• 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:
    The invention relates to stiffening structures, wing structures and methods for making stiffening structures. According to an exemplary embodiment, a stiffening structure comprises a first longitudinal member, a second longitudinal member, and a first rib extending from the first longitudinal member to the second longitudinal member and which is integral with the first member. longitudinal and the second longitudinal element. The first longitudinal member has a first wall, a second wall, and a junction wall that joins the first wall and the second wall. The first wall, the second wall and the junction wall form a space having a trapezoidal shape.
    公开号:FR3035071A1
    申请号:FR1653306
    申请日:2016-04-14
    公开日:2016-10-21
    发明作者:Brenden Autry；Bryan Williams；Travis Cope；Susan Daggett；John Mcguire；Michael Mckee；Charles Aitken
    申请人:Gulfstream Aerospace Corp；
    IPC主号:
    专利说明:

    [0001] [0001] TECHNICAL FIELD [0001] The technical field generally relates to stiffening structures, wing structures and methods for the manufacture of stiffening structures. and more particularly relates to stiffening structures and integrated wing structures formed of composite materials and methods of manufacturing such stiffening structures.
    [0002] BACKGROUND [0002] The stiffening structures for stiffening long flat panels often use a ladder-type configuration attached to the panels to provide rigidity and support for the panels. Applications of such stiffening structures include fuselages, fins and other wing-like parts used in the civil and military aviation industry. Figure 1 illustrates a typical ladder-type structure attached to a wing-cladding panel 16. A first spar 12 and a second spar 14 extend along a length of the wing-cladding panel 16 for a long time. base end 20 to one end end 22. A third spar 18 is located between the first spar 12 and the second spar 14 and extends along a portion of the first spar 12 and second spar 14 since base end 20. A number of ribs 24 couple the first spar 12 to the third spar 18 and the third spar to the second spar 14. The spars and ribs are typically of an I-beam configuration or a C-beam configuration. Therefore, in order to further stiffen the structure 10, a central portion 26 is embedded in the wing cladding panel in the area of the ribs. The central portion is typically formed by a resinous honeycomb material. While these ladder-type configurations stiffen and reinforce long structures, such as fuselage or wing type structures, they have many drawbacks. The ladder-like configuration elements, such as ribs and spars, are typically attached to each other using fastening devices, e.g. screws, bolts, or nuts. Therefore, the manufacture of ladder-type configurations using such fastening mechanisms is relatively time-consuming and expensive. The fasteners and fasteners are further generally formed of metal which adds weight to the stiffening structures. The ladder-type configurations further provide only limited stiffening support, thereby requiring the stiffening structures to utilize additional stiffening mechanisms, such as a central portion 26. Therefore, it is desirable to to provide stiffening structures formed of a rigid composite material, but of low weight. It is further desirable to provide stiffening structures which are of a time and cost advantageous fabrication. It is also desirable to provide methods for making such stiffening structures. Other aspects and desirable features of the present invention will become apparent from the following detailed description of the invention and the appended claims, taken in conjunction with the accompanying drawings and the present context of the invention. BRIEF SUMMARY [0005] Reinforcement structures, wing structures, and methods for fabricating stiffening structures are provided. According to an exemplary embodiment, a stiffening structure comprises a first longitudinal member, a second longitudinal member, and a first rib extending from the first longitudinal member to the second longitudinal member and is integral with the first longitudinal member. first longitudinal member and the second longitudinal member. The first longitudinal member has a first wall, a second wall, and a junction wall that joins the first wall 25 and the second wall. The first wall, the second wall and the junction wall form a space having a trapezoidal shape. According to another embodiment, a wing structure comprises a first wing panel having a first end and a longitudinal axis and a stiffening structure fixedly attached to the first wing panel. The stiffening structure includes a first spar and a second spar each extending from the first end along the longitudinal axis of the first wing panel. The first spar 23035071 and the second spar each have a length. A third spar is located between the first spar and the second spar and extends along at least a portion of the length of the first spar and / or the second spar. A first rib extends from the first spar to the third spar and is integral with the first spar and the third spar. A second rib extends from the third spar to the second spar and is integral with the third spar and the second spar. [0007] According to another embodiment, a method for manufacturing a stiffening structure comprises depositing a flexible and drapeable composite material inside the cavity of a mold, inserting the mold in a bag, making a vacuum in the bag, processing the flexible and drapeable composite material to form the stiffening structure within the mold, and removing the stiffening structure from the mold. The stiffening structure comprises a first longitudinal member and a second longitudinal member. A first rib extends from the first longitudinal member 15 to the second longitudinal member and is integral with the first longitudinal member and the second longitudinal member. A second rib extends from the first longitudinal member to the second longitudinal member and is integral with the first longitudinal member and the second longitudinal member. The first longitudinal member and the second longitudinal member each have a first wall, a second wall, and a junction wall which joins the first wall and the second wall. The first wall, the second wall, and the junction wall form a space having a trapezoidal shape. BRIEF DESCRIPTION OF THE DRAWINGS [0008] The various embodiments are explained below in connection with the drawings of the following figures, in which identical numbers indicate identical elements: FIG. 1 is a perspective view a conventional ladder type configuration typically used for wing type structures; Figure 2 is a stiffening structure attached to a cladding panel according to an exemplary embodiment; Figure 3 is a cross-sectional view of the longitudinal members of the stiffening structure of Figure 2 along the axis 3-3; Figure 4 is a wing structure according to an exemplary embodiment; Figure 5 is a cross-sectional view of the longitudinal members of the stiffening structure of Figure 4 according to an exemplary embodiment; and [0014] Fig. 6 is a block diagram of a method for forming a stiffening structure according to an exemplary embodiment.
