JOINING FIBER-CONTAINING COMPOSITE MATERIAL

Abstract

Connection structure, comprehensive: a first element (50a, 50b) with a hole (55a, 55b) extending along an axis direction (A, B); wherein the first element (50a, 50b) comprises a cylindrical element (52a, 52b) defining the hole (55a, 55b), and an inner surface of the hole (55a) comprising a first inner surface (55a1, 155a1) extending from the opening end (54a2) in a direction parallel to the longitudinal axis (A), a second inner surface (55a2, 155a2) extending from a distal end of the first inner surface (55a1, 155a1) in the longitudinal direction A-direction to be inclined with respect to the longitudinal axis (A), and a third inner surface (55a3, 155a3) extending in the direction parallel to the longitudinal axis (A) from a distal end of the second inner surface (55a2, 155a2) in the direction of the longitudinal axis (A), a second element (30) with a hollow shaft element (31a, 31b), wherein the shaft element (31a, 31b) comprises a first section (35a1, 135a1) extending in the direction parallel to the longitudinal axis (A) from a position in the longitudinal axis A-direction corresponding to the opening end (54a2) of the cylindrical element (52a), a second section (35a2, 135a2) extending from a distal end of the first section (35a1, 135a1) in the longitudinal axis A-direction to be inclined with respect to the longitudinal axis (A), and a third section (35a3, 135a3) extending in the direction parallel to the longitudinal axis (A) from a distal end of the second section (35a2, 135a2) in the longitudinal direction A-direction. wherein the shaft element (31a, 31b) is formed from a fiber-containing composite material and has a shape that fits into the hole (55a, 55b), wherein the second element (30) is connected to the first element (50a, 50b) via the shaft element (31a, 31b) such that its movement in the axial direction (A, B) is restricted, wherein the first section (35a1, 135a1), the second section (35a2, 135a2) and the third section (35a3, 135a3) each extend along a corresponding of the first interior surface (55a1, 155a1), the second interior surface (55a2, 155a2) and the third interior surface (55a3, 155a), and wherein the first section (35a1, 135a1), the second section (35a2, 135a2) and the third section (35a3, 135a3) each have an outer surface designed to adhere firmly to a corresponding inner surface of the first inner surface (55a1, 155a1), the second inner surface (55a2, 155a2) and the third inner surface (55a3, 155a3).

Description

CROSS-REFERENCE TO RELATED REGISTRATIONS

[0001] This application is based on JP 2018-167876 A (filed on 7 September 2018), the contents of which are hereby incorporated in their entirety by reference, and claims that priority. TECHNICAL AREA

[0002] The present disclosure relates to the connection between a fiber-containing composite material and another element. BACKGROUND

[0003] A fastener, such as a bolt, is used to connect another element to a composite element made of a fiber-reinforced composite material. In a connection design disclosed in JP 2014-237429 A, a connecting body of an aircraft reaction member is made of the fiber-reinforced composite material, and the connecting body is joined to a sleeve using a helical fastener.

[0004] DE 10 2016 221 309 A1 relates to a support structure for a power transmission element. US 2014 / 0 332 626 A1 relates to an aircraft reaction connection. EP 2 801 519 A1 relates to an aircraft reaction connection. JP S63-214 430 A relates to a rod-shaped body. WO 2010 / 024 990 A1 relates to the manufacture of a tie rod made of fiber-reinforced composite material. WO 96 / 05 440 A1 relates to a method for joining metal and fiber-reinforced composite material. WO 2014 / 170 690 A1 relates to a winglet and a braided composite spar for a winglet. FR 3 043 357 A1 relates to a support structure for a power transmission element. US patent 2016 / 271888 A1 relates to a process for manufacturing a resin molded article. EP 0 370 472 A2 relates to a process for manufacturing monolithic hollow elements.

[0005] If a bolt hole is formed in the composite element made of the fiber-containing composite material for inserting the bolt, the reinforcing fibers contained in the composite element are cut, thus reducing the strength of the composite element. SUMMARY

[0006] One objective of the present disclosure is to provide a new connection structure capable of alleviating or solving at least part of the conventional problem described above.

[0007] More precisely, one objective of the present disclosure is to join a composite element made of a fiber-containing composite material to another element without cutting the reinforcing fibers contained in the composite element. Other objects of the present disclosure are made apparent by the entire description herein.

[0008] A connecting structure according to an embodiment of the present invention comprises a first element and a second element, wherein the first element has a hole extending along an axial direction, wherein the second element comprises a shaft element, wherein the shaft element is formed from a fiber-containing composite material and has a shape that fits into the hole, wherein the second element is connected to the first element via the shaft element, such that its movement in the axial direction is limited.

[0009] According to this embodiment, the shaft element of the second element is arranged in the hole formed in the first element, thus connecting the second element to the first. Therefore, the second element can be connected to the first without cutting any reinforcing fibers, as these fibers are contained within the shaft element of the second element. This prevents any loss of strength in the shaft element of the second element, which is made of a fiber-reinforced composite material.

[0010] In one 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, wherein the second section is closer to a distal end of the shaft element than the first position and the second width is greater than the first width.

[0011] According to this embodiment, the first element can support the second element axially by utilizing a portion of it located at the first axial position. Thus, the first element can counteract a tensile load acting on the second element in a direction from the distal end to the proximal end of the shaft element by utilizing the section of the shaft element located at the first axial position. Therefore, according to this embodiment, it is possible to connect the first element more firmly to the second element.

[0012] In one embodiment of the present invention, the shaft element has a third width at a third position in the axial direction, wherein the third position is closer to the distal end of the shaft element than the second position and the third width is smaller than the second width.

[0013] According to this embodiment, the first element can support the second element axially by utilizing a portion of it located at the third axial position. Depending on the embodiment, this allows for a more secure connection between the first and second elements.

[0014] In one embodiment of the present invention, the shaft element has a fourth width at a fourth position in the axial direction, wherein the fourth position is closer to a proximal end of the shaft element than the first position and the fourth width is larger than the first width.

[0015] According to this embodiment, the first element can support the second element axially by utilizing the section of the second element that is located at the first axial position. Depending on the embodiment, this allows for a more secure connection between the first and second elements.

[0016] In the present invention, the shaft element is hollow.

[0017] According to the embodiment, it is possible to achieve a weight reduction of the second element.

[0018] In one embodiment of the present invention, the shaft element has a non-circular cross-section in a direction perpendicular to the axial direction.

[0019] According to the embodiment, multiple forces can be transmitted between the first element and the second element.

[0020] According to the present invention, the first element comprises a cylindrical element that defines the hole, and the cylindrical element may have a smaller thickness at its proximal end in the axial direction than at a distal end side of the proximal end in the axial direction.

[0021] According to this embodiment, a section of the thin cylindrical element is elastically deformed, so that a stress acting on the cylindrical element can be relieved from the shaft element. Therefore, even if a large stress acts on a connecting body, it is unlikely that the cylindrical element will break.

[0022] In one embodiment of the present invention, the cylindrical element is made of a metal.

[0023] According to the embodiment, the shaft element made of a fiber-containing composite material can be connected to the cylindrical element made of metal without the use of a connecting element, such as a bolt, which could break reinforcing fibers out of the fiber-containing composite material.

[0024] In one embodiment of the present invention, the shaft element comprises a first reinforcing fiber extending in a first direction. Furthermore, the shaft element comprises a connecting section and a non-connecting section, wherein the connecting section overlaps the cylindrical element axially, and the non-connecting section does not overlap the connecting section axially. In this embodiment, the angle formed by the first direction with the axial direction in the connecting section is greater than the angle formed by the first direction with the axial direction in the non-connecting section.

[0025] In one embodiment of the present invention, the shaft element further comprises a second reinforcing fiber extending in a second direction which differs from the first direction and is woven with the first reinforcing fiber, and an angle formed by the second direction with the axial direction in the connecting section is smaller than an angle formed by the second direction with the axial direction in the non-connecting section.

[0026] According to this embodiment, the second reinforcing fiber is woven with the first reinforcing fiber in the shaft element, thereby increasing the shaft element's strength. Furthermore, the angle formed by the stretching direction (the second direction) of the second reinforcing fiber with the axial direction is larger in the connection section of the shaft element. Therefore, the shaft element is more easily deformed laterally in the connection section than in the non-connection section. This makes it easier to shape the shaft element to fit the hole.

[0027] In one embodiment of the present invention, a reinforcing element is provided in the non-connecting section of the shaft element, wherein the reinforcing element is made of a fiber-containing composite material which contains reinforcing fibers that are aligned in a circumferential direction around the axial direction.

[0028] According to the embodiment, the non-connecting section of the shaft element can be reinforced by the reinforcing element.

