• 专利附录
  • 专利说明
  • 权利要求
  • 类似技术
  • 同族专利
  • 引用文献
  • 法律状态
  • 优先权
    • 专利摘要:
    Process for manufacturing monocoque reinforced structures and structure obtained, the method comprising using base components (100) of a partially cured composite material having grooves (150) in its outer contour (110) and joining the base components (100) between yes, apply a filler (3) in the slits (150), apply a coating (2) of composite material on the base components (100) and apply heat on the set formed by the base components (100) coated with the coating (2) until a complete cure of the assembly is obtained, such that a monocoque reinforced structure of composite material formed by the coating (2) and the base components (100) cohesive with the coating (2) is obtained, wherein the base components (100)) that form part of the manufactured structure itself, make the mold function during the manufacturing process, avoiding the need to use molds on which to deposit the composite material that must subsequently be removed from the structure finally obtained. (Machine-translation by Google Translate, not legally binding)
    公开号:ES2699721A1
    申请号:ES201730921
    申请日:2017-07-11
    公开日:2019-02-12
    发明作者:Martinez Manuel Torres
    申请人:Torres Martinez M；
    IPC主号:
    专利说明:

    [0001]
    [0002] MANUFACTURING PROCEDURE FOR MONOCASCO REINFORCED STRUCTURES
    [0003]
    [0004] Sector of the technique
    [0005]
    [0006] The present invention is related to the sector of composite materials, proposing a manufacturing process that allows to obtain structures with reinforcements integrated in a single piece, according to a monocoque configuration, and therefore without the need to have to add said reinforcements later, thus allowing to increase the automation of the process, simplify the structure and improve its behavior. The invention is of preferential application to the manufacture of aeronautical fuselages, wings and blades of wind turbines, although there are other possible applications, especially in the field of transport, such as for example the manufacture of railway wagons, bus chassis, rockets satellites, or similar structures.
    [0007]
    [0008] State of the art
    [0009]
    [0010] The manufacture of parts and components in composite material is a technology increasingly demanded in a large number of sectors, maintaining the aeronautical, the automobile and the wind as the most important today. The use of this material allows to achieve mechanical properties comparable to those of metals, material that has been used until now in these markets, but with a significant weight reduction on them.
    [0011]
    [0012] However, one of the main problems of manufacturing with this type of materials is that the level of automation achieved is not yet very high, so that by manually manufacturing the possibility of errors and failures due to the human factor increases considerably. Another drawback associated with manufacturing with this type of material is the need for molds, generally with high costs. The need for complex, large and expensive molds is first imposed by the low consistency of the material before the curing process, which prevents proper positioning of the same in the absence of these, and the need to withstand high temperatures in the process of curing with minimal deformations.
    [0013] On the other hand, sectors such as aeronautics, which are usually characterized by being quite conservative mainly for safety reasons, have been using the same manufacturing technology for structures such as the wings or the fuselage for years, although they are increasingly using more material. compound for its components, thus replacing the higher weight metal components. The technology they employ, with a minimum level of automation for the possibilities existing today, is based on a fabrication of the wings or the fuselage by sections, which necessarily implies the use of a large number of rivets for the joints, as well as the need for many laborious manual tasks.
    [0014]
    [0015] Moreover, large aeronautical structures, such as a fuselage, are usually composed of several independent components such as skins, stringers and frames, generating when joining a component capable of supporting the structural efforts during the different actions of the aircraft. Today, all these components are also manufactured by sections, very manually, separately and externally to the fuselage, having to be subsequently positioned and placed inside it, which implies a complex manufacturing process, as well as a large number of rivets, usually mechanical and placed manually.
    [0016]
    [0017] The use and necessity of such quantity of rivets will affect both the weight of the structure, which will increase significantly, and the process of certification of the aircraft that contains them. The certification of these large structures thus manufactured is often long and costly. The certification of a manufacturing by sections, according to the regulations, involves certifying each section, each joint and, therefore, each rivet individually, with the amount of time that this entails and the extra cost involved. Therefore, the use of multiple rivets in a structure slows down its certification process and, therefore, increases the time of entry into the market.
