Tooling structure integrally shared by flaperon forming, cementing and assembling

Abstract

The utility model discloses a tooling structure integrally shared by forming, cementing and assembling a flaperon. The flaperon consists of an upper skin, a bearing structure and a lower skin, the force bearing structure comprises a main force bearing frame, flaperon end ribs arranged at the two ends of the main force bearing frame, a plurality of flaperon sub-ribs and flaperon honeycomb sections, the flaperon sub-ribs and the flaperon honeycomb sections are arranged in the main force bearing frame, and a plurality of flaperon connectors are further arranged on the main force bearing frame; the tool structure comprises a bottom frame; the mold body is arranged on the bottom frame, the mold body is provided with a forming face used for forming an upper skin and a lower skin in a paving mode, and the mold body is further detachably provided with a main force bearing frame positioning module, an end rib positioning module and a plurality of connector positioning modules.

Description

TECHNICAL FIELD

[0001] The utility model relates to the field of composite material forming technology, and specifically relates to a tool structure for forming, gluing and assembling flaperon integrally. BACKGROUND

[0002] The flap section is a main component of the high-lift system of an airplane, which plays a very important role in the takeoff, landing and cruising flight of the airplane, can effectively improve the lift during takeoff and the lift-drag ratio during landing, thereby effectively shortening the takeoff and taxiing distance of the airplane and improving the performance of the airplane. The aileron section and the elevator section are key components of the main control system of the airplane, and the pilot controls the differential deflection of the left and right ailerons to generate a roll moment, so that the airplane performs a roll maneuver.

[0003] At present, the traffic equipment such as airplanes, ships and automobiles gradually presents a trend of lightweight development, and a large amount of composite materials are used. The latest generation of wide-body passenger planes use a large amount of advanced lightweight materials, especially the proportion of the use of composite materials is further increased, and becomes the main material of the airframe structure (for example, the use amount of composite materials of Boeing 787 accounts for 50% of the structure weight of the airplane, and A350XWB also accounts for as high as 20%), and the use of composite materials significantly reduces the structure weight of the airplane. The overall forming of large composite materials can reduce the number of parts and fasteners, thereby achieving the purpose of weight reduction, and also effectively reducing the cost.

[0004] The co-curing, co-bonding and secondary bonding process is the most basic method of overall forming of composite materials, and is also the main technical approach to reduce the weight and cost of composite materials. The flaperon and other composite material sections are indispensable important components of the high-lift system and the main control system of the airplane, and with the reduction of the cost of composite materials, it is very necessary to study the key technology of low-cost and rapid forming of composite material sections. The co-curing, co-bonding and secondary bonding process is the most basic method of overall forming of composite materials, and is also the main technical approach to reduce the cost and weight of composite materials. Among them, ① the co-curing forming process refers to a process method in which different composite parts are simultaneously bonded and cured in one curing; ② the co-bonding refers to a process method in which one or more parts that have been cured and formed are bonded to an integral part with another part that has not been cured through an adhesive in one curing; and ③ the secondary bonding process refers to a process in which different composite parts that have been cured are bonded again through an adhesive.

[0005] However, the composite sandwich structure formed by co-curing is difficult to control the internal quality of the skin due to the honeycomb core, and the skin forming pressure cannot be too high and the pressure distribution is uneven; and the composite section structure formed by co-bonding is prone to shrinkage and collapse of the core due to the early curing of the lower skin, and is not conducive to quality control. Therefore, based on the product quality and the complexity of the structure, the composite flap vane forming needs to select a secondary bonding forming method for the forming and bonding assembly of the flap vane, but the secondary bonding form is limited by step curing and high cost, so in order to reduce the cost of composite flap vane product manufacturing, a structure form of a set of tooling for composite forming, bonding and assembly is planned. Practical new type content

[0006] The utility model discloses a kind of tooling structures of flap vane forming bonding assembly integrated commonly, to solve the above problems.

[0007] To achieve the above object, the utility model is realized by the following technical solutions:

[0008] The utility model discloses a kind of tooling structures of flap vane forming bonding assembly integrated commonly, to solve the above problems.