    [0003] DETAILED DESCRIPTION [0015] The following detailed description is simply intended to be exemplary in nature and is not intended to be limiting of the invention or application and uses of the invention. Furthermore, there is no intention to be bound by any theory presented in the foregoing context or the detailed description which follows. [0016] Various exemplary embodiments of stiffening structures, wing structures and methods of making stiffening structures are presented here. The stiffening structures comprise integral longitudinal members and ribs, and are formed from a single mold. From this point of view, the manufacture of the structures is efficient both in terms of time and cost. The elements and ribs of the structures are configured with two walls providing a significantly greater load bearing support than single wall supports of conventional ladder type configurations. The stiffening structures are further fabricated from composite materials making the structures lighter than conventional ladder-type configurations containing metal. Referring to Figure 2, a stiffening structure 50 according to an exemplary embodiment is attached to a panel 52. The panel 52 may be any panel requiring stiffening or additional support to carry the load . The panel, for example, may be used in the aeronautical or aerospace industry for an aircraft fuselage, an airplane horizontal stabilizer, and the like. The stiffening structure 50 is attached to the panel 52 using any suitable fastening mechanism, such as, for example, an adhesive, screws, nails, clips and the like. The stiffening structure 50 comprises a plurality of longitudinal members 53 including a longitudinal member 54 and a longitudinal member 56 which both extend from a first end 60 to a second end 62 of the panel 52. an exemplary embodiment, the longitudinal members 53 are substantially parallel to each other, although in other embodiments the longitudinal members 10 can cross each other. In one embodiment, a longitudinal member 64 is positioned between the longitudinal member 54 and the longitudinal member 56. The lengths of the longitudinal member 54, the longitudinal member 56, and the longitudinal member 64 may be independent of each other. others. Their lengths and positions relative to each other depend on the application and configuration of the overall structure, such as for example a fuselage of an aircraft. In one embodiment, the longitudinal members 53 are curvilinear, as shown in Figure 2. In another embodiment not shown, the longitudinal members 53 are linear. While FIG. 2 specifically illustrates longitudinal members 54, 64 and 56, it will be appreciated that the stiffening structure 50 may comprise two or more longitudinal members 20 with the number of longitudinal members depending on the overall application for which the stiffening structure will be used. [0019] The stiffening structure 50 also comprises a plurality of ribs 66. In an exemplary embodiment, the ribs 66 are substantially perpendicular to the longitudinal members 53, although the ribs may form an angle with respect to the longitudinal members in a longitudinal direction. alternative embodiment. Each rib 66 extends from a longitudinal member 53 to an adjacent longitudinal member, for example from the longitudinal member 54 to the longitudinal member 64 or from the longitudinal member 64 to the longitudinal member 56. The ribs 66 are integral with the longitudinal members 53 at the intersections between the ribs and the longitudinal members. In this respect, the stiffening structure has no joints between the ribs and the longitudinal members, which would provide areas of weakness for the overall structure. The number of ribs and the spacing of the ribs from each other depends on the application and configuration of the overall structure. In one embodiment, the ribs are curvilinear, as shown in Figure 2. In another embodiment not shown, the ribs are linear. FIG. 3 is a cross-sectional view of the stiffening structure 50 along the axis 3-3 of FIG. 2. As illustrated in FIG. 3, the longitudinal element 54, the longitudinal element 56 and the longitudinal member 64 are double-walled, namely that the longitudinal members have a first wall 68 and a second wall 70 coupled through a junction wall 72 which is relatively parallel to the panel 52. In this regard, the walls 68, 70 and 72 form a space 78 having a trapezoidal shape. Bases 76 integral with the first wall 68 and the second wall 70 are fixable to the panel 52. As indicated above, the bases 76 are immobilized on the panel 52 using any suitable fastening mechanism, such as an adhesive, screws, nails, clips and the like. While not shown, the ribs 66 considered here also have walls 68, 70 and 72 which form a trapezoidal shaped space. With a trapezoidal cross-sectional shape, the ribs 66 and longitudinal members 53 are double-walled with walls 68 and 70, and therefore provide a much greater force to the stiffening structure 50 than the single-walled ribs and the longitudinal members of the conventional ladder-type configuration as illustrated in FIG. 1. In this regard, additional reinforcing mechanisms, such as the recessed central portion 26 of FIG. 1 typically used in conventional ladder-type configurations, are