    [0018]
    [0019] Next, we describe a series of documents that show the manufacturing procedures of large structures for different sectors as they are done today, that is, by sections, using complex molds and a large number of rivets.
    [0020]
    [0021] US2012 / 0175807 discloses a method of manufacturing blades of wind turbine in composite material by means of a split system of shell molds, comprising an upper half mold and a lower one having a series of mechanical joints.
    [0022]
    [0023] The document ES2572027 describes a method of manufacturing a component of a split blade of a wind turbine that has elements of connection with other components of the blades.
    [0024]
    [0025] US2017 / 0043542 presents a method of manufacturing wind turbine blades, in which sections of blades, preferably half-shells, are manufactured by the use of specific molds.
    [0026]
    [0027] The document ES2322638 does present an automated process for the manufacture of wind turbine blades, but which is still dependent on a mandrel on which the skin is taped and which must be removed at the end of the blade manufacturing process.
    [0028]
    [0029] Document US2015 / 0274326 presents a method and its associated system for the manufacture of structures in carbon fiber, starting in this case from a series of components before integrating in a single component, through connections between them.
    [0030]
    [0031] Document US2007 / 0210211 describes a fuselage and a method of manufacturing thereof, wherein said structure is manufactured in at least two parts that end up being joined by means of binders at its ends, obtaining a structure with at least one relatively binding zone review.
    [0032]
    [0033] Document US2012 / 0219764 presents complete sections of fuselage made of composite material, constructed using structural reinforcement components in the manner of frames and stringers, in which said reinforcing components, however, are added to the skin through joints.
    [0034]
    [0035] The document US2013 / 0020009 presents a method for the manufacture of a fuselage in composite material, in which on a mandrel that acts as a mold both a wrapping of reinforcement components as stringers and a wrapping of the skins of the fuselage. The process is semi-manual, requires unions, and is done in two phases: the stringers, previously preformed, are placed manually, and the coating with the skin is performed with AFP.
    [0036]
    [0037] Document US2011 / 0052845 describes a method for manufacturing a hollow body in carbon fiber, in a single piece, preferably oriented to the manufacture of aircraft fuselages. However, said proposal defines a structure that does not incorporate structural reinforcements integrated into the structure and requires an external mold on which to position the component in the manufacturing process.
    [0038]
    [0039] The document US2015 / 0122413 presents a method of manufacturing fuselage sections in a single component through a retractable rotary system that allows having grooves for the introduction of stringers and the joint manufacture of said component, said retractable rotary system acting as a mold of the set on which the skin of composite material is laminated, without introducing frames and without actually producing a complete fuselage.
    [0040]
    [0041] US2011 / 0303791 presents a fuselage section and its production method, from which a component is obtained that does not require complementary stiffening structures since the internal lamination generates sufficient rigidity through a correct orientation of the fibers, using a completely laminated interior surface and then the placement of blocks of reinforcing fibers in different directions, to finally use a new outer laminate, requiring the use of a mold on which to place the material that forms the final component.
    [0042]
    [0043] Therefore, a solution is necessary that allows monocoque structures made of composite material through fully automated processes, without the need to use molds or a large number of rivets to obtain the structure, and without the need to subsequently add to the structure. External reinforcements structure.
    [0044]
    [0045] Object of the invention
    [0046]
    [0047] The invention relates to a method of manufacturing a monocoque reinforced structure of preferential application in the aeronautical and wind sector, although it is applicable to structures with similar requirements of other sectors, such as, for example, rail cars. , the bus chassis, or the shuttle rockets of satellites. The structure directly obtained from said method is also object of the invention.
    [0048]
    [0049] The invention makes it possible to manufacture a composite structure without the need to use molds on which to deposit the composite material that must subsequently be removed from the final piece obtained, as well as to eliminate or reduce the use of rivets as much as possible, with the consequent reduction of weight of the structure finally obtained. With all this, it is possible to increase the level of automation of the manufacturing process of the structure, simplifying it and improving its behavior and resistance to traction, compression and torsion.