[0009] The tooling structure includes:

[0010] Bottom frame, which facilitates the hot air to form a stable and uniform temperature gradient field to make curing more stable, and the side is provided with a furnace test plate area to facilitate the placement and curing of the furnace test plate;

[0011] And mold main body, it is set on the bottom frame, the mold main body has forming surface for laying and forming upper skin and lower skin on the mold main body, the mold main body is detachably provided with main load-bearing frame positioning module for positioning main load-bearing frame when cementing, end rib positioning module for positioning flap vane end rib and a plurality of joint positioning modules for facilitating the assembly of flap vane joint.

[0012] Specifically, the utility model discloses a kind of tooling structures of flap and aileron forming gluing assembly integration common, corresponding flap and aileron composite overall assembly is flap and aileron box section structure, as part of aviation main lifting system and auxiliary control system, flap and aileron box section interior is designed using full composite structure, and high-strength aluminum alloy joint (flap and aileron joint) is used to be assembled and connected using wing connection suspension point.

[0013] Further, a kind of tooling structures of flap and aileron forming gluing assembly integration common: the tooling structure further includes: end rib stress support module, which is movably arranged in the inner side of the end rib positioning module.

[0014] Preferably, the utility model is movably arranged (wandering design) in the two sides of end rib positioning module and end rib stress support module, i.e. end rib stress support module is not fixedly arranged, which can support force to flap and aileron end rib during gluing process to ensure that end rib is not deformed, and the movable arrangement of end rib stress support module can ensure stress transmission during curing process.

[0015] Further, a kind of tooling structures of flap and aileron forming gluing assembly integration common: the tooling structure further includes: a plurality of joint support modules, which are arranged on the main load-bearing frame positioning module corresponding to the position of the joint positioning module, and the joint support module is used to shield the joint positioning module but not in contact with the joint positioning module.

[0016] Preferably, the joint support module designed by the utility model can cover the joint positioning module area, facilitate curing bag during gluing process, to avoid that joint positioning module punctures vacuum bag during curing bag process, and the joint support module forms avoidance with internal joint positioning module, to prevent interference phenomenon.

[0017] Further, a kind of tooling structures of flap and aileron forming gluing assembly integration common: the tooling structure further includes: main load-bearing frame support module, which is movably arranged in the inner side of the main load-bearing frame positioning module.

[0018] Further, a kind of tooling structures of flap and aileron forming gluing assembly integration common: the main load-bearing frame support module is formed by a plurality of main load-bearing frame support sub-modules.

[0019] Preferably, the main load-bearing frame support module designed by the utility model is movably arranged, i.e. each main load-bearing frame support sub-module exists independently and moves, and the arrangement of main load-bearing frame support module can ensure that main load-bearing frame is not deformed during gluing process, while ensuring the gluing quality of main load-bearing frame and skin.

[0020] Further, a tool structure for forming, bonding and assembling the flap and aileron integrally: the main load-bearing frame positioning module comprises: a front beam positioning module and a rear beam positioning module; the front beam positioning module, the rear beam positioning module and the end rib positioning module enclose a structure matching the shape of the load-bearing structure, and a plurality of joint support modules are arranged on the front beam positioning module.

[0021] Further, a tool structure for forming, bonding and assembling the flap and aileron integrally: the front beam positioning module is formed by splicing a plurality of front beam positioning sub-modules, and a plurality of joint support modules are arranged at the splicing positions of the front beam positioning sub-modules.

[0022] Further, a tool structure for forming, bonding and assembling the flap and aileron integrally: the rear beam positioning module is formed by splicing a plurality of rear beam positioning sub-modules.

[0023] Preferably, the front and rear beam positioning modules (i.e. the main load-bearing frame positioning module) are designed to be formed by splicing a plurality of sub-modules, which can ensure the positioning of the rear edge sub-component and the straightness in the length direction, and also can ensure that each sub-module is light in weight, facilitating loading and unloading and transportation.

[0024] Further, a tool structure for forming, bonding and assembling the flap and aileron integrally: the mold body is further provided with a plurality of bolt holes and pin holes, and the main load-bearing frame positioning module, the end rib positioning module and a plurality of joint positioning modules are detachably arranged on the mold body through bolts and positioning pins.

