CN102179782B - Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool - Google Patents
Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool Download PDFInfo
- Publication number
- CN102179782B CN102179782B CN201110085587A CN201110085587A CN102179782B CN 102179782 B CN102179782 B CN 102179782B CN 201110085587 A CN201110085587 A CN 201110085587A CN 201110085587 A CN201110085587 A CN 201110085587A CN 102179782 B CN102179782 B CN 102179782B
- Authority
- CN
- China
- Prior art keywords
- wing
- locator
- wing tip
- wing root
- root
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Abstract
The invention belongs to composite-material structure forming technologies, and relates to a locating tool for frameworks/reinforced ribs of an integrated composite-material wing structural member and an application method of the locating tool. The locating tool is characterized in that: at the two ends of longitudinal direction of skin-covering molds (1), framework/reinforced rib curing mold locating devices are respectively arranged on the skin-covering molds outside a skin-covering molded surface; and the application method is characterized by comprising the following steps of: installing a wing root locator (3) and a wing tip locator (6); assembling and connecting a wing root connecting segment (4), a wing tip connecting segment (7) and a framework/reinforced rib curing mold (2); locating the framework/reinforced rib curing mold (2); placing a soft mold; packaging in a vacuum bag; installing a wing root transverse beam (5) and a wing tip transverse beam (8); and disassembling pins and fixing bolts of the locators. By the locating tool and the application method, the positional precision of the frameworks/reinforced ribs of an integrated composite-material wall panel is ensured, the requirement of assembly and coordination between the integrated composite-material wing structural member and other structural members is met, and the assembly quality is improved.
Description
Technical field
The invention belongs to the composite structure forming technique, relate to the positioning tool and the method for using thereof of a kind of composite aerofoil integrated member skeleton or reinforcement.
Background technology
Composite progressively has been applied to large-scale main force support structure through for many years development.Referring to Fig. 1, the last figure among Fig. 1 is a kind of up and down composite aerofoil integrated member of covering that has, and the composite skeleton that is fitted and connected with covering is up and down being arranged between the covering up and down.Figure below among Fig. 1 is a kind of down composite aerofoil integrated member of covering that has, and the composite reinforcement that is fitted and connected with following covering is only arranged on covering down.The bearing of trend of skeleton or reinforcement is the vertical of composite aerofoil, i.e. spanwise; The orientation of skeleton or reinforcement is laterally, i.e. chordwise.Because main force support structure is strict more to the skeleton or the reinforcement status requirement of aerofoil integrated member, therefore, the skeleton or the reinforcement positional precision of control composite aerofoil integrated member are particularly important in forming process.Generally speaking, the positioning accuracy of the skeleton of composite aerofoil integrated member or reinforcement be ± 1.5mm about.When composite aerofoil integrated member chordwise size is very big, will become very serious by thermal expansion skeleton or the reinforcement position deviation of bringing that do not match during curing.At present; The material that covering mould and positioner adopt is generally steel; Its thermal coefficient of expansion and composite differ greatly, if composite is curing molding under the high temperature, when between skeleton or reinforcement solidify mould and covering mould, adopting alignment pin to be connected to locate; Though normal temperature state lower skeleton or reinforcement solidify the accurate positioning of mould; But, will significantly increase by the do not match skeleton that causes or the position deviation of reinforcement of the thermal expansion between covering mould and the covering in the high-temperature molding process, be difficult to guarantee skeleton or the positional precision of reinforcement on the composite aerofoil integrated member; Can not satisfy the assembly coordination requirement between composite aerofoil integrated member and other member, even cause product rejection.At present; The skeleton on the composite aerofoil integrated member or the localization method of reinforcement are: when composite aerofoil integrated member is very big along skeleton or reinforcement lateral dimension; Under the normal temperature state; The two ends of skeleton or reinforcement curing mould are located with alignment pin, advance before the autoclave, the alignment pin at skeleton or reinforcement curing mould two ends is removed.The shortcoming of above-mentioned localization method is: the positional precision of skeleton or reinforcement is poor, still can not satisfy the assembly coordination requirement between composite aerofoil integrated member and other member.Its reason is; Because skeleton or reinforcement solidify not constraint of mould, because in the hot setting process, skeleton or reinforcement blank are software; Vacuumize or when pressurizeing; Skeleton or reinforcement solidify between mould and the covering can produce slide displacement, and skeleton or reinforcement solidify mould and also can produce yaw motion, and each skeleton or reinforcement solidify and do not have constraint each other between the mould; Each skeleton or reinforcement solidify the displacement difference that mould moves with the covering thermal expansion, and these all cause the positional precision of skeleton or reinforcement uncontrollable.
Summary of the invention
The objective of the invention is: the positioning tool and the method for using thereof that propose a kind of composite aerofoil integrated member skeleton or reinforcement; To guarantee the positional precision of moulding back skeleton or reinforcement; Satisfy the assembly coordination requirement between composite aerofoil integrated member and other member, improve assembly quality.