[0029] An aircraft reaction element according to one embodiment of the present invention comprises a sleeve and a connecting body, wherein the sleeve slidably supports an actuator, the actuator being attached directly or indirectly to a moving surface of an aircraft and configured to drive the moving surface, and wherein the connecting body comprises a shaft element made of a fiber-reinforced composite material and is connected to the sleeve. In this embodiment, the sleeve has a hole extending along an axial direction of the shaft element, and the shaft element is shaped to fit into the hole and is positioned in the hole such that its movement in the axial direction is restricted.

[0030] According to the embodiment, the connecting body in the aircraft reaction element can be connected to the sleeve without reducing the strength of the connecting body.

[0031] A drive device for moving surfaces according to an embodiment of the present invention comprises the aircraft reaction element described above and an actuator that is attached directly or indirectly to a moving surface of an aircraft and is configured to drive the moving surface.

[0032] According to the embodiment, a drive device for moving surfaces is obtained, which includes the aircraft reaction element, improved by the connection between the connecting body and the sleeve.

[0033] One embodiment of the present invention relates to a method for joining a first element to a second element, wherein the first element has a hole extending along an axial direction, and the second element comprises a shaft element made of a fiber-reinforced composite material. The joining method comprises the steps of: (A) manufacturing the first element, (B) manufacturing a core, (C) obtaining a laminate by forming a fiber-reinforced composite layer on the core, (D) inserting at least a portion of the laminate into the hole of the first element, (E) causing the core to expand, and (F) obtaining the shaft element in a shape that fits into the hole by curing the fiber-reinforced composite layer.

[0034] According to the embodiment, the second element, which includes the shaft element, can be connected to the first element without loss of strength of the shaft element, wherein the shaft element consists of a fiber-containing composite material.

[0035] The joining method according to one embodiment of the present invention further comprises the step of removing the core.

[0036] According to the embodiment, the core is removed, thus achieving a weight reduction of a connecting structure.

[0037] In one embodiment of the present invention, a peel layer is provided on an outer surface of the core, and the fiber-containing composite layer is formed on the peel layer.

[0038] According to the embodiment, the removal of the core is facilitated.

[0039] One embodiment of the present invention relates to a method for manufacturing an aircraft reaction element connected to an actuator, wherein the actuator is mounted on a moving surface of an aircraft and configured to drive the moving surface. The manufacturing method comprises the steps of: (A) Manufacturing a sleeve configured to slidably support the actuator and having a hole extending along an axial direction, (B) Manufacturing a core, (C) Obtaining a laminate by forming a fiber-containing composite layer on the core, (D) Inserting at least part of the laminate into the hole of the sleeve, (E) Generating an expansion of the nucleus and (F) Obtaining a bonding body by curing the fiber-containing composite layer.

[0040] According to the embodiment, an aircraft reaction element is obtained in which the connecting body is connected to the sleeve without reducing the strength of the connecting body. List of characters Fig. Figure 1 is a perspective view of a wing with a drive device for movable surfaces according to an embodiment of the present invention. Fig. 2 is a side view of the in Fig. 1 of the depicted wing. Fig. 3 is a perspective view of a Fig. 1 of the depicted aircraft reaction element. Fig. 4 is a sectional view of the in Fig. 1. Aircraft reaction element shown along a line II. Fig. 5 is a sectional view of the in Fig. 4 depicted aircraft reaction element along a line II-II. Fig. 6 is a perspective view of a sleeve that is in the Fig. The aircraft reaction element shown in section 1 is included. Fig. 7 is an enlarged sectional view, showing a portion of the [unclear text] at an enlarged scale. Fig. Figure 1 shows the aircraft reaction element. This enlarged sectional view shows a connection structure between a shaft element and the sleeve, which is located in the Fig. The aircraft reaction element shown in section 1 is included. Fig. Figure 8 is a schematic view, schematically showing on an enlarged scale a distal end of a connecting body located in the Fig. The aircraft reaction element shown in section 1 is included. For clarity, a sleeve 50a is shown in its broken state. Fig. Figure 9 is an enlarged sectional view showing, on an enlarged scale, a portion of an aircraft reaction element according to a further embodiment of the present invention. This enlarged sectional view shows a connection structure between a shaft element and a sleeve contained in the aircraft reaction element according to a further embodiment. Fig. Figure 10 is a schematic view, schematically showing on an enlarged scale a distal end of a connecting part contained in the aircraft reaction element according to another embodiment of the present invention. For clarity, a sleeve 50a is shown in a broken state. Fig. Figure 11 is a sectional view of the aircraft reaction element according to a further embodiment of the present invention, which is cut along a plane perpendicular to its longitudinal axis. Fig. Figure 12 is a sectional view of the aircraft reaction element according to a further embodiment of the present invention, which is cut along the plane perpendicular to its longitudinal axis. Fig. Figure 13 is a perspective view of the aircraft reaction element according to a further embodiment of the present invention. Fig. Figure 14 is a flowchart illustrating a method for manufacturing the aircraft reaction element according to an embodiment of the present invention. Fig. 15A to Fig. Figures 15F are schematic views illustrating the method for manufacturing the aircraft reaction element according to an embodiment of the present invention. Fig. 15A shows a core. Fig. Figure 15B is a perspective view of a laminate obtained by forming a fiber-containing composite layer on the core. Fig. 15C is a sectional view of the in Fig. 15B shows a laminate cut along a plane perpendicular to its longitudinal axis. Fig. Figure 15D shows a composite laminate obtained by mounting one of the sleeves onto a laminate and a forming tool for shaping the composite laminate. Fig. Figure 15E is a schematic view showing, on an enlarged scale, the proximity of a distal end of the composite laminate placed in the molding tool. Fig. Figure 15F is a schematic representation of the composite laminate after the expansion of the core in the mold. DESCRIPTION OF EXAMPLE FORMS OF EXECUTION

[0041] Various embodiments of the present invention are described below with reference to the accompanying figures. Constituent elements common to a multitude of drawings are identified by the same reference numerals throughout the entire multitude of drawings. It should be noted that the drawings are not necessarily drawn to scale for the sake of clarity. Some components may be omitted from the drawings for the sake of clarity.

[0042] A drive device for moving surfaces according to an embodiment of the present invention is now mainly discussed in relation to Fig. 1 and Fig. 2 described. Fig. Figure 1 is a perspective view of part of a wing with a drive device for movable surfaces according to an embodiment of the present invention, and Fig. Figure 2 is a side view of the wing. A moving surface drive device 1 is installed and configured and arranged in an aircraft to drive a moving surface 101 of a wing 100 of the aircraft. Examples of the moving surface 101 are primary flight control surfaces such as an aileron, rudder, and elevator, or secondary flight control surfaces such as a flap and spoiler.

[0043] The driving 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, wherein the reaction link 20 is configured and arranged to assist a reaction force from the movable surface 101 when the movable surface 101 is driven by the actuator 10.

[0044] The actuator 10 is connected to a support mechanism 102 provided in the wing 100 and to a connecting shaft 103 of the movable surface 101. The movable surface 101 is rotatably mounted relative to the wing 100 via a pivot axis 104. The actuator 10 causes the movable surface 101 to rotate about the pivot axis 104. A distal end section 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 section of the rod 12 is connected to a horn arm (not shown) that is connected to the movable surface 101. That is, the actuator 10 can also be indirectly connected to the movable surface 101.

[0045] The actuator 10 is a fluid pressure-driven linear actuator in which a working fluid, such as hydraulic oil, is supplied to and discharged from a cylinder 11, thereby moving the rod 12 back and forth in the axial direction. The actuator 10 can be driven by a method other than the use of fluid pressure. For example, the actuator 10 can be an electromechanical linear drive with an electric motor.

[0046] As in Fig. As shown in Figure 1, the actuator 10 comprises a connecting section 13, which is connected to the reaction element 20 and the support section 102. The connecting section 13 is located on one side of the cylinder 11 opposite the side from which the rod 12 projects. The connecting section 13 includes a shaft 13A, which extends orthogonally to the axis of the rod 12 in the direction of a support axis J. Here, the extension direction of the shaft 13A can be referred to as the support axis direction.

[0047] The reaction element 20 is rotatably connected to the pivot shaft 104 and the shaft 13A of the connecting section 13. The reaction element 20 serves to prevent a reaction force that is generated when the movable surface 101 is driven by the actuator 10, which acts directly from the movable surface 101 onto the wing 100. The reaction element 20 can be connected directly or indirectly to the movable surface 101. In a case where the reaction element 20 is indirectly connected to either the movable surface 101 or the actuator 10, it is connected to the movable surface 101 or the actuator 10 via a connecting mechanism.