    [0050]
    [0051] The method of manufacturing monocoque reinforced structures of the invention comprises:
    [0052]
    [0053] - using base components of a partially cured composite material having grooves in their outer contour and joining the base components together, - applying a filler in the grooves,
    [0054] - apply a coating of composite material on the base components that have the filling in the slits, and
    [0055] - Applying heat on the assembly formed by the base components coated with the coating to obtain a complete curing of the assembly, such that a monocoque reinforced structure of composite material formed by the coating and the base components cohesive with the coating is obtained.
    [0056]
    [0057] In this way, the base components, being made of a partially cured composite material, have a sufficient stiffness so that the composite coating can be deposited on them, based on unidirectional continuous fibers, with which the base components make the function of mold, but with the advantage that the base components should not be removed from the structure finally obtained, unlike the molds that are used in the manufacture of components in composite material of the state of the art, since The base components of the invention are part of the monocoque reinforced structure finally obtained. In addition, the curing of the base components together with the coating that surrounds them creates a unique cohesive structure of composite material that hardly requires the use of metal rivets for their structural union, with the consequent weight reduction, time and manufacturing costs that this entails. On the other hand, when using a base component with grooves, additional reinforcements are generated that are also part of the monocoque reinforced structure finally obtained, so there is no need to subsequently add reinforcements to the structure.
    [0058]
    [0059] According to one example of the invention, base components made of material in dry fiber format are used, which are impregnated with resin through an infusion process and partially cured by applying heat at a temperature below the curing temperature of the resin to achieve a percentage of advance of the curing reaction comprised between 40% and 80%.
    [0060]
    [0061] According to another example of the invention, base components manufactured on preimpregnated fiber material that are partially cured by applying heat at a temperature lower than the curing temperature of the resin are used to achieve a percentage of advance of the curing reaction comprised between a 40% and 80%.
    [0062]
    [0063] The assembly formed by the base components coated with the coating is completely cured by applying heat at the curing temperature of the resin until a percentage of advance of the curing reaction of 100% is achieved.
    [0064]
    [0065] Additionally, and prior to applying the filler in the grooves, it is preferable to apply in accordance with a preferred embodiment a filler material on the joined base components to obtain a uniform exterior surface of the base components.
    [0066]
    [0067] Additionally, and prior to applying the filler in the slits, it is also preferable to arrange fiber bundles, or "rovings", at the ends of the slits.
    [0068]
    [0069] Optionally, the filling can be removed from the slits after obtaining the complete curing of the reinforced monocoque structure, thereby optimizing the weight thereof.
    [0070]
    [0071] The monocoque reinforced structure obtained by the process of the invention comprises the composite base components which are bonded together and coated with the composite coating, where the base components have an outer contour with two open ends and each open end has a wing that projects transversely to the interior of the base component, and where the contour The exterior of the base components has some grooves in which the filling is available.
    [0072]
    [0073] Additionally, to obtain greater rigidity, each wing has a fold projecting longitudinally towards the interior of the base component according to a plane parallel to the outer contour. Also additionally each wing has a widened area in the lower part of the base component.
    [0074]
    [0075] Additionally, a reinforcement ring is arranged on the folds of each two consecutively joined base components.
    [0076]
    [0077] Preferably, the grooves have a wavy configuration and extend in the axial direction along the entire width of the outer contour of the base component.
    [0078]
    [0079] Preferably the grooves of the base components have a radius of curvature of between 50 and 500 mm.
    [0080]
    [0081] According to the described process, the union of two base components generates a geometry equivalent to that of a structural frame, which will be integrated into the generated structure, while the grooves of the axially attached base components generate an equivalent geometry to that of a structural spar.
    [0082]
    [0083] With all this and the invention results in a monocoque structure manufactured as a single piece, with reinforcement components integrated into the manufacturing which leads to virtually avoid all rivets and additional bonding systems between the different components, very small weight and low manufacturing costs thanks to the great automation of the process and the reduction of direct labor required, reducing in turn the problems arising from manual work and increasing productivity with respect to the current state of the art.
    [0084]
    [0085] Description of the figures
    [0086]
    [0087] Figure 1 shows a perspective view of a base component with slits forming part of the reinforced monocoque structure of the invention.
    [0088]
    [0089] Figure 1b shows a perspective view of two base components with slits before join.
    [0090]
    [0091] Figure 2 shows a partial perspective view of a set of base components with slits joined together.