Technical scheme of the present invention is: the positioning tool of a kind of composite aerofoil integrated member skeleton or reinforcement; Comprise covering mould and skeleton or reinforcement curing mould that steel are made; On the covering mould, skin-covering face is arranged; The covering that uncured covering blank is arranged on skin-covering face or solidify; On the covering of uncured covering blank or curing, be arranged with the curing mould that has skeleton or reinforcement blank, the quantity and the position of skeleton or reinforcement curing mould are confirmed by composite aerofoil integrated member drawing; It is characterized in that: on the covering mould beyond vertical two ends of covering mould, the skin-covering face, respectively have a skeleton or reinforcement to solidify the mould positioner; Positioner in abutting connection with skin-covering face wing root one side is the wing root positioner, is the wing tip positioner in abutting connection with the positioner of skin-covering face wing tip one side; The wing root positioner is connected to form by several wing root positioning components and a wing root crossbeam; The quantity of wing root positioning component is identical with the quantity that skeleton or reinforcement solidify mould, and each wing root positioning component is made up of wing root locator, wing root linkage section, wing root locator set bolt, wing root locator pin, wing root linkage section bolt and wing root linkage section pin; The wing root locator by a base plate I, vertically with base plate I upper surface be connected to two riser I and baffle plate whole, that be parallel to each other and constitute; Baffle plate is between two riser I, near the outward flange of two riser I; Baffle plate is vertical with base plate I with riser I respectively, and baffle plate is fixed on the base plate I through baffle plate bolt and baffle plate pin; Wing root locator fixed bolt hole and wing root locator pin hole is arranged on the base plate I; There are corresponding wing root locator retaining thread hole and wing root locator pin hole in corresponding position on the covering mould; Through wing root locator set bolt and wing root locator pin the wing root locator is fixed on the covering mould, the material of wing root locator is identical with the material of covering mould; The wing root linkage section is a cuboid; The inner face of wing root linkage section is connected with the wing root end that skeleton or reinforcement solidify mould; Wing root end at skeleton or reinforcement curing mould has a wing root connecting plate; The inner face of wing root linkage section is connected to integral body through wing root linkage section bolt and wing root linkage section pin with the wing root connecting plate, the outer end of wing root linkage section between two riser I, the outer end of wing root linkage section and two riser I matched in clearance; The outer face of wing root linkage section and the inner surface of baffle plate are fitted, and the material of wing root linkage section is identical with the material of covering mould; The wing root crossbeam is a long slab; It is positioned at the outside of wing root locator; Fit in the outer face of the riser I of the inner surface of wing root crossbeam and all wing root locators; Wing root crossbeam screwed hole and wing root crossbeam pin hole are arranged on the outer face of wing root locator riser I; On the wing root crossbeam with riser I outer face on wing root crossbeam screwed hole and the corresponding position of wing root crossbeam pin hole corresponding wing root transom bolt hole and wing root crossbeam pin hole are arranged, through wing root transom bolt and wing root crossbeam pin the wing root crossbeam is fixed on the outer face of riser I of all wing root locators; The wing root crossbeam is made by thermal coefficient of expansion and composite material skin identical materials;
The wing tip positioner is connected to form by several wing tip positioning components and a wing tip crossbeam; The quantity of wing tip positioning component is identical with the quantity that skeleton or reinforcement solidify mould, and each wing tip positioning component is made up of wing tip locator, wing tip linkage section, wing tip locator set bolt, wing tip locator pin, wing tip linkage section bolt and wing tip linkage section pin; The wing tip locator is connected to two riser II whole, that be parallel to each other and constitutes with vertical with base plate II upper surface by a base plate II; Wing tip locator fixed bolt hole and wing tip locator pin hole is arranged on the base plate II; There are corresponding wing tip locator retaining thread hole and wing tip locator pin hole in corresponding position on the covering mould; Through wing tip locator set bolt and wing tip locator pin the wing tip locator is fixed on the covering mould, the material of wing tip locator is identical with the material of covering mould; The wing tip linkage section is a cuboid; The inner face of wing tip linkage section is connected with the tip end that skeleton or reinforcement solidify mould; Tip end at skeleton or reinforcement curing mould has a wing tip connecting plate; The inner face of wing tip linkage section is connected to integral body through wing tip linkage section bolt and wing tip linkage section pin with the wing tip connecting plate; The outer end of wing tip linkage section between two riser II, the outer end of wing tip linkage section and two riser II matched in clearance, the material of wing tip linkage section is identical with the material of covering mould; The wing tip crossbeam is a long slab; It is positioned at the outside of wing tip locator; Fit in the outer face of the riser II of the inner surface of wing tip crossbeam and all wing tip locators; Wing tip crossbeam screwed hole and wing tip crossbeam pin hole are arranged on the outer face of wing tip locator riser II; On the wing tip crossbeam with riser II outer face on wing tip crossbeam screwed hole and the corresponding position of wing tip crossbeam pin hole corresponding wing tip transom bolt hole and wing tip crossbeam pin hole are arranged, through wing tip transom bolt and wing tip crossbeam pin the wing tip crossbeam is fixed on the outer face of riser II of all wing tip locators; The wing tip crossbeam is made by thermal coefficient of expansion and composite material skin identical materials.
The method for using of positioning tool as described above is characterized in that, the step of use is following:
1, on the covering mould that has good covering blank of laying or curing back covering, wing root locator and wing tip locator are installed; On the covering mould, wing root locator and wing tip locator are located by connecting with wing root locator pin and wing tip locator pin respectively, and fastening with wing root locator set bolt and wing tip locator set bolt;
2, the wing root linkage section being solidified the mould assembling with wing tip linkage section and skeleton or reinforcement is connected; The wing root connecting plate that all wing root linkage sections and wing tip linkage section and corresponding skeleton or reinforcement are solidified on the mould is connected the location with wing root linkage section pin with wing tip linkage section pin respectively with the wing tip connecting plate, with wing root linkage section bolt and wing tip linkage section bolted;
3, skeleton or reinforcement solidify the location of mould; Skeleton or the reinforcement that will have skeleton or a reinforcement blank solidifies the wing root linkage section of mould through two ends and wing tip linkage section and assembles with the wing root locator and the wing tip locator at two ends respectively; Guarantee the outer face of wing root linkage section and the baffle inner surface applying location of wing root locator; The two sides of wing root linkage section cooperate the location with the medial surface of two parallel riser I of wing root locator, and the two sides of wing tip linkage section cooperate the location with the medial surface of two parallel riser II of wing tip locator;
4, lay soft mode; Need lay the corresponding soft mode of position of sound production of soft mode at skeleton or reinforcement blank;
5, encapsulated vacuum bag guarantees that positioner is positioned at outside the vacuum bag, and vacuumizes;
6, the wing root crossbeam is installed on the end face of the outside of all wing root locators; The wing tip crossbeam is installed on the end face of the outside of all wing tip locators; Wing root locator and wing root crossbeam are located through wing root crossbeam pin hole on the outer face of all wing root locator two parallel riser I and the wing root crossbeam pin hole on the wing root crossbeam with wing root crossbeam pin, and the wing root crossbeam screwed hole that passes through on the outer face of all wing root locator two parallel riser I with the wing root transom bolt is connected fastening with the wing root crossbeam wing root locator with wing root transom bolt hole on the wing root crossbeam; Wing tip locator and wing tip crossbeam are located through wing tip crossbeam pin hole on the outer face of all wing tip locator two parallel riser II and the wing tip crossbeam pin hole on the wing tip crossbeam with wing tip crossbeam pin, and the wing tip crossbeam screwed hole that passes through on the outer face of all wing tip locator two parallel riser II with the wing tip transom bolt is connected fastening with the wing tip crossbeam wing tip locator with wing tip transom bolt hole on the wing tip crossbeam;
7, keep any skeleton or reinforcement to solidify the wing root locator at mould two ends and the annexation of wing tip locator and covering mould, remove wing root locator that wing root locator that remaining skeleton or reinforcement solidify the mould two ends is connected with the covering mould and pin and pin and wing tip locator set bolt with the wing tip locator that wing root locator set bolt and wing tip locator are connected with the covering mould.
