 454, so just promoting pin 228 with instrument contact pin pin 460 with the back plate, main rotor blades 100 separates, make main rotor blades 100 to remove from leading-edge sheath erecting device 400 with bearing set 300.
Those skilled in the art can find out at an easy rate that the present invention has reached whole purpose set forth above.Specification sheets more than having read lags behind, and those skilled in the art can do various variations and equivalent substitutes to the present invention, and realizes in this manual extensively disclosed other aspects of institute.Therefore, protection scope of the present invention only should be limited by the application's claims and equivalent thereof.
Claims (12)
1. equipment that assembles helicopter main rotor blade subassembly, above-mentioned blade subassembly comprises: a lower aerofoil covering, a fuse, a top airfoil covering, and a spar assembly with a top and a butt, the said equipment comprises:
(a) bottom assembly, this assembly comprises:
A base that has the profiling dimple of top airfoil, the profiling dimple of above-mentioned top airfoil have a butt and a top;
Be arranged near the oblique rail of first and second guiding of profiling dimple of above-mentioned top airfoil, the oblique rail of above-mentioned first guiding is arranged near the above-mentioned butt, and the oblique rail of above-mentioned second guiding is arranged near the above-mentioned top; And
Near many frontal advance cams of profiling dimple that are arranged on above-mentioned top airfoil;
(b) one is designed to the top assembly that matches with above-mentioned bottom assembly, and this top assembly has a supporting member and one by above-mentioned supporting members supports, flexible fluid-tight diaphragm, and
(c) the fluid-tight diaphragm of above-mentioned flexibility and above-mentioned top airfoil profiling dimple when top assembly and bottom assembly are combined together, surround a die cavity between the two.
2. equipment as claimed in claim 1 is characterized in that it also comprises:
(a) roots and tops supporting plug, its shape can be used for being connected with the top of above-mentioned spar assembly;
(b) one is used for supporting plug with the butt bonded assembly butt of above-mentioned spar assembly; And
(c) above-mentioned top supporting plug and butt supporting plug respectively have guide surface and are designed to be used for and the oblique rail bonded assembly of above-mentioned guiding ways, so that above-mentioned spar assembly is positioned on the position of aiming at above-mentioned top airfoil profiling dimple in chordwise and spanwise.
3. equipment as claimed in claim 2 is characterized in that, the above-mentioned oblique rail that respectively leads comprises:
(a) one forms on oblique rail and ends at a cylindrical-conical oblique track surface, and makes above-mentioned oblique track surface be designed to and can contact with above-mentioned ways; And
(b) be arranged to basically and the parallel bolt of above-mentioned oblique track surface for one, above-mentioned bolt can move as straight line with respect to above-mentioned taper shape, and above-mentioned bolt can be operated, and when contacting with above-mentioned oblique track surface with the above-mentioned ways of box lunch, forces above-mentioned ways to press to above-mentioned taper shape.
4. equipment as claimed in claim 2 is characterized in that it also comprises:
(a) top gear case that is connected on the above-mentioned top supporting plug; With
(b) butt gear case that is connected on the above-mentioned butt supporting plug;
(c) running of above-mentioned top and butt gear case can make the longitudinal axis rotation of the main rotor blades branch unit of above-mentioned spar assembly or above-mentioned autogyro around an above-mentioned spar assembly, and can move the direction of the main rotor blades of above-mentioned spar assembly or above-mentioned autogyro to perpendicular.
5. equipment as claimed in claim 4 is characterized in that it also comprises:
A hoisting device that is connected on above-mentioned top and the butt gear case, the running of above-mentioned hoisting device can make the main rotor blades branch unit of above-mentioned spar assembly or above-mentioned autogyro move to the direction and the substantially horizontal direction of perpendicular.
6. equipment as claimed in claim 1 is characterized in that, above-mentioned bottom assembly also comprises: a vacuum source that has many pipelines to extend out from it; And the profiling dimple of above-mentioned top airfoil includes many holes, and above-mentioned pipeline is communicated with above-mentioned these holes, just can deflate from above-mentioned die cavity so start above-mentioned vacuum source.
7. equipment as claimed in claim 1 is characterized in that, the main rotor blades branch unit of above-mentioned autogyro also comprises many trailing edge instrument contact pin that are connected above it, in the contact pin of the above-mentioned trailing edge instrument of each piece a hole is arranged, and, wherein,
Above-mentioned bottom assembly also comprises near many spring loaded trailing edge instrument contact pin pins of above-mentioned top airfoil profiling dimple that are arranged on, and the shaped design of above-mentioned spring loaded trailing edge instrument contact pin pin becomes in the hole can insert in the contact pin of above-mentioned trailing edge instrument, thereby is convenient in spanwise and chordwise the main rotor blades branch unit of above-mentioned autogyro is positioned on the assembly of above-mentioned bottom.