    [0092]
    [0093] Figure 3 shows a partial sectional view of two base components with slits joined together.
    [0094]
    [0095] Figure 4 shows a partial sectional view of the reinforced monocoque structure of the invention.
    [0096]
    [0097] Figure 5 shows a partial sectional view like that of the previous figure with an inner reinforcing ring.
    [0098]
    [0099] Figure 6 shows the reinforced monocoque structure formed by base components with grooves.
    [0100]
    [0101] Figure 7 shows a sectional view of the layers forming the reinforced monocoque structure according to a preferred embodiment of the invention.
    [0102]
    [0103] Figure 8 shows an aeronautical fuselage obtained by the method of the invention.
    [0104]
    [0105] Figure 9 shows a perspective view of a base component with slits forming part of the reinforced monocoque structure of the invention for an amphibious version of the fuselage.
    [0106]
    [0107] Figure 10 shows the reinforced monocoque structure formed by base components with slits for the amphibious version of the fuselage.
    [0108]
    [0109] Detailed description of the invention
    [0110]
    [0111] The invention relates to a reinforced monocoque structure of a composite material, preferably glass fibers or carbon fibers, which is made without the use of molds on which to deposit the composite material which must subsequently be removed from the piece finally obtained, since a part of the manufactured structure itself is used to make the mold function during the manufacturing process.
    [0112]
    [0113] The monocoque reinforced structure of composite material finally obtained is preferably used for the manufacture of the fuselage of an aircraft, as shown in the examples of figures 8 and 10, however it can be used to manufacture other types of structures such as for example monocoque structures in the wind, naval or automotive sector (wind turbine blades, vehicle chassis, ship hull, submarine, etc.).
    [0114]
    [0115] Figure 1 shows a base component (100) used in the fabrication of the structure and that serves as a mold for the deposition of a coating (2) of composite material, resulting in the base component (100) forming an indivisible part of the reinforced monocoque structure finally obtained by the manufacturing process of the invention, whereby the process does not require the use of a specific mold or removal after the curing process of the composite material.
    [0116]
    [0117] The base component (100) comprises an outer contour (110) that is configured to receive the coating (2) of composite material, said outer contour (110) defining the geometry of the monocoque reinforced structure finally obtained. The outer contour (110) has two open ends in each of which is located a wing (120) projecting transversely to the interior of the base component (100), the wing (120) being intended to establish a connection with other components base (100). Preferably the outer contour (110) of the base component (100) has a cylindrical, conical or prismatic hollow geometry, according to the geometry of the monocoque structure to be manufactured.
    [0118]
    [0119] Additionally, each wing (120) has a fold (130) projecting longitudinally towards the interior of the base component (100) according to a plane parallel to the exterior contour (110), said fold (130) providing additional rigidity to the wing (120). ) of the base component (100). Likewise, the wings (120) additionally have a widened area (140) in the lower part of the base component (100), which in the case of using the structure as an aircraft fuselage, would correspond to the area where the aircraft is located. floor of the aircraft.
    [0120]
    [0121] The base component (100) has slits (150) in its outer contour (110) which they act as structural reinforcement.
    [0122]
    [0123] The slits (150) define an alternating distribution of valleys and ridges on the outer contour (110), which gives the base component (100) a high resistance. The valleys correspond to the slits (150), which project towards the interior of the base component (100), and the crests correspond to the zones established between slits (150), which project towards the exterior of the base component (100). ) with respect to the valleys.
    [0124]
    [0125] As seen in the figures, preferably the slits (150) have a wavy configuration and extend in the axial direction along the entire width of the outer contour (110) of the base component (100), ie the slits (150). ) extend between the open ends of the outer contour (110), which allows the base component (100) to have a high strength in the axial direction.
    [0126]
    [0127] In any case, this undulating configuration and the arrangement of the slits (150) along the entire width of the outer contour (110) is not limiting, the slits (150) being able to have other shapes or extend in other directions different from the axial, as well as not occupying the entire width of the outer contour (110), but portions of said width.
    [0128]
    [0129] The slits (150) have a radius of curvature that is selected according to the structural requirements of the structure to be manufactured, a radius of curvature of between 50 and 500mm having been preferably selected.