Advantage of the present invention is: when having eliminated the moulding of composite integral panel, because the skeleton of the composite integral panel that metal skin mould and composite material skin thermal expansion coefficient difference bring or the position deviation of reinforcement; Satisfy the assembly coordination requirement between composite aerofoil integrated member and other member, improved assembly quality.
Description of drawings
Fig. 1 is the generalized section of composite aerofoil integrated member typical structure.Last figure among Fig. 1 is the composite aerofoil integrated member that is made up of skeleton and following covering, and chain-dotted line is represented the last covering of aerofoil, is up and down skeleton between the covering, and skeleton and last covering be mechanical connection separately.Figure below among Fig. 1 is the composite aerofoil integrated member that is made up of reinforcement and following covering, and following is reinforcement above the covering.
Fig. 2 is a structural representation of the present invention.
Fig. 3 is before the wing root crossbeam 5 of positioning tool of the present invention is installed, the assembling sketch map of wing root linkage section 4 and wing root locator 3.
Fig. 4 is the perspective view of wing root locator 3 among the present invention.
Fig. 5 is the sketch map that a kind of skeleton or reinforcement solidify mould among the present invention, and wherein 2a is the wing root connecting plate, and 2b is the wing tip connecting plate.
Fig. 6 is the structural representation of wing root linkage section 4 and wing tip linkage section 7 among the present invention.
Fig. 7 is that wing root linkage section 4 solidifies the sketch map after mould 2 is connected with wing tip linkage section 7 with skeleton or reinforcement.
Fig. 8 is the structural representation of wing root crossbeam 5 and wing tip crossbeam 8 among the present invention.
Fig. 9 is structure and mold shape, the position view of composite aerofoil integrated member among the embodiment 1.
Figure 10 is structure and mold shape, the position view of composite aerofoil integrated member among the embodiment 2.
The specific embodiment
Explain further details in the face of the present invention down.Referring to Fig. 2; The positioning tool of a kind of composite aerofoil integrated member skeleton or reinforcement; Comprise that the covering mould 1 that steel are made solidifies mould 2 with skeleton or reinforcement, has skin-covering face, the covering that uncured covering blank is arranged or solidify on covering mould 1 on skin-covering face; On the covering of uncured covering blank or curing, be arranged with the curing mould 2 that has skeleton or reinforcement blank, the quantity and the position of skeleton or reinforcement curing mould 2 are confirmed by composite aerofoil integrated member drawing; It is characterized in that: on the covering mould 1 beyond vertical two ends of covering mould 1, the skin-covering face, respectively have a skeleton or reinforcement to solidify the mould positioner; Positioner in abutting connection with skin-covering face wing root one side is the wing root positioner, is the wing tip positioner in abutting connection with the positioner of skin-covering face wing tip one side; The wing root positioner is connected to form by several wing root positioning components and a wing root crossbeam 5; The quantity of wing root positioning component is identical with the quantity that skeleton or reinforcement solidify mould 2, and each wing root positioning component is made up of wing root locator 3, wing root linkage section 4, wing root locator set bolt, wing root locator pin, wing root linkage section bolt and wing root linkage section pin; Referring to Fig. 4; Wing root locator 3 by a base plate 3a, vertically with base plate 3a upper surface be connected to two riser 3b and baffle plate 3c whole, that be parallel to each other and constitute; Baffle plate 3c is between two riser 3b, near the outward flange of two riser 3b; Baffle plate 3c is vertical with base plate 3a with riser 3b respectively, and baffle plate 3c is fixed on the base plate 3a through baffle plate bolt and baffle plate pin; Referring to Fig. 3, the height of two riser 3b of wing root locator 3 is more preferably greater than the height of wing root linkage section 4; Its benefit is: because in the high-temperature molding process; Can produce relative displacement between the wing root locator 3 of removal wing root locator pin and wing root locator set bolt and the covering mould 1; Between two riser 3b of wing root locator 3 and the wing root linkage section 4 fit in the plane; The deflection that can not cause skeleton or reinforcement to solidify mould, thus Forming Quality guaranteed.