[0025] The beneficial effects of the utility model are as follows:

[0026] The forming tool for the upper and lower skins of the flap and aileron, the tool for bonding the flap and aileron assembly and the tool required for assembling the flap and aileron joint are combined, the forming, bonding and assembling of the composite material flap and aileron product are integrally shared by the tool, the processing and manufacturing of the tool and the investment are reduced, thereby greatly reducing the cost of the tool. Meanwhile, the tool structure designed according to the utility model can complete the forming, bonding and assembling processes of the composite material flap and aileron on the same tool structure, reduces the secondary positioning step of the composite material flap and aileron product and avoids the risk of secondary positioning. BRIEF DESCRIPTION OF DRAWINGS

[0027] In order to more clearly illustrate the technical scheme of the embodiments of the utility model, the drawings required in the embodiment description will be briefly introduced as follows: obviously, the drawings in the following description are only some embodiments of the utility model, and other drawings can be obtained by those skilled in the art without creative labor on the basis of the drawings.

[0028] Figure 1 It is a structure schematic view of the composite flap of the embodiment 1 of the utility model;

[0029] Figure 2 It is a structure schematic view of the tool structure of the flap forming, gluing, assembling and integrating of the embodiment 1 of the utility model;

[0030] Figure 3 It is a schematic view of the tool structure of the embodiment 1 of the utility model not being assembled completely.

[0031] Markings in the drawing:

[0032] 1-bearing structure, 11-main bearing frame, 12-flap end rib, 13-flap sub-rib, 14-flap honeycomb section, 15-flap joint; 2-bottom frame; 3-mold main body, 31-forming surface, 32-main bearing frame positioning module, 33-end rib positioning module, 34-joint positioning module, 35-end rib stress support module, 36-joint support module, 37-main bearing frame support module, 321-front beam positioning module, 322-rear beam positioning module, 371-main bearing frame support sub-module, 3211-front beam positioning sub-module, 3221-rear beam positioning sub-module. DETAILED DESCRIPTION

[0033] The technical solutions in the embodiments of the utility model will be described clearly and completely below with reference to the drawings in the embodiments of the utility model. Obviously, the described embodiments are only part of the embodiments of the utility model, rather than all the embodiments. The description of the at least one exemplary embodiment is actually only illustrative, but not as any limitation on the utility model and its application or use. Based on the embodiments in the utility model, all other embodiments obtained by those skilled in the art without creative labor fall within the scope of protection of the utility model.

[0034] In the description of the utility model, need understanding is, the orientation or position relation that the terms "upper", "lower", "left", "right", "top", "bottom", "front", "back" and the like indicate, is only for the convenience of describing the utility model and simplifying the description, and is not indicate or imply that the device or element indicated must have a particular orientation, construct and operate with a particular orientation, therefore can not be understood as the limitation to the utility model. In addition, the terms "first", "second" are only for the purpose of description, and can not be understood as indicating or implying relative importance or implicitly indicating the number of the technical features indicated. Therefore, the features limited by "first", "second" can be explicitly or implicitly included one or more features. Moreover, the terms "first", "second" and the like are used to distinguish similar objects, and do not have to be used to describe a particular order or sequence. It should be understood that the data used in this way can be interchanged under appropriate circumstances, so that the embodiments of the utility model described herein can be implemented in an order other than those illustrated or described herein.

[0035] Embodiment 1

[0036] As Figures 1-2 shown, the utility model discloses a kind of tooling structures of flap gull wing forming glue joint assembly integration, and composite material flap gull wing is made of upper skin, load-bearing structure 1 and lower skin;Wherein, the load-bearing structure 1 includes: main load-bearing frame 11, flap gull wing end rib 12 being arranged at the both ends of the main load-bearing frame 11 and several flap gull wing sub-ribs 13 and flap gull wing honeycomb section 14 being arranged in the main load-bearing frame 11, several flap gull wing joints 15 (as shown in Figure 1 ), which is flap gull wing box section structure, as part of the main lift system and auxiliary control system of aircraft, flap gull wing box section is designed using full composite material structure, and high-strength aluminum alloy joint is used for assembly connection at wing connection suspension point;

