SUPPORT STRUCTURE FOR FORCE TRANSMISSION ELEMENT, AIRCRAFT REACTION LINK, FLIGHT CONTROL SURFACE CON

专利摘要:
It is an object to provide a support structure (BS) for a force transmission element (50), an aircraft reaction link (20), a flight control surface control unit (1), a method mounting a force transmitting member (50), and a method of manufacturing an aircraft reaction link (20) for weight reduction while providing the necessary strength. In accordance with one aspect, the reaction link (20) comprises a bearing (50) and a connecting body (30) made of a fiber reinforced plastic and supporting the bearing (50). The link body (30) includes a support portion that supports the pad (50), and the fibers (60) included in the support portion are continuous.
公开号:FR3043357A1
申请号:FR1660504
申请日:2016-10-28
公开日:2017-05-12
发明作者:Tsutomu Yasui
申请人:Nabtesco Corp；
IPC主号:

专利说明:

SUPPORT STRUCTURE FOR FORCE TRANSMISSION ELEMENT, DAVION REACTION CONNECTION, FLIGHT CONTROL SURFACE CONTROL UNIT, FORCE TRANSMISSION ELEMENT MOUNTING METHOD, AND DAVION REACTION BINDING METHOD FOR MANUFACTURING
RELATED APPLICATIONS
The present application is based on Japanese Patent Application No. 2015-217581 (filed November 5, 2015) and has the corresponding priority.
TECHNICAL AREA
The present invention relates to a support structure for a force transmission element, an aircraft reaction link, a flight control surface control unit, a method of mounting a transmission element. by force, and a method of manufacturing an aircraft reaction link.
BACKGROUND OF THE INVENTION
[0003] The aircraft are provided with flight control surfaces comprising primary control surfaces formed as rudder faces such as ailerons, rudders or elevators, and secondary control surfaces such as flaps. or spoilers. Flight control surface control units for controlling these flight control surfaces are provided with an actuator mounted on a flight control surface and an aircraft reaction link pivotally connected to the actuator. and at the flight control surface.
To reduce the weight of aircraft, many aircraft components made of metallic materials such as titanium alloys are currently replaced by elements made from fiber reinforced plastics. Among these components, it is well known that certain reaction bonds are made of fiber-reinforced plastics instead of metallic materials (see Japanese Patent Application Publication No. 2014-237429).
An example of such aircraft reaction links is the reaction linkage 200 shown in FIG. 19a, which comprises a linkage body 210 which establishes a connection between a flight control surface and an actuator, and bearings 220 for slidably supporting a connection pin of the actuator. The connecting body 210 is made of a fiber reinforced plastic. The pads 220 are connected to the end portions of the connecting body 210 via fasteners 230. More specifically, each of the end portions of the connecting body 210 includes a pair of flat plates. Each pair of flat plates 211 has a through hole 212 into which a clip 230 is inserted (see Fig. 19b). The pad 220 is partially inserted between the pair of flat plates 211. A clip 230 is inserted into the through hole 212 to secure between them the pad 220 and the pair of flat plates 211.
The end portion of the connecting body 210 comprises first fibers 241 and second fibers 242. The first fibers 241 extend in a first direction DR1 in which the connecting body 210 extends as shown in FIG. Figure 19b. The second fibers 242 extend in a second direction DR2 orthogonal to the first direction DR1. However, since a through-hole is formed in the pair of flat plates 211, the first fibers 241 of the connecting body 210 in the gray region of Fig. 19b are cut through the through-hole 212 and therefore can not take over. tensile force applied to the pad 220 (force applied towards the white arrow in Figure 19b). Consequently, the tensile force applied on the pad 220 is taken up mainly by the second fibers 242, which are farther away in the end portion of the connecting body 210 than the through hole 212.
To overcome such a problem, the conventional aircraft reaction links have been configured to increase the number of layers of the second fibers 242 further away from the end portion of the connecting body 210 than the through hole 212 or to increasing the area of a portion of the end portion farther than the through hole 212, so as to increase the bearing force of the pad 220. However, in conventional aircraft reaction links, the end portion the bonding body 210 is larger, resulting in a greater weight for the reaction bond. Such a defect is not specific to aircraft reaction links but is common for supporting force transmitting element structures in which a force transmitting member such as a force transmitting pad is supported by a fiber reinforced plastic.
SUMMARY OF THE INVENTION
An object of the present invention is to provide a support structure for a force transmission element, an aircraft reaction link, a flight control surface control unit, a mounting method of a force transmitting member, and a method of manufacturing an aircraft reaction link that provides for weight reduction while providing the necessary strength.
[0009] (1) In one embodiment of the force transmission member support structure according to the present invention, a structural member supports a force transmitting member, the structural member being made of a reinforced plastic of fibers having continuous fibers, the force transmitting member being configured to transmit a force, wherein the continuous fibers comprised in the fiber reinforced plastic support the force transmitting member to regain strength.
If the fibers surrounding the force transmission element are cut, in particular those which extend in a direction such that they are subjected to a tensile force which pulls on the structural element, the fibers surrounding the the force transmission element can not take up the tensile force applied to the force transmission element. In the force transmission member support structure according to the present invention, the fibers which extend in a direction such that they are subjected to a tensile force which pulls on the structural member are continuous. As a result, more fibers can take up the tensile force applied to the force transmission element. Therefore, since it is not necessary to excessively reinforce a portion of the structural member that supports the force transmitting member, it is possible to provide the necessary strength and reduce the weight of the portion. of the structural element that supports the force transmission element. The support of an element relates to the retention of the element so as to produce a force in a direction opposite to the applied force. The direction of the applied force corresponds to the direction of the vector resulting from the combination of the direction vectors of the fibers.
(2) In one embodiment of the force transmission member support structure, the fibers that support the force transmitting member are wrapped around the force transmitting member. With this arrangement, when a pulling force pulling on the structural member is applied to the force transmitting member, the fibers extending from the structural member and wrap around the element transmission of force can resume the tensile force applied to the force transmission element. The fibers that support the force transmitting member take up a force that pulls the fibers in their extension direction. Since the fibers have maximum tensile strength in their direction of extension and further the fibers are wrapped around the force transmitting member, the force can be resumed more effectively. As a result, the force transmitting member can be stably supported with a lower number of fibers, which more effectively provides the necessary strength and reduces the weight of the force transmission member support structure.
(3) In one embodiment of the force transmission element support structure, the fibers included in the structural element comprise first fibers which extend in a first direction and second fibers which extend in a second direction different from the first direction, and the first fibers and the second fibers are woven together.
With this arrangement, the friction force acting between the first fibers and the second fibers when a force is applied in the direction of extension of the fibers provides a bonding force between the fibers greater than that of an arrangement where the first fibers and the second fibers are not woven together, i.e. fibers of the first fibers and the second fibers are formed on the other fibers from the first fibers and the second fibers. Therefore, the strength of the structural element can be increased.
(4) In one embodiment of the force transmission element support structure, fiber angles formed by the first direction and the second direction with a longitudinal direction of the structural member in a portion of the structural member close to the force transmitting member is less than the corners in a portion of the structural member remote from the force transmitting member.
With this arrangement, angles of the fibers in a portion of the structural element close to the force transmission element are lower (the fibers extend in directions closer to the longitudinal direction of the element). structural). Therefore, when the fibers that support the force transmitting member are wrapped around the force transmitting member, the first fibers and the second fibers are prevented from being bent or twisted. As a result, the deformation of the structural element due to the tensile force can be reduced and the force transmission element can be better supported.
(5) In one embodiment of the force transmission member support structure, the fiber angles in the structural member decrease non-discretely toward the force transmitting member. With this arrangement, the manufacture of the structural member is facilitated with respect to the case where the angles of the fibers in the structural member vary discretely towards the force transmitting member. Compared in particular to the case where the angles of the fibers are greatly reduced in a portion close to the force transmission element, it is avoided that the first fibers 61 and the second fibers 62 are strongly folded or bent.
(6) In one embodiment of the force transmission member support structure, the first fibers and the second fibers are wound around the force transmitting member, and a winding direction of the first fibers around the force transmitting member is opposed to a winding direction of the second fibers around the force transmitting member.
With this arrangement, the direction of the first fiber is opposite to the direction of the second fiber, and these fibers are not excessively bent or twisted. The tensile force can be supported in a well-balanced manner in the longitudinal direction of the structural element.
(7) In one embodiment of the force transmission element support structure, the first direction and the second direction are different from a longitudinal direction of the structural member, and the fibers included in the structural member further comprises third fibers extending longitudinally and wound around the force transmitting member.
With this arrangement, the third fibers extend in the longitudinal direction, and it is therefore avoided that at least the fibers of a portion of the third fibers are excessively folded or twisted when they are wrapped around the element. of force transmission. Thus, when a pulling force pulls the force transmitting member away from the structural member, the tensile force can be effectively resumed in the direction of extension of the third fibers. As a result, the third fibers can better support the force transmission element.
(8) In one embodiment of the force transmission member support structure, the third fibers comprise fibers wrapped around the force transmitting member in a first winding direction and fibers. wrapped around the force transmitting element in a second winding direction opposite to the first winding direction.
With this arrangement, the fibers of the portion of the third fibers where the third fibers begin to be wound around the force transmission element are not excessively bent or twisted compared to the case where the third fibers are wrapped around the force transmitting element in one direction. The tensile force can be supported in a well-balanced manner in the longitudinal direction of the structural element.