Wing root locator fixed bolt hole and wing root locator pin hole is arranged on the base plate 3a; There are corresponding wing root locator retaining thread hole and wing root locator pin hole in corresponding position on covering mould 1; Through wing root locator set bolt and wing root locator pin wing root locator 3 is fixed on the covering mould 1, the material of wing root locator 3 is identical with the material of covering mould 1; Referring to Fig. 6; Wing root linkage section 4 is cuboids, and the inner face of wing root linkage section 4 is connected with the wing root end that skeleton or reinforcement solidify mould 2, referring to Fig. 5; Wing root end at skeleton or reinforcement curing mould 2 has a wing root connecting plate 2a; The inner face of wing root linkage section 4 is connected to integral body through wing root linkage section bolt and wing root linkage section pin with wing root connecting plate 2a, the outer end of wing root linkage section 4 between two riser 3b, the outer end of wing root linkage section 4 and two riser 3b matched in clearance; The inner surface of the outer face of wing root linkage section 4 and baffle plate 3c is fitted, and the material of wing root linkage section 4 is identical with the material of covering mould 1; Referring to Fig. 8; Wing root crossbeam 5 is long slabs; It is positioned at the outside of wing root locator 3; Fit in the outer face of the riser 3b of the inner surface of wing root crossbeam 5 and all wing root locators 3; Wing root crossbeam screwed hole and wing root crossbeam pin hole are arranged on the outer face of wing root locator 3 riser 3b, on the wing root crossbeam 5 with riser 3b outer face on wing root crossbeam screwed hole and the corresponding position of wing root crossbeam pin hole corresponding wing root transom bolt hole and wing root crossbeam pin hole are arranged, through wing root transom bolt and wing root crossbeam pin wing root crossbeam 5 is fixed on the outer face of riser 3b of all wing root locators 3; Wing root crossbeam 5 is made by thermal coefficient of expansion and composite material skin identical materials;
The wing tip positioner is connected to form by several wing tip positioning components and a wing tip crossbeam 8; The quantity of wing tip positioning component is identical with the quantity that skeleton or reinforcement solidify mould 2, and each wing tip positioning component is made up of wing tip locator 6, wing tip linkage section 7, wing tip locator set bolt, wing tip locator pin, wing tip linkage section bolt and wing tip linkage section pin; Wing tip locator 6 is connected to two riser 3b whole, that be parallel to each other and constitutes with vertical with base plate 3a upper surface by a base plate 3a; Identical with wing root locator 3, the height of 6 two riser 3b of wing tip locator is more preferably greater than the height of wing tip linkage section 7; Wing tip locator fixed bolt hole and wing tip locator pin hole is arranged on the base plate 3a; There are corresponding wing tip locator retaining thread hole and wing tip locator pin hole in corresponding position on covering mould 1; Through wing tip locator set bolt and wing tip locator pin wing tip locator 6 is fixed on the covering mould 1, the material of wing tip locator 6 is identical with the material of covering mould 1; Referring to Fig. 6; Wing tip linkage section 7 is cuboids; The tip end that the inner face of wing tip linkage section 7 and skeleton or reinforcement solidify mould 2 is connected, referring to Fig. 5, in the tip end of skeleton or reinforcement curing mould 2 a wing tip connecting plate 2b is arranged; The inner face of wing tip linkage section 7 is connected to integral body through wing tip linkage section bolt and wing tip linkage section pin with wing tip connecting plate 2b; The outer end of wing tip linkage section 7 between two riser 3b, the outer end of wing tip linkage section 7 and two riser 3b matched in clearance, the material of wing tip linkage section 7 is identical with the material of covering mould 1; Referring to Fig. 8; Wing tip crossbeam 8 is long slabs; It is positioned at the outside of wing tip locator 6; Fit in the outer face of the riser 3b of the inner surface of wing tip crossbeam 8 and all wing tip locators 6; Wing tip crossbeam screwed hole and wing tip crossbeam pin hole are arranged on the outer face of wing tip locator 6 riser 3b, on the wing tip crossbeam 8 with riser 3b outer face on wing tip crossbeam screwed hole and the corresponding position of wing tip crossbeam pin hole corresponding wing tip transom bolt hole and wing tip crossbeam pin hole are arranged, through wing tip transom bolt and wing tip crossbeam pin wing tip crossbeam 8 is fixed on the outer face of riser 3b of all wing tip locators 6; Wing tip crossbeam 8 is made by thermal coefficient of expansion and composite material skin identical materials.
The method for using of positioning tool as described above is characterized in that, the step of use is following:
1, on the covering mould 1 that has good covering blank of laying or curing back covering, wing root locator 3 and wing tip locator 6 are installed; On covering mould 1, wing root locator 3 and wing tip locator 6 are located by connecting with wing root locator pin and wing tip locator pin respectively, and fastening with wing root locator set bolt and wing tip locator set bolt;
2,, wing root linkage section 4 and wing tip linkage section 7 and skeleton or reinforcement are solidified mould 2 assemblings be connected referring to Fig. 7; The wing root connecting plate 2a that all wing root linkage sections 4 and wing tip linkage section 7 and corresponding skeleton or reinforcement are solidified on the mould 2 is connected the location with wing root linkage section pin with wing tip linkage section pin respectively with wing tip connecting plate 2b, with wing root linkage section bolt and wing tip linkage section bolted;
3, skeleton or reinforcement solidify the location of mould 2; Skeleton or the reinforcement that will have skeleton or a reinforcement blank solidify the wing root linkage section 4 of mould 2 through two ends and wing tip linkage section 7 respectively with the wing root locator 3 and 6 assemblings of wing tip locator at two ends; Guarantee the outer face of wing root linkage section 4 and the baffle plate 3c inner surface applying location of wing root locator 3; The two sides of wing root linkage section 4 cooperate the location with the medial surface of two parallel riser 3b of wing root locator 3, and the two sides of wing tip linkage section 7 cooperate the location with the medial surface of two parallel riser 3b of wing tip locator 6; Skeleton or the reinforcement that has skeleton or a reinforcement blank solidify mould 2 for skeleton or reinforcement blank and skeleton or reinforcement curing mould 2 during by its moulding the relative position of each other fit together;
4, lay soft mode; Need lay the corresponding soft mode of position of sound production of soft mode at skeleton or reinforcement blank; The position that need lay soft mode is positioned at skeleton or the reinforcement blank does not solidify the side that mould 2 is fitted with skeleton or reinforcement, solidifies mould 2 moulding skeleton or reinforcements with skeleton or reinforcement;
5, encapsulated vacuum bag guarantees that positioner is positioned at outside the vacuum bag, and vacuumizes;
6, wing root crossbeam 5 is installed on the end face of the outside of all wing root locators 3; Wing tip crossbeam 8 is installed on the end face of the outside of all wing tip locators 6; With wing root crossbeam pin through the wing root crossbeam pin hole on wing root crossbeam pin hole on the outer face of 3 liang of parallel riser 3b of all wing root locators and the wing root crossbeam 5 with wing root locator 3 and wing root crossbeam 5 location, and the wing root crossbeam screwed hole that passes through on the outer face of 3 liang of parallel riser 3b of all wing root locators with the wing root transom bolt is connected fastening with wing root crossbeam 5 wing root locator 3 with wing root transom bolt hole on the wing root crossbeam 5; With wing tip crossbeam pin through the wing tip crossbeam pin hole on wing tip crossbeam pin hole on the outer face of 6 liang of parallel riser 3b of all wing tip locators and the wing tip crossbeam 8 with wing tip locator 6 and wing tip crossbeam 8 location, and the wing tip crossbeam screwed hole that passes through on the outer face of 6 liang of parallel riser 3b of all wing tip locators with the wing tip transom bolt is connected fastening with wing tip crossbeam 8 wing tip locator 6 with wing tip transom bolt hole on the wing tip crossbeam 8;
7, the annexation that keeps any skeleton or reinforcement to solidify wing root locator 3 and wing tip locator 6 with the covering mould 1 at mould 2 two ends is removed wing root locator that wing root locator 3 that remaining skeleton or reinforcement solidify mould 2 two ends is connected with covering mould 1 and is pinned and pin and wing tip locator set bolt with the wing tip locator that wing root locator set bolt and wing tip locator 6 are connected with covering mould 1.