    [0130]
    [0131] Preferably the base components (100) are made of fiberglass or carbon fiber, using unidirectional fiber that is applied in the optimal directions defined by the structural design of the base component (100). According to an example of the invention, the base components (100) are made of dry fiber which subsequently requires the addition of resin for curing. According to another example of the invention, the base components (100) are made of fiber preimpregnated with resin and therefore do not require a subsequent addition of resin.
    [0132]
    [0133] With all this in mind, for the manufacture of the reinforced monocoque structure of the invention, a set of base components (100) of a partially cured composite material are used. Partial curing allows the composite material of the base components (100) it acquires a sufficient stiffness for its handling in later phases of the process, so that the own fibers of composite material acquire enough rigidity to fulfill the function of mold on which to deposit the coating (2), but keeps the resin of the composite material applied in a "live" state, capable of generating a bond with a new layer of composite material with minimal loss of mechanical properties at the interface between layers.
    [0134]
    [0135] According to one embodiment of the invention, base components (100) of dry fiber are used, which are impregnated with resin by means of an infusion process and which are heated by applying a temperature lower than the curing temperature of the resin until a percentage is obtained. of advance of the curing reaction comprised between 40% and 80% in the composite material of the base components (100).
    [0136]
    [0137] According to another embodiment of the invention, base components (100) of prepreg are used which are heated by applying a temperature lower than the curing temperature of the resin until achieving a percentage of advance of the curing reaction comprised between 40% and 80% in the composite material of the base components (100).
    [0138]
    [0139] Subsequently, once the base components (100) are partially cured and have acquired sufficient rigidity for their manipulation, they are joined together to define a surface on which the coating (2) must be applied, corresponding to the geometry of the structure to obtain.
    [0140]
    [0141] To do this, the base components (100) are axially joined to one another, facing each other by their wings (120). Preferably the joint is made using chemical means, however mechanical means or a combination of chemical and mechanical means could be used to establish the joint.
    [0142]
    [0143] Before applying the covering (2) on the outer contour (110) of the base components (100) a filling (3) is applied in the slits (150), so that an exterior contour (110) of a surface is guaranteed on which to apply the coating (2).
    [0144]
    [0145] Preferably the filling (3) that is applied in the slits (150) is of a material that has a lower density than the density of the composite material from which the base component (100) is manufactured, so that the weight of the base component (100) is optimized, which is a critical factor in the applications to which the base component is intended. invention. For example, the filler (3) can be a low density foam or a similar material.
    [0146]
    [0147] The set of base components (100) axially joined with the filler (3) in the grooves (150) generates the surface on which the coating (2) of composite material, such as fiberglass or carbon fiber, is applied. Preferably the composite coating (2) is applied using automatic wrapping techniques. For example, a wrapping head is used that applies tapes or fibers of composite material on the outer contour (110) of the base components (100) according to defined orientations to achieve a laminate that meets the final requirements of the structure to be obtained. . Alternatively, the coating (2) can be applied using manual techniques without altering the concept of the invention.
    [0148]
    [0149] Additionally, prior to the application of the filling (3) in the grooves (150) and the lining (2), it is preferable to coat the outer contour (110) of the base components (100) already joined with a filling material (4) that allows to guarantee a continuous geometry and without cavities or recesses that hinder the subsequent process of application of the filling (3) and application of the coating (2), or that may worsen the final properties of the structure finally obtained.
    [0150]
    [0151] The filler material (4) applied preferably acts as a structural reinforcement for the bonding of the base components (100). This filling material (4) is applied over the entire outer contour (110) of the base components (100), that is covering the crests and valleys, so that a continuity in the obtained structure is obtained.
    [0152]
    [0153] Finally, the base components (100) axially bonded and coated with the coating (2) are completely cured by applying heat so that the base components (100) and the coating (2) are cohesive together forming a single structure, where it is not removal of any mold is necessary since the base components (1) that fulfilled said function are part of the structure obtained.
    [0154]
    [0155] Optionally, after curing the filling (3) of the slits (150) is removed, thereby further optimizing the weight of the monocoque structure obtained. For this, the filling (3) it can be a soluble material, so that its elimination is obtained by circulating a solvent through the slits (150).