[0048] The landing gear drive device 1, configured as described above, operates as follows. A fluid pressure device (not shown) for supplying a working fluid to the actuator 10 operates based on instructions from a flight controller (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 or retract into the cylinder 11, as shown in Fig. Figure 2 shows that the movable surface 101, which is connected to the rod 12 via the connecting shaft 103, rotates about the axis of rotation 104. While the movable surface 101 rotates, the reaction element 20 oscillates about the axis of rotation 104. The reaction element 20 also oscillates about the shaft 13A. As a result of this movement, the reaction element 20 receives a reaction force from the movable surface 101, which is generated when the movable surface 101 is driven by the actuator 10.

[0049] Next, the reaction element 20 is described according to an embodiment of the present invention with reference to Fig. 3 to Fig. 8 is described in more detail. As shown in these drawings, the reaction element 20 comprises a U-shaped connecting body 30 in a top view. The connecting body 30 can also be in a linear form or a J-shape other than the U-shape.

[0050] 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 parallel to the longitudinal axis A. The longitudinal axis A and the longitudinal axis B indicate a longitudinal direction of the connecting body 30. The shaft element 31a and the shaft element 31b extend in parallel directions, so that they are spaced apart from each other. The shaft element 31a and the shaft element 31b are essentially of the same shape. Hereinafter, a description of the shaft element 31a also applies to the shaft element 31b, unless it should be interpreted differently from the context or in view of the nature of the present invention. A direction along the longitudinal axis A may be referred to as the direction of the longitudinal axis A, and a direction along the longitudinal axis B may be referred to as the direction of the longitudinal axis B.The longitudinal direction A and the longitudinal axis B can be collectively referred to simply as the axis direction. With respect to a proximal end and a distal end of each element, the distal end is located on a top surface in . Fig. 4 and the proximal end on a subside in Fig. 4 in the direction along the longitudinal axis A (or the longitudinal axis B), unless the context indicates otherwise.

[0051] A proximal end of shaft element 31a in the longitudinal axis A direction and a proximal end of shaft element 31b in the longitudinal axis B direction are connected to each other via a connecting section 32. The connecting section 32 comprises a straight section 33 and curved sections 34, which are provided at both ends of the straight section 33, the straight section 33 extending in a direction orthogonal to both the longitudinal axis A and the longitudinal axis B. A pair of shaft elements 31a and 31b can be formed integrally with the connecting section 32.

[0052] According to the present invention, the shaft element 31a is hollow, as shown in Fig. 4 and Fig. Figure 5 shows that the shaft element 31a can be shaped to be rigid. Since the shaft element 31a is hollow, it is possible to reduce the weight of the shaft element 31a and, optionally, of the connecting body 30. In one embodiment of the present invention, as shown in Figure 5, the shaft element 31a can be shaped to be rigid. Fig. As shown in Figure 5, the shaft element 31a is formed in a circular shape or a substantially circular shape when viewed in section. The cross-sectional shape of the shaft element 31a is not limited to a circular shape or a substantially circular shape. Modifications of the shaft element 31a are described later.

[0053] An upper layer (not shown) can be formed on the shaft element 31a. This upper layer can be applied for various purposes. For example, it can be applied to provide weather resistance to the connecting body 30, increase its strength, enhance its decorative appearance, provide lightning protection, or serve other purposes. The upper layer can be made of a fiber-reinforced composite material or a material other than a fiber-reinforced composite. A fiber-reinforced plastic used for the upper layer can contain glass fibers as reinforcing fibers. The upper layer with lightning protection can, for example, consist of a metal mesh. To provide lightning protection, a grounding wire can be attached to a surface of the shaft element 31a.

[0054] A sleeve 50a is provided at a distal end of the shaft element 31a in the longitudinal axis A-direction and a sleeve 50b is provided at a distal end of the shaft element 31b in the longitudinal axis B-direction.

[0055] Sleeves 50a and 50b, for example, are made of a metallic material. Possible metallic materials for sleeves 50a and 50b include titanium alloy, chromium-molybdenum steel, nickel-chromium-molybdenum steel, stainless steel, and other common metallic materials. Sleeves 50a and 50b can also be made of a material other than metal. For example, sleeves 50a and 50b can be made of a ceramic material, a fiber-reinforced plastic such as CFRP, or a variety of resin materials.

[0056] In one embodiment of the present invention, the connecting body 30 is made of a fiber-containing composite material (“fiber-containing composite material”). The fiber-containing composite material is, for example, a fiber-reinforced plastic (FRP). Reinforcing fibers made from various raw materials can be used as reinforcing fibers contained in the connecting body 30. For example, the connecting body 30 can consist of a carbon fiber-reinforced plastic (CFRP) containing carbon fibers as reinforcing fibers. PAN-based carbon fibers, pitch-based carbon fibers, or any other known type of carbon fiber can be used as carbon fibers.The connecting body 30 can 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 (ZFK) or another fiber reinforced plastic.

[0057] The connecting body 30 can be made entirely or partially of a fiber-reinforced composite material. For example, only the shaft elements 31a and 31b of the connecting body 30 may be made of a fiber-reinforced composite material. In this case, the connecting section 32 may be made of a material other than the fiber-reinforced composite, such as a metal. Furthermore, only a portion of the pair of shaft elements 31a and 31b on a distal end face of the connecting body 30 may be made of a fiber-reinforced composite material. The connecting body 30 may be made of a fiber-reinforced composite material consisting of a combination of many different fiber types.

[0058] As described above, in one embodiment of the present invention, the shaft elements 31a and 31b are made of a fiber-reinforced composite material. The shaft elements 31a and 31b made of a fiber-reinforced composite material comprise a configuration in which they consist entirely of the fiber-reinforced composite material and a configuration in which they consist partially of the fiber-reinforced composite material. That is to say, the shaft elements 31a and 31b made of a fiber-reinforced composite material here refer to shaft elements that consist at least partially of the fiber-reinforced composite material.For example, it is possible that a section of the shaft element 31a to be connected to the sleeve 50a (a connecting section 35a referred to below) is made of a fiber-containing composite material and a section of the shaft element 31a, which is not the section to be connected to the sleeve 50a, is made of a material other than the fiber-containing composite material.

[0059] Now, an alignment of the reinforcing fibers in the shaft element 31a is shown with reference to Fig. 8 described in more detail. As in Fig. As shown in Figure 8, the shaft element 31a comprises a plurality of reinforcing fibers 60. A matrix resin is filled into a gap between the reinforcing fibers 60. For the sake of clarity, the matrix resin is omitted in Figure 8. Fig. 8.

[0060] The reinforcing fibers 60 comprise 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 consisting 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 thread produced by stack pressing, a filament, or a braid that is a knitted cord including tows. The first reinforcing fiber 61, the second reinforcing fiber 62, and the third reinforcing fiber 63 can be made of the same material or of different materials.

[0061] The first reinforcing fiber 61 extends in a first direction D1, which differs from the longitudinal axis A. The second reinforcing fiber 62 extends in a second direction D2, which differs from both the longitudinal axis A and the first direction D1. The third reinforcing fiber 63 extends in a third direction D3 parallel to the longitudinal axis A. In the illustrated embodiment, an acute angle formed by the first direction D1 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 D1. Each of the first directions D1 and the second direction D2 can form any angle with the longitudinal axis A.

[0062] In the illustrated embodiment, the first reinforcing fiber 61, the second reinforcing fiber 62, and the third reinforcing fiber 63 are interwoven. It is possible that the first to third reinforcing fibers 61 to 63 are not interwoven but form corresponding layers in the order in which they form, 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.

[0063] As in Fig. As shown in Figure 8, in one embodiment, the angle formed by the angle D1 of the first reinforcing fiber 61 with the longitudinal axis A in the connection section 35a of the shaft element 31a is greater than the angle formed by the angle D1 of the first reinforcing fiber 61 with the longitudinal axis A in the non-connection section 36a of the shaft element 31a. That is, in the connection section 35a, the direction of extension of the first reinforcing fiber 61 is more perpendicular to the longitudinal axis A than in the non-connection section 36a. Likewise, the angle formed by the angle D2 of the second reinforcing fiber 62 with the longitudinal axis A in the connection section 35a of the shaft element 31a is greater than the angle formed by the angle D2 of the second reinforcing fiber 62 with the longitudinal axis A in the non-connection section 36a of the shaft element 31a.This means that in the connecting section 35a, the stretching direction of the second reinforcing fiber 62 is directed more perpendicular to the longitudinal axis A than in the non-connecting section 36a.

[0064] A head 40 is provided at a proximal end of the connecting body 30. The head 40 is connected to the axis of rotation 104. In the illustrated embodiment, the head 40 is connected to the center of the straight section 33 of the connecting section 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 section 32 is inserted. The second body 42 has a through hole 42a that extends in the same direction as the extension direction of the mounting hole 41a. A bearing (not shown) can be mounted on the through hole 42a. The through hole 42a rotatably supports the axis of rotation 104 over the bearing.