8. method of making helicopter main rotor blade subassembly, above-mentioned blade subassembly comprises: a lower aerofoil covering, one within it portion form cylindrical-conical fuse, a top airfoil covering, and a spar assembly with a top and a butt; Said method comprises the following steps:
(a) provide a blade pinch device, the bottom assembly that this device has a shape and top assembly to match,
Above-mentioned bottom assembly comprises:
A base that has the profiling dimple of top airfoil, the profiling dimple of above-mentioned top airfoil have a butt and a top,
Near at least two oblique rails of guiding of profiling dimple that are arranged on above-mentioned top airfoil, the oblique rail of above-mentioned guiding portion within it forms taper shape, and wherein at least one oblique rail that leads is arranged near the above-mentioned butt, and at least one oblique rail that leads is arranged near the above-mentioned top, and
Near many frontal advance cams of profiling dimple that are arranged on above-mentioned top airfoil,
Above-mentioned top assembly comprises:
A supporting member that is supporting the waterproof diaphragm of a flexibility between the fluid-tight diaphragm of above-mentioned flexibility and the profiling dimple of above-mentioned top airfoil, when top assembly and bottom assembly are combined together, surrounds a die cavity;
(b) the profiling dimple of above-mentioned top airfoil covering and fuse and above-mentioned top airfoil is combined;
(c) roots and tops supporting plug is connected with the top of above-mentioned spar assembly combines; And end bearing plug one by one is connected with the butt of above-mentioned spar assembly combines, above-mentioned top supporting plug and butt supporting plug all have and are designed for guide surface and the ways combined with the oblique rail of above-mentioned guiding;
(d), above-mentioned spar assembly is aimed in spanwise be positioned in the profiling dimple of above-mentioned top airfoil by means of at least one above-mentioned guide surface being leaned against on above-mentioned at least one oblique rail that leads;
(e) by means of above-mentioned ways being advanced in the taper shape of the oblique rail of above-mentioned guiding with the frontal advance cam, and above-mentioned spar assembly is advanced in the taper shape of above-mentioned fuse, above-mentioned spar assembly is aimed in chordwise be positioned in the profiling dimple of above-mentioned top airfoil;
(f) above-mentioned lower aerofoil covering and above-mentioned fuse and spar combination of components are got up, form the blade subassembly of autogyro;
(g) top assembly and bottom assembly are assembled together; And
(h) air extraction in the above-mentioned die cavity is come, so the vacuum behind the air extraction makes the fluid-tight diaphragm of above-mentioned flexibility be applied to thrust on the blade subassembly of above-mentioned autogyro.
9. method as claimed in claim 8 is characterized in that, it also comprised the following steps: before the above-mentioned step that top assembly and bottom assembly are assembled together, a polishing plate and a ventilation pkt. flap on above-mentioned blade subassembly.
10. method as claimed in claim 8, it is characterized in that, above-mentioned bottom assembly also comprises a vacuum source, this vacuum source has many pipelines to extend out above it, and terminate on corresponding many holes of profiling dimple of above-mentioned top airfoil, so the above-mentioned vacuum source that starts just can be evacuated above-mentioned die cavity.
11. method as claimed in claim 8, it is characterized in that, it comprises that also one is designed to and can supports plug bonded assembly top bearing assembly with above-mentioned top, with one be designed to can with above-mentioned butt supporting plug bonded assembly butt bearing assembly, above-mentioned top bearing assembly and butt bearing assembly are used to support above-mentioned spar assembly or blade subassembly in operation.
12. method as claimed in claim 11 is characterized in that, above-mentioned top bearing assembly and butt bearing assembly comprise:
A top gear case that is connected on the above-mentioned top supporting plug, with a butt gear case that is connected on the above-mentioned glorious supporting plug, above-mentioned top and butt gear case can make above-mentioned spar assembly or blade subassembly rotate around a longitudinal axis of above-mentioned spar assembly in operation, and in operation above-mentioned spar assembly or blade subassembly are moved to the direction of perpendicular; And
A hoisting device that is connected on above-mentioned top gear case and the butt gear case, above-mentioned hoisting device can make above-mentioned spar assembly or blade subassembly move to the direction and the substantially horizontal direction of perpendicular in operation.