    [0156]
    [0157] The removal of the filling (3), or its maintenance in the grooves (150), will depend on the weight requirements of the structure to be obtained and its local buckling behavior, so for example, the filling (3) can be maintained when a low density foam or a similar material is used, since it does not compromise the weight of the structure.
    [0158]
    [0159] The coating (2) applied on the joined base components (100) also acts as a structural reinforcement. Said lining (2) is applied on the outer contour (110) of the base components (100) making contact with the filling (3) of the grooves (150) and with the areas of the outer contour (110) established between grooves (150). ), this is the ridges of the outer contour (110). In this way, the cohesion of the base components (100) and the coating (2) is established by the crests.
    [0160]
    [0161] In the preferred case of applying the filling material (4), the cohesion of the base components (100) and the coating (2) is also stable in the areas where the crests are covered by the filling material (4).
    [0162]
    [0163] Thus, when manufacturing the fuselage of an aircraft, the union of the lining (2) and the outer contour (110) of the base components (100) corresponds to the skin of the fuselage, the union of the wings (120) of two consecutive base components (100) corresponds to the frames of the fuselage. The fuselage generated does not require rivets for joining different stretches of fuselage, since the fuselage is not manufactured in sections but in a single piece, where the retention of the base components (100) is obtained by applying the coating (2) that surrounds them. Not even rivets are required for the joining of frames to the skin, since the base components (100) are joined with the coating (2) in the curing process, which results in a fuselage of a reduced weight .
    [0164]
    [0165] In addition, the grooves (150) of several base components (100) axially joined together make the function of reinforcing beams of the fuselage, so that it is not necessary to add in a subsequent process said reinforcement beams to the structure finally obtained, with the consequent saving of time that this entails, in addition to not requiring rivets to join the stringers to the structure, since the base components (100) carry intrinsically defined the stringers themselves.
    [0166]
    [0167] According to the described process, the union of two base components (100) generates in its area of union a geometry equivalent to that of a structural frame. The union of the wings (120) coming from each of the two base components (100) to be joined generates the equivalent to a structural profile soul, the joining of the grooves (150) generates the equivalent to a structural beam, while the folds (130) of each of the two base components (100) generate a structural profile wing. In the example of the invention of FIG. 5, an additional reinforcement is added to the joint on the inner part thereof, on the surface generated internally by the folds (130) of the base components (1), on which it adds a reinforcing ring (5) that offers greater consistency to the joints between base components (1) and reinforces the structural frame generated in said joint.
    [0168]
    [0169] According to a preferred embodiment of the invention, prior to applying the filling (3) in the slots (150) of the joined base components (100), fiber bundles (6), commonly known as "rovings", are arranged in the ends of the slits (150) Specifically a bundle of fibers (6) is arranged at each transition between a valley and a crest of the outer contour (110) of a base component (100).
    [0170]
    [0171] The bundles of fiber (6) or "rovings" act as an additional reinforcement and avoid cracks in the transition between valleys and ridges that are critical points of stress concentration, being finally integrated into the monocoque structure resulting from the manufacturing process. provided that the fiber bundles (6) or "rovings" are carbon fiber with the fibers oriented in certain directions.
    [0172]
    [0173] Figure 7 shows a sectional view of a preferred non-limiting embodiment of the reinforced monocoque structure obtained according to the method of the invention. In said section there is observed a base component (100) on whose outer contour (110) the filler material (4) has been deposited, subsequently in the grooves (150) there have been applied the fiber bundles (6) and the filling (3), and subsequently the coating (2) has been applied.
    [0174]
    [0175] In Figure 9 there is shown a base component (100) that is part of a reinforced monocoque structure for an amphibious fuselage version, while in figure 10 the amphibious fuselage version is shown.
    权利要求:
    Claims (1)
    [0001]
    1- Process for manufacturing reinforced monocoque structures, characterized in that it comprises:
    - using base components (100) of a partially cured composite material having grooves (150) in its outer contour (110) and joining the base components (100) to each other,
    - apply a filler (3) to the slits (150),
    - applying a coating (2) of composite material on the base components (100) having the filling (3) in the slits (150), and
    - applying heat on the assembly formed by the base components (100) coated with the coating (2) until obtaining a complete curing of the assembly, such that a monocoque reinforced structure of composite material formed by the coating (2) and the components is obtained base (100) cohesive with the coating (2).