[0065] As described above, the sleeve 50a is connected to the distal end of the shaft element 31a of the connecting body 30. A connecting structure consisting of the connecting body 30 and the sleeve 50a connected to the connecting body 30 is an embodiment of a connecting structure according to the present invention. Likewise, the sleeve 50b is connected to the distal end of the shaft part 31b of the connecting body 30. A connecting structure consisting of the connecting body 30 and the sleeve 50b connected to the connecting body 30b is also an example of the connecting structure according to the present invention.

[0066] In the following, the connection construction, which consists of the shaft element 31a of the connection body 30 and the sleeve 50a, and the connection construction, which consists of the shaft element 31b of the connection body 30 and the sleeve 50b, are described mainly with reference to Fig. 6 and Fig. 7 described. The connection structure, which consists of the shaft element 31b and the sleeve 50b, is essentially the same as the connection structure, which consists of the shaft element 31a and the sleeve 50a, and so the following mainly describes the connection structure, which consists of the shaft element 31a and the sleeve 50a, without a description of the connection structure, which consists of the shaft element 31b and the sleeve 50b.

[0067] First, the sleeve 50a will be described. Fig. Figure 6 is a perspective view of the sleeve 50a when it is not mounted on the connecting body 30, and Fig. Figure 7 is an enlarged cross-sectional view showing, on an enlarged scale, part of the aircraft reaction member 20. This enlarged section view shows the connection structure consisting of the shaft element 31a, which is contained in the aircraft reaction member 20, and the sleeve 50a.

[0068] As shown, the sleeve 50a comprises a sleeve body 51a and a cylindrical element 52a extending from the sleeve body 51a to a proximal end face of the longitudinal axis A. The sleeve body 51a can be formed integrally with the cylindrical element 52a.

[0069] The sleeve body 51a has a through hole 51a1. The through hole 51a1 extends through the sleeve body 51a along an axial direction J of the shaft 13A.

[0070] The cylindrical element 52a comprises a cylindrical base section 53a, which is connected to the sleeve body 51a, and an opening section 54a, which extends from the base section 53a in the direction of the proximal end side of the longitudinal axis A and is open towards the proximal end side of the longitudinal axis A.

[0071] In the illustrated embodiment, the base section 53a comprises an annular side wall 53a1 with substantially uniform outer and inner widths and a bottom wall 53a2, which is provided at a distal end of the side wall 53a1 in the direction of the longitudinal axis A. As described above, the base section 53a is formed in a lower cylindrical shape with the bottom wall 53a2. The base section 53a is connected to the sleeve body 51a at the bottom wall 53a2.

[0072] In the illustrated embodiment, the opening section 54a has an annular side wall 54a1. The side wall 54a1 is connected to a proximal end of the side wall 53a1 of the base section 53a in the longitudinal axis A-direction. The side wall 54a1 extends from the position where it is connected to the side wall 53a1 to an opening end 54a2 substantially along the longitudinal axis A. In the illustrated embodiment, the side wall 54a1 has an outer width (a dimension in a width direction orthogonal to the longitudinal direction A-direction) at a proximal end section of the side wall 54a1 near a proximal end therein that is smaller than at a distal end section therein, which is closer to a distal end than the proximal end section in the longitudinal direction A-direction.In one embodiment, the opening section 54a is configured to have a smaller outer width (a dimension in a lateral direction orthogonal to the longitudinal axis A) at a proximal end of the longitudinal axis A. Thus, the opening section 54a is configured to have a thickness at a proximal end of it in the longitudinal axis A (namely, a thickness at the opening end 54a2) than a thickness at a position closer to a distal end of it than the opening end 54a2 in the longitudinal axis A. According to this embodiment, a thin section of the cylindrical element 52a near the opening end 54a2 is elastically deformed, and thus, even when the shaft element 31a moves in the longitudinal direction A, any stress caused by the movement and acting on the cylindrical element 52a can be relieved from the shaft element 31a.Therefore, it is unlikely that the shaft element 31a and the cylindrical element 52a will break. The cylindrical element 52a can be shaped such that it has a thickness that decreases towards its proximal end in the longitudinal axis A-direction.

[0073] In the illustrated embodiment, the hole 55a formed in the cylindrical element 52a extends from the opening end 54a2 of the opening section 54a to the bottom wall 53a2 of the base section 53a essentially along the longitudinal axis A direction. The hole 55a is defined by the inner surfaces of the side wall 53a1 and the bottom wall 53a2 of the base section 53a, as well as an inner surface of the side wall 54a1 of the opening section 54a.

[0074] In the illustrated embodiment, an inner surface of the hole 55a comprises a first inner surface 55a1 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 55a1 in the longitudinal direction A to be inclined with respect 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 direction of the longitudinal axis A, a fourth inner surface 55a4 extending from a distal end of the third inner surface 55a3 in the direction of the longitudinal axis A to be inclined with respect 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 direction of the longitudinal axis A.The inner surface 55a2 is inclined in a direction away from the longitudinal axis A towards its distal end in the longitudinal direction A. The inner surface 55a4 is inclined in the direction of the longitudinal axis A towards its distal end in the direction of the longitudinal axis 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 the direction of the longitudinal axis A for distances 11, 12, 13, 14, and 15, respectively.

[0075] In one embodiment of the present invention, the hole 55a is configured such that it has a width (a dimension in the lateral direction orthogonal to the longitudinal direction A) that varies depending on its position in the longitudinal direction A. That is, the cylindrical element 52a is shaped such that it has a width that varies depending on its position in the longitudinal direction A. In the illustrated embodiment, the hole 55a has a first width d1 at position P1 in the longitudinal axis A, a second width d2 at position P2 in the longitudinal axis A, and a third width d3 at position P3 in the longitudinal axis A. In the direction of the longitudinal axis A, position P1 lies in a region where the first inner surface 55a1 extends. Position P2 is located at a position closer to the distal end than position P1 in the longitudinal direction A.For example, in the longitudinal direction A, position P2 lies within a region where the third inner surface 55a3 extends. Position P3 is located closer to the distal end than position P2 in the longitudinal direction A. For example, in the longitudinal axis A, position P3 lies within a region where the fifth inner surface 55a5 extends. In the illustrated embodiment, the second width d2 is larger than the first width d1 and the third width d3. The third width d3 can be equal to, smaller than, or larger than the first width d1. As described above, in the illustrated embodiment, at a position corresponding to the third inner surface 55a3, the hole 55a formed in the cylindrical element 52a has a larger width than at any other position.A section of the cylindrical element 52a corresponding to the inner surface 55a3 in the longitudinal axis A-direction can be designated as the large section 52a1. The width of any component of the sleeve 50a or the hole 55a can refer to a dimension of that component or hole 55a in a lateral direction orthogonal to the longitudinal axis A. For example, the first width d1 of the hole 55a at position P1 can refer to a dimension of the hole 55a in a lateral direction at position P1. In the longitudinal direction A-direction, 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.

[0076] The sleeve 50b comprises a sleeve body 51b and a fitting 52b, which is connected to the distal end of the shaft part 31b. The sleeve body 51b is fastened to the fitting 52b by a fastening element 53b. The sleeve body 51b has a through-hole 51b1. The through-hole 51b1 extends through the sleeve body 51b along the axial direction J of the shaft 13A.

[0077] The fitting 52b of the sleeve 50b has a hole 55b extending along the axis B. The hole 55b extends through the fitting 52b along the axis B. An inner circumferential surface of the hole 55b is shaped similarly to an inner circumferential surface of the hole 55a, so a detailed description is unnecessary.

[0078] The connecting section 35a at the distal end of the shaft element 31a is housed in the hole 55a of the cylindrical element 52a. The portion of the shaft element 31a covered by the cylindrical element 52a is referred to as the connecting section 35a, and a portion of the shaft element 31a not covered by the cylindrical element 52a can be referred to as the non-connecting section 36a.