not necessary in the stiffening structure 50 considered here. The dimensions of the trapezoidal shape, namely the height, the length, the width of the top and the width of the bottom of the space 78 of the ribs 66 and the longitudinal elements 53 depend on the application and the configuration of the overall structure . In one embodiment, the "span area" 74 defined as the width of the bottom of the space 78 or the distance between the walls 68 and 70 as measured at the panel 52 is sufficiently wide that the stiffening 50 can be easily removed from a mold during manufacture, as discussed in more detail later. The number of longitudinal members 53 and ribs 66, span areas 74 and the spacing of the longitudinal and rib members are dependent on the use of the overall application for which the stiffening structure will be used. [0021] Figure 4 illustrates a stiffening structure 100 according to another exemplary embodiment. In this embodiment, the stiffening structure 100 is immobilized on a cladding panel 102 which may be a cladding board 3035071 used in the aerospace or aerospace industry to form a wing structure 101, such as a wing, fin, a fin or the like. The stiffening structure 100 includes a spar 104 and a spar 106 which are generally along a longitudinal axis 108 of the cladding panel 102 from a first end 110 to a second end 112 of the cladding panel 102. The spar 114 is positioned between the spar 104 and the spar 106. A spar 114 is located from the first end 110 of the cladding panel along the longitudinal axis 108 and terminates at a point between the first end 110 and the spur. second end 112 of the liner panel along at least a portion of a length of the spar 104 and / or the spar 106. While two spars 104 and 106 extending along the liner panel 102 are illustrated in Figure 4, it will be appreciated that the stiffening structure 100 is not so limited and may have more than two such longitudinal members extending from the first end 110 to the second end 112 of the covering panel. Similarly, while only one spar 114 is shown in FIG. 4 being positioned between the spar 104 and the spar 106, the stiffening structure 100 is not so limited, and more than one spar 114 can be positioned. between them. The length of the spar 104, the spar 106 and the spar 114 and their relative positions relative to each other depend on the application and configuration of the overall structure, such as for example a main wing or fin. The stiffening structure 100 also includes a rib 116 extending from the spar 104 to the spar 114. In an exemplary embodiment, a rib 116 also extends from the spar 114 to the spar. 106. The rib 116 is in one piece with the longitudinal members. In this respect, the stiffening structure 100 has no joints between the ribs and the longitudinal members, which would provide areas of weakness for the overall structure. In an exemplary embodiment, the stiffening structure 100 has the three ribs 116 spaced from each other and extending between the spar 104 and the spar 114 and between the spar 114 and the spar 106. The spacing of the ribs relative to each other depends on the application and configuration of the overall stiffening structure. While three ribs are shown in FIG. 4 being positioned between the spar 104 and the spar 114 and between the spar 114 and the spar 106, it will be appreciated that the stiffening structure is not so limited and may have , two or more ribs between the spar 104 and the spar 114. Similarly, the stiffening structure may have one, two or more ribs between the spar 114 and the spar 106. [0023] In a As an exemplary embodiment, the stiffening structure 100 of the wing structure 101 is coupled to the cladding board 102 and to a cladding board 118, as illustrated in FIG. 5. More specifically, junction walls 72 of the stiffening structure 100 are fixed to the covering panel 118, and the bases 76 are fixed to the covering panel 102. The stiffening structure 100 is immobilized on the u-shaped cladding panels. utilizing any suitable fastening mechanism, such as, for example, an adhesive, screws, nails, clips and the like, or a mixture thereof. In this regard, the stiffening structure 100 directly provides stiffening and load-bearing support for the cladding board 102 as well as the cladding board 118. As discussed in more detail in the following, the stiffening structure is formed by a flexible and drapeable composite material which can be draped within crevices and on the edges of a tool mold but which, during processing, imparts adequate reinforcing and stiffening properties for a desired application . In an exemplary embodiment, the stiffening structure is formed by carbon fiber reinforced plastic (CFRP). Such CFRP materials may be in the form of a braided fabric, a woven fabric, a unidirectional ribbon, a sheet molding mixture, or a bulk molding mixture. In one embodiment, the material is a CFRP triaxial braid. The material is, for example, QISOTM triaxial braided fabric available from A & P Technology of Cincinnati, Ohio. [0025] A method 200 for manufacturing a stiffening structure according to an exemplary embodiment is illustrated in FIG. 6. A stiffening structure master tool is formed with dimensions identical to the stiffening structure to be manufactured