    2 - Process for manufacturing reinforced monocoque structures, according to claim 1, characterized in that base components (100) manufactured on material in dry fiber format are impregnated with resin through an infusion process and are partially cured by applying heat at a temperature lower than the curing temperature of the resin until achieving a percentage of advance of the curing reaction comprised between 40% and 80%.
    3. Process for manufacturing monocoque reinforced structures, according to claim 1, characterized in that base components (100) manufactured on preimpregnated fiber material that are partially cured by applying heat at a temperature lower than the curing temperature of the base are used. the resin until achieving a percentage of advance of the curing reaction comprised between 40% and 80%.
    4 - Method of manufacturing monocoque reinforced structures according to any one of the preceding claims, characterized in that the assembly formed by the base components (100) coated with the coating (2) are completely cured by applying heat.
    5.- Manufacturing procedure of reinforced monocoque structures, according to a any of the preceding claims, characterized in that the composite coating (2) is applied using automatic wrapping techniques.
    6. - Process for manufacturing monocoque reinforced structures, according to any of the preceding claims, characterized in that prior to applying the filling (3) in the grooves (150) a filling material (4) is applied on the base components ( 100) joined to obtain a uniform outer surface of the base components (100).
    7. Process for manufacturing monocoque reinforced structures according to any of the preceding claims, characterized in that prior to applying the filling (3) in the slits (150) fiber bundles (6) are arranged at the ends of the slits (150).
    8. Process for manufacturing monocoque reinforced structures according to any one of the preceding claims, characterized in that the filling (3) is removed from the slits (150) after obtaining complete curing.
    9. - Reinforced monocoque structure obtained by the method of any one of the preceding claims, characterized in that it comprises base components (100) of a material! compound that are joined together and covered with a composite lining (2), where the base components (1) have an outer contour (110) with two open ends and each open end has a wing (120) projecting transversally towards the inside of the base component (100), and wherein the outer contour (110) of the base components (100) has slits (150) in which a filling (3) is available.
    10. - Reinforced monocoque structure according to the preceding claim, characterized in that each wing (120) has a fold (130) projecting longitudinally towards the interior of the base component (100) according to a plane parallel to the outer contour (110).
    11. - Reinforced monocoque structure according to claim 9 or 10, characterized in that each wing (120) has a widened area (140) in the lower part of the base component
    (100)
    12. Reinforced monocoque structure according to claim 10 or 11, characterized in that a reinforcing ring (5) is arranged on the folds (130) of each two base components (100) consecutively joined.
    13. Reinforced monocoque structure according to any of claims 9 to 12, characterized in that the grooves (150) have a wavy configuration and extend in the axial direction along the entire width of the outer contour (110) of the base component (100)
    14. Reinforced monocoque structure according to any of claims 9 to 13, characterized in that the grooves (150) of the base components (100) have a radius of curvature comprised between 50 and 500 mm.
    15. Reinforced monocoque structure according to any of claims 9 to 14, characterized in that fiber bundles (6) are arranged at the ends of the slits (150).
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    同族专利:
    公开号 | 公开日
    ES2699721B2|2019-07-10|
    引用文献:
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    优先权:
    申请号 | 申请日 | 专利标题
    ES201730921A|ES2699721B2|2017-07-11|2017-07-11|MANUFACTURING PROCEDURE FOR MONOCASCO REINFORCED STRUCTURES AND STRUCTURE OBTAINED|ES201730921A| ES2699721B2|2017-07-11|2017-07-11|MANUFACTURING PROCEDURE FOR MONOCASCO REINFORCED STRUCTURES AND STRUCTURE OBTAINED|
    EP17881077.6A| EP3556650A4|2016-12-16|2017-12-15|Method for producing reinforced monocoque structures and structure obtained|
    PCT/ES2017/070820| WO2018109255A1|2016-12-16|2017-12-15|Method for producing reinforced monocoque structures and structure obtained|
    US16/469,357| US20200017186A1|2016-12-16|2017-12-15|Method for manufacturing a one-piece reinforced structure and obtained structure|
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