Applications Claiming Priority (4)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US08/838,295 US5832605A (en) | 1997-04-16 | 1997-04-16 | Methods for fabricating a helicopter main rotor blade |
| US08/843,527 | 1997-04-16 | ||
| US08/838,295 | 1997-04-16 | ||
| US08/843,527 US5836062A (en) | 1997-04-16 | 1997-04-16 | Apparatus for assembling a helicopter main rotor blade subassembly |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN1252754A CN1252754A (en) | 2000-05-10 |
| CN1064897C true CN1064897C (en) | 2001-04-25 |
Family
ID=27126014
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN988042304A Expired - Fee Related CN1064897C (en) | 1997-04-16 | 1998-03-25 | Apparatus and method for assembling a helicopter main rotor blade subassembly |
Country Status (7)
| Country | Link |
|---|---|
| EP (1) | EP1019243A1 (en) |
| JP (1) | JP4067574B2 (en) |
| KR (1) | KR100521734B1 (en) |
| CN (1) | CN1064897C (en) |
| CA (1) | CA2286830A1 (en) |
| TW (1) | TW412457B (en) |
| WO (1) | WO1998046419A1 (en) |
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| CN106457614A (en) * | 2014-04-24 | 2017-02-22 | Lm Wp 专利控股有限公司 | A wind turbine blade manufacturing system and method |
| US10213823B2 (en) | 2014-07-09 | 2019-02-26 | The Boeing Company | Autonomous flexible manufacturing system for building a fuselage |
| KR101884936B1 (en) * | 2016-12-29 | 2018-08-03 | 한국항공우주산업 주식회사 | Mold for roving spar of helicopter |
| DE102017001402A1 (en) * | 2017-02-14 | 2018-08-16 | Senvion Gmbh | Centering at the trailing edge of the mold half shells |
| CN111483609B (en) * | 2020-05-18 | 2024-06-04 | 西安爱生技术集团公司 | Middle wing part gluing and folding tool for small and medium-sized unmanned aerial vehicle |
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| US5430937A (en) * | 1994-07-15 | 1995-07-11 | United Technologies Corporation | Apparatus and methods for fabricating a helicopter main rotor blade |
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| US2451131A (en) * | 1940-09-06 | 1948-10-12 | Vidal Corp | Method of making reinforced structures |
| US3171163A (en) * | 1963-02-11 | 1965-03-02 | Boeing Co | Mold with first and second hinged portions composed of laminations adjustable with respect to one another |
| US3305420A (en) * | 1963-12-19 | 1967-02-21 | Parsons Corp | Method and apparatus for applying bonding pressures of differing magnitudes to adjacent surfaces of a workpiece |
| FR2555501A1 (en) * | 1983-11-28 | 1985-05-31 | Septem Sa | METHOD FOR MANUFACTURING HOLLOW RIGID STRUCTURES IN RESIN-IMPREGNATED FIBERS, DEVICE FOR IMPLEMENTING SAME AND STRUCTURE OBTAINED |
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- 1998-03-25 EP EP98912007A patent/EP1019243A1/en not_active Withdrawn
- 1998-03-25 KR KR10-1999-7009519A patent/KR100521734B1/en not_active IP Right Cessation
- 1998-03-25 CN CN988042304A patent/CN1064897C/en not_active Expired - Fee Related
- 1998-03-25 WO PCT/US1998/005781 patent/WO1998046419A1/en active IP Right Grant
- 1998-03-25 CA CA002286830A patent/CA2286830A1/en not_active Abandoned
- 1998-03-25 JP JP54392598A patent/JP4067574B2/en not_active Expired - Fee Related
- 1998-04-15 TW TW087105760A patent/TW412457B/en not_active IP Right Cessation
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5430937A (en) * | 1994-07-15 | 1995-07-11 | United Technologies Corporation | Apparatus and methods for fabricating a helicopter main rotor blade |
| US5528828A (en) * | 1994-07-15 | 1996-06-25 | United Technologies Corporation | Methods for fabricating a helicopter main rotor blade |
| US5570631A (en) * | 1994-07-15 | 1996-11-05 | Leahy; Kevin P. | Apparatus for fabricating a helicopter main rotor blade |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104080592A (en) * | 2012-02-02 | 2014-10-01 | Lmwp专利控股有限公司 | A cradle for a wind turbine blade |
| CN104080592B (en) * | 2012-02-02 | 2017-06-06 | Lm Wp 专利控股有限公司 | For the bracket of wind turbine blade |
| CN104384920A (en) * | 2014-08-26 | 2015-03-04 | 中国直升机设计研究所 | Assembly device and method of light helicopter structural part |
| CN104384920B (en) * | 2014-08-26 | 2018-10-02 | 中国直升机设计研究所 | A kind of light helicopter structural member assembly devices and methods therefor |
Also Published As
| Publication number | Publication date |
|---|---|
| TW412457B (en) | 2000-11-21 |
| CA2286830A1 (en) | 1998-10-22 |
| EP1019243A1 (en) | 2000-07-19 |
| KR100521734B1 (en) | 2005-10-17 |
| KR20010006429A (en) | 2001-01-26 |
| JP4067574B2 (en) | 2008-03-26 |
| JP2001520599A (en) | 2001-10-30 |
| CN1252754A (en) | 2000-05-10 |
| WO1998046419A1 (en) | 1998-10-22 |
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