Operation principle of the present invention is: the positioning component that adopts the plane to cooperate has guaranteed positioning accuracy; Adopt crossbeam with composite thermal coefficient of expansion same material; When having eliminated the moulding of composite integral panel, because the skeleton of the composite integral panel that metal skin mould and composite material skin thermal expansion coefficient difference bring or the position deviation of reinforcement through crossbeam and the synchronous heat expansion of covering; Thereby well guarantee to solidify the positional precision of back skeleton and reinforcement; Satisfy the assembly coordination requirement between composite aerofoil integrated member and other member, improved assembly quality.
Embodiment one
1, a kind of up and down composite aerofoil integrated member of covering that has is at composite
the type skeleton that has 5 to be fitted and connected with covering up and down up and down between the covering; The positioning tool of composite aerofoil integrated member skeleton; Comprise that covering mould and 5 skeletons that 1 steel is made solidify mould; What skeleton solidified mould is shaped as
shape; Skeleton solidifies the outside that mould is positioned at
type skeleton; The inboard of each
type skeleton be [the shape soft mode, one has 5 soft modes; On the covering mould, skin-covering face is arranged, uncured covering blank is arranged on skin-covering face, on uncured covering blank, be arranged with 5 curing moulds that have the skeleton blank; By 5 wing root positioners and 5 wing tip positioners; The wing root positioner is connected to form by 5 wing root positioning components and 1 wing root crossbeam, and each wing root positioning component is made up of 1 wing root locator, 1 wing root linkage section, 4 wing root locator set bolts, 4 wing root locator pins, 4 wing root linkage section bolts and 4 wing root linkage section pins; The wing tip positioner is connected to form by 4 wing tip positioning components and 1 wing tip crossbeam, and each wing tip positioning component is made up of 1 wing tip locator, 1 wing tip linkage section, 4 wing tip locator set bolts, 4 wing tip locator pins, 4 wing tip linkage section bolts and 4 wing tip linkage section pins; Through wing root locator set bolt, wing root locator pin and wing tip locator set bolt, wing tip locator pin wing root locator and wing tip locator are fixed on the covering mould, the material of wing root locator and wing tip locator is a steel; One has 5 wing root linkage sections and 5 wing tip linkage sections, and the material of wing root linkage section and wing tip linkage section is a steel; 1 wing root crossbeam and 1 wing tip crossbeam are arranged, and the material of wing root crossbeam and wing tip crossbeam is a composite material laminated board, and the thickness of laminate is 15mm.
The use step of above-mentioned positioning tool is following:
1, wing root locator and wing tip locator are installed on the covering mould that has the good covering blank of laying;
2, wing root linkage section and wing tip linkage section and skeleton being solidified the mould assembling is connected; Utilize the blank of laying mould difference laying
the type skeleton of
type skeleton; And it is taken off, the combination pre-determined bit is to the covering blank;
3, the installing and locating skeleton solidifies mould; With skeleton solidify mould through wing root linkage section and wing tip linkage section installing and locating to the covering mould that has uncured covering blank, with
type skeleton blank and its combination and location;
4, lay soft mode; Put into corresponding soft mode and fixing in the inboard of
type skeleton blank;
5, encapsulated vacuum bag guarantees that positioner is positioned at outside the vacuum bag, and vacuumizes;
6, the wing root crossbeam is installed on the end face of the outside of all wing root locators; The wing tip crossbeam is installed on the end face of the outside of all wing tip locators;
7, the skeleton in the middle of keeping solidifies the wing root locator at mould two ends and the annexation of wing tip locator and covering mould, removes wing root locator that wing root locator that remaining skeleton solidifies the mould two ends is connected with the covering mould and pins and pin and wing tip locator set bolt with the wing tip locator that wing root locator set bolt and wing tip locator are connected with the covering mould.