(9) In one embodiment of the force transmission element support structure, only the third fibers are wound around the force transmission element. With this arrangement, only the third fibers are wound around the force transmission element, while the first fibers and the second fibers are not. As a result, the winding work is reduced and the productivity of the support structure for the force transmission element can be increased.
(10) In one embodiment of the force transmission member support structure, the fibers wound around the force transmitting member form stacked layers. With this arrangement where the fibers wrapped around the force transmitting member form stacked layers, it is possible to avoid increasing the area of the portion of the force transmitting member on which the fibers are wound. As a result, it is possible to provide the necessary strength and reduce the weight of the force transmitting member.
(11) In one embodiment of the force transmission member support structure, all fibers included in the structural member are wrapped around the force transmitting member. Thanks to this arrangement, all the fibers included in the structural element support the force transmission element, and a tensile force produced between the structural element and the force transmission element is therefore taken up by all the fibers. As a result, the force transmitting member can be better supported with fewer fibers, and it is possible to provide the necessary strength and more effectively reduce the weight of the support structure for the transmission element. strength.
(12) In one embodiment of the force transmission member support structure, only a portion of the fibers included in the structural member are wrapped around the force transmitting member. With this arrangement where the fibers of only a portion of the fibers included in the structural member are wrapped around the force transmitting member, the winding work is reduced relative to the case where all fibers included in structural element are wrapped around the force transmission element. Therefore, the productivity of the support structure for the force transmission element can be increased while maintaining the balance of strength and weight of the support structure for the force transmission element.
[0027] (13) In one embodiment of the force transmission element support structure, the force transmission element comprises a projection which can be inserted into an opening portion formed in a portion of distal end of the structural element, and the projection is conically reduced towards one of its ends.
With this arrangement, when a compression force in a compression direction of the opening portion of the structural member is applied to the force transmitting member, the conical portions of the projection come into contact with the opening portion of the structural member such that the structural member can support the force transmitting member.
(14) In one embodiment of the force transmission member support structure, a reinforcing member for reinforcing the attachment between the structural member and the force transmitting member is provided on a portion. of the opening portion that overlaps the projection.
With this arrangement, the reinforcing element fixes the structural element and the force transmission element, and therefore prevents the force transmission element from moving relative to the structural element. Further, when compressive force in a compression direction of the force transmitting member to the structural member is applied to the force transmitting member, the structural member can better support the transmission member. strength.
(15) In one embodiment of the force transmission member support structure, the reinforcing member is made of a continuous fiber included in the fiber reinforced plastic and wound on an outer side of the fibers that support the force transmission element. The outer side of the fibers refers to the near side of the outer surface.
With this arrangement, when a compressive force in a compression direction of the opening portion of the structural member is applied to the force transmitting member, the reinforcing member can prevent enlargement. of the opening portion of the structural element. As a result, the structural member and the force transmitting member can be supported firmly without increasing the size of the support structure for the force transmitting member.
(16) In one embodiment of the force transmission member support structure, the fiber of the reinforcing member is wound regularly. With this arrangement, excessive expansion of the portion provided with the reinforcing member from the structural member can be avoided. It is thus possible to avoid an increase in the size of the support structure for the force transmission element.
[0034] (17) In one embodiment of the force transmission element support structure, the reinforcing element fixes end portions of the fibers that support the force transmission element. With this arrangement, it can be avoided that fibers supporting the force transmitting member with the reinforcing member are removed from the structural member. In other words, although fiber-reinforced plastics generally tend to be removed, the fibers can be effectively prevented from being removed by reinforcing the end portions of the fibers.
(18) In one embodiment of the force transmission element support structure, the opening portion formed in a distal end portion of the structural member has a conical shape with a surface of corresponding larger opening to a distal end of the opening portion.
With this arrangement, when a compression force in a compression direction of the opening portion of the structural element is applied to the force transmission element, the conical portions of the opening portion of the structural member comes into contact with the projection of the force transmitting member such that the structural member can support the force transmitting member. In addition, when the projection is provided with conical portions, the conical portions of the projection are in surface contact with the conical portions of the opening portion of the structural member. Thus, when a compressive force is applied to the force transmitting member, the structural member can better support the force transmitting member.
(19) In one embodiment of the force transmission element support structure, the force transmission element has an outer peripheral surface around which the fibers are wound, and the two axial ends of the outer peripheral surface of the force transmitting member is provided with a rib extending radially from the outer peripheral surface of the force transmitting member.
With this arrangement, when the fibers that support the force transmission element are wound around the force transmission element, it prevents the fibers from turning away from the force transmission element. The winding of the fibers around the force transmission element can thus be facilitated.
(20) In one embodiment of the aircraft reaction link according to the present invention, the aircraft reaction link is mounted directly or indirectly on a flight control surface of an aircraft and connected to an actuator which controls the flight control surface, and the aircraft reaction link comprises: a bushing which serves as a force transmitting member slidably supporting the actuator; and a linkage body which comprises a structural member supporting the bushing, wherein the force transmission member support structure described in (1) above is used by the linkage body to support the bushing.
This arrangement produces the same effect as the aforementioned support structure for the force transmission element, and it is therefore possible to provide the necessary strength and reduce the weight of the aircraft reaction link.
[0041] (21) In one embodiment of the flight control surface control unit according to the present invention, the flight control surface control unit comprises the aircraft reaction link described above and the actuator. This arrangement produces the same effect as the above aircraft reaction link, and it is therefore possible to provide the necessary strength and reduce the weight of the flight control surface control unit.
(22) In one embodiment of the method of mounting a force transmitting member according to the present invention, the method of mounting a force transmitting member on a structural member, the transmission member of a force being configured to transmit a force, the structural member being made of a fiber reinforced plastic and supporting the force transmitting member, the method comprises: a winding step of winding fibers around a core to form the structural element; a temporary fixing step of continuously winding the fibers around the force transmitting member; a resin impregnation step of impregnating the fibers with a resin; and a final setting step by curing the resin impregnating the fibers to secure the structural member and the force transmitting member.
With this arrangement, the mounting of the force transmission element on the structural element can be facilitated. As a result, a support structure for the force transmission element having the necessary strength and a reduced weight can be produced at low cost.
[0044] (23) In one embodiment of the method of manufacturing an aircraft reaction link according to the present invention, the manufacturing method of manufacturing an aircraft reaction link, the reaction link of aircraft being mounted directly or indirectly on an aircraft flight control surface and connected to an actuator controlling the flight control surface, the aircraft reaction link comprising a linkage body made of a plastic reinforced with fiber and a pad attached to the bonding body, the method comprises: a winding step of winding fibers around a core to form a portion of the bonding body; a temporary pad fixing step of continuously winding the fibers around the pad; a resin impregnation step of impregnating the fibers with a resin; and a final pad fixing step by curing the resin impregnating the fibers to secure the pad to the bonding body.
With this arrangement, the mounting of the pad on the connecting body can be facilitated. As a result, an aircraft reaction link providing the necessary strength and reduced weight can be produced at reduced cost.
A reduction in weight can be obtained while providing the necessary resistance through the support structure for a force transmission element, the aircraft reaction link, the control surface control unit of flight, the method of mounting a force transmission element, and the method of manufacturing an aircraft reaction link according to the present invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0047] Figure 1 is a perspective view of a wing portion on which is installed a flight control surface control unit according to one embodiment.
Figure 2 is a side view of Figure 1.
Figure 3 is a perspective view of an aircraft reaction link shown in Figure 1.
Figure 4 is an exploded perspective view of an opening portion in a connecting body and a pad of the aircraft reaction link.
Figure 5a is a side view of a portion of the connecting body and the pad.
Figure 5b is a plan view of Figure 5a.
Figure 6 is a perspective view of a portion of the connecting body and the pad.
Figure 7 is a side view of the connecting body of Figure 6 omitting a reinforcing member.
Figure 8a is a side view of the pad.
Figure 8b is a side view of the pad.
Figure 8c is a plan view of a portion of the connecting body and the pad.
Figure 9 is a schematic sectional view of a portion of the connecting body and the pad.
Fig. 10 is a flowchart describing a method of manufacturing an aircraft reaction link.
Figure 11a is a schematic bottom view of a portion of the connecting body.
Figure 11b is a schematic side view of a portion of the connecting body.
Figure 11c is a schematic side view of a portion of the connecting body.
Fig. 12 is a schematic side view of a portion of the link body and pad in a variation of the aircraft reaction link.
Fig. 13 is a side view of a portion of the link body and pad in a variation of the aircraft reaction link.
Fig. 14 is a side view of a portion of the link body and pad in a variation of the aircraft reaction link.
Fig. 15 is a side view of a portion of the link body and pad in a variation of the aircraft reaction link.
Fig. 16 is a side view of a portion of the link body and pad in a variation of the aircraft reaction link.
Fig. 17 is a side view of a portion of the link body and pad in a variation of the aircraft reaction link.
Fig. 18 is a plan view of a portion of a structural member and a force transmitting member in a variation of the support structure for the force transmitting member.
Figure 19a is a perspective view of a conventional aircraft reaction link.
Fig. 19b is a plan view of a portion of the connecting body of the conventional aircraft reaction link.
DESCRIPTION OF DETAILS OF EMBODIMENTS
A flight control surface control unit according to one embodiment will now be described with reference to the drawings. For convenience, Figure 1 omits a portion of the connection structure between the flight control surface control unit and the flight control surface. As shown in FIG. 1, the flight control surface control unit 1 may be provided on an aircraft so as to control the flight control surface 101 of a wing 100 of the aircraft. The flight control surface 101 may be constituted by a fin, a rudder, a elevator or other aircraft control surfaces. The flight control surface controlled by the flight control surface control unit 1 may also be constituted by a flap or a spoiler.
The flight control surface control unit 1 may include an actuator 10 for controlling the flight control surface 101 and a reaction link 20 for resisting a reaction force of the flight control surface 101. produced when the actuator 10 controls the flight control surface 101. The reaction link 20 may be an example of an aircraft reaction link.
As shown in FIG. 2, the actuator 10 can be connected to a support 102 provided on the wing 100 and to a connection axis 103 of the flight control surface 101. The actuator 10 can rotate the flight control surface 101 about a pivot axis 104 which supports the flight control surface 101 so that it can rotate relative to the wing 100. The actuator 10 can be a linear actuator hydraulically configured such that a hydraulic oil is fed to a jack 11 and drained thereof so as to go and varnish a rod 12 in its axial direction. The actuator 10 may also be an electromechanical linear actuator comprising an electric motor and a ball screw mechanism. One end of the rod 12 may be rotatably connected to the connecting pin 103. That is, the actuator 10 may be directly connected to the flight control surface 101. It is also possible that the end of the rod 12 is connected to a horn arm (not shown) connected to the flight control surface 101. That is, the actuator 10 may also be indirectly connected to the control surface flight 101.
As shown in Figure 1, the actuator 10 may include a connecting portion 13 which connects to the reaction connection 20 and the support 102. The connection portion 13 may be provided on one side of the cylinder 11 opposite to the side from which the rod 12 may be projected. The connecting portion 13 may include an axis 13A which extends orthogonally to the axis of the rod 12.
The reaction link 20 may be rotatably connected to the pivot axis 104 and to the axis 13A of the connection portion 13. When the actuator 10 controls the flight control surface 101, the link Reaction 20 can prevent the force applied to the mobile flight control surface 101 from directly impacting the stationary wing 100.
The flight control surface control unit 1 thus configured can operate as follows. A hydraulic supply unit (not shown) for supplying a hydraulic oil to the actuator 10 can operate on the basis of instructions from a flight controller (not shown), so that the hydraulic oil can be supplied with fuel. cylinder 11 of the actuator 10 and drained thereof. As shown in FIG. 2, the rod 12 can thus be extended or retracted by the jack 11, and the flight control surface 101 connected to the rod 12 via the connecting pin 103 can therefore rotate about the axis When the flight control surface 101 rotates, the reaction link 20 can pivot about the pivot 104. The reaction link 20, which can support the axis 13A rotatably, can also take up a reaction force. from the flight control surface 101 when the actuator 10 drives the flight control surface 101.
The constitution of the reaction link 20 will now be described with reference to FIGS. 2 to 9. As shown in FIGS. 2 and 3, the reaction link 20 may include a connecting body 30 for a pivotal connection between the pivot axis 104 and the axis 13A of the actuator 10, a head 40 positioned on an end portion of the connecting body 30 on the side of the pivot axis 104 and connected to the pivot axis 104, and a pair of pads 50 attached to the connecting body 30 and slidably supporting the axis 13A. The pair of pads 50 can thus support the actuator 10 in a sliding manner. The bearings 50 may correspond to force transmission elements to take up a force of the actuator 10.
The connecting body 30 may substantially have a U-shape in a plan view. The connecting body 30 may include a pair of legs 31A, 31B which extend straight along the longitudinal axis C indicating the longitudinal direction of the connecting body 30 and spaced parallel to each other. Each of the legs 31A, 31B may have a substantially rectangular section. The legs 31A, 31B may be interconnected to a corresponding end side via a connecting portion 32. The connecting portion 32 may include a straight portion 33 and curved portions 34 provided at both ends of the straight portion 33 The straight portion 33 may extend in a direction orthogonal to the longitudinal axis C. The pair of legs 31A, 31B and the connecting portion 32 may be integrated. The connecting body 30 may be straight or J-shaped instead of substantially U-shaped. If the connecting body 30 is straight or J-shaped, one or two bearings 50 may be connected to the connecting body 30. If the connecting body 30 is straight or J-shaped and is connected to the two bearings 50, these two bearings 50 can be connected to both longitudinal ends of the connecting body 30.
The connecting body 30 may be made of a fiber reinforced plastic (FRP or Fiber Reinforced Plastic). More preferably, the connecting body 30 may be made of a carbon fiber reinforced plastic (CFRP) or Carbon Fiber Reinforced Plastic. Usable carbon fibers may include polyacrylonitrile-based carbon fibers and pitch-based carbon fibers. It is also possible that the connecting body 30 is formed for example of glass fiber reinforced plastic (GFRP), a glass mat reinforced thermoplastic (GMT), a boron fiber reinforced plastic (BFRP) , Aramid fiber reinforced plastic (AFRP, KFRP), Dyneema fiber reinforced plastic (DFRP), Xyron-reinforced plastic (ZFRP), etc. It is also possible that the connecting body 30 comprises a fiber-reinforced plastic only in the pair of legs 31A, 31B and that the connecting portion 32 is formed of a material other than fiber-reinforced plastics, such as a metallic material. It is also possible that the connecting body 30 comprises a fiber-reinforced plastic only in a portion of the end portions of the pair of legs 31A, 31B. It is also possible to use a fiber-reinforced plastic comprising a plurality of fiber types combined or using a plurality of types of combined fiber reinforced plastics.
The head 40 may be connected to the middle of the straight portion 33 of the connecting portion 32. The head 40 may consist of a first head body 41 and a second head body 42. The first body head 41 and the second substantially U-shaped head body 42 may be attached together to form a mounting hole 43 into which the connection portion 32 is pinched. The first head body 41 may be extending from the connecting portion 32 to the ends of the pair of legs 31A, 31B. The second head body 42 may extend from the connecting portion 32 in the opposite direction to the ends of the pair of legs 31A, 31 B. The second head body 42 may have a bearing hole 42A extending therethrough in the extension direction of the connecting portion 32. A bearing 44 may be mounted in the bearing hole 42A. An example of a bearing 44 is a ball bearing. The pivot 104 (see FIG. 2) can be mounted in the bearing 44. The head 40 can thus be rotatably connected to the pivot 104. An interval is formed between the mounting hole 43 and the connecting portion 32. A shim 45 can be fretted in the meantime.
A fiber 46 may be wound on the outer peripheral surface of the first head body 41 and the second head body 42. The fiber 46 may consist of either a fiber or a plurality of fibers. This fiber can attach between them the first head body 41 and the second head body 42.
The pads 50 may be connected to the end portion of the leg 31A and the end portion of the leg 31 B. The pads 50 may thus be supported by the connecting body 30. The structure in which the connecting body 30 supports the bearings 50 may hereinafter be referred to as the bushing support structure BS. The connecting body 30 may correspond to a structural element supporting the bearings 50. If the connecting body 30 comprises a fiber-reinforced plastic only in the legs 31A, 31B, the legs 31A, 31B may correspond to the structural elements. If the connecting body 30 comprises a fiber-reinforced plastic only in a portion of the end portions of the legs 31A, 31B, the portion of the end portions of the legs 31A, 31B formed of fiber-reinforced plastic may correspond to the structural elements. In addition, the bushing support structure BS may correspond to a support structure for the force transmission elements.
FIG. 4 represents an exploded view of the end portion of the leg 31A and the pad 50 connected to the leg 31A, and FIGS. 5a and 5b show that the pad 50 is connected to the end portion. of the leg 31A. Part of the bushing support structure BS is omitted in Figures 4, 5a and 5b. The end of the leg portion 31B and the pad 50 connected to the leg 31B may also be configured as shown in Figures 4, 5a and 5b.
As shown in FIG. 4, the bushing 50 may include a bushing body 51 slidably supporting the axis 13A of the actuator 10 (see FIG. 2 for both) and an inserted insertion projection 52. in an opening portion 35 formed in the end portion of the leg 31A. The insertion projection 52 may correspond to a projection.
The bearing body 51 may comprise a through hole 51A which passes through in the axial direction of the axis 13A (hereinafter referred to as "axial direction J1"). The axis 13A can be inserted through the through hole 51A. At the ends of the outer periphery of the bushing body 51 opposed to each other in the axial direction J1, arc-shaped ribs 51B can be formed integrally with the body of the 51. The ribs 51B may extend radially outwardly from the outer peripheral surface 51C of the pad body 51. Each of the ribs 51B may also consist of a plurality of circumferentially short and shaped projections. the ribs 51B may also be formed separately from the pad body 51. It is also possible that the ribs 51B are omitted.
The insertion projection 52 may extend towards the connecting body 30 (leg 31A). As shown in Fig. 4, the insertion projection 52 may have a conical rectangular shape consisting of a pair of planar surfaces 52X and a pair of side surfaces 52Y. More specifically, the pair of planar surfaces 52X may be similarly inclined to converge toward the end of the insertion projection 52 so as to form a conical portion 52A. The shape of the conical portion 52A can thus be symmetrical. The pair of side surfaces 52Y may be similarly inclined to converge towards the end of the insertion projection 52 so as to form a conical portion 52B. The shape of the conical portion 52B can thus be symmetrical. The conical portions 52A, 52B symmetrical shapes can resume a properly balanced effort. At the end of the insertion projection 52, a screw hole 52C may extend in a longitudinal direction CD. One or the other of the conical portions 52A and 52B may be omitted. In addition, the planar surfaces 52X need not be symmetrically arranged, and likewise the side surfaces 52Y need not be symmetrically arranged. It may be required that each pair of flat surfaces 52X and 52Y side surfaces be conical only.
As shown in FIG. 4, among the inner surfaces of the opening portion 35 of the leg 31A, a pair of inner surfaces 35X facing the flat surfaces 52X may be similarly inclined to diverge toward the end. of the opening portion 35 so as to constitute a conical portion 35A. The shape of the conical portion 35A can thus be symmetrical. Of the inner surfaces of the opening portion 35, a pair of inner surfaces 35Y facing the side surfaces 52Y may be similarly inclined to diverge toward the end of the opening portion 35 so as to form a conical portion 35B. The shape of the conical portion 52B can thus be symmetrical. Therefore, the opening surface of the opening portion 35 may be larger towards the end of the leg 31A (opening portion 35). One or the other of the conical portions 35A and 35B may be omitted. In addition, the inner surfaces 35X need not necessarily be arranged symmetrically, and likewise the inner surfaces 35Y need not be arranged symmetrically. It may be required that each pair of 35X inner surfaces and 35Y inner surfaces be conical only.
As shown in FIG. 5a, the pair of flat surfaces 52X may be parallel to the pair of inner surfaces 35X. Thus, when the insertion projection 52 is inserted into the opening portion 35, the pair of inner surfaces 35X and the pair of planar surfaces 52X may be in surface contact with each other. As shown in Fig. 5b, the pair of side surfaces 52Y may be parallel to the pair of inner surfaces 35Y. Thus, when the insertion projection 52 is inserted into the opening portion 35, the pair of inner surfaces 35Y and the pair of side surfaces 52Y may be in surface contact with each other.
With such an arrangement, the contact area between the planar surfaces 52X and the inner surfaces 35X and the contact surface between the side surfaces 52Y and the inner surfaces 35Y may be sufficiently large to reduce the stress concentrations, which eliminates the need for excessively large thickness. Therefore, a weight reduction can be achieved while providing the necessary strength for the bushing support structure BS.
The leg 31A and the bearing support structure BS will now be described in detail with reference to Figures 4 to 9. Since the leg 31B has the same configuration, the corresponding description will be omitted. Figures 6 to 9 show a portion of the leg 31 A.
As shown in Figure 6, the connecting body 30 may include a core 36 having a rectangular section, a plurality of fibers 60 wound around the core 36, and a reinforcing member 70 covering a portion of the leg 31A. The core 36 may for example be formed of a thermal foam plastic insulation, and more preferably an extruded polystyrene foam thermal insulation. The shape of the core 36 may be similar to that of the connecting body 30. As shown in FIGS. 4 and 5, the core 36 may comprise a recess 36A which extends towards the longitudinal axis C of the leg 31A (FIG. see Figure 3) (hereinafter referred to as "CD longitudinal direction"). The end wall 36B of the recess 36A may comprise a through hole 36C which passes therethrough in the longitudinal direction CD. A bolt B can be inserted into the through hole 36C in the end wall 36B of the core 36. The bolt B can be screwed into the screw hole 52C in the insertion projection 52 of the bushing 50. The core 36 and the bushing 50 can be connected. This connection can also be achieved by other methods, such as adhesion, as long as core 36 and pad 50 remain connected during manufacture. The core 36 may also have any non-rectangular sectional shape, for example circular. The core 36 may furthermore be made of any material other than a plastic foam thermal insulator, such as a resinous material or a metallic material.
As shown in FIG. 6, the fibers 60 may comprise first fibers 61, second fibers 62 and third fibers 63. The first fibers 61, the second fibers 62 and the third fibers 63 may each consist of the same material and constituted by a bundle of fiber bundles (filaments) comprising a large number of monofilaments. In addition, it is also possible for the first fibers 61, the second fibers 62 and the third fibers 63 to be each of the monofilament, filament, spun yarn spinning yarn, braid or knitted rope type comprising tows. It is further possible that the first fibers 61, the second fibers 62 and the third fibers 63 each consist of a different material. The reinforcing member 70 can reinforce the attachment between the connecting body 30 and the pad 50.
Figure 7 omits for convenience the reinforcing element 70 of the connecting body 30 shown in Figure 6. As shown in Figure 7, the first fibers 61 may extend in a first direction D1 different from the direction longitudinal CD. The second fibers 62 may extend in a second direction D2 different from the longitudinal direction CD and the first direction D1. The third fibers 63 may extend in longitudinal direction CD. The first fibers 61, the second fibers 62 and the third fibers 63 may be woven together and wound around the core 36 (see FIG. 6). The first direction D1 can form an acute angle of 45 ° with the longitudinal direction CD, and the second direction D2 can form an acute angle of 45 ° with the longitudinal direction CD towards the direction opposite to the first direction D1. The first fibers 61 and the second fibers 62 may therefore be orthogonal to each other. The leg 31A may include a plurality of layers each consisting of fibers 61-63 woven together (two layers in this embodiment). The acute angle formed by the first direction D1 with the longitudinal direction CD may be different from 45 °, and be for example 30 °. The acute angle formed by the second direction D2 with the longitudinal direction CD may be different from 45 °, and be for example 30 °. It is therefore also possible that the first direction D1 and the second direction D2 are not orthogonal to each other. It is also possible that the acute angle formed by the first direction D1 with the longitudinal direction CD and the acute angle formed by the second direction D2 with the longitudinal direction CD are not necessarily the same. It is possible, for example, that one be 15 ° and the other 30 °. Since these acute angles are smaller, the tensile strength in the longitudinal direction CD is greater, but the resistance force to a fiber expansion force in the direction orthogonal to the longitudinal direction CD is lower . The acute angles must therefore be determined appropriately according to real efforts. It is also possible that the fibers 61 to 63 are not woven together but form respective layers stacked for example in the order of the first fibers 61, the second fibers 62 and the third fibers 63. In this case, the first fibers 61 may be wound first around the core 36, then the second fibers 62 may be wound around the core 36 so as to be stacked on the first fibers 61, and then the third fibers 63 may be wound around the core 36 so as to stacked on the second fibers 62. The stacking order of the first fibers 61, the second fibers 62 and the third fibers 63 may be changed as needed.
The bushing support structure BS may include a support portion 37 in which the fibers 61 to 63 extending from the opening portion 35 of the leg 31A may encircle the bushing 50 to thereby support the bushing 50. The fibers 61 to 63 included in the support portion 37 may be continuous. The fibers 61 to 63 included in the support portion 37 may be wrapped around the pad 50 as follows. In this embodiment, the fibers 61 to 63 extending from the opening portion 35 of the leg 31A may be wound around the outer peripheral surface 51C of the pad body 51, such as with an arrangement around the cushion 50.
Among the first fibers 61 included in the support portion 37, those extending from the opening portion 35 in one of the side surfaces 31Y of the leg 31A may extend to a lateral surface 51X of the bearing body 51 on the same side as one of the flat surfaces 31X of the leg 31A. These first fibers 61 on said one side surface 51X may extend around the outer peripheral surface 51C of the pad body 51 and further extend via the other side surface 51Y of the pad body 51 toward the proximal side of said pad body 51C. other surface of the flat surfaces 31X of the leg 31A.
Among the second fibers 62 included in the support portion 37, those extending from the opening portion 35 in said one of the side surfaces 31Y of the leg 31A may extend to the other side surface 51Y The second fiber 62 on the other side surface 51Y may extend around the outer peripheral surface 51C of the pad body 51 and further extend via a lateral surface 51X to the proximal side of the pad body 51. said other surface among the flat surfaces 31X of the leg 31A. That is, the direction in which the first fibers 61 extending from said one of the side surfaces 31Y of the leg 31A are wound around the outer peripheral surface 51C of the pad body 51 can be opposed to the wherein the second fibers 62 extending from said one of the side surfaces 31Y of the leg 31A are wrapped around the outer peripheral surface 51C of the pad body 51.
Although this is not shown in Figure 7, among the first fibers 61 included in the support portion 37, those extending from the opening portion 35 in said other of said side surfaces 31Y of the leg 31A (in the bottom of the drawing) may extend to the other lateral surface 51Y of the bearing body 51. These first fibers 61 on the other lateral surface 51Y may extend around the outer peripheral surface 51C of the body of the pad 51 and further extending via said one side surface 51X of the pad body 51 to the proximal side of said one of the flat surfaces 31X of the leg 31A. Of the second fibers 62 included in the support portion 37, those extending from the opening portion 35 into said other of the side surfaces 31Y of the leg 31A may extend toward said one side surface 51X of the pad body 51. These second fibers 62 on said one side surface 51X may extend around the outer peripheral surface 51C of the pad body 51 and further extend via the other side surface 51Y to the proximal side of said one of the surfaces. 31X planes of the 31A leg. The direction in which the first fibers 61 extending from said other one of the side surfaces 31Y of the leg 31A are wound around the pad body 51 can thus be opposed to the direction in which the second fibers 62 extending from said other side surfaces 31Y of the leg 31A are wound around the bearing body 51. Therefore, in comparison with the case where these fibers are wound in the same direction, it is possible to prevent the fibers being excessively folded, and the fibers can be arranged in good equilibrium orthogonal to the longitudinal direction CD. The entire BS bearing support structure can thus withstand the traction force in good balance. In addition, the amount of fiber that extends to the side surface 51Y may be different from the amount of fiber that extends to the side surface 51X, depending on the stress conditions.
The direction in which the first fibers 61 which extend from said one of the side surfaces 31Y of the leg 31A are wound around the bearing body 51 can thus be opposite to the direction in which the second fibers 61 which extend from said other side surfaces 31Y of the leg 31A are wound around the pad body 51. Similarly, the direction in which the second fibers 62 extending from said one of the side surfaces 31Y of the leg 31A are wrapped around of the bearing body 51 may be opposed to the direction in which the second fibers 62 extending from said other side surfaces 31Y of the leg 31A are wound around the bearing body 51. Therefore, in comparison with the case where these fibers are wound in the same direction, it can be avoided that the fibers are excessively folded, and the fibers can be arranged in good equ it is orthogonal to the longitudinal direction CD. The entire BS bearing support structure can thus withstand the traction force in good balance. In addition, the amount of fiber that extends to the side surface 51Y may be different from the amount of fiber that extends to the side surface 51X, depending on the stress conditions.
Among the third fibers 63 included in the support portion 37, those included in the two side surfaces 31Y of the leg 31A in the opening portion 35 may diverge in two directions to the lateral surfaces 51X, 51Y of the body pad 51, extend around the outer peripheral surface 51C of the bearing body 51, and extend further to the proximal side of the two flat surfaces 31X of the leg 31 A. Of the third fibers 63 included in the portion of 37, those included in said one of the lateral surfaces 31X of the opening portion 35 may extend in the longitudinal direction CD, extend around the outer peripheral surface 51C of the bearing body 51, and extend more away to the proximal side of said other surface of the flat surfaces 31X. On the other hand, among the third fibers 63 included in the support portion 37, those included in said other surface of the lateral surfaces 31X of the opening portion 35 can extend in the longitudinal direction CD, extend around the outer peripheral surface 51C of the pad body 51, and extend further to the proximal side of said one of the flat surfaces 31X. The third fibers 63 may thus include fibers wrapped around the outer peripheral surface 51C of the pad body 51 in a first winding direction (as indicated by the arrow Y1 in Fig. 8a) and fibers wound in a second winding direction (as indicated by the arrow Y2 in FIG. 8b) opposite to the first winding direction. Therefore, in comparison with the case where these fibers are wound in the same direction, it can be avoided that the fibers are excessively bent, and the fibers can be arranged in good equilibrium orthogonal to the longitudinal direction CD. The entire BS bearing support structure can thus withstand the traction force in good balance. In addition, the amount of fiber wound in the first winding direction may be different from the amount of fiber wound in the second direction, depending on the stress conditions. The fibers 61 to 63 included in the support portion 37 may extend around the pad 50 and further to the proximal side of the leg 31A. Such end portions of these fibers may also be referred to as "terminal end portions".
As shown in FIG. 8a, the fibers 61 to 63 included in the support portion 37 can be wound around the outer peripheral surface 51C of the bearing body 51 in the direction of the arrow Y1, and then, as shown in FIG. 8b, these fibers can be wound around the outer peripheral surface of the bearing body 51 in the direction of the arrow Y2, opposite to the direction of the arrow Y1. The fibers 61 to 63 included in the support portion 37 can thus be wound around the outer peripheral surface 51C of the pad body 51 so as to form stacked layers.
As shown in FIG. 8c, the end-end portions of the fibers 61 to 63 included in the support portion 37 and wound around the bushing 50 can be positioned on the outer side of the fibers 61 to 63 constituting the portion d. opening. FIG. 8c shows that only the end-end portions of the third fibers 63 included in the support portion 37 can extend in the longitudinal direction CD, but the end-end portions of the first fibers 61 and the portions Terminal ends of the second fibers 62 included in the support portion 37 may also extend longitudinally CD in the same manner.
As shown in FIG. 6, the reinforcing element 70 may be provided from the outside on the end-end portions of the fibers 61 to 63. The reinforcement element 70 may thus strengthen the attachment of the pad 50 by the support portion 37. The reinforcing member 70 may include a fiber 71 identical to the fibers 60. The fiber 71 may be wound with a plurality of turns around the leg 31A in a direction orthogonal to the longitudinal direction CD. The fiber 71 can be wound regularly around the leg 31A. The fiber 71 may also include different substances or have a configuration different from that of the fibers 60.
As shown in FIGS. 6 and 9, the fiber 71 may be wound around the leg 31A on the region extending in the longitudinal direction CD of the portion of the connecting body 30 in which the opening portion 35 overlaps the insertion projection 52 of the pad 50 to the end of the end end portions of the fibers 61 to 63. The fiber 71 may be wrapped around the leg 31A to form an outermost layer on the fibers 61 to 63 included in the support portion 37. The reinforcing member 70 can thus secure the end portion of the support portion 37. This arrangement can reduce the possibility of removing the fibers 61 to 63 at the end of their portions of terminal end, which provides the necessary resistance and reduces weight.
A process for manufacturing the reaction link 20 described above will now be described with reference to FIG. 10. In particular, a method of fixing the bushing 50 on the connecting body 30 will be described in detail. In the following detailed description referring to FIG. 10, the elements of the reaction link 20 accompanied by a reference number refer to the elements of the reaction link shown in FIGS. 3 to 9.
This manufacturing method may include a link manufacturing step (step S10) and a head mounting step (step S20). The link manufacturing step may in turn include a resin impregnation step (step S11), a winding step (step S12), a temporary pad fixing step (step S13) and a fixing step final pad (step S14). In addition, the resin impregnation step, the winding step, the temporary pad fixing step and the final pad fixing step can respectively correspond to a resin impregnation step, a step winding, a temporary fixing step and a final fixing step in a method of fixing a force transmission element.
First, in the resin impregnation step, an impregnating fluid reservoir containing a thermosetting resin (eg, unsaturated polyester) as an impregnating fluid can be prepared. Then, the fibers 61 to 63 which extend from a winding machine (not shown) can be dipped into the impregnating fluid reservoir, the winding machine being used to wind the fibers 61 to 63 around the core 36. In the resin impregnation stage, the unsaturated polyester may be replaced for example by an epoxy resin, a polyamide resin or a phenolic resin. In addition, the thermosetting resin may be replaced by, for example, an ultraviolet curable resin, a light curable resin or a thermoplastic resin (eg, methyl methacrylate).
Then, in the winding step, a unit comprising the core 36 and the pads 50 previously connected to each other via the bolts B can be prepared. The fibers 61 to 63 impregnated with thermosetting resin in the resin impregnation step can then be woven together and wrapped around the unit by the winding machine. The fibers 61 to 63 may for example be wound around the core 36 and the insertion projections 52 of the pads 50 from the opening portion 35 of the leg 31A to the opening portion 35 of the leg 31 B. Fibers 61 to 63 may further be woven and wrapped around core 36 and insertion projections 52 to form two layers. The fibers 61 to 63 included in the support portion 37 may extend from the opening portion 35 of the leg 31A or the opening portion 35 of the leg 31 B. That is, at the winding step, the portion of the connecting body 30 other than the support portion 37 may be formed.
Then, in the temporary cushion fixing step, the fibers 61 to 63 which extend from the opening portion 35 of the leg 31A or the opening portion 35 of the leg 31B can be wound around the outer peripheral surface 51C of the pad body 51 so as to encircle the pad 50 in the circumferential direction of the pad 50. More specifically, as shown in FIGS. 8a and 8b, the fibers 61 to 63 which extend from the pad portion opening 35 of leg 31A may be wound in turn to form radially stacked layers of pad 50. Therefore, all fibers 61-63 included in support portion 37 may be wound around pad 50. The terminal end portions of the fibers 61 to 63 may extend along the flat surfaces 31X of the opening portion 35 of the leg 31A to the proximal side of the leg 31A. Similarly, the fibers 61 to 63 extending from the opening portion 35 of the leg 31B may be wound around the outer peripheral surface 51C of the pad body 51 and extend along the flat surfaces 31X of the leg 31B to the proximal side of the connecting body 30. The support portion 37 can thus be formed.
The fiber 71 of the reinforcing element 70 can then be wound by the winding machine by the outside around the region which extends from an opening end of the opening portion 35 of the 31A to the end end portion portions of the fibers 61 to 63. The fiber 71 extending from the winding machine can be dipped into the impregnation fluid reservoir and then wound around the connecting body 30. Fiber 71 may also be wrapped around leg 31B in the same manner. In this embodiment, the fibers 60 and the fiber 71 may comprise the same substances and have the same configuration, and therefore the reinforcing element 70 may be made by the same manufacturing machine as the connecting body 30.
Then, at the final pad attachment step, the bonding body made in the temporary pad fixing step can be heated. The resin which impregnates the fibers 61 to 63 can thus harden to complete the binding body 30. If the thermosetting resin is replaced for example by an ultraviolet curable resin in the resin impregnation step, the bonding body can be irradiated with ultraviolet radiation at the final pad fixing step for curing the resin impregnating the fibers 61 to 63.
It is also possible for the fibers 61 to 63 to be wound around the core 36 and for the fiber 71 to be wrapped around the legs 31A, 31B at the winding step and at the temporary cushion fixing step. before the fibers 61 to 63 and 71 are soaked in the impregnating fluid reservoir in the resin impregnation step. It is further possible that in the resin impregnation step, the fibers 61 to 63 are sprayed with a thermosetting resin, an ultraviolet curable resin, a light curable resin or a thermoplastic resin instead of being dipped in the fluid reservoir. In addition, the unit comprising the core 36 and the bearings 50 connected via the bolts B may be prepared before the resin impregnation step.
Finally, at the head mounting step, the head 40 can be mounted on the connecting body 30. More specifically, as shown in Figure 3, the first head body 41 and the second head body 42 can be attached to each other on the straight portion 33 of the connecting body 30. The shim 45 can be hooped in the mounting hole 43 formed between the head bodies 41, 42 attached to each other, and the fibers 46 can be wound around the outer periphery of the head bodies 41, 42.
The actuation of the reaction link 20 will now be described with reference to Figures 2 and 11. The actuation of the reaction link 20 in the leg 31 B, which may be the same as that of the leg 31 A , will be omitted. Figures 11a-11c simplify fibers 61-63 to facilitate the description. FIG. 11a represents only the third fibers 63, whereas FIG. 11b represents only the first fibers 61 and the second fibers 62.
As shown in FIG. 2, when a reaction force produced when the actuator 10 controls the flight control surface 101 is applied to the actuator 10, the bushing 50 may be subjected to a traction force, a compressive force or a torsion force via the axis 13A which connects the actuator 10 and the reaction connection 20 between them. The tensile force applied to the bearing 50 can follow a direction in which the bearing 50 is separated from the end portion of the leg 31A, as indicated by the white arrows in Figures 11a and 11b. The compressive force applied to the pad 50 may follow a direction in which the pad 50 is pushed to the leg 31 A, as indicated by the white arrow in Fig. 11c. The torsional stress applied to the bearing 50 can rotate about the axis 13A, as indicated by the hatched arrow in FIG. 11c, because of the frictional force between the axis 13A and the bearing 50, etc., or can rotate around the longitudinal direction CD.
As shown in FIG. 11b, the first fibers 61 and the second fibers 62 included in the support portion 37 may be wound around the bearing body 51 continuously from the opening portion 35 of the leg 31A. That is, the first fibers 61 and the second fibers 62 included in the support portion 37 may be continuous. Therefore, as indicated by the white arrows in Figs. 11a and 11b, when a tensile stress is applied to the bushing 50, the force applied to the first fibers 61 and the second fibers 62 included in the carrier portion 37 and wound around the pad body 51 may be taken up by all the first fibers 61 and second fibers 62 included in the leg 31A. It is the same for the third fibers 63, which are not shown in Figure 11b. The leg 31A can thus support the pad 50. To support the pad 50, the pad 50 can be retained in such a way that the fibers 61 to 63 can produce a force opposite to the direction of the force applied to the fibers 61 to 63 in the leg 31A via the pad 50. The direction of the force applied to the fibers 61 to 63 may correspond to the direction of the vector resulting from the combination of the direction vectors of the fibers 61 to 63 subjected to the force.
More specifically, as indicated by the white arrow in Fig. 11a, when a pulling force is applied to the pad 50, i.e. when the fibers 61 to 63 included in the support portion 37 and wrapped around the pad body 51 are drawn in the direction of the white arrow, the terminal end portions of the fibers 61 to 63 may be subjected to a tensile force in the fiber direction 61 to 63 (longitudinal direction). A reaction force opposing the pulling force can therefore act on the fibers 61 to 63 in the direction of the large arrows. In addition, the fibers 61 to 63 included in the support portion 37 may extend from the proximal side of the connecting body 30 before being wound around the pad body 51. Such end portions (referred to herein as after as "initial end portions") can extend in the longitudinal direction CD, as the terminal end portions of the fibers 61 to 63. A reaction force can thus also act on the fibers 61 to 63 in the direction indicated by the big arrows. In particular, the third fibers 63, which can extend in the longitudinal direction CD in the planar surfaces of the connecting body 30 and can be wound around the outer peripheral surface 51C of the pad body 51, may tend to be effectively subjected to the tensile force in the extension direction of the third fibers 63. Accordingly, the third fibers 63 can support the bushing 50 effectively and firmly.
As indicated by the white arrow in FIG. 11c, when a compression force is applied to the bushing 50, the first fibers 61 and the second fibers 62 included in the connecting body 30 can take up a force. In addition, as shown in FIG. 11c, the inner surfaces 35Y of the opening portion 35 of the connecting body 30, which may be in surface contact with the lateral surfaces 52Y of the insertion projection 52 of the pad 50, may regain strength. Although not shown in Fig. 11c, the inner surfaces 35X of the aperture portion 35, which may be in surface contact with the planar surfaces 52X of the insertion projection 52, may regain a force. Further, since the reinforcing member 70 can produce a high pressure between the inner surfaces 35X, 35Y of the opening portion 35 and the flat surfaces 52X and the side surfaces 52Y of the insertion projection 52, the The insertion projection 52 may be less inclined to move relative to the opening portion 35 to the proximal side of the leg 31 A. The surface contact may suppress a stress concentration and eliminate the need for an excessive increase in the resistance to point contact and linear contact, which provides the necessary strength and reduces the weight of the bushing support structure BS.
As indicated by the hatched arrows in FIG. 11c, when a twisting force is applied to the bushing 50, a force can be applied to the first fibers 61 and the second fibers 62 included in the connecting body 30 (leg 31A) via the fibers 61-63 wrapped around the outer peripheral surface 51C of the pad body 51 (the third fibers 63 are omitted in Fig. 11c). The first fibers 61 and the second fibers 62 included in the connecting body 30 Gambe 31A) can be drawn respectively in the first direction D1 and in the second direction D2. The first fibers 61 and the second fibers 62 included in the connecting body 30 Gambe 31A) can take up the torsion force applied to the pad 50. The legs 31A, 31B can thus support the pad 50 against the applied torsion force at the pad 50.
This embodiment can produce the following advantageous effects. (1) The first fibers 61 and the second fibers 62 may be woven together. Therefore, the frictional force acting between the first fibers 61 and the second fibers 62 can increase the bond strength between the fibers 61, 62, compared to an arrangement in which the first fibers 61 and the second fibers 62 are not woven. together, i.e., fibers of the first fibers 61 and the second fibers 62 may be formed on the other fibers from said first fibers 61 and said second fibers 62. The resistance of the connecting body 30 may thus be increased. In addition, since the third fibers 63 can also be woven with the first fibers 61 and the second fibers 62, the strength of the connecting body 30 can be further increased.
(2) The third fibers 63 may include fibers wrapped around the outer peripheral surface 51C of the pad body 51 in a first winding direction (as indicated by the arrow Y1 in Fig. 8a) and fibers wound in a second winding direction (as indicated by the arrow Y2 in Figure 8b) opposite the first winding direction. Therefore, the portion of the third fibers 63 included in the support portion 37 where the third fibers 63 may begin to be wound around the pad 50 may not be bent or twisted with respect to the case where the third fibers 63 are wound into a circumferential direction of the bearing 50. The tensile force can be supported well balanced in the longitudinal direction CD.
(3) Since all the fibers 61 to 63 included in the connecting body 30 can be wound around the bearing 50, the traction force produced between the connecting body 30 and the bearing 50 can be taken up by therefore, the pad 50 may be better supported with a lower fiber count, which more effectively provides the necessary strength and reduces the weight of the pad support structure BS.
(4) Since the bonding body 30 may include stacked fiber layers 61 to 63, the strength of the bonding body 30 may be increased relative to the case where the bonding body 30 comprises a single layer .
(5) Since the first fibers 61 and the second fibers 62 which extend from the opening portion 35 in the side surfaces 31Y of the legs 31A, 31B may be wrapped around the pad 50 in directions In contrast, the first fibers 61 and / or the second fibers 62 may not be excessively bent or twisted. The tensile force can be supported well balanced in longitudinal direction CD.
(6) The third fibers 63 which extend from the opening portion 35 in the side surfaces 31Y of the legs 31A, 31B may diverge in two directions and be wound around the bushing 50 in opposite directions. The third fibers 63 may thus not be excessively bent or twisted with respect to the case where the third fibers 63 extending from the opening portion 35 in the side surfaces 31Y of the legs 31A, 31B are wrapped around the pad 50 in one direction. Therefore, the tensile stress can be supported well balanced in the longitudinal direction.
(7) Since the fibers 61 to 63 can be wound around the outer peripheral surface 51C of the pad body 51 of the pad 50 to form stacked layers, the size of the outer peripheral surface 51C of the body pad 51 may be less than where the fibers 61-63 are wrapped around the outer peripheral surface 51C of the pad body 51 so as not to form stacked layers. As a result, it is possible to provide the necessary strength and reduce the weight of the bushing support structure BS.
[0103] (8) The insertion projection 52 of the pad 50 may have tapered portions 52A, 52B tapered towards their end. Thus, when compressive force is applied to the bushing 50, the tapered portions 52A, 52B may contact the opening portions 35 of the legs 31A, 31B so that the connecting body 30 can support the bushing 50. .
[0104] (9) The opening portions of the leg 31A, 31B may comprise conical portions 35A, 35B with an upper opening surface towards their end. Thus, when compressive force is applied to the bushing 50, the tapered portions 35A, 35B may come into contact with the insertion projection 52 of the bushing 50 so that the connecting body 30 can support the bushing 50. , the conical portion 52A of the insertion projection 52 may be in surface contact with the conical portion 35A of the opening portion 35, and the conical portion 52B of the insertion projection 52 may be in surface contact with the portion conical 35B of the opening portion 35. Accordingly, the connecting body 30 can bear more firmly the pad 50.
[0105] (10) The reaction link 20 may include a reinforcing member 70 which reinforces the attachment of the pad 50 by the support member 37. The support portion 37 and the pad 50 can thus be more firmly attached together.
(11) Since the reinforcing member 70 can be provided on the portion of the connecting body 30 in which the insertion projection 52 of the pad 50 overlaps the opening portion 35, the opening portion 35 can be pushed against the insertion projection 52. Thus, when a compressive force is applied to the bearing 50, the bearing 50 may be less likely to move relative to the connecting body 30.
(12) Since the reinforcing member 70 can fix the terminal end portions of the fibers 61 to 63 included in the support portion 37, it is possible to prevent the terminal end portions of the fibers 61 to 63 are removed from the legs 31A, 31B.
[0108] (13) The reinforcing element 70 may be positioned on the outer side of the terminal end portions of the fibers 61 to 63 included in the support portion 37 on the portion of the connecting body 30 in which the projection of insertion 52 of the bushing 50 overlaps the opening portion 35. Thus, when a compressive force is applied to the bushing 50, the reinforcing element 70 can prevent widening of the opening portion 35. As a result, the connecting body 30 and the pad 50 can be supported firmly without increasing the size of the pad support structure BS.
[0109] (14) The reinforcing element 70, which may be constituted by the fiber 71, may be manufactured by the same winding machine as the connecting body 30. The manufacture of the bearing support structure BS may thus be facilitated.
(15) Since the fiber 71 is wound regularly, it can be avoided that the opening portion 35 of the leg 31A comprising the support portion 37 widens excessively. It is thus possible to avoid an increase in size of the bearing support structure BS.
(16) Since the pad body 51 of the pad 50 is provided with a pair of ribs 51 B, when the fibers 61-63 included in the support portion 37 are wrapped around the outer peripheral surface 51C of the pad body 51, the ribs 51B can prevent the fibers 61 to 63 from moving in the axial direction J1. When the fibers 61 to 63 are wrapped around the outer peripheral surface 51C of the pad body 51, it is possible to prevent the fibers 61 to 63 from being deflected from the outer peripheral surface 51C. The winding of the fibers 61 to 63 around the outer peripheral surface 51C of the pad body 51 is thus facilitated.
[0112] Variations
The description of the above embodiment illustrated a non-limiting example of a support structure for a force transmission element, an aircraft reaction link, a flight control surface control unit, a flight control method, mounting a force transmitting member, and a method of manufacturing an aircraft reaction link according to the present invention. Any of the following embodiment variations or combinations of two of the following embodiment variations may be used to implement a support structure for a force transmitting element, an aircraft reaction link, a flight control surface control unit, a method of mounting a force transmission element, and a method of manufacturing an aircraft reaction link according to the present invention. It should be noted that, for convenience, FIG. 12 represents only the third fibers 63 and does not represent the first fibers 61 and the second fibers 62.
[0113] Variation 1
In the above embodiment, it is also possible that any two of the fibers 61 to 63 extending from the opening portion 35 of the leg 31A are all wrapped around the outer peripheral surface 51C of the body. of pad 51, and that the remaining fibers of the fibers 61 to 63 are all or partially cut at the end of the opening portion 35 and are not wound around the outer peripheral surface 51C so as to form the portion of It is furthermore possible that any of the fibers 61-63 are all wound around the outer peripheral surface 51C of the pad body 51, and that the two remaining fibers of the fibers 61-63 are all or partially cut at the end of the opening portion 35 and are not wound around the outer peripheral surface 51C so as to form the support portion 37. If the required strength of the connecting body 30 is greater than the resistance required to support the pad body 51, the fibers 61 to 63 may be all or partially cut to reduce the weight of the fibers, thereby further reducing the weight. providing the necessary strength of the bearing support structure. Further, since the fibers 61 to 63 are all or partly not wrapped around the pad body 51, the production time is shorter and thus the productivity of the pad bearing structure BS is greater than the case where the fibers 61 to 63 are all wrapped around the bushing body 51. Due to the lower number of fibers wrapped around the bushing body 51, the productivity of the bushing support structure BS may be higher. The same modification can be applied to the fibers 61 to 63 which extend from the opening portion 35 of the leg 31B so as to produce the same effects.
[0114] Variation 2
In the embodiment above, it is also possible to modify the method of winding the fibers 61 to 63 included in the support portion 37 around the outer peripheral surface 51C of the bearing body 51 as described in the points ( a) to (c) below. This modification makes it possible to wind the fibers in bulk and thus simplifies the work and the manufacturing equipment with respect to the case where the fibers are wound in two directions, (a) Among the fibers 61 to 63 included in the support portion 37 the first fibers 61 and the second fibers 62 may be wound in a single circumferential direction of the outer peripheral surface 51C of the pad body 51. (b) Among the fibers 61 to 63 included in the support portion 37, the third fibers 63 may be wound in a single circumferential direction of the outer peripheral surface 51C of the pad body 51. (c) All fibers 61-63 included in the support portion 37 may be wound in a single circumferential direction of the outer peripheral surface 51C of the bearing body 51.
[0115] Variation 3
In the embodiment above, it is also possible to modify the angles of the fibers, represented by the (acute) angles of the first direction D1 and the second direction D2 with respect to the longitudinal direction CD, as described in FIGS. points (a) and (b) below, (a) As shown in FIG. 13, the angles of the fibers in the opening portion 35, which is in the connecting body 30 and near the support portion 37, may be smaller than the angles in portions of the connecting body 30 further from the support portion 37 than the opening portion 35. With this arrangement, when the first fibers 61 and the second fibers 62 included in the portion of support 37 are wound around the bearing body 51, it is possible to prevent the first fibers 61 and the second fibers 62 from being strongly folded or twisted. The deformation of the connecting body 30 due to the tensile force can therefore be restricted, and the pad 50 can be firmly supported by the first fibers 61 and the second fibers 62. At the same time, the first fibers 61 and the second fibers 62 can receive the tensile force more effectively, (b) As shown in FIG. 14, the fiber angles can be lower towards the support portion 37 of the connecting body 30. With this arrangement, the manufacture of the connecting body 30 can be facilitated with respect to the case where the angles of the first fibers 61 and the second fibers 62 vary in a discrete manner when the first fibers 61 and the second fibers 62 included in the support portion 37 are wound around the body of the Bearing 51. Compared in particular in the case where the fiber angles are greatly reduced in a portion near the bearing body 51, it can be avoided that the first fibers 61 and the second fibers 62 are strongly folded or twisted.
[0116] Variation 4
In the embodiment above, it is also possible to modify the third fibers 63 as described in points (a) and (b) below. Further, the third fibers 63 of the above embodiment may be omitted, (a) The third fibers 63 may not be disposed on one to three of the four side surfaces of the legs 31A, 31B. (B) third fibers 63 may extend in a direction not parallel to the longitudinal direction CD. The third fibers 63 may for example intersect the longitudinal direction CD.
[0117] Variation 5
In the embodiment above, it is also possible for the fiber 71 of the reinforcing element 70 to be wound around the leg 31A as described in points (a) to (h) below. The reinforcing member 70 may further be mounted in the same manner on the leg 31 B. (a) As shown in Fig. 15, the fiber 71 may be wound only around the end end portions of the fibers 61 to 63 which extends to the proximal side of the leg 31A beyond the conical portions 35A, 35B of the opening portion 35. This arrangement can prevent the terminal end portions of the fibers 61 to 63 from being removed due to the shear force produced by a pulling force applied to the bearing body 51 and may further reduce the weight, (b) As shown in FIG. 16, the fiber 71 may be wound only around the conical portions 35A, 35B of the portion opening 35 of the leg 31A. This arrangement can effectively prevent the fibers 61 to 63 from being removed due to expansion of the opening portion 35 when a compressive force is applied to shrug the pad body 51 into the opening portion 35. As a result, it is possible to provide the necessary strength against the compressive force and to reduce the weight of the bearing support structure BS. (c) As shown in Fig. 17, the fiber 71 may be wrapped around the end end portions of the fibers 61-63 which extend toward the proximal side of the leg 31A beyond the conical portions 35A, 35B of the opening portion 35, and around the distal end portions of the conical portions 35A, 35B of the opening portion 35 of the leg 31A. The fibers of a plurality of fibers 71 can thus be arranged on the leg 31A by separating them from one another. This arrangement can prevent the terminal end portions of the fibers 61 to 63 from being removed due to the shear force produced by a pulling force applied to the pad body 51 and can further reduce the weight. This arrangement can further effectively prevent fibers 61 to 63 from being removed due to expansion of the opening portion 35 when a compressive force is applied to shrug the pad body 51 into the opening portion. 35. As a result, it is possible to provide the necessary strength against the compressive force and to reduce the weight of the bushing support structure BS. Furthermore, since the fibers of a plurality of fibers 71 can be arranged separating them from one another, it is possible to provide the necessary strength and reduce the weight of the bushing support structure BS by relative to the case where the fiber 71 is arranged over the entire surface, (d) The fiber 71 may be wrapped around the proximal side of the leg 31A beyond the terminal end portions of the fibers 61 to 63. (e) The fiber 71 may be wound around only a portion of the distal end portions of the conical portions 35A, 35B of the opening portion 35 in the leg 31A, or only a portion of the proximal portion of the tapered portions 35A. , 35B. (f) The fiber 71 may be wrapped around the legs 31A, 31B so as to extend neither parallel nor perpendicular to the extension direction of the legs 31A, 31B. (g) The fiber 71 may include a plurality of chord-like fibers such as the first fibers 61 and the second fibers 62 woven together, and may be wrapped around the legs 31A, 31B. (h) The fiber 71 may be wrapped around the legs 31A, 31B so to form stacked layers. These arrangements can increase the strength of the bushing support structure BS when it is subjected to the compressive force.
[0118] Variation 6
In the above embodiment, it is possible for the fiber 71 of the reinforcing member 70 to be replaced by an adhesive, a heat-shrinkable sheath, an adhesive tape or an annular element divided into a plurality of parts.
[0119] Variation 7
In the above embodiment, the reinforcing member 70 may be omitted. In this case, the terminal end portions of the fibers 61 to 63 included in the support portion 37 may for example be rewoven with the fibers 61 to 63 included in the side surfaces 31Y of the opening portion 35 of the legs 31A , 31 B.
[0120] Variation 8
In the above embodiment, it is also possible to enlarge a gap between the fibers 61 to 63 woven together and wound to form the connecting body 30, to insert the pad 50 into the enlarged gap, and to curing the resin impregnating the fibers 61 to 63 at the final pad attachment step. The pad 50 can thus be fixed to the end portion of the connecting body 30. In this case, the opening portion 35 can be omitted on the legs 31A, 31B of the connecting body 30, and the projection of insertion 52 can be omitted from the bearing 50. The ribs 51B can also be omitted from the bearing body 51. The bearing 50 can thus be fixed by a method other than the winding of the fibers 61 to 63.
[0121] Variation 9
In the above embodiment, it is also possible for a plurality of bearings 50 to be arranged on the longitudinal end of the core 36 at intervals in the longitudinal direction CD. In this case, the pads 50 can be supported on the legs 31A, 31B by the support portion 37.
[0122] Variation 10
In the above embodiment, it is also possible that after winding the fibers 60 around the core 36, the insertion projection 52 of the pad 50 is inserted into the opening portion 35 of the legs 31 A, 31B to connect the core 36 and the pad 50.
[0123] Variation 11
In the above embodiment, it is also possible for the feedback link 20 to be connected indirectly to the flight control surface 101 or to the actuator 10.
In this case, the head 40 of the reaction link 20 may for example be provided with a connection portion such as a screw portion or a hole instead of the bearing hole 42A and the bearing 44. The connecting portion may be connected to a link for connection to the flight control surface 101. If the link body 30 is straight or J-shaped, one end of the link body 30 may be connected to the bushing 50, and the other end of the link body 30 may be connected to the bushing 50, and the other end may be provided with a connecting portion such as a screw portion or a hole. The connection portion may be connected to a link for connection to the flight control surface 101 or the actuator 10.
[0124] Variation 12
In the embodiment above, the pads 50 may be replaced by other force transmission elements. The force transmission elements may be for example axes or bolts. In sum, any element other than the bearings 50 can be used as a force transmitting element in that it transmits a force to a structural element such as the connecting body 30. In addition, the force transmitting element can be made not only of metallic materials, but also of ceramic materials, fiber-reinforced plastics such as CFRP, or resins. In sum, the force transmitting member may be made of any material to the extent that it can transmit a force to a structural member.
[0125] Variation 13
In the above embodiment, the bolster support structure BS in which the fibers 61 to 63 included in the support portion 37 can be wound around the bolster 50 to support the bolster 50 is applied to a reaction link. 'plane. This support structure for a force transmission element can be applied to other parts than aircraft reaction links. As shown in FIG. 18, for example, the support structure for a force transmission element can be configured so that a bushing 120 serving as a force transmission element can be supported by a structural element 110 made of fiber reinforced plastics. The fibers 111 which constitute the structural element 110 can support the pad 120 while extending continuously. In the variation 13, the pad 120 is a non-limiting example of the force transmission element shown in FIG. 18. The force transmission element may for example comprise a hole for a bearing or an axis instead of a hole. The hole or the axis may have a rectangular or polygonal section and a circular section. The fibers 111 may be woven together as the fibers 61 to 63 of the above embodiment.
It will be apparent to those skilled in the art that the present invention can be integrated in many specific forms without departing from the scope of the invention. Some components may for example be omitted from the components described in the embodiments (or one or more aspects thereof). Components of different embodiments may further be suitably combined.

权利要求:
Claims (23)
[1" id="c-fr-0001]
A support structure (BS) for a force transmission member (50), comprising: a structural member (30) made of a fiber reinforced plastic having continuous fibers (60), wherein the support structure ( BS) allows the structural member (30) to support the force transmitting member (50), the force transmitting member (50) being configured to transmit a force, and wherein the continuous fibers (60) included in the fiber reinforced plastic support the force transmitting member (50) to regain strength.
[2" id="c-fr-0002]
The power transmission element support structure (BS) (50) according to claim 1, wherein the fibers (60) which support the force transmission element (50) are wound around the element of the force transmission element (50). transmission of force (50).
[3" id="c-fr-0003]
The power transmission element support structure (BS) (50) according to claim 1, wherein the fibers (60) included in the structural element (30) comprise first fibers (61) which extend in a first direction (D1) and second fibers (62) which extend in a second direction (D2) different from the first direction (D1), and the first fibers (61) and the second fibers (62) are woven together.
[4" id="c-fr-0004]
The power transmission element (50) support structure (BS) according to claim 3, wherein fiber angles (61, 62) formed by the first direction (D1) and the second direction (D2) with a longitudinal direction (CD) of the structural element (30) in a portion of the structural element (30) close to the force transmission element (50) are less than the angles in a portion of the structural element ( 30) remote from the force transmission element (50).
[5" id="c-fr-0005]
The power transmission element support structure (BS) (50) according to claim 4, wherein the fiber angles (61, 62) in the structural member (30) decrease non-discretely towards the force transmission element (50).
[6" id="c-fr-0006]
The power transmission member support structure (BS) (50) according to claim 3, wherein the first fibers (61) and the second fibers (62) are wound around the force transmission member ( 50), and a winding direction of the first fibers (61) around the force transmitting member (50) is opposed to a winding direction of the second fibers (62) around the force transmitting member (50).
[7" id="c-fr-0007]
The power transmission element support structure (BS) (50) according to claim 3, wherein the first direction (D1) and the second direction (D2) are different from a longitudinal direction (CD) of the structural member (30), and the fibers (60) included in the structural member further comprise third fibers (63) extending in a longitudinal direction (CD) and wound around the force transmitting member (50).
[8" id="c-fr-0008]
The power transmission member support structure (BS) (50) according to claim 7, wherein the third fibers (63) comprise fibers wrapped around the force transmitting member (50) in a first winding direction (Y1) and fibers wrapped around the force transmitting member (50) in a second winding direction (Y2) opposite the first winding direction (Y1).
[9" id="c-fr-0009]
The force transmitting member support structure (BS) (50) according to claim 7, wherein only the third fibers (63) are wound around the force transmitting member (50).
[10" id="c-fr-0010]
The force transmitting member support structure (BS) (50) according to claim 2, wherein the fibers (60) wound around the force transmitting member (50) form stacked layers.
[11" id="c-fr-0011]
The force transmitting member support structure (BS) (50) according to claim 2, wherein all the fibers (60) included in the structural member (30) are wound around the transmission element of the transmission member. force (50).
[12" id="c-fr-0012]
The force transmitting member support structure (50) according to claim 2, wherein only a portion of the fibers (60) included in the structural member (30) are wrapped around the element transmission of force (50).
[13" id="c-fr-0013]
The force transmitting member support structure (BS) (50) according to claim 2, wherein the force transmitting member (50) comprises a projection (52) which can be inserted into a portion of aperture (35) formed in a distal end portion of the structural member (30), and the projection (52) is conically reduced toward one end thereof.
[14" id="c-fr-0014]
The power transmission member support structure (BS) (50) according to claim 13, wherein a reinforcing member (70) for reinforcing the attachment between the structural member (30) and the transmission member a force portion (50) is provided on a portion of the opening portion (35) which overlaps the projection (52).
[15" id="c-fr-0015]
The power transmission member support structure (BS) (50) according to claim 14, wherein the reinforcing member (70) is made from a continuous fiber (71) included in the reinforced plastic of fibers and wound on an outer side of the fibers (60) which support the force transmitting member (50).
[16" id="c-fr-0016]
The power transmission element support structure (BS) (50) according to claim 15, wherein the fiber (71) of the reinforcing element (70) is wound regularly.
[17" id="c-fr-0017]
The force transmitting member support structure (BS) (50) according to claim 15, wherein the reinforcing member (70) attaches end portions of the fibers (60) which support the transmission of force (50).
[18" id="c-fr-0018]
The force transmitting member support structure (BS) (50) according to claim 13, wherein the opening portion (35) formed in the distal end portion of the structural member (30) has a conical shape with a corresponding larger opening area towards a distal end of the opening portion (35).
[19" id="c-fr-0019]
The power transmission member support structure (BS) (50) according to claim 2, wherein the force transmission member (50) has an outer peripheral surface (51C) around which the fibers (60) ) are wound, and the two axial ends of the outer peripheral surface (51C) of the force transmission element (50) are provided with a rib (51B) extending radially from the outer peripheral surface (51 C) of the force transmission element (50).
[20" id="c-fr-0020]
An aircraft reaction link (20) mounted directly or indirectly on a flight control surface (101) of an aircraft and connected to an actuator (10) for controlling the flight control surface (101), the aircraft reaction link (20) comprising: a bushing (50) serving as a force transmitting member, the bushing (50) being configured to slidably support the actuator (10); and a connecting body (30) comprising a structural member (31A, 31B), the structural member (31A, 31B) being configured to support the pad (50), wherein the support structure (BS) according to claim 1 is used by the connecting body (30) to support the pad (50).
[21" id="c-fr-0021]
A flight control surface control unit (1) comprising: the aircraft reaction link (20) of claim 20; and the actuator (10).
[22" id="c-fr-0022]
A method of mounting a force transmitting member (50) on a structural member (30), the force transmitting member (50) being configured to transmit a force, the structural member (30) being constituted a fiber-reinforced plastic supporting the force transmission member (50), the method comprising: a winding step (S12) of winding fibers (60) around a core (36) to form the structural member (30); a temporary securing step (S13) of continuously winding the fibers (60) around the force transmitting member (50); a resin impregnation step (S11) for impregnating the fibers (60) with a resin; and a final setting step (S14) for curing the resin impregnating the fibers (60) to secure the structural member (30) and the force transmitting member (50).
[23" id="c-fr-0023]
A method of manufacturing an aircraft reaction link (20), the aircraft reaction link (20) being mounted directly or indirectly on a flight control surface (101) of an aircraft and connected to an actuator (10) which controls the flight control surface (101), the aircraft reaction link (20) comprising a linkage body (30) made of fiber reinforced plastic and a pad (50). ) attached to the connecting body (30), the method comprising: a winding step (S12) of winding fibers (60) around a core (36) to form a portion of the connecting body (30) ; a temporary pad fixing step (S13) of continuously winding the fibers (60) around the pad (50); a resin impregnation step (S11) for impregnating the fibers (60) with a resin; and a final pad fixing step (S14) for curing the resin impregnating the fibers (60) to secure the pad (50) to the connecting body (30).

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同族专利:

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公开号 | 公开日

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US20170130764A1|2017-05-11|

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JP2017087841A|2017-05-25|

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DE102016221309A1|2017-05-11|

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JP6626690B2|2019-12-25|

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US10493703B2|2019-12-03|

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法律状态:
2017-10-23| PLFP| Fee payment|Year of fee payment: 2 |

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2018-10-26| PLFP| Fee payment|Year of fee payment: 3 |

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2020-10-23| PLFP| Fee payment|Year of fee payment: 5 |

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2021-10-26| PLFP| Fee payment|Year of fee payment: 6 |

优先权:

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申请号 | 申请日 | 专利标题

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JP2015217581A|JP6626690B2|2015-11-05|2015-11-05|Support structure of force transmission member|

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