[0037] The tooling structure includes:

[0038] Bottom frame 2, which facilitates the passage of hot air to form a stable and uniform temperature gradient field to make curing more stable, and the edge side is provided with a furnace test plate area to facilitate the laying and curing of the furnace test plate;

[0039] And mold main body 3, which is arranged on the bottom frame 2, the mold main body 3 has a forming surface 31 for laying and forming the upper skin and the lower skin, and the mold main body 3 is detachably provided with a main load-bearing frame positioning module 32 for positioning the main load-bearing frame 11, an end rib positioning module 33 for positioning the flap gull wing end rib 12 and several joint positioning modules 34 for facilitating the assembly of the flap gull wing joint 15;

[0040] Preferably, the tool structure further comprises: end rib stress support modules 35 movably arranged on the inner side of the end rib positioning modules 33, joint support modules 36 arranged on the main load-bearing frame positioning modules 32 corresponding to the positions of the joint positioning modules 34 and used for shielding the joint positioning modules 34 without contacting the joint positioning modules 34, and main load-bearing frame support modules 37 movably arranged on the inner side of the main load-bearing frame positioning modules 32.

[0041] The main load-bearing frame positioning modules 32 comprise front beam positioning modules 321 formed by splicing a plurality of front beam positioning sub-modules 3211 and rear beam positioning modules 322 formed by splicing a plurality of rear beam positioning sub-modules 3221, the front beam positioning modules 321, the rear beam positioning modules 322 and the end rib positioning modules 33 form a structure matching the shape of the load-bearing structure 1, and the main load-bearing frame support modules 37 are formed by splicing a plurality of main load-bearing frame support sub-modules 371.

[0042] The main load-bearing frame positioning modules 32, the end rib positioning modules 33 and the joint positioning modules 34 are detachably arranged on the mold body 3 through bolts and positioning pins.

[0043] The end rib stress support modules 35 in the above embodiment 1 are movably arranged (not fixedly arranged), which can support the end rib 12 to ensure that the end rib is not deformed during the gluing process, and the movable arrangement of the end rib stress support modules can ensure force transmission during the curing process; the arrangement of the main load-bearing frame support modules 32 in embodiment 1 can ensure that the main load-bearing frame is not deformed during the gluing process and ensure the gluing quality of the main load-bearing frame and the skin; the arrangement of the joint support modules 36 in embodiment 1 can cover the joint positioning modules 34, facilitate curing and bag making during the gluing process, and avoid the joint positioning modules 34 from piercing the vacuum bag during the curing and bag making process; on the other hand, the joint support modules 36 form an avoidance with the internal joint positioning modules 34 to prevent interference; the front and rear beam positioning modules 321 and 322 in embodiment 1 are designed to be formed by splicing a plurality of sub-modules, which can ensure that each sub-module is relatively light in weight, facilitating loading, unloading and carrying.

[0044] The working process of the utility model is as follows:

[0045] Firstly, all positioning modules on the mold body 3 are removed, the corresponding bolt holes and pin holes are blocked by using hard pressure sensitive tape, and on this basis, the upper and lower skins of the composite material are laid, cured and formed;

[0046] Secondly, the load-bearing structure 1 is manufactured by using another mold, the pressure sensitive tape blocking the bolt holes and pin holes is removed, a plurality of joint positioning modules 35 are installed on the mold body 3 by means of bolts and positioning pins, a plurality of rear beam positioning sub-modules 3221 are installed on the mold body 3 to form a rear beam positioning module 322, a plurality of front beam positioning sub-modules 3211 are installed on the mold body 3 to form a front beam positioning module 321, an end rib positioning module 33 is installed on the mold body 3, the front beam positioning module 321, the rear beam positioning module 322 and the end rib positioning module 33 are enclosed to form a structure matching the shape of the load-bearing structure 1, then an end rib stress support module 35 is placed on the inner side of the end rib positioning module 33, and a plurality of main load-bearing frame support sub-modules 371 are placed on the inner side of the main load-bearing frame positioning module 32, so as to form a main load-bearing frame support module 37, after the installation of the above structure is completed, the load-bearing structure 1 is placed and glued on this basis, a joint support module 36 is installed at the joint of the front beam positioning sub-module 3211 before a vacuum bag is made, and the joint support module 36 can shield the joint positioning module 34 but not contact the joint positioning module 34, and the joint support module 36 is used to reduce the difficulty and risk of bag making;