Embodiment two
A kind of down composite aerofoil integral panel of covering that has only has 10 composite T type reinforcements that are fitted and connected with following covering on covering down; The positioning tool of composite aerofoil integrated member reinforcement; Comprise that covering mould and 5 reinforcements that 1 steel is made solidify mould; The cross sectional shape that reinforcement solidifies mould is a rectangle; A left side is played the I reinforcement and is solidified mould between first T type reinforcement 9 and second T type reinforcement 10, and the II reinforcement solidifies mould between the 3rd T type reinforcement 11 and the 4th T type reinforcement 12, and the III reinforcement solidifies mould between the 5th T type reinforcement 13 and the 6th T type reinforcement 14; The IV reinforcement solidifies mould between the 7th T type reinforcement 15 and the 8th T type reinforcement 16; The V reinforcement solidifies mould between the 9th T type reinforcement 17 and the tenth T type reinforcement 18, and all T type reinforcements do not solidify the side that mould fits with reinforcement and are not provided with L type soft mode, and one has 10 L type soft modes; On the covering mould, skin-covering face is arranged, covering is arranged on skin-covering face, on covering, be arranged with 5 curing moulds that have the reinforcement blank; By 5 wing root positioners and 5 wing tip positioners; The wing root positioner is connected to form by 5 wing root positioning components and 1 wing root crossbeam, and each wing root positioning component is made up of 1 wing root locator, 1 wing root linkage section, 4 wing root locator set bolts, 4 wing root locator pins, 4 wing root linkage section bolts and 4 wing root linkage section pins; The wing tip positioner is connected to form by 5 wing tip positioning components and 1 wing tip crossbeam, and each wing tip positioning component is made up of 1 wing tip locator, 1 wing tip linkage section, 4 wing tip locator set bolts, 4 wing tip locator pins, 4 wing tip linkage section bolts and 4 wing tip linkage section pins; Through wing root locator set bolt, wing root locator pin and wing tip locator set bolt, wing tip locator pin wing root locator and wing tip locator are fixed on the covering mould, the material of wing root locator and wing tip locator is a steel; One has 5 wing root linkage sections and 5 wing tip linkage sections, and the material of wing root linkage section and wing tip linkage section is a steel; 1 wing root crossbeam and 1 wing tip crossbeam are arranged, and the material of wing root crossbeam and wing tip crossbeam is the INVAR alloy;
The use step of above-mentioned positioning tool is following:
1, having installation wing root locator and wing tip locator on the covering mould of covering;
2, wing root linkage section and wing tip linkage section and reinforcement being solidified the mould assembling is connected; Utilize reinforcement to solidify the side T type reinforcement blank shop layer of mould laying and its applying, utilize the T type reinforcement blank shop layer of laying mould laying opposite side, and it is taken off from the laying mould;
3, the installing and locating reinforcement solidifies mould; The reinforcement that will have a reinforcement blank shop layer solidify mould through wing root linkage section and wing tip linkage section installing and locating to the covering mould that has covering, and T type reinforcement blank shop layer and its combination of opposite side fixed;
4, lay soft mode; The T type reinforcement blank shop layer that L type soft mode is placed to the opposite side of T type reinforcement is gone up and is fixed;
5, encapsulated vacuum bag guarantees that positioner is positioned at outside the vacuum bag, and vacuumizes;
6, the wing root crossbeam is installed on the end face of the outside of all wing root locators; The wing tip crossbeam is installed on the end face of the outside of all wing tip locators;
7, keep the I reinforcement to solidify the wing root locator at mould two ends and the annexation of wing tip locator and covering mould, remove wing root locator that wing root locator that remaining reinforcement solidifies the mould two ends is connected with the covering mould and pin and pin and wing tip locator set bolt with the wing tip locator that wing root locator set bolt and wing tip locator are connected with the covering mould.
Claims (2)
1. the positioning tool of composite aerofoil integrated member skeleton or reinforcement; Comprise covering mould [1] and skeleton or reinforcement curing mould [2] that steel are made; On covering mould [1], skin-covering face is arranged; The covering that uncured covering blank is arranged on skin-covering face or solidify is arranged with the curing mould [2] that has skeleton or reinforcement blank on the covering of uncured covering blank or curing, the quantity and the position of skeleton or reinforcement curing mould [2] are confirmed by composite aerofoil integrated member drawing; It is characterized in that: on the covering mould beyond vertical two ends of covering mould [1], the skin-covering face, respectively have a skeleton or reinforcement to solidify the mould positioner; Positioner in abutting connection with skin-covering face wing root one side is the wing root positioner, is the wing tip positioner in abutting connection with the positioner of skin-covering face wing tip one side; The wing root positioner is connected to form by several wing root positioning components and a wing root crossbeam [5]; The quantity of wing root positioning component is identical with the quantity that skeleton or reinforcement solidify mould [2], and each wing root positioning component is made up of wing root locator [3], wing root linkage section [4], wing root locator set bolt, wing root locator pin, wing root linkage section bolt and wing root linkage section pin; Wing root locator [3] by a base plate I, vertically with base plate I upper surface be connected to two riser I and baffle plate [3c] whole, that be parallel to each other and constitute; Baffle plate [3c] is between two riser I, near the outward flange of two riser I; Baffle plate [3c] is vertical with base plate I with riser I respectively, and baffle plate [3c] is fixed on the base plate I through baffle plate bolt and baffle plate pin; Wing root locator fixed bolt hole and wing root locator pin hole is arranged on the base plate I; Go up corresponding position at covering mould [1] corresponding wing root locator retaining thread hole and wing root locator pin hole are arranged; Through wing root locator set bolt and wing root locator pin wing root locator [3] is fixed on the covering mould [1], the material of wing root locator [3] is identical with the material of covering mould [1]; Wing root linkage section [4] is a cuboid; The inner face of wing root linkage section [4] is connected with the wing root end that skeleton or reinforcement solidify mould [2]; Wing root end at skeleton or reinforcement curing mould [2] has a wing root connecting plate [2a]; The inner face of wing root linkage section [4] is connected to integral body through wing root linkage section bolt and wing root linkage section pin with wing root connecting plate [2a], the outer end of wing root linkage section [4] between two riser I, the outer end of wing root linkage section [4] and two riser I matched in clearance; The inner surface of the outer face of wing root linkage section [4] and baffle plate [3c] is fitted, and the material of wing root linkage section [4] is identical with the material of covering mould [1]; Wing root crossbeam [5] is a long slab; It is positioned at the outside of wing root locator [3]; Fit in the outer face of the riser I of the inner surface of wing root crossbeam [5] and all wing root locators [3]; Wing root crossbeam screwed hole and wing root crossbeam pin hole are arranged on the outer face of wing root locator [3] riser I; Wing root crossbeam [5] go up with riser I outer face on wing root crossbeam screwed hole and the corresponding position of wing root crossbeam pin hole corresponding wing root transom bolt hole and wing root crossbeam pin hole are arranged, pinning through wing root transom bolt and wing root crossbeam is fixed on wing root crossbeam [5] on the outer face of riser I of all wing root locators [3]; Wing root crossbeam [5] is made by thermal coefficient of expansion and composite material skin identical materials;