for the first time. final end product, such as the fin, the main wing or any other structure requiring stiffening and / or load-bearing support (step 202). Since a mold for the stiffening structure will be made from the stiffening structure master tool, the stiffening structure master tool is formed of any suitable material that can tolerate the processing of the material. from which the mold will be made. In one embodiment, the stiffening structure master tool is formed by rigid foam. Once the stiffening structure master tool is formed, a female mold of the stiffening structure is made from the stiffening structure master tool (step 204). In an exemplary embodiment, the mold is formed from the same material from which the desired stiffening structure will be made. In another exemplary embodiment, the mold is made of a material having a coefficient of thermal expansion that is similar to the coefficient of thermal expansion of the material from which the desired stiffening structure will be made. In this regard, the size changes between the mold and the desired stiffening structure during processing of the stiffening structure will be minimal or non-existent, so that the stiffening structure can be removed from the mold relatively easily and without damaging it. the stiffening structure. In another embodiment, the mold is made of any suitable material that can withstand the processing of the material of the desired stiffening structure. The mold may for example be formed of a metal or a rigid foam. Next, the material from which the desired stiffening structure is to be formed is placed in the mold cavity (step 206). As indicated above, the stiffening structure can be made from a flexible and drapeable composite material that can be put into place inside crevices and over mold edges. In an exemplary embodiment, the stiffening structure is formed by CFRP. In another embodiment, the stiffening structure is formed by a triaxial braid CFRP. Layers of the material are set up and draped within the mold to completely cover the mold walls and conform to the characteristics of the mold. The layers are disposed on intersections of ribs and spars so that the resulting stiffening structure is formed with integral spars and ribs. A material connection can be used to achieve even coverage of the mold. In an exemplary embodiment, the mold is placed inside an airtight bag in which a vacuum is made (step 208) and the material is then treated (step 210). The treatment process depends on the type of material selected for the stiffening structure. In an exemplary embodiment, the material is autoclaved at material-dependent temperatures. For stiffening structures made of QISOT ™ tri-axial woven fabric MIM-A-16.25 / E752, for example, the mold and the material are subjected to a treatment temperature of nearly 350 ° F. In another embodiment, the material is treated by room temperature treatment with post-treatment. Other methods of treatment are also possible. Once treated, the stiffening structure is removed from the mold (step 212). The stiffening structure may then be inspected, finished, and optionally bonded or otherwise affixed to one or more cladding panels (step 214). [0029] Therefore, various exemplary embodiments of stiffening structures, wing structures, and methods for making stiffening structures are provided herein. The stiffening structures comprise integral ribs and spars formed from a single mold. From this point of view, the manufacture of structures is efficient in terms of time and cost. The elements and ribs of the structures are configured with two walls that provide a larger load-bearing support than single-walled supports of conventional ladder-type configurations. The stiffening structures are further manufactured from composite materials such that the structures are lighter than conventional ladder-type configurations which contain metal. While at least one exemplary embodiment has been presented in the foregoing detailed description of the invention, it should be appreciated that a large number of variants exist. It should also be appreciated that the exemplary embodiment or exemplary embodiments are only examples, and do not intend to limit the scope, applicability or configuration of the invention in any way that this is. On the contrary, the foregoing detailed description will provide those skilled in the art with a roadmap adapted for implementing an exemplary embodiment of the invention. It goes without saying that various modifications may be made to the operation and arrangement of the elements described in an exemplary embodiment without departing from the scope of the invention as set forth in the appended claims.
    权利要求:
    Claims (19)
    [0001]
    REVENDICATIONS1. A stiffening structure comprising: a first longitudinal member and a second longitudinal member; a first rib extending from the first longitudinal member to the second longitudinal member and which is integral with the first longitudinal member and the second longitudinal member; wherein the first longitudinal member has a first wall, a second wall, and a joint wall that joins the first wall and the second wall, and wherein the first wall, the second wall, and the joint wall form a space having a trapezoidal shape.
    [0002]
    2. stiffening structure according to claim 1, wherein the second longitudinal member has a first wall, a second wall, and a junction wall which joins the first wall and the second wall, and wherein the first wall, the second wall; and the junction wall form a space having a trapezoidal shape.
    [0003]
    The stiffening structure according to claim 1, wherein the first rib has a first wall, a second wall, and a junction wall which joins the first wall and the second wall, and wherein the first wall, the second wall. and the junction wall form a space having a trapezoidal shape.
    [0004]
    The stiffening structure of claim 1, wherein the stiffening structure comprises carbon fiber reinforced plastic.
    [0005]
    The stiffening structure according to claim 1, wherein the first longitudinal member and the second longitudinal member are curvilinear. 30
    [0006]
    The stiffening structure of claim 1, further comprising a panel attached to the first longitudinal member and the second longitudinal member.
    [0007]
    A wing structure comprising: a first wing panel having a first end and a longitudinal axis; and a stiffening structure fixedly attached to the first wing panel and comprising: a first spar and a second spar each extending from the first end along the longitudinal axis of the first spider panel; wing, the first spar and the second spar each having a length; a third spar that is between the first spar and the second spar and extends along at least a portion of the length of the first spar and / or the second spar; a first rib extending from the first spar to the third spar 10 and which is integral with the first spar and the third spar; and a second rib extending from the third spar to the second spar and which is integral with the third spar and the second spar. 15
    [0008]
    8. wing structure according to claim 7, wherein the first spar and the second spar each have a first wall, a second wall, and a junction wall which joins the first wall and the second wall, and wherein the first wall, the second wall and the junction wall form a space having a trapezoidal shape.
    [0009]
    9. wing structure according to claim 7, wherein the third spar has a first wall, a second wall, and a connecting wall which joins the first wall and the second wall, and wherein the first wall, the second wall; and the junction wall form a space having a trapezoidal shape.
    [0010]
    The wing structure according to claim 7, wherein the first rib and the second rib each have a first wall, a second wall, and a junction wall which joins the first wall and the second wall, and wherein the first wall, the second wall and the junction wall form a space having a trapezoidal shape.
    [0011]
    The wing structure of claim 7, wherein the stiffening structure comprises carbon fiber reinforced plastic.
    [0012]
    Wing structure according to claim 7, wherein the wing structure is a main wing, a fin or a horizontal stabilizer. 12 3035071
    [0013]
    A method for manufacturing a stiffening structure, the method comprising the steps of: depositing a flexible and drapeable composite material within a cavity of a mold; Inserting the mold into a bag; the realization of a vacuum in the bag; processing the flexible and drapeable composite material to form the stiffening structure within the mold; and removing the mold stiffening structure, the stiffening structure comprising: a first longitudinal member and a second longitudinal member; a first rib extending from the first longitudinal member to the second longitudinal member and which is integral with the first longitudinal member and the second longitudinal member; and a second rib extending from the first longitudinal member to the second longitudinal member and which is integral with the first longitudinal member and the second longitudinal member, wherein the first longitudinal member and the second longitudinal member each have a first wall, a second wall, and a junction wall which joins the first wall and the second wall, and wherein the first wall, the second wall and the junction wall form a trapezoidal shaped space.
    [0014]
    The method of claim 13, wherein the removal of the stiffening structure comprises the removal of the stiffening structure where the first rib and the second rib each have a first wall, a second wall, and a junction wall which joins together the first wall and the second wall, and wherein the first wall, the second wall and the junction wall form a space having a trapezoidal shape.
    [0015]
    15. The method of claim 13, wherein the deposition comprises depositing a carbon fiber reinforced plastic (CFRP).
    [0016]
    The method of claim 15, wherein the deposition comprises depositing a triaxial braid of CFRP. 13 3035071
    [0017]
    The method of claim 13, further comprising, prior to deposition, manufacturing the mold so that the first longitudinal member and the second longitudinal member are formed curvilinearly. 5
    [0018]
    The method of claim 13, wherein the deposition comprises depositing within the mold made from the flexible and drapeable composite material.
    [0019]
    The method of claim 13, further comprising attaching the stiffening structure to a cladding panel. 14
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    法律状态:
    2017-04-26| PLFP| Fee payment|Year of fee payment: 2 |
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    申请号 | 申请日 | 专利标题
    US14/687,022|US9919791B2|2015-04-15|2015-04-15|Stiffening structures, wing structures, and methods for manufacturing stiffening structures|
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