[0047] Finally, after the composite material flap vane glue joint is completed, all positioning modules on the mold body 3 are removed, only the rear beam positioning module 322, the end rib positioning module 33 and the joint positioning module 34 (as shown in Figure 3 ) are reserved, the joint positioning module 34 is used to position the joint, and on the basis of positioning, hole making and fastener installation assembly work are performed to form the flap vane joint 15.

[0048] The above is the preferred embodiment of the utility model, which is only used to explain the utility model, and does not limit the utility model. Any obvious changes or changes derived from the technical solution of the utility model are still within the protection scope of the utility model.

Claims

1. A tooling structure for integrated assembly and bonding of flaps and ailerons, characterized in that, The flap vane is composed of an upper skin, a force bearing structure (1) and a lower skin. The force bearing structure (1) comprises a main force bearing frame (11), flap vane end ribs (12) arranged at both ends of the main force bearing frame (11), flap vane sub-ribs (13) and flap vane honeycomb segments (14) arranged inside the main force bearing frame (11), and a plurality of flap vane joints (15) arranged on the main force bearing frame (11). The tool structure comprises: a bottom frame (2); and a mold main body (3) arranged on the bottom frame (2), wherein the mold main body (3) is provided with a forming surface (31) for laying and forming the upper skin and the lower skin, and the mold main body (3) is further detachably provided with a main force bearing frame positioning module (32), an end rib positioning module (33) and a plurality of joint positioning modules (34). The tool structure further comprises an end rib stress support module (35) movably arranged on the inner side of the end rib positioning module (33). The tool structure further comprises a plurality of joint support modules (36) arranged on the main force bearing frame positioning module (32) corresponding to the positions of the joint positioning modules (34), and the joint support modules (36) are used to shield the joint positioning modules (34) but not in contact with the joint positioning modules (34).

2. The tooling structure for the integrated assembly of a flap and a slat by forming and bonding according to claim 1, wherein The tool structure further comprises a main force bearing frame support module (37) movably arranged on the inner side of the main force bearing frame positioning module (32).

3. The tooling structure for the integrated assembly of a flap and a slat by forming and bonding according to claim 2, wherein The main force bearing frame support module (37) is formed by splicing a plurality of main force bearing frame support sub-modules (371).

4. The tooling structure for the integrated assembly of a flap and a slat by adhesive bonding according to claim 1, wherein The main force bearing frame positioning module (32) comprises a front beam positioning module (321) and a rear beam positioning module (322). The front beam positioning module (321), the rear beam positioning module (322) and the end rib positioning module (33) are enclosed to form a structure matching the outer shape of the force bearing structure (1), and a plurality of joint support modules (36) are arranged on the front beam positioning module (321).

5. The tooling structure for the integrated assembly of a flap and a slat by forming and bonding according to claim 4, wherein The front beam positioning module (321) is formed by splicing a plurality of front beam positioning sub-modules (3211), and a plurality of joint support modules (36) are arranged at the splicing positions of the front beam positioning sub-modules (3211).

6. The tooling structure for the integrated assembly of a flap and a slat by adhesive bonding according to claim 4, wherein The rear beam positioning module (322) is formed by splicing a plurality of rear beam positioning sub-modules (3221).

7. The tooling structure for the assembly of a flap and aileron, according to any one of claims 1 to 6, characterized in that, The mold main body (3) is further provided with a plurality of bolt holes and pin holes, and the main force bearing frame positioning module (32), the end rib positioning module (33) and the plurality of joint positioning modules (34) are detachably arranged on the mold main body (3) through bolts and positioning pins.

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