[0079] The connecting section 35a of the shaft element 31a is formed in a shape that fits into the hole 55a of the cylindrical element 52a.In the illustrated embodiment, the connecting section 35a comprises a first section 35a1 extending in the direction parallel to the longitudinal axis A from a position in the longitudinal axis A direction corresponding to the opening end 54a2 of the cylindrical element 52a, a second section 35a2 extending from a distal end of the first section 35a1 in the longitudinal axis A direction to be inclined with respect to the longitudinal axis A, a third section 35a3 extending in the direction parallel to the longitudinal axis A from a distal end of the second section 35a2 in the longitudinal direction A direction, a fourth section 35a4 extending from a distal end of the third section 35a3 in the longitudinal direction A direction to be inclined with respect to the longitudinal axis A, and a fifth section 35a5 extending in the direction parallel to the longitudinal axis A from a distal end of the fourth section 35a4 in the direction A direction.In one embodiment, the first section 35a1, the second section 35a2, the third section 35a3, the fourth section 35a4, and the fifth section 35a5 each extend along a corresponding inner surface 55a1, 55a2, 55a3, 55a4, and 55a5, respectively. In another embodiment, the first section 35a1, 55a2, 55a3, 55a4, and 55a5 each have an outer surface configured to adhere firmly to a corresponding inner surface 55a1, 55a2, 55a3, 55a4, and 55a5, respectively. The connecting section 35a has a width (outer width) that corresponds 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 position P1 in the longitudinal direction A, the second width d2 at position P2 in the longitudinal axis A, and the third width d3 at position P3 in the longitudinal axis A. Thus, the connecting section 35a is configured to have a width d1 at the first section 35a1 at position P1, a width d2 at the third section 35a3 at position P2, and a width d3 at the fifth section 35a5 at position P3. As described above, the connecting section 35a of the shaft element 31a is configured to have the width d1 at position P1 in the longitudinal direction A and the width d2 at position P2 closer to the distal end than position P1 in the longitudinal axis A, with the width d2 being greater than the width d1.Furthermore, the connecting section 35a of the shaft element 31a is configured to have the width d3 at position P3 closer to the distal end than position P2 in the longitudinal axis A-direction, with the width d3 being smaller than the width d2.

[0080] The connecting section 35a is formed in a shape corresponding to the inner surface of the cylindrical element 52a defining the hole 55a, and thus the connecting section 35a has a width (outer width) at every point on the longitudinal axis A that corresponds to the width (inner width) of the hole 55a. Therefore, the connecting section 35a has a width d1 at position P1 on the longitudinal axis A, a width d2 at position P2, and a width d3 at position P3 on the longitudinal axis A.

[0081] In the connection structure described above between the connecting body 30 and the sleeve 50a, the shaft element 31a of the connecting body 30 is formed in a shape that fits into the hole 55a, and the shaft element 31a formed in this shape is positioned in the hole 55a. Thus, the movement of the shaft element 31a in the longitudinal axis A-direction is restricted in the hole 55a, and the shaft element 31a is protected from falling out of the hole 55a. Therefore, the connecting body 30 is connected to the sleeve 50a via the shaft element 31a without cutting any reinforcing fibers, which are contained within the shaft element 31a. As described above, in the base structure formed by the connection of the connecting body 30 to the sleeve 50a, it is possible to prevent a loss of strength in the shaft element 31a, which is made of fiber-reinforced plastic.Similarly, the connecting body 30 is connected to the sleeve 50b via the shaft element 31b without cutting any reinforcing fibers, which are contained within the shaft element 31b. It is also possible to connect the shaft element 31a to the sleeve 50a and the shaft element 31b to the sleeve 50b using an adhesive. Even when using an adhesive, the reinforcing fibers contained in the shaft element 31a and the shaft element 31b are prevented from being cut.

[0082] In the connection structure described above between the connecting body 30 and the sleeve 50a, the sleeve 50a has the wide section 52a1, and the wide section 52a1 accommodates the third section 35a3 of the shaft element 31a, the third section 35a3 being designed as wide. Thus, the sleeve 50a supports the third section 35a3 of the shaft element 31a in the longitudinal direction A by using a section that is closer to the proximal end than the wide section 52a1 in the longitudinal direction A. In particular, when a tensile load acts on the connecting body 30 in the direction of the proximal end in the longitudinal axis A direction, the tensile load is absorbed by the inclined inner surface 55a2 of the hole 55a of the sleeve 50a. Therefore, if a tensile load acts on the connecting body 30 towards the proximal end in the longitudinal axis A direction, the sleeve 50a can counteract the tensile load using the inner surface 55a2.This allows the shaft element 31a to be more reliably protected from falling out of the hole 55a, so that the connecting body 30 can be more firmly connected to the sleeve 50a.

[0083] Furthermore, the sleeve 50a supports the third section 35a3 of the shaft element 31a in the longitudinal direction A by utilizing a section that is closer to the distal end than the wide section 52a1 in the longitudinal direction A. Specifically, when a compressive load acts on the connecting body 30 towards the distal end in the longitudinal axis A direction, the compressive load is absorbed by the inclined inner surface 55a4 of the hole 55a of the sleeve 50a. Thus, when a compressive load acts on the connecting body 30 towards the distal end in the longitudinal axis A direction, the sleeve 50a can counteract the compressive load by utilizing the inner surface 55a4. This allows the connecting body 30 to be more firmly connected to the sleeve 50a. Furthermore, the use of the inner surface 55a4 counteracts a pressure load acting on the connecting body 30, thus preventing stress from concentrating on the distal end of the shaft element 31a.Thus, it is possible to prevent the shaft element 31a from buckling under pressure.

[0084] In the foregoing embodiment, the angle formed by the first reinforcing fiber 61 contained in the shaft element 31a with its longitudinal axis A in the connecting section 35a is greater than the angle formed by the first reinforcing fiber 61 with its longitudinal axis A in the non-connecting section 36a. Therefore, the shaft element 31a is more easily deformed in the lateral direction in the connecting section 35a than in the non-connecting section 36a. This makes it easy to shape the shaft element 31a to fit into the hole 55a.

[0085] In the foregoing embodiment, the first reinforcing fiber 61 is woven with the second reinforcing fiber 62. This increases the strength of the shaft element 31a. Furthermore, the angle formed by the second reinforcing fiber 62 with the longitudinal axis A in the connecting section 35a is smaller than the angle formed by the second reinforcing fiber 62 with the longitudinal axis A in the non-connecting section 36a. This makes it easy to shape the shaft element 31a to fit into the hole 55a.

[0086] The connection structure between the shaft element 31a and the hole 55a in the preceding embodiment is only one embodiment of the present invention, and the shape of the hole 55a and the shape of the shaft element 31a to be installed therein can be modified as necessary. An example of a further embodiment of the connection structure, formed by joining the connecting body 30 with the sleeve 50a, is now described with reference to Fig. 9 described. Fig. Figure 9 shows a connection structure between a shaft element and a hole in another embodiment of the present invention.

[0087] As in Fig. Figure 9 shows that in a further embodiment of the present invention, a cylindrical element 52a in the connecting structure has a hole 155a instead of the hole 55a.As shown, an inner surface of the hole 155a comprises a first inner surface 155a1 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 155a1 in a direction of the longitudinal axis A to be inclined with respect to the longitudinal axis A, a third inner surface 155a3 extending in a direction parallel to the longitudinal axis A from a distal end of the second inner surface 155a2 in the direction of the longitudinal axis A, a fourth inner surface 155a4 extending from a distal end of the third inner surface 155a3 in the direction of the longitudinal axis A to be inclined with respect to the longitudinal axis A, and a fifth inner surface 155a5 extending in a direction parallel to the longitudinal axis A from a distal end of the fourth inner surface 155a4 in the direction of the longitudinal axis A.The inner surface 155a2 is inclined in a direction towards the longitudinal axis A towards a distal end thereof in the longitudinal direction A. The inner surface 155a4 is inclined in a direction away from the longitudinal axis A towards a distal end thereof in the longitudinal direction A. Therefore, a sleeve 50a encompasses in the in . Fig. In the embodiment shown in Figure 9, a curved section 152a1 is provided, which curves inwards in the width direction of the hole 155a.

[0088] In the illustrated embodiment, the hole 155a has a first width d11 at position P11 in the longitudinal axis A-direction, a second width d12 at position P12 in the longitudinal axis A-direction, and a third width d13 at position P13 in the longitudinal axis A-direction. In the direction of the longitudinal axis A, position P11 lies within a region where the first inner surface 155a1 extends. Position P12 is located closer to the distal end than position P11 in the longitudinal direction A. For example, in the longitudinal axis A-direction, position P12 lies within a region where the third inner surface 155a3 extends. Position P13 is located closer to the distal end than position P12 in the longitudinal direction A. For example, in the longitudinal axis A-direction, position P13 lies in an area where the fifth inner surface 155a5 extends.In the illustrated embodiment, the second width d12 is smaller than the first width d11 and the third width d13. The third width d13 can be equal to, smaller than, or larger than the first width d11. As described above, in the illustrated embodiment, the hole 155a formed in a cylindrical element 152a has a smaller width at a position corresponding to the third inner surface 155a3 than at any other position. In the longitudinal 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.