The wing tip positioner is connected to form by several wing tip positioning components and a wing tip crossbeam [8]; The quantity of wing tip positioning component is identical with the quantity that skeleton or reinforcement solidify mould [2], and each wing tip positioning component is made up of wing tip locator [6], wing tip linkage section [7], wing tip locator set bolt, wing tip locator pin, wing tip linkage section bolt and wing tip linkage section pin; Wing tip locator [6] is connected to two riser II whole, that be parallel to each other and constitutes with vertical with base plate II upper surface by a base plate II; Wing tip locator fixed bolt hole and wing tip locator pin hole is arranged on the base plate II; Go up corresponding position at covering mould [1] corresponding wing tip locator retaining thread hole and wing tip locator pin hole are arranged; Through wing tip locator set bolt and wing tip locator pin wing tip locator [6] is fixed on the covering mould [1], the material of wing tip locator [6] is identical with the material of covering mould [1]; Wing tip linkage section [7] is a cuboid; The inner face of wing tip linkage section [7] is connected with the tip end that skeleton or reinforcement solidify mould [2]; Tip end at skeleton or reinforcement curing mould [2] has a wing tip connecting plate [2b]; The inner face of wing tip linkage section [7] is connected to integral body through wing tip linkage section bolt and wing tip linkage section pin with wing tip connecting plate [2b]; The outer end of wing tip linkage section [7] between two riser II, the outer end of wing tip linkage section [7] and two riser II matched in clearance, the material of wing tip linkage section [7] is identical with the material of covering mould [1]; Wing tip crossbeam [8] is a long slab; It is positioned at the outside of wing tip locator [6]; Fit in the outer face of the riser II of the inner surface of wing tip crossbeam [8] and all wing tip locators [6]; Wing tip crossbeam screwed hole and wing tip crossbeam pin hole are arranged on the outer face of wing tip locator [6] riser II; Wing tip crossbeam [8] go up with riser II outer face on wing tip crossbeam screwed hole and the corresponding position of wing tip crossbeam pin hole corresponding wing tip transom bolt hole and wing tip crossbeam pin hole are arranged, pinning through wing tip transom bolt and wing tip crossbeam is fixed on wing tip crossbeam [8] on the outer face of riser II of all wing tip locators [6]; Wing tip crossbeam [8] is made by thermal coefficient of expansion and composite material skin identical materials.
2. the method for using of positioning tool as claimed in claim 1 is characterized in that, the step of use is following:
2.1, go up at the covering mould [1] that has the good covering blank of laying or solidify the back covering wing root locator [3] and wing tip locator [6] be installed; Upward wing root locator [3] and wing tip locator [6] are located by connecting with wing root locator pin and wing tip locator pin respectively at covering mould [1], and fastening with wing root locator set bolt and wing tip locator set bolt;
2.2, wing root linkage section [4] and wing tip linkage section [7] and skeleton or reinforcement solidified mould [2] assembling be connected; The wing root connecting plate [2a] that all wing root linkage sections [4] and wing tip linkage section [7] and corresponding skeleton or reinforcement are solidified on the mould [2] is connected the location with wing root linkage section pin with wing tip linkage section pin respectively with wing tip connecting plate [2b], with wing root linkage section bolt and wing tip linkage section bolted;
2.3, skeleton or the reinforcement location of solidifying mould [2]; Skeleton or the reinforcement that will have skeleton or a reinforcement blank solidifies the wing root linkage section [4] of mould [2] through two ends and wing tip linkage section [7] and assembles with the wing root locator [3] and the wing tip locator [6] at two ends respectively; Guarantee the outer face of wing root linkage section [4] and baffle plate [3c] the inner surface applying location of wing root locator [3]; The two sides of wing root linkage section [4] cooperate the location with the medial surface of two parallel riser I of wing root locator [3], and the two sides of wing tip linkage section [7] cooperate the location with the medial surface of two parallel riser II of wing tip locator [6];
2.4, lay soft mode; Need lay the corresponding soft mode of position of sound production of soft mode at skeleton or reinforcement blank;
2.5, the encapsulated vacuum bag, guarantee that positioner is positioned at outside the vacuum bag, and vacuumize;
2.6, wing root crossbeam [5] is installed on the outside end face of all wing root locators [3]; Wing tip crossbeam [8] is installed on the outside end face of all wing tip locators [6]; Wing root locator [3] and wing root crossbeam [5] are located through wing root crossbeam pin hole on the outer face of all wing root locator [3] two parallel riser I and the wing root crossbeam pin hole on the wing root crossbeam [5] with wing root crossbeam pin, and the wing root crossbeam screwed hole that passes through on the outer face of all wing root locator [3] two parallel riser I with the wing root transom bolt is connected fastening with wing root crossbeam [5] wing root locator [3] with wing root transom bolt hole on the wing root crossbeam [5]; Wing tip locator [6] and wing tip crossbeam [8] are located through wing tip crossbeam pin hole on the outer face of all wing tip locator [6] two parallel riser II and the wing tip crossbeam pin hole on the wing tip crossbeam [8] with wing tip crossbeam pin, and the wing tip crossbeam screwed hole that passes through on the outer face of all wing tip locator [6] two parallel riser II with the wing tip transom bolt is connected fastening with wing tip crossbeam [8] wing tip locator [6] with wing tip transom bolt hole on the wing tip crossbeam [8];
2.7, keep any skeleton or reinforcement to solidify the wing root locator [3] and the annexation of wing tip locator [6] at mould [2] two ends with covering mould [1], remove wing root locator that wing root locator [3] that remaining skeleton or reinforcement solidify mould [2] two ends is connected with covering mould [1] and pin and pin and wing tip locator set bolt with the wing tip locator that wing root locator set bolt and wing tip locator [6] are connected with covering mould [1].
