ASSEMBLY OF A COMPOSITE MATERIAL CONTAINING FIBERS

Abstract

An assembly structure according to one embodiment of the present invention comprises a first member and a second member, the first member having a hole (55a) extending along an axis direction, the second member comprising a shaft member (31a), the shaft member (31a) being formed of a composite material containing fibers and having a shape to fit into the hole (55a), the second member being assembled to the first member via the shaft member (31a) such that its movement in the axis direction is restricted. Figure for abstract: FIG. 4

Description

Title of the invention: ASSEMBLY OF A COMPOSITE MATERIAL CONTAINING FIBERS

[0001] The present application is based on Japanese Patent Application Serial No. 2018-167876 (filed on September 7, 2018) and claims priority therefrom. TECHNICAL FIELD

[0002] The present description relates to an assembly between a composite material containing fibers and another element. BACKGROUND

[0003] A fastener such as a bolt is used to join another member to a composite member made of a fiber-containing composite material. In a joining structure described in Japanese Patent Application Publication No. 2014-237429, a connecting body of an aircraft reaction connection is made of the fiber-containing composite material, and the connecting body is joined to a socket using a bolt-shaped fastener.

[0004] When a bolt hole for inserting the bolt therethrough is formed in the composite member made of the fiber-containing composite material, reinforcing fibers contained in the composite member are cut, so that the strength of the composite member decreases. SUMMARY

[0005] An object of the present description is to provide a novel assembly structure capable of mitigating or solving at least in part the classic problem described above.

[0006] More specifically, an object of the present description is to assemble a composite element made of a composite material containing fibers to another element without cutting reinforcing fibers contained in the composite element. Other objects of the present description will appear upon reading the complete description given herein.

[0007] An assembly structure according to one embodiment of the present invention comprises a first member and a second member, the first member having a hole extending along an axis direction, the second member comprising a shaft member, the shaft member being formed of a composite material containing fibers and having a shape to fit into the hole, the second member being assembled to the first member via the shaft member such that its movement in the axis direction is restricted.

[0008] According to the embodiment, the shaft element of the second element is disposed in the hole formed in the first element, and thus the second element is assembled to the first element. As a result, the second element can be assembled to the first element without cutting reinforcing fibers, the reinforcing fibers being contained in the shaft element of the second element. Thus, it is possible to prevent a decrease in strength of the shaft element of the second element, the shaft element being made of a composite material containing fibers.

[0009] In an embodiment of the present invention, the shaft element has a first width at a first position in the axial direction and a second width at a second position in the axial direction, the second part being closer to a distal end of the shaft element than the first position, the second width being greater than the first width.

[0010] According to the embodiment, the first member can support the second member in the axis direction by using a portion thereof located at the first position in the axis direction. Thus, the first member can oppose a tensile load acting on the second member in a direction from the distal end toward a proximal end of the shaft member by using its portion located at the first position in the axis direction. Therefore, according to the embodiment, it is possible to more firmly assemble the first member to the second member.

[0011] In one embodiment of the present invention, the shaft member has a third width at a third position in the axis direction, the third position being closer to the distal end of the shaft member than the second position, the third width being smaller than the second width.

[0012] According to the embodiment, the first member can support the second member in the axis direction by using a portion thereof located at the third position in the axis direction. Thus, according to the embodiment, it is possible to more firmly assemble the first member to the second member.

[0013] In one embodiment of the present invention, the shaft member has a fourth width at a fourth position in the axis direction, the fourth position being closer to a proximal end of the shaft member than the first position, the fourth width being larger than the first width.

[0014] According to the embodiment, the first member can support the second member in the axis direction by using the portion thereof located at the first position in the axis direction. Thus, according to the embodiment, it is possible to more firmly assemble the first member to the second member.

[0015] In one embodiment of the present invention, the shaft member is hollow.

[0016] According to the embodiment, it is possible to obtain a weight reduction of the second element.

[0017] In one embodiment of the present invention, the shaft member has a non-circular cross-section in a direction perpendicular to the axis direction.

[0018] According to the embodiment, a torque of forces can be transmitted between the first element and the second element.

[0019] In one embodiment of the present invention, the first member comprises a cylindrical member defining the hole, and the cylindrical member has a lesser thickness at its proximal end in the axis direction than a distal end side of the proximal end in the axis direction.

[0020] According to the embodiment, a portion of the cylindrical member formed to be thin is elastically deformed, and thus a stress acting on the cylindrical member from the shaft member can be released. Thus, even when a large stress acts on a connecting body, it is unlikely that the cylindrical member will be broken.

[0021] In one embodiment of the present invention, the cylindrical member is made of a metal.

[0022] According to the embodiment, the shaft member made of a fiber-containing composite material can be joined to the cylindrical member made of metal without the use of a joining element such as a bolt, which could break reinforcing fibers contained in the fiber-containing composite material.

[0023] In one embodiment of the present invention, the shaft member comprises a first reinforcing fiber extending in a first direction. In addition, the shaft member comprises a joining portion and a non-joining portion, the joining portion overlapping the cylindrical member in the axis direction, the non-joining portion not overlapping the joining portion in the axis direction. In the embodiment, an angle formed by the first direction with the axis direction in the joining portion is greater than an angle formed by the first direction with the axis direction in the non-joining portion.

[0024] In one embodiment of the present invention, the shaft member further comprises a second reinforcing fiber extending in a second direction different from the first direction and woven with the first reinforcing fiber, and an angle formed by the second direction with the axis direction in the joining portion is less than an angle formed by the second direction with the axis direction in the non-joining portion.

[0025] According to the embodiment, in the shaft member, the second reinforcing fiber is woven with the first reinforcing fiber, and thus the strength of the shaft member can be increased. Furthermore, an angle formed by an extension direction (the second direction) of the second reinforcing fiber with the axis direction is larger in the joining portion of the shaft member. Therefore, in the assembly portion, the shaft member is more easily deformed in a width direction than in the non-assembly portion. This makes it easier to form the shaft member into a shape to fit into the hole.

[0026] In one embodiment of the present invention, a reinforcing member is arranged in the non-assembly portion of the shaft member, the reinforcing member being made of a fiber-containing composite material that contains reinforcing fibers oriented in a circumferential direction surrounding the axis direction.

[0027] According to the embodiment, the non-assembly portion of the shaft element may be reinforced by the reinforcing element.

[0028] An aircraft reaction link according to an embodiment of the present invention comprises a socket and a link body, the socket slidably supporting an actuator, the actuator being mounted directly or indirectly on a movable surface of an aircraft and configured to drive the movable surface, the link body comprising a shaft member made of a composite material containing fibers and being assembled to the socket. In the embodiment, the socket has a hole extending along an axis direction of the shaft member, and the shaft member is formed into a shape to fit into the hole and disposed in the hole such that its movement in the axis direction is limited.

[0029] According to the embodiment, in the aircraft reaction connection, the connection body can be assembled to the socket without decreasing the strength of the connection body.

[0030] A moving surface drive device according to one embodiment of the present invention comprises the aircraft reaction link described above and an actuator mounted directly or indirectly on a moving surface of an aircraft and configured to drive the moving surface.

[0031] According to the embodiment, a mobile surface drive device is obtained comprising the aircraft reaction connection improved in terms of assembly between the connection body and the socket.

[0032] One embodiment of the present invention provides a method for joining a first member to a second member, the first member having a hole extending along an axis direction, the second member comprising a shaft member made of a fiber-containing composite material. The joining method comprises the steps of: (A) preparing the first member, (B) preparing a core, (C) obtaining a laminate by forming a layer of fiber-containing composite material on the core, (D) inserting at least a portion of the laminate into the hole of the first member, (E) causing expansion of the core, and (F) obtaining the shaft member in a shape to fit into the hole by curing the layer of composite material containing fibers.

[0033] According to the embodiment, the second element comprising the shaft element can be assembled to the first element without reducing the strength of the shaft element, the shaft element being made of a composite material containing fibers.

[0034] The assembly method according to one embodiment of the present invention further comprises the step of removing the core.

[0035] According to the embodiment, the core is removed, and it is therefore possible to obtain a weight reduction of an assembly structure.

[0036] In one embodiment of the present invention, a shrinkage layer is disposed on an outer surface of the core, and the fiber-containing composite material layer is formed on the shrinkage layer.

[0037] According to the embodiment, the removal of the core is facilitated.

[0038] One embodiment of the present invention provides a method for manufacturing an aircraft reaction link connected to an actuator, the actuator being mounted on a movable surface of an aircraft and configured to drive the movable surface. The manufacturing method comprises the steps of: (A) preparing a socket configured to slidably support the actuator and having a hole extending along an axis direction, (B) preparing a core, (C) obtaining a laminate by forming a fiber-containing composite material layer on the core, (D) inserting at least a portion of the laminate into the hole of the socket, (E) causing expansion of the core, and (F) obtaining a link body by curing the fiber-containing composite material layer.

[0039] According to the embodiment, an aircraft reaction connection is obtained in which the connection body is connected to the socket without reducing the strength of the connection body. BRIEF DESCRIPTION OF THE DRAWINGS

[0040] [Fig. 1] is a perspective view of a portion of a wing comprising a movable surface drive device according to one embodiment of the present invention.

[0041] [Fig.2] is a side view of the wing shown in [Fig.l].

[0042] [Fig.3] is a perspective view of an aircraft reaction link shown on [Fig.l].

[0043] [Fig.4] is a sectional view of the aircraft reaction link shown in the [Fig.l] along a line II.

[0044] [Fig.5] is a sectional view of the aircraft reaction link shown in the [Fig.4] along a line II-II.

[0045] [Fig.6] is a perspective view of a socket included in the reaction link aircraft shown in [Fig.l].

[0046] [Fig.7] is an enlarged sectional view showing, on an enlarged scale, a portion of the aircraft reaction link shown in [Fig.l]. This enlarged sectional view shows an assembly structure between a shaft member and the bushing included in the aircraft reaction link shown in [Fig.l].

[0047] [Fig.8] is a schematic view showing schematically, on an enlarged scale, a distal end of a connecting body included in the aircraft reaction connection shown in [Fig.l]. For convenience of explanation, a socket 50a is shown in a broken state.

[0048] [Fig.9] is an enlarged sectional view showing, on an enlarged scale, a portion of an aircraft reaction link according to another embodiment of the present invention. This enlarged sectional view shows an assembly structure between a shaft element and a bushing included in the aircraft reaction link according to another embodiment.

[0049] [Fig. 10] is a schematic view schematically showing, on an enlarged scale, a distal end of a connecting body included in the aircraft reaction connection according to another embodiment of the present invention. For convenience of explanation, a socket 50a is shown in a broken state.

[0050] [Fig. 11] is a sectional view of the aircraft reaction link according to another embodiment of the present invention, cut along a plane perpendicular to the longitudinal axis direction thereof.

[0051] [Fig. 12] is a sectional view of the aircraft reaction link according to another embodiment of the present invention, cut along the plane perpendicular to the longitudinal axis direction thereof.

[0052] [Fig. 13] is a perspective view of the aircraft reaction link according to another embodiment of the present invention.

[0053] [Fig. 14] is a flowchart showing a method of manufacturing the aircraft reaction link according to an embodiment of the present invention.

[0054] Figures 15A to 15F are schematic views for showing the manufacturing method of the aircraft reaction link according to an embodiment of the present invention. [Fig.15A] shows a core.

[0055] [Fig. 15B] is a perspective view of a laminate obtained by forming a layer of composite material containing fibers on the core.

[0056] [Fig.l5C] is a sectional view of the laminate shown in [Fig.l5B], cut along a plane perpendicular to the longitudinal axis direction thereof.

[0057] [Fig.l5D] shows a composite laminate obtained by mounting one of the sockets on a laminate and a molding mold for molding the composite laminate.

[0058] [Fig.l5E] is a schematic view showing, on an enlarged scale, a vicinity of a distal end of the composite laminate placed in the molding mold.

[0059] [Fig. 15F] is a schematic view showing the composite laminate after expansion of the core in the casting mold. DESCRIPTION OF EXAMPLE EMBODIMENTS

[0060] The following describes various embodiments of the present invention with reference to the accompanying drawings where appropriate. Component elements common to a plurality of drawings are designated by the same reference numerals throughout the plurality of drawings. It should be noted that the drawings are not necessarily drawn to scale for convenience of explanation. In the drawings, certain component elements may be omitted for convenience of explanation.

[0061] A moving surface drive device according to one embodiment of the present invention will now be described with reference mainly to [Fig. 1] and [Fig. 2]. [Fig. 1] is a perspective view of a portion of a wing comprising a moving surface drive device according to one embodiment of the present invention, and [Fig. 2] is a side view of the wing. A moving surface drive device 1 is installed in an aircraft and configured and arranged to drive a moving surface 101 of a wing 100 of the aircraft. Examples of the moving surface 101 include primary flight control surfaces such as an aileron, a rudder, and a control surface, or secondary flight control surfaces such as a flap and a spoiler.

[0062] The movable surface drive device 1 comprises an actuator 10 and a reaction link 20. The actuator 10 is configured and arranged to drive the movable surface 101. The reaction link 20 is configured and arranged to support a reaction force from the movable surface 101 when the movable surface 101 is driven by the actuator 10.

[0063] The actuator 10 is connected to a support mechanism 102 arranged in the wing 100 and to a connecting shaft 103 of the movable surface 101. The movable surface 101 is supported so as to be rotatable relative to the wing 100 via a pivot shaft 104. The actuator 10 causes the movable surface 101 to rotate about the pivot shaft 104. A distal end portion of a rod 12 is rotatably connected to the connecting shaft 103. That is, the actuator 10 is directly connected to the movable surface 101. It is also possible that the distal end portion of the rod 12 is connected to a horn arm (not shown) connected to the movable surface 101. That is, the actuator 10 may also be indirectly connected to the movable surface 101.

[0064] The actuator 10 is a hydraulic linear actuator in which a working fluid such as a hydraulic oil is supplied to and discharged from a cylinder 11, thereby causing the rod 12 to reciprocate in an axis direction thereof. The actuator 10 may be an actuator driven by any method other than the use of fluid pressure. For example, the actuator 10 may be an electromechanical linear actuator comprising an electric motor.

[0065] As shown in [Fig.l], the actuator 10 comprises a connecting portion 13 connected to the reaction link 20 and the support portion 102. The connecting portion 13 is arranged on a side of the cylinder 11 opposite to a side thereof from which the rod 12 protrudes. The connecting portion 13 comprises a shaft 13A extending in a direction of a support axis J orthogonal to the axis direction of the rod 12. Here, the extending direction of the shaft 13A can be called the support axis direction.

[0066] The reaction link 20 is rotatably connected to the pivot shaft 104 and the shaft 13A of the connection portion 13. The reaction link 20 serves to prevent a reaction force generated when the movable surface 101 is driven by the actuator 10 from acting directly on the wing 100 from the movable surface 101. The reaction link 20 may be directly or indirectly connected to the movable surface 101. The reaction link 20 may be directly or indirectly connected to the actuator 10. In a case where the reaction link 20 is indirectly connected to the movable surface 101 or the actuator 10, the reaction link 20 is connected to the movable surface 101 or the actuator 10 via a link mechanism.

[0067] The movable surface drive device 1 thus configured operates in the following manner. A fluid pressure device (not shown) for supplying a working fluid to the actuator 10 operates on the basis of instructions from a flight control device (not shown), and thus the working fluid is supplied to and discharged from the cylinder 11 of the actuator 10. This causes the rod 12 to protrude from the cylinder 1 or retract into it, as shown in [Fig. 2], and thus the movable surface 101 connected to the rod 12 via the connecting shaft 103 rotates about the pivot shaft 104. When the movable surface 101 rotates, the reaction link 20 tilts about the pivot shaft 104. The reaction link 20 also tilts about the shaft 13A.As a result of this movement, the reaction link 20 receives, from the moving surface 101, a reaction force generated when the moving surface 101 is driven by the actuator 10.

[0068] Next, the reaction link 20 according to one embodiment of the present invention will be described in more detail with reference to FIGS. 3 to 8. As shown in these drawings, the reaction link 20 comprises a link body 30 formed in a U-shape in a plan view. The link body 30 may also have a linear shape or a J-shape other than the U-shape.

[0069] The connecting body 30 comprises a shaft element 31a extending linearly along a longitudinal axis A and a shaft element 31b extending linearly along a longitudinal axis B extending parallel to the longitudinal axis A. The axis Ion- longitudinal axis A and longitudinal axis B indicate a longitudinal direction of the connecting body 30. The shaft member 31a and the shaft member 31b extend in parallel directions so as to be spaced apart from each other. The shaft member 31a and the shaft member 31b are formed in substantially the same shape. Here, a description relating to the shaft member 31a also applies to the shaft member 31b, unless otherwise construed in view of the context or nature of the present invention. Here, a direction along the longitudinal axis A may be referred to as a longitudinal axis direction A, and a direction along the longitudinal axis B may be referred to as a longitudinal axis direction B. The longitudinal axis direction A and the longitudinal axis direction B may be collectively referred to simply as an axis direction.Herein, when referring to a proximal end and a distal end of each element, the distal end is on a top side in [Fig.4] and the proximal end is on a bottom side in [Fig.4] in the direction along the longitudinal axis A (or the longitudinal axis B), unless otherwise construed in light of the context.

[0070] A proximal end of the shaft member 31a in the longitudinal axis direction A and a proximal end of the shaft member 31b in the longitudinal axis direction B are connected to each other via a connecting portion 32. The connecting portion 32 includes a straight portion 33 and curved portions 34 arranged at both ends of the straight portion 33, the straight portion 33 extending in a direction orthogonal to the longitudinal axis A and the longitudinal axis B. A pair of the shaft members 31a and 31b may be integrally formed with the connecting portion 32.

[0071] In one embodiment of the present invention, the shaft member 31a is hollow, as shown in FIGS. 4 and 5. The shaft member 31a may be formed to be solid. In the case where the shaft member 31a is formed to be hollow, it is possible to achieve a weight reduction of the shaft member 31a and ultimately the connecting body 30. In one embodiment of the present invention, as shown in [Fig. 5], the shaft member 31a is formed into a circular shape or a substantially circular shape as observed in section. A sectional shape of the shaft member 31a is not limited to the circular shape or the substantially circular shape. Examples of modification of the shaft member 31a will be described later.

[0072] A top layer not shown may be formed on the shaft member 31a. The top layer may be applied for various purposes. The top layer may be applied to, for example, provide weather resistance to the connecting body 30, increase the strength of the connecting body 30, improve the decorative character of the connecting body 30, provide a lightning protection function, or other purposes. The upper layer may be made of a composite material containing fibers or a material other than the composite material containing fibers. A fiber-reinforced plastic material used for the upper layer may contain glass fibers as reinforcing fibers. The upper layer having the lightning protection function may be formed, for example, of a wire mesh. In order to impart the lightning protection function, a ground wire may be attached to a surface of the shaft member 31a.

[0073] A bushing 50a is arranged at a distal end of the shaft member 31a in the longitudinal axis direction A, and a bushing 50b is arranged at a distal end of the shaft member 31b in the longitudinal axis direction B.

[0074] The sockets 50a and 50b are made of, for example, a metallic material. As the metallic material used for the sockets 50a and 50b, a titanium alloy, a chromium-molybdenum steel, a nickel-chromium-molybdenum steel, a stainless steel, and other known metallic materials can be used. The sockets 50a and 50b may be made of a material other than the metallic material. For example, the sockets 50a and 50b may be made of a ceramic material, a fiber-reinforced plastic material such as CFRP, or any various types of resinous materials.

[0075] In one embodiment of the present invention, the connecting body 30 is made of a composite material that contains fibers ("fiber-containing composite material"). The fiber-containing composite material is, for example, a fiber-reinforced plastic (FRP). Reinforcing fibers made of any of various raw materials may be used as the reinforcing fibers contained in the connecting body 30. For example, the connecting body 30 may be made of a carbon fiber-reinforced plastic (CFRP) material containing carbon fibers as the reinforcing fibers. As the carbon fibers, PAN-based carbon fibers, pitch-based carbon fibers, or any other known type of carbon fibers may be used.The connecting body 30 may be made of a glass fiber reinforced plastic (GFRP), a glass mat reinforced thermoplastic (GMT), a boron fiber reinforced plastic (BFRP), an aramid fiber reinforced plastic (AFRP, KFRP), a Dyneema fiber reinforced plastic (DFRP), a Zylon fiber reinforced plastic (ZFRP), or any other type of fiber reinforced plastic.

[0076] The connecting body 30 may be made entirely or partially of a composite material containing fibers. For example, only the shaft elements 31a and 31b of the connecting body 30 may be made of a composite material containing fibers. In this case, the connecting portion 32 may be made of a material other than than the fiber-containing composite material, such as, for example, a metal material. In addition, in the connecting body 30, only a portion of the pair of shaft members 31a and 31b on a distal end side thereof may be made of a fiber-containing composite material. The connecting body 30 may be made of a fiber-containing composite material formed from a combination of a plurality of types of fibers or a combination of a plurality of types of fiber-containing composite materials.

[0077] As described above, in one embodiment of the present invention, the shaft members 31a and 31b are made of a fiber-containing composite material. Here, the shaft members 31a and 31b made of a fiber-containing composite material include a configuration in which they are entirely made of the fiber-containing composite material and a configuration in which they are partially made of the fiber-containing composite material. That is, here, the shaft members 31a and 31b made of a fiber-containing composite material refers to shaft members made at least partially of the fiber-containing composite material.For example, it is possible that a portion of the shaft member 31a to be joined to the socket 50a (a joining portion 35a mentioned below) is made of a composite material containing fibers, and a portion of the shaft member 31a other than the portion to be joined to the socket 50a is made of a material other than the composite material containing fibers.

[0078] Now, an orientation of the reinforcing fibers in the shaft member 31a will be described in more detail with reference to [Fig. 8]. As shown in [Fig. 8], the shaft member 31a comprises a plurality of reinforcing fibers 60. A matrix resin is filled in a space between the reinforcing fibers 60. For a clear representation of the reinforcing fibers 60, the matrix resin is omitted in [Fig. 8].

[0079] The reinforcing fibers 60 include a first reinforcing fiber 60, a second reinforcing fiber 62, and a third reinforcing fiber 63. The first reinforcing fiber 61, the second reinforcing fiber 62, and the third reinforcing fiber 63 are each a filament bundle composed of a large number of monofilaments. It is possible that the first reinforcing fiber 61, the second reinforcing fiber 62, and the third reinforcing fiber 63 are each a monofilament, a staple yarn made by discontinuous spinning, a filament, or a braid which is a knitted cord comprising rovings. The first reinforcing fiber 61, the second reinforcing fiber 62, and the third reinforcing fiber 63 may be made of the same material or different materials.

[0080] The first reinforcing fiber 61 extends in a first direction DI different from the longitudinal axis A. The second reinforcing fiber 62 extends in a second direction D2 different from the longitudinal axis A and the first direction DI. The third reinforcing fiber 63 extends in a third direction D3 parallel to the longitudinal axis A. In the embodiment shown, an acute angle formed by the first direction DI with the longitudinal axis A is, for example, 45°, and an acute angle formed by the second direction D2 with the longitudinal axis A is, for example, 45° in a direction opposite to the first direction DI. Each of the first direction DI and the second direction D2 can form any angle with the longitudinal axis A.

[0081] In the embodiment shown, the first reinforcing fiber 61, the second reinforcing fiber 62, and the third reinforcing fiber 63 are woven together. It is possible that the first to third reinforcing fibers 61 to 63 are not woven together but form respective layers stacked together in the order of, for example, the first reinforcing fiber 61, the second reinforcing fiber 62, and the third reinforcing fiber 63. The stacking order of the first reinforcing fiber 61, the second reinforcing fiber 62, and the third reinforcing fiber 63 can be changed as desired.

[0082] As shown in [Fig.8], in one embodiment, an angle formed by an angle DI of the first reinforcing fiber 61 with the longitudinal axis A in the joining portion 35a of the shaft member 31a is greater than an angle formed by the angle DI of the first reinforcing fiber 61 with the longitudinal axis A in the non-joining portion 36a of the shaft member 31a. That is, in the joining portion 35a, an extension direction of the first reinforcing fiber 61 is directed more perpendicular to the longitudinal axis A than in the non-joining portion 36a. Similarly, an angle formed by an angle D2 of the second reinforcing fiber 62 with the longitudinal axis A in the joining portion 35a of the shaft member 31a is greater than an angle formed by the angle D2 of the second reinforcing fiber 62 with the longitudinal axis A in the non-joining portion 36a of the shaft member 31a.That is, in the joining portion 35a, an extension direction of the second reinforcing fiber 62 is directed more perpendicular to the longitudinal axis A than in the non-joining portion 36a.

[0083] A head 40 is arranged at a proximal end of the connecting body 30. The head 40 is connected to the pivot shaft 104. In the embodiment shown, the head 40 is connected to the middle of the straight portion 33 of the connecting part 32. The head 40 comprises a first body 41 and a second body 42. The first body 41 has a mounting hole 41a into which the connecting part 32 is inserted. The second body 42 has a through hole 42a extending in the same direction as an extension direction of the mounting hole 41a. A bearing not shown may be mounted in the through hole 42a. The through hole 42a rotatably supports the pivot shaft 104 via the bearing.

[0084] As described above, the bushing 50a is assembled to the distal end of the shaft member 31a of the connecting body 30. An assembly structure composed of the connecting body 30 and the bushing 50a assembled to the connecting body 30 is an embodiment of an assembly structure according to the present invention. Similarly, the bushing 50b is assembled to the distal end of the shaft member 31b of the connecting body 30. An assembly structure composed of the connecting body 30 and the bushing 50b assembled to the connecting body 30b is also an example of the assembly structure according to the present invention.

[0085] Hereinafter, the assembly structure composed of the shaft member 31a of the connecting body 30 and the socket 50a and the assembly structure composed of the shaft member 31b of the connecting body and the socket 50b will be described with reference mainly to [Fig. 6] and [Fig. 7]. The assembly structure composed of the shaft member 31b and the socket 50b is substantially identical to the assembly structure composed of the shaft member 31a and the socket 50a, and thus the following mainly describes the assembly structure composed of the shaft member 31a and the socket 50a, omitting a description of the assembly structure composed of the shaft member 31b and the socket 50b.

[0086] First, the bushing 50a will now be described. [Fig. 6] is a perspective view of the bushing 50a when not mounted on the connecting body 30, and [Fig. 7] is an enlarged sectional view showing, on an enlarged scale, a portion of the aircraft reaction connection 20. This enlarged sectional view represents an assembly structure composed of the shaft element 31a included in the aircraft reaction connection 20 and the bushing 50a.

[0087] As shown, the socket 50a includes a socket body 51a and a cylindrical member 52a extending from the socket body 51a toward a proximal end side of the longitudinal axis A. The socket body 51a may be integrally formed with the cylindrical member 52a.

[0088] The socket body 51a has a through hole 51al. The through hole 51al extends through the socket body 51a along a J-axis direction of the shaft 13A.

[0089] The cylindrical member 52a includes a cylindrical base portion 53a connected to the socket body 51a and an opening portion 54a extending from the base portion 53a toward the proximal end side of the longitudinal axis A and which is open toward the proximal end side of the longitudinal axis A. The cylindrical member 52a has a hole 55a extending along the longitudinal axis A.

[0090] In the illustrated embodiment, the base portion 53a comprises a ring-shaped side wall 53al having substantially uniform outer and inner widths and a bottom wall 53a2 arranged at a distal end of the side wall 53al in the longitudinal axis direction A. As described above, the base portion 53a is formed into a bottomed cylindrical shape having the bottom wall 53a2. The base portion 53a is connected at the bottom wall 53a2 to the socket body 51a.

[0091] In the embodiment shown, the opening portion 54a has a ring-shaped side wall 54al. The side wall 54al is connected to a proximal end of the side wall 53al of the base portion 53a in the longitudinal axis direction A. The side wall 54al extends from a position at which it connects to the side wall 53al to an opening end 54a2 substantially along the longitudinal axis A. In the embodiment shown, at a proximal end portion of the side wall 54al close to its proximal end in the longitudinal axis direction A, the side wall 54a1 has an outer width (dimension in a width direction orthogonal to the longitudinal axis direction A) smaller than that of its distal end portion closer to its distal end than the proximal end portion in the longitudinal axis direction A.In one embodiment, the opening portion 54a is configured to have an outer width (a dimension in a width direction orthogonal to the longitudinal axis direction A) smaller toward a proximal end of the longitudinal axis A. Thus, the opening portion 54a is configured to have a thickness at its proximal end in the longitudinal axis direction A (i.e., a thickness at the opening end 54a2) less than a thickness thereof at a position closer to its distal end than the opening end 54a2 in the longitudinal axis direction A.According to the embodiment, a part of the cylindrical element 52a near the opening end 54a2, the part being formed to be thin, is elastically deformed, and thus even when the shaft element 31a moves in the longitudinal axis direction A, a stress caused by the movement and acting on the cylindrical element 52a from the shaft element 31a can be relaxed. Thus, the shaft element 31a and the cylindrical element 52a are not likely to be broken. The cylindrical element 52a can be formed to have a smaller thickness toward a proximal end thereof in the longitudinal axis direction A..

[0092] In the embodiment shown, the hole 55a formed in the cylindrical member 52a extends from the opening end 54a2 of the opening portion 54a to the bottom wall 53a2 of the base portion 53a along substantially the longitudinal axis direction A. The hole 55a is defined by inner surfaces of the side wall 53al and the bottom wall 53a2 of the base portion 53a as well as by an in surface interior of the side wall 54al of the opening part 54a.

[0093] In the embodiment shown, an inner surface of the hole 55a comprises a first inner surface 55al extending from the opening end 54a2 in a direction parallel to the longitudinal axis A, a second inner surface 55a2 extending from a distal end of the first inner surface 55al in the longitudinal axis direction A so as to be inclined relative to the longitudinal axis A, a third inner surface 55a3 extending, in the direction parallel to the longitudinal axis A, from a distal end of the second inner surface 55a2 in the longitudinal axis direction A, a fourth inner surface 55a4 extending from a distal end of the third inner surface 55a3 in the longitudinal axis direction A so as to be inclined relative to the longitudinal axis A, and a fifth inner surface 55a5 extending, in the direction parallel to the longitudinal axis A,from a distal end of the fourth inner surface 55a4 in the longitudinal axis direction A. The inner surface 55a2 is inclined in a direction away from the longitudinal axis A toward its distal end in the longitudinal axis direction A. The inner surface 55a4 is inclined in a direction toward the longitudinal axis A toward its distal end in the longitudinal axis direction A. The first inner surface 55a1, the second inner surface 55a2, the third inner surface 55a3, the fourth inner surface 55a4, and the fifth inner surface 55a5 extend in a direction of the longitudinal axis A by distances 11, 12, 13, 14, and 15, respectively.

[0094] In one embodiment of the present invention, the hole 55a is formed to have a width (a dimension in a width direction orthogonal to the longitudinal axis direction A) varying depending on a position in the longitudinal axis direction A. That is, the cylindrical member 52a is formed to have a width varying depending on a position in the longitudinal axis direction A. In the illustrated embodiment, the hole 55a has a first width d1 at a position P1 in the longitudinal axis direction A, a second width d2 at a position P2 in the longitudinal axis direction A, and a third width d3 at a position P3 in the longitudinal axis direction A. In the longitudinal axis direction A, the position P1 is in an area in which the first inner surface 55a1 extends. The position P2 is at a position closer to the distal end than the position P1 in the longitudinal axis direction A.For example, in the longitudinal axis direction A, the position P2 is in an area in which the third inner surface 55a3 extends. The position P3 is at a position closer to the distal end than the position P2 in the longitudinal axis direction A. For example, in the longitudinal axis direction A, the position P3 is in a . area in which the fifth inner surface 55a5 extends. In the embodiment shown, the second width d2 is greater than the first width d1 and the third width d3. The third width d3 may be equal to the first width d1 or less than or greater than the first width d1. As described above, in the embodiment shown, at a position corresponding to the third inner surface 55a3, the hole 55a formed in the cylindrical member 52a has a width greater than that at any other position. Here, a portion of the cylindrical member 52a corresponding to the inner surface 55a3 in the longitudinal axis direction A may be referred to as a wide portion 52al. Here, a width of any component element of the socket 50a or the hole 55a may refer to a dimension of any component element or the hole 55a in a width direction orthogonal to the longitudinal axis direction A.For example, the first width dl of the hole 55a at position P1 may refer to a dimension of the hole 55a in a width direction thereof at position P1. In the longitudinal axis direction A, position P1 is an example of the first position, position P2 is an example of the second position, and position P3 is an example of the third position.

[0095] The socket 50b comprises a socket body 51b and a connector 52b assembled to the distal end of the shaft member 31b. The socket body 51b is secured to the connector 52b using a fastener 53b. The socket body 51b has a through hole 51bl. The through hole 51bl extends through the socket body 51b along the J-axis direction of the shaft 13A.

[0096] The fitting 52b of the socket 50b has a hole 55b extending along the axis direction B. The hole 55b extends through the fitting 52b along the axis direction B. An inner peripheral surface of the hole 55b has a shape similar to that of an inner peripheral surface of the hole 55a, and a detailed description thereof is, therefore, omitted.

[0097] The assembly portion 35a at the distal end of the shaft member 31a is housed in the hole 55a of the cylindrical member 52a. Here, a portion of the shaft member 31a covered by the cylindrical member 52a may be referred to as the assembly portion 35a, and a portion of the shaft member 31a not covered by the cylindrical member 52a may be referred to as the non-assembly portion 36a.

[0098] The assembly portion 35a of the shaft member 31a is formed into a shape that fits into the hole 55a of the cylindrical member 52a. In the embodiment shown, the assembly portion 35a comprises a first portion 35al extending, in the direction parallel to the longitudinal axis A, from a position in the longitudinal axis direction A corresponding to the opening end 54a2 of the cylindrical member 52a, a second portion 35a2 extending from a distal end of the first portion 35al in the longitudinal axis direction A so as to be inclined relative to the longitudinal axis A, a third portion 35a3 extending, in the direction parallel to the longitudinal axis A, from a distal end of the second portion 35a2 in the longitudinal axis direction A, a fourth portion 35a4 extending from a distal end of the third portion 35a3 in the longitudinal axis direction A so as to be inclined relative to the longitudinal axis A, and a fifth portion 35a5 extending, in the direction parallel to the longitudinal axis A, from a distal end of the fourth portion 35a4 in the longitudinal axis direction A.In one embodiment, the first portion 35al, the second portion 35a2, the third portion 35a3, the fourth portion 35a4, and the fifth portion 35a5 each extend along a corresponding one of the first inner surface 55al, the second inner surface 55a2, the third inner surface 55a3, the fourth inner surface 55a4, and the fifth inner surface 55a5. In one embodiment, the first portion 35al, the second portion 35a2, the third portion 35a3, the fourth portion 35a4, and the fifth portion 35a5 each have an outer surface formed to closely adhere to a corresponding one of the first inner surface 55al, the second inner surface 55a2, the third inner surface 55a3, the fourth inner surface 55a4, and the fifth inner surface 55a5.The joining portion 35a has a width (outer width) equal to a width (inner width) of the inner surface of the hole 55a. As described above, the hole 55a has the first width d1 at the position P1 in the longitudinal axis direction A, the second width d2 at the position P2 in the longitudinal axis direction A, and the third width d3 at the position P3 in the longitudinal axis direction A, and thus the joining portion 35a is formed to have a width d1 at the first portion 35a1 located at the position P1, a width d2 at the third portion 35a3 located at the position P2, and a width d3 at the fifth portion 35a5 located at the position P3.As described above, the assembly portion 35a of the shaft member 31a is configured to have the width d1 at the position P1 in the longitudinal axis direction A and the width d2 at the position P2 closer to the distal end than the position P1 in the longitudinal axis direction A, the width d2 being greater than the width d1. In addition, the assembly portion 35a of the shaft member 31a is configured to have the width d3 at the position P3 closer to the distal end than the position P2 in the longitudinal axis direction A, the width d3 being less than the width d2.

[0099] The assembly portion 35a is formed in a shape matching the inner surface of the cylindrical element 52a defining the hole 55a, and therefore at any position on the longitudinal axis A, the assembly portion 35a has a width (outer width) equal to the width (inner width) of the hole 55a. Therefore, the assembly portion 35a has the width d1 at the position P1 on the longitudinal axis A, the width d2 at the position P2, and the width d3 at position P3 on the longitudinal axis A.

[0100] In the above-described assembly structure between the connecting body 30 and the socket 50a, the shaft member 31a of the connecting body 30 is formed into a shape that fits into the hole 55a, and the shaft member 31a formed into this shape is disposed in the hole 55a. Thus, in the hole 55a, movement of the shaft member 31a in the longitudinal axis direction A is restricted, and the shaft member 31a cannot fall out of the hole 55a. Therefore, the connecting body 30 is assembled to the socket 50a via the shaft member 31a without cutting reinforcing fibers, the reinforcing fibers being contained in the shaft member 31a. As described above, in the predetermined structure formed by assembling the connecting body 30 to the socket 50a, it is possible to prevent a decrease in the strength of the shaft member 31a made of a fiber-reinforced plastic material.Similarly, the connecting body 30 is joined to the socket 50b via the shaft member 31b without cutting reinforcing fibers, the reinforcing fibers being contained in the shaft member 31b. It is also possible to use an adhesive to join the shaft member 31a to the socket 50a and to join the shaft member 31b to the socket 50b. Also, in the case of using an adhesive, reinforcing fibers contained in the shaft member 31a and the shaft member 31b cannot be cut.

[0101] In the above-described assembly structure between the connecting body 30 and the bushing 50a, the bushing 50a has the wide portion 52al, and the wide portion 52al receives the third portion 35a3 of the shaft member 31a, the third portion 35a3 being formed to be wide. Thus, the bushing 50a supports the third portion 35a3 of the shaft member 31a in the longitudinal axis direction A by using a portion thereof closer to the proximal end than the wide portion 52al in the longitudinal axis direction A. Specifically, when a tensile load toward the proximal end in the longitudinal axis direction A acts on the connecting body 30, the tensile load is received by the inclined inner surface 55a2 of the hole 55a of the bushing 50a.Accordingly, when a tensile load toward the proximal end in the longitudinal axis direction A acts on the connecting body 30, the bushing 50a can oppose the tensile load by utilizing the inner surface 55a2. Thus, the shaft member 31a can be more reliably prevented from falling out of the hole 55a, so that the connecting body 30 can be more firmly assembled to the bushing 50a.

[0102] In addition, the bushing 50a supports the third portion 35a3 of the shaft member 31a in the longitudinal axis direction A by using a portion thereof closer to the distal end than the wide portion 52a 1 in the longitudinal axis direction A. Specifically, when a compressive load directed toward the distal end in the longitudinal axis direction A acts on the connecting body 30, the compressive load is received by the inclined inner surface 55a4 of the hole 55a of the bushing 50a. Accordingly, when a compressive load directed toward the distal end in the longitudinal axis direction A acts on the connecting body 30, the bushing 50a can oppose the compressive load by using the inner surface 55a4. Thus, the connecting body 30 can be more firmly joined to the bushing 50a. In addition, a compressive force acting on the connecting body 30 is opposed by using the inner surface 55a4, and thus it is possible to prevent stress from being concentrated on the distal end of the shaft member 31a. Thus, it is possible to prevent the shaft member 31a from deforming under a compressive load.

[0103] In the preceding embodiment, an angle formed by the first reinforcing fiber 61 contained in the shaft member 31a with the longitudinal axis direction A in the joining portion 35a is greater than an angle formed by the first reinforcing fiber 61 with the longitudinal axis direction A in the non-joining portion 36a. Therefore, in the joining portion 35a, the shaft member 31a deforms more easily in the width direction than in the non-joining portion 36a. This facilitates processing of the shaft member 31a into a shape to fit into the hole 55a.

[0104] In the preceding embodiment, the first reinforcing fiber 61 is woven with the second reinforcing fiber 62. Thus, the strength of the shaft member 31a can be increased. In addition, an angle formed by the second reinforcing fiber 62 with the longitudinal axis direction A in the joining portion 35a is smaller than an angle formed by the second reinforcing fiber 62 with the longitudinal axis direction A in the non-joining portion 36a. This facilitates processing of the shaft member 31a into a shape to fit into the hole 55a.

[0105] The assembly structure between the shaft member 31a and the hole 55a in the preceding embodiment is merely one embodiment of the present invention, and the shape of the hole 55a and the shape of the shaft member 31a to be fitted therein may be changed as appropriate. An example of another embodiment of the assembly structure formed by assembling the connecting body 30 to the socket 50a will now be described with reference to [Fig. 9]. [Fig. 9] shows an assembly structure between a shaft member and a hole in another embodiment of the present invention.

[0106] As shown in [Fig. 9], in the assembly structure according to another embodiment of the present invention, a cylindrical element 52a has a hole 155a instead of the hole 55a. As shown, an inner surface of the hole 155a includes a first inner surface 155al extending from an opening end 54a2 in a direction parallel to a longitudinal axis A, a second inner surface 155a2 extending from a distal end of the first inner surface 155al in a longitudinal axis direction A so as to be inclined relative to the longitudinal axis A, a third inner surface 155a3 extending, in the direction parallel to the longitudinal axis A, from a distal end of the second inner surface 155a2 in the longitudinal axis direction A, a fourth inner surface 155a4 extending from a distal end of the third inner surface 155a3 in the longitudinal axis direction A so as to be inclined relative to the longitudinal axis A, and a fifth inner surface 155a5 extending, in the direction parallel to the longitudinal axis A, from a distal end of the fourth inner surface 155a4 in the longitudinal axis direction A.The inner surface 155a2 is inclined in a direction toward the longitudinal axis A toward its distal end in the longitudinal axis A direction. The inner surface 155a4 is inclined in a direction away from the longitudinal axis A toward a distal end thereof in the longitudinal axis A direction. Therefore, in the embodiment shown in [Fig.9], a socket 50a includes a bulged portion 152al that bulges inward in a width direction of the hole 155a.

[0107] In the illustrated embodiment, the hole 155a has a first width dl 1 at a position P1 1 in the longitudinal axis direction A, a second width dl 2 at a position P12 in the longitudinal axis direction A, and a third width dl 3 at a position P13 in the longitudinal axis direction A. In the longitudinal axis direction A, the position P1 1 is in an area in which the first inner surface 155a1 extends. The position P12 is at a position closer to the distal end than the position P1 in the longitudinal axis direction A. For example, in the longitudinal axis direction A, the position P12 is in an area in which the third inner surface 155a3 extends. The position P13 is at a position closer to the distal end than the position P12 in the longitudinal axis direction A.For example, in the longitudinal axis direction A, position P13 is in an area in which the fifth inner surface 155a5 extends. In the illustrated embodiment, the second width d12 is less than the first width d11 and the third width d13. The third width d13 may be equal to the first width d11 or less than or greater than the first width d11. As described above, in the illustrated embodiment, at a position corresponding to the third inner surface 155a3, the hole 155a formed in a cylindrical member 152a has a width less than that at any other position. In the longitudinal axis direction A, position P12 is an example of the first position, position P13 is an example of the second position, and position P11 is an example of the fourth position.

[0108] In the embodiment shown in [Fig.9], an assembly portion 35a of a shaft member 31a is formed into a shape to fit into the hole 155a of the cylindrical element 52a. Specifically, in the embodiment shown, the assembly portion 35a comprises a first portion 135al extending, in the direction parallel to the longitudinal axis A, from a position in the longitudinal axis direction A corresponding to the opening end 54a of the cylindrical member 52a, a second portion 135a2 extending from a distal end of the first portion 135al in the longitudinal axis direction A so as to be inclined with respect to the longitudinal axis A, a third portion 135a3 extending, in the direction parallel to the longitudinal axis A, from a distal end of the second portion 135a2 in the longitudinal axis direction A, a fourth portion 135a4 extending from a distal end of the third portion 135a3 in the longitudinal axis direction A so as to be inclined with respect to the longitudinal axis A, and a fifth portion 135a4 extending from a distal end of the third portion 135a3 in the longitudinal axis direction A so as to be inclined with respect to the longitudinal axis A, and a fifth portion 135a4 extending from a distal end of the third portion 135a3 in the longitudinal axis direction A so as to be inclined with respect to the longitudinal axis A. 135a5 extending,in the direction parallel to the longitudinal axis A, from a distal end of the fourth portion 135a5 in the longitudinal axis direction A. In one embodiment, the first portion 135al, the second portion 135a2, the third portion 135a3, the fourth portion 135a4, and the fifth portion 135a5 each extend along a corresponding surface among the first inner surface 155al, the second inner surface 155a2, the third inner surface 155a3, the fourth inner surface 155a4, and the fifth inner surface 155a5. In one embodiment, the first portion 135al, the second portion 135a2, the third portion 135a3, the fourth portion 135a4, and the fifth portion 135a5 each have an outer surface formed to closely adhere to a corresponding one of the first inner surface 155al, the second inner surface 155a2, the third inner surface 155a3, the fourth inner surface 155a4,and the fifth inner surface 155a5. The joining portion 35a has a width (outer width) equal to a width (inner width) of the inner surface of the hole 155a. Therefore, the joining portion 35a is formed to have a width dl 1 at the first portion 135a1 located at the position P11, a width dl2 at the third portion 135a3 located at the position P12, and a width dl3 at the fifth portion 135a5 located at the position P3. As described above, the joining portion 35a of the shaft member 31a is configured to have the width dl2 at the position P12 in the longitudinal axis direction A and the width dl3 at the position P13 closer to the distal end than the position P12 in the longitudinal axis direction A, the width dl3 being greater than the width dl2. Moreover,the assembly portion 35a of the shaft member 31a is configured to have the width dl 1 at the position P1 1 closer to the proximal end than the position P12 in the longitudinal axis direction A, the width dl 1 being greater than the width dl2.

[0109] In the assembly structure of the embodiment, the socket 50a has the part bulged portion 152al, and the bulged portion 152al is received by the third portion 135a3 of the shaft member 31a, the third portion 135a3 being formed to be narrow. Thus, the bushing 50a supports the first portion 135al of the shaft member 35al in the longitudinal axis direction A by using a portion thereof closer to the distal end than the bulged portion 152al in the longitudinal axis direction A. Specifically, when a compressive load directed toward the distal end in the longitudinal axis direction A acts on a connecting body 30, the compressive load is received by the inclined inner surface 155a2 of the hole 155a of the bushing 50a. Accordingly, when a compressive load directed toward the distal end in the longitudinal axis direction A acts on the connecting body 30, the bushing 50a can oppose the compressive load by using the inner surface 155a2.Accordingly, when a compressive load directed toward the distal end in the longitudinal axis direction A acts on the connecting body 30, the bushing 50a can oppose the compressive load by using the inner surface 155a2. Thus, the connecting body 30 can be firmly assembled to the bushing 50a. In addition, a compressive force acting on the connecting body 30 is opposed by using the inner surface 155a2, and thus it is possible to prevent the shaft member 31a from deforming under the compressive load.

[0110] In addition, the bushing 50a supports the fifth portion 135a5 of the shaft member 31a in the longitudinal axis direction A by using a portion thereof closer to the distal end than the bulged portion 152al in the longitudinal axis direction A. Specifically, when a tensile load toward the proximal end in the longitudinal axis direction A acts on the connecting body 30, the tensile load is received by the inclined inner surface 155a4 of the hole 155a of the bushing 50a. Accordingly, when a tensile load toward the distal end in the longitudinal axis direction A acts on the connecting body 30, the bushing 50a can oppose the tensile load by using the inner surface 155a4. Thus, the connecting body 30 can be more firmly joined to the bushing 50a.

[0111] The assembly structure to which the present invention is applied may take various forms other than the embodiment shown in [Fig. 9]. For example, the cylindrical member 52a may have any other portion formed to be wide in addition to the wide portion 52al. In addition, the cylindrical member 52a may have any other portion formed to protrude inward in the width direction in addition to the bulged portion 152al. The hole 55a and the hole 155a may be formed in various shapes capable of receiving the shaft member 31a.

[0112] Next, examples of modification of the connecting body 30 will now be described with reference to FIGS. 10 to 12. [Fig. 10] is a schematic view schematically showing, on an enlarged scale, a distal end of a connecting body connection included in an aircraft reaction connection according to another embodiment of the present invention. [Fig.l 1] is a sectional view of the aircraft reaction connection according to another embodiment of the present invention cut along a plane perpendicular to its longitudinal axis direction A. [Fig. 12] is a sectional view of the aircraft reaction connection according to another embodiment of the present invention cut along the plane perpendicular to its longitudinal axis direction A.

[0113] As shown in [Fig. 10], a connecting body 30 according to another embodiment of the present invention comprises a reinforcing member 70. The reinforcing member 70 is formed of a sheet made of a fiber-reinforced plastic material. The reinforcing member 70 is formed, for example, of a fiber-reinforced plastic sheet containing reinforcing fibers oriented in a circumferential direction of a shaft member 31a. As reinforcing fibers contained in the reinforcing member 70, reinforcing fibers of the same type as the reinforcing fibers 61 can be used. In one embodiment, the reinforcing member 70 is arranged at a portion of the connecting body 30 other than an assembly portion 35a of the shaft member 31a.For example, the reinforcing member 70 is arranged at a connection portion 32 and / or a non-assembly portion 36a of the shaft member 31a. The reinforcing member 70 is arranged at a portion other than the assembly portion 35a, and by thereby forming the assembly portion 35a into a shape to fit into a hole 55a, the reinforcing member 70 does not interfere with the processing of the assembly portion 35a.

[0114] As shown in Figs. 11 and 12, the shaft member 31a of the connecting body 30 may be formed to have a non-circular cross-section perpendicular to the longitudinal axis direction A. For example, as shown in [Fig. 11], the shaft member 31a may be formed to have a rectangular cross-section perpendicular to the longitudinal axis direction A. When the shaft member 31a is formed to have a rectangular cross-section, corners of the rectangular cross-section need not be right angles and may be rounded to a practical appropriate degree, as shown. As shown in [Fig. 12], the shaft member 31a may be formed to have an elliptical cross-section perpendicular to the longitudinal axis direction A.

[0115] The shaft member 31a is formed to have a non-circular cross-section perpendicular to the longitudinal axis direction A, and thus a torque forces can be transmitted between a bushing 50a and the shaft member 31a.

[0116] Next, a reaction linkage according to another embodiment of the present invention will now be described with reference to [Fig. 13]. [Fig. 13] is a view in perspective of an aircraft reaction link 120 according to another embodiment of the present invention. The aircraft reaction link 120 is different from the aircraft reaction link 20 in that it includes a caulking pin 121. The caulking pin 121 is a member for further strengthening a connection between the shaft member 31a and the bushing 50a. Specifically, in this embodiment, the shaft member 31a has a small-diameter shaft member through-hole, and the bushing 50a has a bushing through-hole formed at a position therein facing the shaft member through-hole. Both the shaft member through-hole and the bushing through-hole may be formed to pass through the longitudinal axis A and extend in a direction perpendicular to the longitudinal axis A.When the bushing 50a is mounted on the shaft member 31a, the bushing through-hole and the shaft member through-hole communicate with each other. A through-hole formed by the bushing through-hole and the shaft member through-hole communicating with each other is called a pin through-hole. The caulking pin 121 is inserted through the pin through-hole. After being inserted through the pin through-hole, the caulking pin 121 is plastically deformed to strengthen the connection between the shaft member 31a and the bushing 50a. The shaft member through-hole formed in the shaft member 31a is formed so as not to cut reinforcing fibers contained in the shaft member 31a. For example, in a case where the reinforcing fibers contained in the shaft member 31a are formed by weaving together a plurality of filament bundles, as shown in [Fig.8], the shaft member through-hole is formed to have a diameter smaller than one pitch of the reinforcing fibers thus woven together. Thus, the caulking pin 121 can be inserted through the shaft member through-hole without interfering with the reinforcing fibers. The caulking pin 121 may be formed in a columnar shape. The caulking pin 121 may have a small-diameter portion arranged at a portion thereof in its axial direction. The small-diameter portion is formed to have a diameter smaller than that of any other portion of the caulking pin 121. After being plastically deformed to assemble the shaft member 31a to the socket 50a, the caulking pin 121 may be cut at the small-diameter portion.

[0117] In the preceding embodiments, the present invention is applied to an aircraft reaction connection and a moving surface drive device. However, the present invention is not limited to the preceding embodiments and also has other applications than an aircraft reaction connection and a moving surface drive device. The present invention generally applies to an assembly structure between a first member and a second member, the first member having a hole, the second member comprising a shaft member made of a fiber-reinforced composite material.

[0118] Next, a method of manufacturing the reaction link 20 according to an embodiment of the present invention will now be described with reference to [Fig. 14] and Figures 15A to 15F.

[0119] First, a socket is prepared in step STI. The socket as mentioned here is, for example, the socket 50a or the socket 50b described in the previous embodiments.

[0120] Next, a core 81 is prepared in step ST2. As illustrated in [Fig.15A], the core 81 is formed into a U-shape approaching the shape of the connecting body 30. In the core 81, however, no bulge is formed corresponding to the third portion 35a3. The core 81 includes a pair of branches 81a and 81b and a connecting portion 81c connecting the proximal ends of the pair of branches 81a and 81b to each other. One end of the branch 81a is closed, and one end of the branch 81b is open. The core 81 is formed so that the branch 81b as one of the branches 81a and 81b is longer than the other branch 81a. The branch 81a and the branch 81b are formed to have substantially the same diameter in respective sections at any position in their axial directions. The core 81 is formed to be hollow. The hollow core 81 is for example a tube made of a synthetic resin.The synthetic resin used to form the core 81 is, for example, nylon, polyurethane, polytetrafluoroethylene, or any other known synthetic resin material.

[0121] Next, in step ST3, a fiber-containing composite material layer 82 is formed on a surface of the core 81. More specifically, first, an impregnation fluid tank containing a matrix resin is prepared. As the matrix resin, a thermosetting resin such as an unsaturated polyester, an epoxy resin, a polyamide resin, or a phenolic resin, a thermoplastic resin such as methyl methacrylate, a UV-curable resin, a light-curable resin, or any other known matrix resin may be used. In this embodiment, it is assumed that unsaturated polyester is used as the matrix resin. A plurality of reinforcing fibers attached to a braiding machine are impregnated into the impregnation liquid tank. The plurality of reinforcing fibers may correspond to the reinforcing fibers 61, 62, and 63 described in the preceding embodiments, respectively.Three reinforcing fibers impregnated with the matrix resin are woven into the core 81 by the braiding machine. Thus, a laminate 83 shown in FIGS. 15B and 15C is formed. The laminate 83 comprises the core 81 and the fiber-containing composite material layer 82 formed on the core 81. The fiber-containing composite material layer 82 is formed so as to . completely cover the branch 81a and the connecting portion 81c and partially cover the branch 81b. The fiber-containing composite material layer 82 is not formed at a distal end of the branch 81b. The reinforcing fibers may be directly wound onto the core 81 or indirectly wound thereon via a shrinkage layer. For example, the shrinkage layer is formed on an outer surface of the core 81 before the reinforcing fibers are wound onto the core 81. The shrinkage layer is made of, for example, a silicone resin. Providing the shrinkage layer facilitates removal of the core 81. It is also possible to provide a shrinkage layer on an outer surface of the laminate 83. Providing the shrinkage layer on the outer surface of the laminate 83 may improve the demolding capability from a molding mold mentioned hereinafter.The layer of fiber-containing composite material 82 may also be formed using any known device suitable for weaving reinforcing fibers other than a braiding machine. Two or more layers of fiber-containing composite material 82 may be formed.

[0122] Next, in step ST4, the socket 50a is mounted on one distal end of the laminate 83 obtained in the manner described above. Specifically, the distal end of the laminate 83 is inserted into the hole 55a formed in the socket 50a. The connector 52b which is a constituent member of the socket 50b is mounted on the other end of the laminate 83. Specifically, the other distal end of the laminate 83 is inserted into the hole 55a formed in the connector 52b. As described above, as shown in [Fig.15D], a composite laminate 84 is obtained by mounting the socket 50a and the connector 52b on the laminate 83.

[0123] Next, in step ST5, the composite laminate 84 is disposed in a molding mold 90. The molding mold 90 comprises an upper mold 91 and a lower mold 92, as shown in [Fig.15D]. The upper mold 91 has a cavity 91a having a shape conforming to the composite laminate 84. Similarly, the lower mold 92 has a cavity 92a having a shape conforming to the composite laminate 84. There is a gap G between the composite laminate 84 disposed in the molding mold 90 and the inner surface of the hole 55a of the socket 50a and between the composite laminate 84 disposed in the molding mold 90 and the inner surface of the hole 55b of the connector 52b. A cap (not shown) is attached to an opening end 81d of the hollow core 8a. The core 81 is connected to a pump (not shown) via the cap and a pipe.

[0124] Then, the molding mold 90 is closed. The molding mold 90 thus closed is placed in a pressing machine not shown. In step ST6, the molding mold 90 placed in the pressing machine is heated, and compression air is sent from the pump into the hollow core 81. The end of the core 81 on the side opposite to the opening end 81d is closed, and thus in the core 81, an internal pressure is generated by the compression air supplied by the pump. Due to the internal pressure, the core 81 expands outward in a width direction thereof. In addition, as the core 81 expands, the fiber-containing composite material layer 82 also expands outward in the width direction so that the gap G between the fiber-containing composite material layer 82 and each of the holes 55a and 55b disappears. Thus, the fiber-containing composite material layer 82 closely adheres to the inner surface of the hole 55a and the inner surface of the hole 55b. The fiber-containing composite material layer 82 is cured in a state of closely adhering to the inner surface of the hole 55a and the inner surface of the hole 55b.

[0125] Next, in step ST7, the thus cured composite laminate 84 is demolded from the molding mold 90, and the core 81 is removed from the composite laminate 84. A portion of the core 81 exposed from the connector 52b is grasped and extracted, and thus, the core 81 is removed from the composite laminate 84. Thus, the connection body 30 with the socket 50a and the connector 52b mounted on its distal ends is obtained. By removing the core 81, it is possible to achieve a weight reduction of an aircraft reaction connection as a finished product.

[0126] Finally, in step ST8, the socket body 51b is mounted on the connector 52b, and thus the socket 50b is obtained. The socket body 51b is fixed to the connector 52b using, for example, the fixing element 53b. In addition, the head 40 is mounted on the connecting body 30.

[0127] By following the processing steps described above, an aircraft reaction connection is obtained in which a connection body is assembled to a socket without decreasing the strength of the connection body.

[0128] The flowchart shown in [Fig. 14] is an example of the manufacturing method of an aircraft reaction link to which the present invention is applied, and the present invention is not limited to the specific flow shown in [Fig. 14],

[0129] Some of the processing steps of the flow shown in [Fig.14] may be omitted for the purpose of the present invention. For example, step ST7 of removing the core 81 may be omitted.

[0130] Processing steps not shown in [Fig. 14] may be performed if necessary. The processing steps not shown in [Fig. 14] may be performed in addition to the processing steps shown in [Fig. 14] or as an alternative to some of the processing steps shown in [Fig. 14]. For example, a process of polishing a surface of the laminate 83 formed in step ST3 may be performed.

[0131] The processing steps shown in [Fig. 14] may be performed in different orders, as required for the purpose of the present invention. For example, step STI of preparing the socket may be performed after step ST2 of preparing the core 81. The processing step of mounting the head 40 on the connecting body 30 may be performed after step ST4 and before step ST5.

[0132] Some of the processing steps shown in [Fig. 14] may be performed simultaneously or in parallel, if possible. For example, the socket preparation step STI and the core preparation step ST2 may be performed in parallel. Processing steps other than these may also be performed simultaneously or in parallel.

[0133] The core 81 may be formed to be solid from a thermally expandable resin composition. The thermally expandable resin composition used for the solid core 81 is a resin composition comprising a binder resin containing thermally expandable graphite.

[0134] In the preceding embodiment, the present invention is applied to a method for manufacturing an aircraft reaction connection. The present invention is therefore not limited to the preceding embodiment. The present invention is also applicable to a method for manufacturing an article other than an aircraft reaction connection. As is evident from the present description, the present invention is widely applied to a method for assembling a first member to a second member, the first member having a hole extending along an axis direction, the second member comprising a shaft member made of a composite material containing fibers.

[0135] The dimensions, materials, arrangements, and processing steps of the various constituent elements described herein are not limited to those explicitly described in the embodiments, and the various constituent elements may be modified to have any dimensions, materials, arrangements, and processing steps within the scope of the present invention. In addition, constituent elements not explicitly described herein may also be added to the described embodiments, and it is also possible to omit some of the constituent elements described in the embodiments.

Claims

Claims

1. Assembly structure, comprising: a first member (50a) comprising a cylindrical member (52a) having a hole (55a, 55a) extending along an axis direction (A); the hole (55a, 155a) being defined by an inner surface of the cylindrical member (52a), an inner surface of the hole (55a, 155a) comprising a first inner surface (55al, 155al) extending from the opening end (54a2) in a direction parallel to the axis direction (A), a second inner surface (55a2, 155a2) extending from a distal end of the first inner surface (55al, 155al) in the axis direction (A) so as to be inclined relative to the axis direction (A), and a third inner surface (55a3, 155a3) extending, in the direction parallel to the axis direction (A), from a distal end of the second inner surface (55a2, 155a2) in the axis direction (A); and a second element (30) comprising a hollow shaft element (31a),the shaft member (31a) comprising a first portion (35a1, 135a1) extending, in the direction parallel to the axis direction (A), from a position in the axis direction (A) corresponding to the opening end (54a2), a second portion (35a2, 135a2) extending from a distal end of the first portion (35a1, 135a1) in the axis direction (A) so as to be inclined relative to the axis direction (A), and a third portion (35a3, 135a3) extending, in the direction parallel to the axis direction (A), from a distal end of the second portion (35a2, 135a2) in the axis direction (A), the shaft member (31a) being formed of a composite material containing fibers and having a shape to fit into the hole (55a, 155a), the second element (30) being assembled to the first element (50a) via the shaft element (31a) so that its movement in the axis direction (A) is limited, wherein the first part (35al, 135al),the second portion (35a2, 135a2), and the third portion (35a3, 135a3) each extend along, and each have an outer surface formed to closely adhere to, a corresponding one of the first inner surface (55a1, 155a1), the second inner surface (55a2, 155a2), and the third inner surface (55a3, 155a3).,

2. An assembly structure according to claim 1, wherein the element shaft member (31a) has a first width (dl) at a first position (PI) in the axis direction and a second width (d2) at a second position (P2) in the axis direction, the second position (P2) being closer to a distal end of the shaft member (31a) than the first position (PI), the second width (d2) being greater than the first width (dl).

3. An assembly structure according to claim 2, wherein the shaft member (31a) has a third width (d3) at a third position (P3) in the axis direction, the third position (P3) being closer to the distal end of the shaft member (31a) than the second position (P2), the third width (d3) being less than the second width (d2).

4. The assembly structure of claim 2, wherein the shaft member (31a) has a fourth width at a fourth position in the axis direction, the fourth position being closer to a proximal end of the shaft member than the first position, the fourth width being greater than the first width.

5. An assembly structure according to claim 1, wherein the shaft member (31a) has a non-circular cross-section in a direction perpendicular to the axis direction.

6. The assembly structure of claim 1, wherein the cylindrical member (52a) has a smaller thickness at its proximal end in the axis direction than at a distal end side of the proximal end in the axis direction.

7. An assembly structure according to claim 6, wherein the cylindrical member (52a) is made of a metallic material among a titanium alloy, a chromium-molybdenum steel, a nickel-chromium-molybdenum steel and a stainless steel.

8. The joining structure of claim 1, wherein the shaft member (31a) comprises a first reinforcing fiber (61) extending in a first direction in which the shaft member (31a) comprises: a joining portion (35a) overlapping the cylindrical member (52a) in the axis direction; and a non-joining portion (36a) not overlapping the joining portion (35a) in the axis direction, and in which an angle formed by the first direction with the axis direction in the joining portion (35a) is greater than an angle formed by the first direction with the axis direction in the non-assembly part (36a).

9. The joining structure of claim 8, wherein the shaft member (31a) further comprises a second reinforcing fiber (62) extending in a second direction different from the first direction and woven with the first reinforcing fiber (61), and wherein an angle formed by the second direction with the axis direction in the joining portion (35a) is greater than an angle formed by the second direction with the axis direction in the non-joining portion (36a).

10. An assembly structure according to claim 8, further comprising: a reinforcing member (70) arranged in the non-assembly portion (36a), the reinforcing member (70) being made of a fiber-reinforced plastic material containing reinforcing fibers oriented in a circumferential direction surrounding the axis direction.

11. An aircraft reaction link, comprising: a socket (50a) slidably supporting an actuator (10), the actuator (10) being mounted directly or indirectly on a movable surface (101) of an aircraft and configured to drive the movable surface (101); and a connecting body (30) comprising a shaft member (31a) made of a composite material containing fibers and which is connected to the socket (50a), wherein the socket (50a) has a hole (55a, 155a) extending along an axis direction (A) of the shaft member (31a), an inner surface of the hole (55a, 155a) comprising a first inner surface (55a1, 155a1) extending from the opening end (54a2) in a direction parallel to the axis direction (A), a second inner surface (55a2, 155a2) extending from a distal end of the first inner surface (55a1, 155a1) and ...155al) in the axis direction (A) so as to be inclined relative to the axis direction (A), and a third inner surface (55a3, 155a3) extending, in the direction parallel to the axis direction (A), from a distal end of the second inner surface (55a2, 155a2) in the axis direction (A), and wherein the shaft member (31a) is formed in a shape to fit into the hole (55a) and disposed in the hole (55a) such that,

12.

13. its movement in the axis direction is limited, the shaft member (31a) comprising a first portion (35al, 135al) extending, in the direction parallel to the axis direction (A), from a position in the axis direction (A) corresponding to the opening end (54a2), a second portion (35a2, 135a2) extending from a distal end of the first portion (35al, 135al) in the axis direction (A) so as to be inclined relative to the axis direction (A), and a third portion (35a3, 135a3) extending, in the direction parallel to the axis direction (A), from a distal end of the second portion (35a2, 135a2) in the axis direction (A), wherein the first portion (35al, 135al), the second portion (35a2, 135a2), and the third part (35a3, 135a3) each extend along, and each have an outer surface formed to closely adhere to, a corresponding one of the first inner surface (55al, 155al),the second inner surface (55a2, 155a2), and the third inner surface (55a3, 155a3)., A moving surface drive device, comprising: the aircraft reaction link (20) according to claim 11; and the actuator (10). An assembly method for assembling a first member to a second member, the first member having a hole (55a) defined by an inner surface of the first member, extending along an axis direction (A), the inner surface (55a, 155a) comprising a first inner surface (55a1, 155a1) extending from the opening end (54a2) in a direction parallel to the axis direction (A), a second inner surface (55a2, 155a2) extending from a distal end of the first inner surface (55a1, 155a1) in the axis direction (A) so as to be inclined relative to the axis direction (A), and a third inner surface (55a3, 155a3) extending, in the direction parallel to the axis direction (A), from a distal end of the second inner surface (55a2, 155a2) in the axis direction (A), the second element (30) comprising a shaft element (31a) made of a composite material containing fibers,the method comprising the steps of:, (A) prepare the first element; (B) preparing a core (81); (C) obtaining a laminate (83) by forming a layer of composite material containing fibers (82) on the core (81); (D) inserting at least a portion of the laminate (83) into the hole (55a) of the first member; (E) causing expansion of the core (81) such that the fiber-containing composite material adheres to the inner surface of the first member, and (F) forming the shaft member (31a) into a shape to fit into the hole (55a) by curing the fiber-containing composite material layer (82).

14. The assembly method of claim 13, further comprising the step of: removing the core (81).

15. The assembly method of claim 13, wherein, in step (C), a shrinkage layer is arranged on an outer surface of the core (81), and the fiber-containing composite material layer is formed on the shrinkage layer.

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