[0089] In the Fig. In the embodiment shown in Figure 9, a connecting section 35a of a shaft element 31a is formed in a shape that fits into the hole 155a of the cylindrical element 52a. In particular, the connecting section 35a in the illustrated embodiment comprises a first section 135a1 extending in the direction parallel to the longitudinal axis A from a position in the longitudinal axis A-direction corresponding to the opening end 54a of the cylindrical element 52a, a second section 135a2 extending from a distal end of the first section 135a1 in the longitudinal axis A-direction such that it is inclined with respect to the longitudinal axis A, a third section 135a3 extending in the direction parallel to the longitudinal axis A from a distal end of the second section 135a2 in the longitudinal direction A-direction, and a fourth section 135a4 extending from a distal end of the third section 135a3 in the longitudinal direction A-direction.to be inclined with respect to the longitudinal axis A, and a fifth section 135a5 extending in the direction parallel to the longitudinal axis A from a distal end of the fourth section 135a5 in the direction of the longitudinal axis A. In one embodiment, the first section 135a1, the second section 135a2, the third section 135a3, the fourth section 135a4, and the fifth section 135a5 each extend along a corresponding inner surface 135a1, the second inner surface 135a2, the third inner surface 135a3, the fourth inner surface 135a4, and the fifth inner surface 135a5. In one embodiment, the first section 135a1, the second section 135a2, the third section 135a3, the fourth section 135a4 and the fifth section 135a5 each have an outer surface which is designed to be firmly connected to a corresponding inner surface 155a1, the second inner surface 155a2, the third inner surface 155a3,The fourth inner surface 155a4 and the fifth inner surface 155a5 are connected. The connecting section 35a has a width (outer width) that corresponds to a width (inner width) of the inner surface of the hole 155a. Therefore, the connecting section 35a is designed such that it has a width d11 at the first section 135a1, which is located at position P11, a width d12 at the third section 135a3, which is located at position P12, and a width d13 at the fifth section 35a5, which is located at position P3. As described above, the connecting section 35a of the shaft element 31a is configured to have a width d12 at position P12 in the longitudinal axis A direction and a width d13 at position P13 closer to the distal end than position P12 in the longitudinal axis A direction, with the width d13 being greater than the width d12. Furthermore, the connecting section 35a of the shaft element 31a is configuredto have the width d11 at position P11 closer to the proximal end than position P12 in the longitudinal axis A-direction, where the width d11 is greater than the width d12.

[0090] In the connection structure of the embodiment, the sleeve 50a has the curved section 152a1, and the curved section 152a1 is received by the third section 135a3 of the shaft element 31a, the third section 135a3 being narrow. Thus, the sleeve 50a supports the first section 135a1 of the shaft element 31a in the longitudinal direction A by using a section that is closer to the distal end than the curved section 152a1 in the longitudinal direction A. In particular, when a compressive load acts on a connecting body 30 towards the distal end in the longitudinal axis A direction, the compressive load is received by the inclined inner surface 155a2 of the hole 155a of the sleeve 50a. Therefore, if a pressure load acts on the connecting body 30 towards the distal end in the longitudinal axis A-direction, the sleeve 50a can counteract the pressure load by using the inner surface 155a2.If a compressive load acts on the connecting body 30 towards its distal end in the longitudinal axis A-direction, the sleeve 50a can counteract this compressive load by utilizing its inner surface 155a2. Thus, the connecting body 30 can be firmly connected to the sleeve 50a. Furthermore, the inner surface 155a2 counteracts any compressive load acting on the connecting body 30, thereby preventing the shaft element 31a from buckling under the compressive load.

[0091] Furthermore, the sleeve 50a supports the fifth section 135a5 of the shaft element 31a in the longitudinal direction A by utilizing a section that is closer to the distal end than the curved section 152a1 in the longitudinal direction A. Specifically, when a tensile load acts on the connecting body 30 towards the proximal end in the longitudinal axis A direction, the tensile load is absorbed by the inclined inner surface 155a4 of the hole 155a of the sleeve 50a. Therefore, when a tensile load acts on the connecting body 30 towards the distal end in the longitudinal axis A direction, the sleeve 50a can counteract the tensile load by utilizing the inner surface 155a4. This allows the connecting body 30 to be more firmly connected to the sleeve 50a.

[0092] The connecting structure to which the present invention is applied can take various other forms than those shown in Fig. 9. The cylindrical element 52a can, for example, have any other section shaped to be wide in addition to the wide section 52a1. Furthermore, the cylindrical element 52a can have any other section shaped to project inwards in the width direction in addition to the convex section 152a1. The hole 55a and the hole 155a can be formed in various shapes that can accommodate the shaft element 31a.

[0093] Next, examples of changes to the connecting body 30 will be presented with reference to Fig. 10 to Fig. 12 described. Fig. Figure 10 is a schematic view showing, schematically on an enlarged scale, a distal end of a connecting part contained in an aircraft reaction element according to another embodiment of the present invention. Fig. Figure 11 is a sectional view of the aircraft reaction element according to a further embodiment of the present invention, which is cut along a plane perpendicular to a longitudinal axis A in the direction of the same. Fig. Figure 12 is a sectional view of the aircraft reaction element according to a further embodiment of the present invention, which is cut along the plane perpendicular to the longitudinal axis A in the direction of the same.

[0094] As in Fig. As shown in Figure 10, a connecting body 30 according to a further embodiment of the present invention comprises a reinforcing element 70. The reinforcing element 70 is formed from a film of fiber-reinforced plastic. The reinforcing element 70 is formed, for example, from a fiber-reinforced plastic sheet containing reinforcing fibers oriented circumferentially to a shaft element 31a. The reinforcing fibers contained in the reinforcing element 70 can be of the same type as the reinforcing fibers 61. In one embodiment, the reinforcing element 70 is provided on a section of the connecting body 30, with the exception of a connecting section 35a of the shaft element 31a. For example, the reinforcing element 70 is provided on a connecting section 32 and / or a non-connecting section 36a of the shaft element 31a.The reinforcing element 70 is provided on a different section than the connecting section 35a, and thus the reinforcing element 70 does not interfere with the processing of the connecting section 35a when forming the connecting section 35a in a shape that fits into a hole 55a.

[0095] As in Fig. 11 and Fig. As shown in Figure 12, the shaft element 31a of the connecting body 30 can be shaped such that it has a non-circular cross-section perpendicular to the longitudinal direction A. For example, as shown in Fig. As shown in Figure 11, the shaft element 31a is shaped to have a rectangular cross-section perpendicular to the longitudinal direction A. If the shaft element 31a is shaped to have a rectangular cross-section, the angles of the rectangular cross-section need not be right angles and can, as shown, be rounded off to a practically suitable dimension. As shown in Fig. As shown in Figure 12, the shaft element 31a can be designed such that it has an elliptical cross-section perpendicular to the longitudinal direction A.

[0096] The shaft element 31a is designed such that it has a non-circular cross-section perpendicular to the longitudinal axis A-direction, so that a few forces can be transmitted between a sleeve 50a and the shaft element 31a.

[0097] Next, a reaction element according to a further embodiment of the present invention will be described with reference to Fig. 13 described. Fig. Figure 13 is a perspective view of an aircraft reaction element 120 according to a further embodiment of the present invention. The aircraft reaction element 120 differs from the aircraft reaction element 20 in that it comprises a bracing pin 121. The bracing pin 121 is an element for further reinforcing the connection between the shaft element 31a and the sleeve 50a. In particular, in this embodiment, the shaft element 31a has a through-hole for a small-diameter shaft element, and the sleeve 50a has a through-hole for a sleeve formed at a position therein facing the through-hole of the shaft element. The through-hole of the shaft element and the through-hole of the sleeve can both be shaped such that they pass through the longitudinal axis A and extend in a direction perpendicular to the longitudinal axis A.When the sleeve 50a is mounted on the shaft element 31a, the through-hole of the sleeve and the through-hole of the shaft element are connected. A through-hole formed by the through-hole of the sleeve and the through-hole of the shaft element, which are connected to each other, is called a bolt through-hole. The mortise bolt 121 is inserted through the bolt through-hole. After insertion through the bolt through-hole, the mortise bolt 121 is plastically deformed to reinforce the connection between the shaft element 31a and the sleeve 50a. The through-hole formed in the shaft element 31a is designed such that no reinforcing fibers contained in the shaft element 31a are cut. In a case where, for example, the reinforcing fibers contained in the shaft element 31a are woven together by a multitude of filament bundles, as in . Fig. As shown in Figure 8, the through-hole of the shaft element is formed such that it has a diameter smaller than a portion of the reinforcing fibers woven together. Thus, the mortise bolt 121 can be inserted through the through-hole of the shaft element without damaging the reinforcing fibers. The mortise bolt 121 can be columnar in shape. The mortise bolt 121 can have a small-diameter section provided along its axis. The small-diameter section is shaped to have a diameter smaller than that of any other part of the mortise bolt 121. After the mortise bolt 121 has been plastically deformed to connect the shaft element 31a to the sleeve 50a, it can be cut at the small-diameter section.

[0098] In the foregoing embodiments, the present invention is applied to an aircraft reaction element and a drive device for moving surfaces. However, the present invention is not limited to the aforementioned embodiments and also has applications other than an aircraft reaction element and a drive device for moving surfaces. The present invention is essentially applied to a connection structure between a first element and a second element, wherein the first element has a hole and the second element comprises a shaft element made of a fiber-reinforced composite material.

[0099] Next, a method for producing the reaction element 20 according to an embodiment of the present invention will be described with reference to Fig. 14 and Fig. 15A to Fig. 15F described.

[0100] In step ST1, a sleeve is prepared. The sleeve mentioned here is, for example, sleeve 50a or sleeve 50b as described in the preceding embodiments.

[0101] Then, in step ST2, a core 81 is prepared. As in Fig. As illustrated in Figure 15A, the core 81 is formed in a U-shape, which approximately corresponds to the shape of the connecting body 30. However, the core 81 does not have a bulge corresponding to the third section 35a3. The core 81 comprises a pair of legs 81a and 81b and a connecting section 81c that joins the proximal ends of the leg pair 81a and 81b. One end of leg 81a is closed, and one end of leg 81b is open. The core 81 is configured such that leg 81b is longer than leg 81a. Leg 81a and leg 81b are configured such that they have substantially the same diameter in their respective sections at any position along its axis. The core 81 is hollow. The hollow core 81 is, for example, a tube made of synthetic resin.The synthetic resin from which core 81 is formed is, for example, nylon, polyurethane, polytetrafluoroethylene, or any other known synthetic resin material.

[0102] Subsequently, in step ST3, a fiber-containing composite layer 82 is formed on a surface of the core 81. Specifically, an impregnation fluid tank containing a matrix resin is first prepared. The matrix resin can be a thermosetting resin such as 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-curing resin; or another known matrix resin. 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 in the impregnation fluid tank. The plurality of reinforcing fibers can correspond to the reinforcing fibers 61, 62, and 63 described in the preceding embodiments. Three reinforcing fibers impregnated with the matrix resin are woven into the core 81 by the braiding machine.This creates a laminate 83, which is in . Fig. 15B and Fig. Figure 15C shows the laminate 83 comprising the core 81 and the fiber-reinforced composite layer 82 formed on the core 81. The fiber-reinforced composite layer 82 is configured to completely cover leg 81a and the connecting section 81c, and to partially cover leg 81b. The fiber-reinforced composite layer 82 is not formed at a distal end of leg 81b. The reinforcing fibers can be wound directly onto the core 81 or indirectly via a release layer. For example, the release layer is formed on an outer surface of the core 81 before the reinforcing fibers are wound onto the core 81. The release layer consists, for example, of a silicone resin. Providing the release layer facilitates the removal of the core 81. It is also possible to provide a release layer on an outer surface of the laminate 83.Providing the release layer on the outer surface of the laminate 83 can improve demoldability from a mold described below. The fiber-reinforced composite layer 82 can also be formed using any known device suitable for weaving reinforcing fibers, with the exception of a braiding machine. Two or more fiber-reinforced composite layers 82 can be formed.

[0103] Subsequently, in step ST4, the sleeve 50a is mounted on one distal end of the laminate 83 obtained as described above. In particular, one distal end of the laminate 83 is inserted into the hole 55a formed in the sleeve 50a. The fitting 52b, which is a component of the sleeve 50b, is mounted on the other end of the laminate 83. In particular, the other distal end of the laminate 83 is inserted into the hole 55a formed in the fitting 52b. As described above, as in Fig. As shown in Figure 15D, a composite laminate 84 is obtained by mounting the sleeve 50a and the connector 52b to the laminate 83. Subsequently, in step ST5, the composite laminate 84 is arranged in a mold 90. The mold 90 comprises an upper mold 91 and a lower mold 92, as shown in Figure 15D. Fig. Figure 15D shows the upper form 91, which has a cavity 91a with a shape corresponding to the composite laminate 84. Similarly, the lower form 92 has a cavity 92a with a shape corresponding to the composite laminate 84. A gap G exists between the composite laminate 84 arranged in the mold 90 and the inner surface of the hole 55a of the sleeve 50a, and between the composite laminate 84 arranged in the mold 90 and the inner surface of the hole 55b of the fitting 52b. A cap (not shown) is attached to an opening end 81d of the hollow core 8a. The core 81 is connected via the cap and a line to a pump (not shown).

[0104] Next, the mold 90 is closed. The closed mold 90 is then placed in a press (not shown). In step ST6, the mold 90, positioned in the press, is heated, and compressed air from the pump is directed into the hollow core 81. The end of the core 81 on the side opposite the opening end 81d is closed, and thus internal pressure is generated in the core 81 by the compressed air supplied by the pump. Due to this internal pressure, the core 81 expands outwards in the width direction. Furthermore, as the core 81 expands, the fiber-reinforced composite layer 82 also expands outwards in the width direction to such an extent that the gap G between the fiber-reinforced composite layer 82 and each of the holes 55a and the hole 55b disappears. Thus, the fiber-containing composite layer 82 adheres firmly to the inner surface of hole 55a and the inner surface of hole 55b.The fiber-containing composite layer 82 is cured in a state of firm adhesion to the inner surface of hole 55a and the inner surface of hole 55b.

[0105] Subsequently, in step ST7, the cured composite laminate 84 is removed from the mold 90, and the core 81 is removed from the composite laminate 84. A portion of the core 81 exposed by the fitting 52b is grasped and pulled out, thus removing the core 81 from the composite laminate 84. This yields the connecting body 30 with the sleeve 50a and the fitting 52b at its distal ends. Removing the core 81 makes it possible to reduce the weight of the finished aircraft reaction element.

[0106] Finally, in step ST8, the sleeve body 51b is mounted on the fitting 52b, thus creating the sleeve 50b. The sleeve body 51b is attached to the fitting 52b, for example, with the fastening element 53b. Furthermore, the head 40 is mounted on the connecting body 30.

[0107] By adhering to the above-described process steps, an aircraft reaction element is obtained in which a connecting body is joined to a sleeve without reducing the strength of the connecting body.

[0108] The in Fig. The flowchart shown in Figure 14 is an example of the method for manufacturing an aircraft reaction element to which the present invention is applied, and the present invention is not limited to the method shown in Figure 14. Fig. The specific flow shown in section 14 is limited.

[0109] Some of the in Fig. The process steps of the flow shown in Figure 14 can be omitted in accordance with the present invention. For example, step ST7 for removing the core 81 can be omitted.

[0110] Process steps that are not in Fig. The actions shown in section 14 can be carried out if necessary. Fig. 14 process steps not shown can be added to those in Fig. 14 process steps shown or alternatively to some of those in Fig. The 14 process steps shown can be carried out. For example, a process for polishing a surface of the laminate 83 formed in step ST3 can be carried out.

[0111] The in Fig. The 14 illustrated process steps can be carried out in various orders as required by the present invention. For example, step ST1 for preparing the sleeve can be performed after step ST2 for preparing the core 81. The process step of assembling the head 40 onto the connecting body 30 can be performed after step ST4 and before step ST5.

[0112] Some of the in Fig. The 14 process steps shown can be carried out simultaneously or in parallel where possible. For example, step ST1 for preparing the sleeve and step ST2 for preparing the core 81 can be carried out in parallel. The other process steps can also be carried out simultaneously or in parallel.

[0113] The core 81 can be shaped so that it consists solidly of a thermally expandable resin composition. The thermally expandable resin composition used for the solid core 81 is a resin composition containing a binder resin with thermally expandable graphite.

[0114] In the foregoing embodiment, the present invention is applied to a method for manufacturing an aircraft reaction element. The present invention is therefore not limited to the aforementioned embodiment.

[0115] The invention also applies to a method for manufacturing an article other than an aircraft reaction element. As can be seen from the disclosure, the present invention is essentially applied to a method for connecting a first element to a second element, wherein the first element has a hole extending along an axial direction, and wherein the second element comprises a shaft element made of a fiber-reinforced composite material.

[0116] The dimensions, materials, arrangements, and process steps of the various components described herein are not limited to those expressly described in the embodiments, and the various components can be modified to have any dimensions, materials, arrangements, and process steps within the scope of the present invention. Furthermore, components not expressly described can be added to the described embodiments, and it is also possible to omit some of the components described in the embodiments.

Claims

[1] Connection structure comprising: a first element (50a, 50b) having a hole (55a, 55b) extending along an axial direction (A, B); wherein the first element (50a, 50b) comprises a cylindrical element (52a, 52b) defining the hole (55a, 55b), and an inner surface of the hole (55a) comprises a first inner surface (55a1, 155a1) extending from the opening end (54a2) in a direction parallel to the longitudinal axis (A), a second inner surface (55a2, 155a2) extending from a distal end of the first inner surface (55a1, 155a1) in the longitudinal direction A direction to be inclined with respect to the longitudinal axis (A), and a third inner surface (55a3, 155a3) extending in the direction parallel to the longitudinal axis (A) from a distal end of the second inner surface (55a2, 155a2) in the direction of the longitudinal axis (A), a second element (30) with a hollow shaft element (31a, 31b), wherein the shaft member (31a, 31b) comprises a first portion (35a1, 135a1) extending in the direction parallel to the longitudinal axis (A) from a position in the longitudinal axis A direction corresponding to the opening end (54a2) of the cylindrical member (52a), a second portion (35a2, 135a2) extending from a distal end of the first portion (35a1, 135a1) in the longitudinal axis A direction to be inclined with respect to the longitudinal axis (A), a third portion (35a3, 135a3) extending in the direction parallel to the longitudinal axis (A) from a distal end of the second portion (35a2, 135a2) in the longitudinal direction A direction, wherein the shaft element (31a, 31b) is formed from a fibrous composite material and has a shape that fits into the hole (55a, 55b), wherein the second element (30) is connected to the first element (50a, 50b) via the shaft element (31a, 31b) so that its movement in the axial direction (A, B) is restricted, wherein the first section (35a1, 135a1), the second section (35a2, 135a2) and the third section (35a3, 135a3) each extend along a corresponding one of the first inner surface (55a1, 155a1), the second inner surface (55a2, 155a2) and the third inner surface (55a3, 155a), and wherein the first portion (35a1, 135a1), the second portion (35a2, 135a2) and the third portion (35a3, 135a3) each have an outer surface configured to firmly 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] The connecting structure according to claim 1, wherein the shaft member (31a, 31b) has a first width (d1, d11) at a first position (P1, P12) in the axial direction (A, B) and a second width (d2, d12) at a second position (P2, P13) in the axial direction (A, B), the second position (P2) being closer to a distal end of the shaft member (31a, 31b) than the first position (P1), and the second width (b2, b12) being larger than the first width (b1, b11). [3] The connecting structure according to claim 2, wherein the shaft member (31a, 31b) has a third width (b3, b13) at a third position (P3) in the axial direction (A, B), the third position (P3) being closer to the distal end of the shaft member (31a, 31b) than the second position (P2), and the third width (d3, d13) being smaller than the second width (d2, d12). [4] The connecting structure according to claim 2, wherein the shaft member (31a, 31b) has a fourth width at a fourth position (P11) in the axial direction (A, B), the fourth position (P11) being closer to a proximal end of the shaft member (31a, 31b) than the first position (P1, 12), and the fourth width being greater than the first width (d1, d11). [5] The connecting structure according to claim 1, wherein the shaft member (31a, 31b) has a non-circular cross section in a direction perpendicular to the axial direction (A, B). [6] The connecting structure according to claim 1, wherein the cylindrical member (52a, 52b) has a smaller thickness at a proximal end thereof in the axial direction (A, B) than at a distal end side of the proximal end in the axial direction (A, B). [7] The connecting structure according to claim 6, wherein the cylindrical member (52a, 52b) is made of a metal. [8] A connecting structure according to claim 1, wherein the shaft element (31a, 31b) comprises a first reinforcing fiber (61) extending in a first direction (D1), wherein the shaft member (31a, 31b) comprises: a connecting portion (35a, 35b) overlapping with the cylindrical member (52a, 52b) in the axial direction (A, B); and a non-connecting portion (36a, 36b) which does not overlap with the connecting portion (35a, 35b) in the axial direction (A, B), and wherein an angle formed by the first direction (D1) with the axial direction (A, B) in the connecting portion (35a, 35b) is greater than an angle formed by the first direction (D1) with the axial direction (A, B) in the non-connecting portion (36a, 36b). [9] The connecting structure according to claim 8, wherein the shaft member (31a, 31b) further comprises a second reinforcing fiber (61) extending in a second direction (D2) different from the first direction (D1) and woven with the first reinforcing fiber (61), and wherein an angle formed by the second direction (D2) with the axial direction (A, B) in the connecting portion is larger than an angle formed by the second direction (D2) with the axial direction in the non-connecting portion (36a, 36b). [10] The interconnection structure of claim 8, further comprising: a reinforcing member (70) provided in the non-connecting portion (36a, 36b), the reinforcing member (70) being made of a fiber-reinforced plastic containing reinforcing fibers (61-63) oriented in a circumferential direction around the axial direction (A, B). [11] An aircraft reaction member (20) comprising: a sleeve (50) slidably supporting an actuator (10), the actuator (10) being directly or indirectly attached to a movable surface (101) of an aircraft and being configured to drive the movable surface (101); and a connecting body (30) comprising a shaft element (31a, 31b) made of a fiber-containing composite material and connected to the sleeve (50), wherein the sleeve (50) has a hole (55a, 55b) extending along an axial direction (A, B) of the shaft element (31a, 31b), wherein an inner surface of the hole (55a) comprises a first inner surface (55a1, 155a1) extending from the opening end (54a2) in a direction parallel to the longitudinal axis (A), a second inner surface (55a2, 155a2) extending from a distal end of the first inner surface (55a1, 155a1) in the longitudinal direction A direction to be inclined with respect to the longitudinal axis (A), and a third inner surface (55a3, 155a3) extending in the direction parallel to the longitudinal axis (A) from a distal end of the second inner surface (55a2, 155a2) in the direction of the longitudinal axis (A), and wherein the shaft member (31a, 31b) is formed in a shape that fits into the hole (55a, 55b) and is arranged in the hole (55a, 55b) so that its movement in the axial direction (A, B) is restricted, wherein the shaft member (31a, 31b) comprises a first portion (35a1, 135a1) extending in the direction parallel to the longitudinal axis (A) from a position in the longitudinal axis A direction corresponding to the opening end (54a2) of the cylindrical member (52a), a second portion (35a2, 135a2) extending from a distal end of the first portion (35a1, 135a1) in the longitudinal axis A direction to be inclined with respect to the longitudinal axis (A), a third portion (35a3, 135a3) extending in the direction parallel to the longitudinal axis (A) from a distal end of the second portion (35a2, 135a2) in the longitudinal direction A direction, wherein the first section (35a1, 135a1), the second section (35a2, 135a2) and the third section (35a3, 135a3) each extend along a corresponding one of the first inner surface (55a1, 155a1), the second inner surface (55a2, 155a2) and the third inner surface (55a3, 155a3), and wherein the first portion (35a1, 135a1), the second portion (35a2, 135a2) and the third portion (35a3, 135a3) each have an outer surface configured to firmly 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). [12] Drive device for moving surfaces, comprising: the aircraft reaction member (20) according to claim 11; and the actuator (10). [13] A joining method for joining a first element (50a, 50b) to a second element (30), wherein the first element has a hole (55a, 55b) extending along an axial direction (A, B), wherein an inner surface of the hole (55a, 55b) comprises a first inner surface (55a1, 155a1) extending from the opening end (54a2) in a direction parallel to the longitudinal axis (A), a second inner surface (55a2, 155a2) extending from a distal end of the first inner surface (55a1, 155a1) in the longitudinal direction A direction to be inclined with respect to the longitudinal axis (A), and a third inner surface (55a3, 155a3) extending in the direction parallel to the longitudinal axis (A) from a distal end of the second inner surface (55a2, 155a2) in the direction of the longitudinal axis (A), wherein the second element comprises a shaft element (31a, 31b) made of a fiber-containing composite material, the method comprising the following steps: (A) preparing the first element (50a, 50b); (B) producing a core (81); (C) obtaining a laminate (83) by forming a fiber-containing composite layer (82) on the core (81); (D) inserting at least a portion of the laminate (83) into the hole (55a, 55b) of the first element (50a, 50b); (E) causing the core (81) to expand such that the fibrous composite layer (82) adheres to an inner surface of the hole (55a, 55b); and (F) Obtaining the shaft element (31a, 31b) in a shape that fits into the hole (55a, 55b) by curing the fiber-containing composite layer (82). [14] The joining method of claim 13, further comprising the step of: Removing the core (81). [15] The joining method according to claim 13, wherein in step (C), a release layer is provided on an outer surface of the core (81) and the fibrous composite layer (82) is formed on the release layer.

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