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110085587A CN102179782B (en) | 2011-04-07 | 2011-04-07 | Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201110085587A CN102179782B (en) | 2011-04-07 | 2011-04-07 | Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102179782A CN102179782A (en) | 2011-09-14 |
| CN102179782B true CN102179782B (en) | 2012-09-05 |
Family
ID=44566172
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201110085587A Active CN102179782B (en) | 2011-04-07 | 2011-04-07 | Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN102179782B (en) |
Families Citing this family (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102423910B (en) * | 2011-11-15 | 2013-09-11 | 中国航空工业集团公司北京航空制造工程研究所 | Co-curing molding die for composite material with wallboard structure |
| CN103640231B (en) * | 2013-12-17 | 2016-02-10 | 沈阳飞机工业（集团）有限公司 | Composite vacuum bag external position device and localization method thereof |
| CN103817957B (en) * | 2014-03-17 | 2016-01-13 | 沈阳飞机工业（集团）有限公司 | The tool locating method of adhesive bonding of composites co-curing |
| CN105904721B (en) * | 2016-06-08 | 2017-10-24 | 江苏恒神股份有限公司 | Standardize equipment cabin of motor train unit carbon fibre composite crossbeam assembly tooling and method |
| CN108237494B (en) * | 2017-04-27 | 2020-12-29 | 浙江大学 | Wing root rib positioning device |
| CN112810165B (en) * | 2020-12-24 | 2022-09-20 | 中国航空制造技术研究院 | Combined tool for molding, assembling and positioning composite material part and design method |
| CN114770998B (en) * | 2022-04-06 | 2023-10-03 | 航天海鹰(镇江)特种材料有限公司 | End packaging method for slender flexible mold assisted forming type beam |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4894903A (en) * | 1988-07-06 | 1990-01-23 | The Boeing Company | Assembly jig and method for making wing panels |
| CN1213998A (en) * | 1996-03-22 | 1999-04-14 | 波音公司 | Determinant wing assembly |
| EP1216816A1 (en) * | 2000-12-22 | 2002-06-26 | Fuji Jukogyo Kabushiki Kaisha | Composite material stiffened panel and manufacturing method thereof |
| CN101791821A (en) * | 2010-04-08 | 2010-08-04 | 中国航空工业集团公司北京航空制造工程研究所 | Forming equipment of large size composite stringer |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2004025946A (en) * | 2002-06-24 | 2004-01-29 | Honda Motor Co Ltd | Wing structure of aircraft |
-
2011
- 2011-04-07 CN CN201110085587A patent/CN102179782B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4894903A (en) * | 1988-07-06 | 1990-01-23 | The Boeing Company | Assembly jig and method for making wing panels |
| CN1213998A (en) * | 1996-03-22 | 1999-04-14 | 波音公司 | Determinant wing assembly |
| EP1216816A1 (en) * | 2000-12-22 | 2002-06-26 | Fuji Jukogyo Kabushiki Kaisha | Composite material stiffened panel and manufacturing method thereof |
| CN101791821A (en) * | 2010-04-08 | 2010-08-04 | 中国航空工业集团公司北京航空制造工程研究所 | Forming equipment of large size composite stringer |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102179782A (en) | 2011-09-14 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN102179782B (en) | Locating tool for frameworks/reinforced ribs of integrated composite-material wing structural member and application method of locating tool | |
| CN106182805B (en) | A kind of manufacturing process of the isometrical tubular structure of carbon fibre composite | |
| CN102019592B (en) | Positioning apparatus for shaping large-size stiffened panel made of composite material | |
| CN103407175B (en) | A kind of integral forming method of fiber-reinforced resin matrix compound material wing box | |
| US9096021B2 (en) | Method and shaping device for producing a composite fiber component for air and space travel | |
| CN102909866A (en) | Method for forming control of long joist axial line of composite material stiffened wall panel | |
| CN104626605A (en) | Composite material wing integral molding technological method and composite material wing integral molding tool | |
| CN110815856A (en) | Soft die manufacturing method for forming I-beam composite material part and application thereof | |
| CN103921450A (en) | Manufacturing method of wing-body integrated honeycomb sandwiched composite material skin | |
| US11584094B2 (en) | Composite material inlay in additively manufactured structures | |
| CN103370186A (en) | Process for manufacturing composite material products, as well as products manufactured with this process | |
| CN101448627A (en) | Method for manufacturing composite structure by retractable die | |
| CN101743117A (en) | Make the mould and the method for aircraft ring frames with composite | |
| CN105269721B (en) | Box-shaped closed-angle structure composite material part forming die | |
| CN103496180B (en) | Composite material E-shaped frame mould and forming method thereof | |
| CN108688194A (en) | Composite material drum Material Stiffened Panel solidifying and molding device and forming method | |
| CN106313586A (en) | Molding tool for composite of closed angle structure | |
| CN106985413B (en) | A kind of forming frock for foam core filled composite material structure winglet | |
| CN108568974A (en) | A kind of closed type composite element forming frock and application method | |
| US10836120B2 (en) | Hybrid composite structures with integrated 3-D printed elements | |
| CN102806617A (en) | Die for integrally forming I-shaped reinforcement composite material wall plate | |
| CN102848498A (en) | Mold for integrally molding J-shaped reinforced composite material wall plate | |
| CN110281547A (en) | A method of realizing deep camber Ω type Material Stiffened Panel co-curing | |
| CN105252790A (en) | Composite material forming mould | |
| JP5564233B2 (en) | Resin casting mold and its manufacturing method |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |