Lateral support device for a rear fuselage tailplane suspension frame of an aircraft

Abstract

The present invention relates to a lateral support device for a rear fuselage tail suspension frame of an aircraft, comprising a lateral connecting rod for connecting the rear fuselage tail suspension frame to a tail suspension connecting plate, comprising a rod body and a first wing portion and a second wing portion at the end of the rod body extending parallel to each other and away from the rod body in the axial direction of the rod body, the first wing portion having a first through hole and the second wing portion having a second through hole, and the through hole center axes of the first through hole and the second through hole being aligned, an eccentric adjustment member configured to be able to pass through the first through hole and the second through hole and having an eccentric adjustment axis with an eccentric distance to the through hole center axes, the eccentric adjustment member being configured to be able to be rotated after it has passed through the first through hole, a lug hole of the suspension frame or the tail suspension connecting plate and the second through hole in this order, so that the eccentric adjustment axis is rotated around the through hole center axes, thereby continuously adjusting the distance of the center of the lateral connecting rod relative to the center of the lug hole.

Description

Technical Field

[0001] The present invention relates to a lateral support device, and more particularly to a lateral support device for a horizontal stabilizer suspension frame on the rear fuselage of an aircraft, the lateral support device being used to support the horizontal stabilizer suspension connecting plate and transfer the horizontal stabilizer load to the horizontal stabilizer suspension frame. Background Technology

[0002] The rear end of the aircraft fuselage includes a vertical tail and a horizontal tail, with the horizontal tail or horizontal stabilizer connected to the rear fuselage via a rear fuselage horizontal tail suspension frame. The rear fuselage horizontal tail suspension frame is used to transfer and diffuse the concentrated load of the horizontal tail, and its main functions include three aspects: (1) providing support for the horizontal tail pivot; (2) serving as the rear end frame of the horizontal tail opening, undertaking the role of opening reinforcement and load diffusion; and (3) serving as the design separation surface of the fuselage to facilitate the installation and disassembly of the overall horizontal tail. The rear fuselage horizontal tail suspension frame mainly includes two structures: a metal truss structure (such as...) Figure 1 (as shown) and web frame structure (such as Figure 2 As shown in the diagram, it specifically includes the frame, horizontal stabilizer suspension joint, and lateral support components. The lateral support components mainly transmit the lateral inertial loads of the horizontal stabilizer and can be divided into... Figure 1 The adjustable lateral support member shown and Figure 2 The fixed lateral support member shown.

[0003] like Figure 1 As shown, the adjustable lateral support member 5 in the metal truss structure 1 adopts an adjustable design and is connected between the horizontal stabilizer suspension joint 4 and the upper half frame 2 or lower half frame 3 of the horizontal stabilizer suspension frame on the rear fuselage. The lateral load of the horizontal stabilizer is transmitted through the Y-type connecting pivot 6 and the adjustable lateral support member 5, no longer compressing the horizontal stabilizer suspension joint 4, thus having a better force transmission advantage. In addition, the length of the lateral support rod can be adjusted by turning the tie rod nut, which can eliminate the cumulative error in the manufacturing and assembly of the horizontal stabilizer suspension frame structure, and has good assembly performance. However, the adjustable lateral support component is relatively heavy, and the assembly is time-consuming and difficult.

[0004] like Figure 2 As shown, the fixed lateral support member 8 in the web frame structure 7 adopts a fixed scheme. The lateral load of the tail is transmitted through the tail main hinge pressing the tail suspension joint 9. The fixed lateral support member 8 is fixed on the tail suspension frame web 10. Therefore, it has no length adjustment function, cannot eliminate the cumulative error of manufacturing and assembly, and has poor assembly performance.

[0005] Therefore, there is a need for a new lateral support device for the rear fuselage horizontal stabilizer suspension frame that combines the advantages of adjustable lateral support components and fixed lateral support components. Summary of the Invention

[0006] This invention proposes a lateral support device for a horizontal stabilizer suspension frame on the rear fuselage of an aircraft. The lateral support device includes a lateral connecting rod for connecting a reinforcing beam of the rear fuselage horizontal stabilizer suspension frame to a horizontal stabilizer suspension connecting plate. The lateral connecting rod includes a rod body and a first end and a second end located at opposite ends of the rod body. Each of the first and second ends has a first wing and a second wing extending parallel to each other and away from the rod body along the axial direction of the rod body. The first wing has a first through-hole, and the second wing has a second through-hole. The first and second through-holes are configured such that their central axes are aligned with each other. An eccentric adjustment component is configured to pass through the first through hole and the second through hole, and the eccentric adjustment component has an eccentric adjustment axis. The eccentric adjustment axis is set such that there is an eccentric distance between the eccentric adjustment component and the central axis of the through hole when the eccentric adjustment component passes through the first through hole and the second through hole. The eccentric adjustment component is configured to be rotatable after it passes through the first through hole, the lug hole on the lug of the reinforcing beam or the flat tail suspension connecting plate, and the second through hole in sequence, so that the eccentric adjustment axis rotates about the central axis of the through hole, thereby continuously adjusting the distance between the center of the lateral connecting rod and the center of the lug hole.

[0007] According to some embodiments, the eccentric adjustment component includes: a bushing assembly, the bushing assembly including a first bushing capable of being received in the first through hole and a second bushing capable of being received in the second through hole, the first bushing and the second bushing each including a bushing body and a bushing through hole, the bushing body being configured such that the bushing body axis is aligned with the central axis of the through hole, wherein the eccentric distance between the bushing body axis and the central axis of the bushing through hole is equal to the eccentric distance between the central axis of the through hole and the eccentric adjustment axis; and a bolt assembly, the bolt assembly including a bolt and a nut, the bolt being configured to pass sequentially through the bushing through hole of the first bushing, the lug hole, and the bushing through hole of the second bushing, such that the bolt axis is aligned with the central axis of the through hole. The eccentric adjustment axes coincide, and the bolt is configured to engage with the first bushing and the second bushing to form a single unit, wherein the threaded end of the bolt extends beyond the bushing through hole of the second bushing, thereby allowing the nut to be screwed onto the threaded end from the second bushing side, wherein when the bolt is rotated, the first bushing and the second bushing can rotate accordingly, allowing the bolt axis to rotate about the central axis of the through hole of the first wing and the second wing, wherein the lateral support device further includes a locking assembly disposed on the outer surface of the first wing, near the first through hole, and the locking assembly is configured to engage with the bolt to lock the rotational movement of the bolt.

[0008] According to some embodiments, the bolt assembly further includes a washer disposed between the outer surfaces of the nut and the second bushing and configured such that the bolt engages with the second bushing via the washer.

[0009] According to some embodiments, both the first bushing and the second bushing include a flange extending radially outward at the end of the bushing body in a direction perpendicular to the axis of the bushing body. When the first bushing is received in the first through hole, the surface of its flange near the bushing body contacts the outer surface of the first wing. When the second bushing is received in the second through hole, the surface of its flange near the bushing body contacts the outer surface of the second wing.

[0010] According to some embodiments, the first bushing has a boss extending away from the bushing body along the axial direction of the bushing through hole at one end near the outer surface of the first wing. The bolt includes an extension extending radially away from the bolt axis at the connection between the head and the screw. The extension has an opening penetrating the extension along the bolt axis. The opening is configured to receive the boss of the first bushing so that the bolt engages with the first bushing. The second bushing has a recess formed along the edge of the bushing through hole at one end near the outer surface of the second wing. The bolt also includes a slot extending along the bolt axis on the threaded surface at the thread end. The washer includes a protrusion extending radially toward the center of the washer on its inner circumferential surface. The thickness of the protrusion is greater than the thickness of the washer, and the protrusion is configured to be received within the recess of the second bushing and the slot of the bolt so that the bolt engages with the second bushing.

[0011] According to some embodiments, the boss of the first bushing includes a pair of bosses that are radially opposite to each other relative to the bushing through hole and extend away from the bushing body along the axis of the bushing through hole, and the opening of the extension includes a pair of openings radially disposed relative to the bolt axis, the pair of openings being configured to receive a corresponding boss of the pair of bosses of the first bushing.

[0012] According to some embodiments, the second bushing has a recess comprising a pair of recesses arranged radially opposite each other along the edge of the bushing through hole, the bolt comprises a pair of slots formed on the threaded surface at the thread end, extending along the bolt axis and arranged radially opposite each other, and the washer comprises a pair of protrusions arranged radially opposite each other on its inner circumferential surface toward the center of the washer, the thickness of the pair of protrusions being greater than the thickness of the washer, and configured to be received in corresponding recesses in the pair of recesses of the second bushing and in corresponding slots in the pair of slots of the bolt.

[0013] According to some embodiments, a pair of bosses of the first bushing are disposed on the flange of the first bushing.

[0014] According to some embodiments, the extension of the bolt is configured as a gear capable of engaging with the locking assembly, the opening penetrating the spokes of the gear and communicating with the tooth groove.

[0015] According to some embodiments, the locking assembly includes a toothed plate that meshes with the gear.

[0016] According to some embodiments, the bushing assembly further includes a lateral connecting rod bushing, the lateral connecting rod bushing including a bushing body and a flange extending radially outward at one end of the bushing body perpendicular to the axis of the bushing body, wherein the bushing body of the lateral connecting rod bushing is received in the first through hole and the second through hole, the flange of the lateral connecting rod bushing is close to the axis of the lateral connecting rod and contacts the inner surfaces of the first wing and the second wing, and the first bushing and the second bushing are respectively received in the bushing through hole of the lateral connecting rod bushing.

[0017] According to some embodiments, the lateral support device further includes a bearing disposed between the first wing and the second wing, and the bolt passes sequentially through the first bushing, the bearing and the second bushing.

[0018] According to some implementations, the bearing is a spherical bearing.

[0019] According to some implementations, the bearing is an eccentric bearing.

[0020] According to some embodiments, the lateral support device further includes bearing limiting shims, which are bolted through and disposed between the first bushing and the bearing, and between the bearing and the second bushing.

[0021] According to some implementations, the bolt is a countersunk head hex bolt.

[0022] According to some embodiments, the body of the lateral connecting rod includes a plurality of openings arranged along the axis of the lateral connecting rod.

[0023] According to some embodiments, the eccentricity distance between the eccentricity adjustment axis of the eccentricity adjustment component and the central axis of the through hole is zero.

[0024] The present invention also proposes a rear fuselage horizontal stabilizer suspension frame, the rear fuselage horizontal stabilizer suspension frame including the lateral support device and the horizontal stabilizer main hinge as described above, the horizontal stabilizer main hinge being disposed between the horizontal stabilizer suspension connecting plates to connect the horizontal stabilizer.

[0025] The present invention also proposes an aircraft comprising a rear fuselage horizontal stabilizer suspension frame as described above.

[0026] The lateral support device of this invention can adjust the distance between the center of the lateral connecting rod and the center of the lug hole of the rear fuselage horizontal stabilizer suspension frame reinforcing beam or the horizontal stabilizer suspension connecting plate by rotating the eccentric adjustment component. This achieves continuous length adjustment to match the hole spacing of the lug holes in the rear fuselage horizontal stabilizer suspension frame reinforcing beam and the horizontal stabilizer suspension connecting plate, thereby eliminating cumulative manufacturing and assembly errors and ensuring a tight connection between the rear fuselage horizontal stabilizer suspension frame reinforcing beam and the horizontal stabilizer suspension connecting plate. The lateral support device of this invention can also achieve directional adjustment through bearings, thereby optimizing the load transmission path of the rear fuselage horizontal stabilizer suspension frame, and further enhancing the continuous length adjustment function through bearings. Furthermore, the lateral support device of this invention has a simple structure, is lightweight, easy to assemble, and has good operability and assembly performance. Attached Figure Description

[0027] The above-described objects, as well as other objects, features, and advantages of the invention, will be more fully understood by referring to the following illustrative and non-limiting detailed description of exemplary embodiments of the invention when taken in conjunction with the accompanying drawings.

[0028] Figure 1 A front view of the rear fuselage horizontal stabilizer suspension frame of the prior art is shown;

[0029] Figure 2 An isometric view of another rear fuselage horizontal stabilizer suspension frame in the prior art is shown;

[0030] Figure 3 A schematic diagram showing the assembly of the rear fuselage horizontal stabilizer suspension frame and the horizontal stabilizer, including the lateral support device according to an embodiment of the present invention;

[0031] Figure 4 A front view of the rear fuselage horizontal stabilizer suspension frame including the lateral support device according to an embodiment of the present invention is shown;

[0032] Figure 5 Show Figure 4 A cross-sectional view of the rear fuselage horizontal stabilizer suspension frame taken along section line A;

[0033] Figure 6 Show Figure 4 An enlarged view of area B of the rear fuselage horizontal stabilizer suspension frame;

[0034] Figure 7 Show along Figure 6 The cross-sectional view taken by section line C in the diagram;

[0035] Figure 8A front view of the lateral connecting rod of the lateral support device according to an embodiment of the present invention is shown;

[0036] Figure 9 This diagram illustrates the motion trajectory of the eccentric adjustment axis of the lateral support device according to an embodiment of the present invention rotating about the central axis of the through hole of the lateral connecting rod. Detailed Implementation

[0037] The invention will now be described with reference to the accompanying drawings, in which preferred exemplary embodiments of the invention are shown. However, the invention may be embodied in other forms and should not be construed as limited to the embodiments disclosed herein. The disclosed embodiments are provided to fully convey the scope of the invention to those skilled in the art.

[0038] During the manufacturing process of the horizontal stabilizer suspension frame on the rear fuselage of an aircraft, dimensional errors in the parts are unavoidable. Therefore, the length of the lateral support member cannot be exactly equal to the connection distance between the horizontal stabilizer suspension connecting plate and the rear fuselage horizontal stabilizer suspension frame reinforcing beam. Thus, it is desirable to provide a lateral support device whose length can be adjusted to fit the connection distance between the horizontal stabilizer suspension connecting plate and the rear fuselage horizontal stabilizer suspension frame reinforcing beam, eliminating accumulated manufacturing and assembly errors, and enabling simplified assembly to reduce costs.

[0039] Figure 3 A schematic diagram of the rear fuselage horizontal stabilizer suspension frame and horizontal stabilizer assembly, including lateral support devices according to an embodiment of the present invention, is shown. As shown, the horizontal stabilizer 45 passes through an opening in the rear fuselage section (not shown) and connects to the rear fuselage horizontal stabilizer suspension frame 11. Four horizontal stabilizer opening reinforcement beams 46 reinforce the opening area of ​​the rear fuselage section and connect to the rear fuselage horizontal stabilizer suspension frame 11. The rear fuselage horizontal stabilizer suspension frame 11 includes an upper horizontal stabilizer suspension frame 12, a lower horizontal stabilizer suspension frame 13, two horizontal stabilizer suspension connecting plates 14 connecting the upper horizontal stabilizer suspension frame 12 and the lower horizontal stabilizer suspension frame 13, and four lateral support devices 15 connecting the upper horizontal stabilizer suspension frame 12 or the lower horizontal stabilizer suspension frame 13 and the horizontal stabilizer suspension connecting plates 14.

[0040] Figure 4The diagram shows a front view of a rear fuselage horizontal stabilizer suspension frame including a lateral support device according to an embodiment of the present invention. The two ends of the horizontal stabilizer suspension connecting plate 14 are respectively connected to the outer ends of the upper half-frame 12 and the lower half-frame 13 of the rear fuselage horizontal stabilizer suspension, such that the upper half-frame 12, the lower half-frame 13, and the connecting plate 14 form a closed rear fuselage horizontal stabilizer suspension frame 11. The horizontal stabilizer suspension connecting plate 14 may be integrally formed as a plate. Preferably, the horizontal stabilizer suspension connecting plate 14 includes an outer horizontal stabilizer suspension connecting plate 16 and an inner horizontal stabilizer suspension connecting plate 17, with a horizontal stabilizer main hinge 20 having a through hole for connecting to the horizontal stabilizer 45 provided between the outer horizontal stabilizer suspension connecting plate 16 and the inner horizontal stabilizer suspension connecting plate 17. As shown in the figure, the rear fuselage horizontal stabilizer suspension frame reinforcement beam, namely the upper half frame reinforcement beam 18 and the lower half frame reinforcement beam 19 of the rear fuselage horizontal stabilizer suspension, as well as the inner connecting plate 17 of the horizontal stabilizer suspension, all include lugs. The lateral support device 15 connects the upper half frame reinforcement beam 18 or the lower half frame reinforcement beam 19 of the rear fuselage horizontal stabilizer suspension to the inner connecting plate 17 of the horizontal stabilizer suspension through the lugs.

[0041] Figure 5 Show Figure 4 The cross-sectional view of the rear fuselage horizontal stabilizer suspension frame taken along section line A. Both the outer horizontal stabilizer suspension connecting plate 16 and the inner horizontal stabilizer suspension connecting plate 17 include through holes that can be aligned with each other. The through holes of the outer horizontal stabilizer suspension connecting plate 16, the inner horizontal stabilizer suspension connecting plate 17, and the horizontal stabilizer main hinge 20 are aligned with each other and then connected together by horizontal stabilizer bolts 21, horizontal stabilizer nuts 22, and horizontal stabilizer suspension connecting plate bushings 23. Specifically, as shown... Figure 4 As shown, the extension line connecting the center of the lug hole of the upper half-frame reinforcing beam 18 of the rear fuselage horizontal stabilizer and the inner side connecting plate 17 of the horizontal stabilizer frame passes through the center of the main hinge of the horizontal stabilizer. Similarly, the extension line connecting the center of the lug hole of the lower half-frame reinforcing beam 19 of the rear fuselage horizontal stabilizer and the inner side connecting plate 17 of the horizontal stabilizer frame also passes through the center of the main hinge of the horizontal stabilizer. This arrangement can make the lateral support device 15 bear the force evenly.

[0042] Figure 6 Show Figure 4 An enlarged view of area B of the rear fuselage horizontal stabilizer suspension frame. Figure 7 Show along Figure 6 The figure shows a cross-sectional view taken by section line C. As shown, the lateral support device 15 of the present invention is connected to the inner connecting plate 17 of the horizontal stabilizer suspension via a lug. The lateral support device 15 can also be connected to the rear fuselage horizontal stabilizer suspension frame reinforcing beam via a lug, and the connection method is the same as that of the lateral support device 15 and the inner connecting plate 17 of the horizontal stabilizer suspension, which will not be described again here.

[0043] The lateral support device 15 of the present invention includes a lateral connecting rod 24 and an eccentric adjustment component 25. The lateral connecting rod 24 is used to connect the rear fuselage horizontal stabilizer suspension frame reinforcing beam to the horizontal stabilizer suspension connecting plate 14, and includes a rod body and a first end and a second end located at opposite ends of the rod body. Each of the first and second ends has a first wing and a second wing extending parallel to each other and away from the rod body along the axial direction of the rod body. The first wing has a first through hole, and the second wing has a second through hole, and the first and second through holes are configured such that their central axes are aligned with each other.

[0044] The eccentric adjustment component 25 is configured to pass through the first and second through holes, and has an eccentric adjustment axis set such that there is an eccentric distance between the eccentric adjustment component 25 and the central axis of the through holes as it passes through the first and second through holes. The eccentric adjustment component 25 is configured to be rotatable after passing through the first through hole, the lug hole on the rear fuselage horizontal stabilizer frame reinforcement beam or the horizontal stabilizer connecting plate 14, and the second through hole, thereby causing the eccentric adjustment axis to rotate about the central axis of the through holes, thus continuously adjusting the distance between the center of the lateral connecting rod 24 and the center of the lug hole.

[0045] As described above, the hole spacing of the lug holes in the rear fuselage horizontal stabilizer suspension frame reinforcing beam and the horizontal stabilizer suspension connecting plate 14 cannot be precisely equal to the hole spacing of the through holes at both ends of the lateral support device 15. The lateral support device 15 of this invention can adjust the distance from the center of the lateral connecting rod 24 to the center of the lug hole of the rear fuselage horizontal stabilizer suspension frame reinforcing beam or the horizontal stabilizer suspension connecting plate 14 by rotating the eccentric adjustment component 25. This achieves continuous length adjustment to match the hole spacing of the lug holes in the rear fuselage horizontal stabilizer suspension frame reinforcing beam and the horizontal stabilizer suspension connecting plate 14, thereby eliminating accumulated manufacturing and assembly errors and tightly connecting the rear fuselage horizontal stabilizer suspension frame reinforcing beam and the horizontal stabilizer suspension connecting plate 14. Furthermore, the lateral support device of this invention has a simple structure, is easy to assemble, and has good assembly performance.

[0046] According to some embodiments, the eccentric adjustment component 25 includes a bushing assembly and a bolt assembly. The bushing assembly includes a first bushing 26 and a second bushing 27, the first bushing 26 being accommodating in a first through-hole and the second bushing 27 being accommodating in a second through-hole. Each of the first bushing 26 and the second bushing 27 includes a bushing body and a bushing through-hole, the bushing body being configured such that its axis is aligned with the central axis of the through-holes of the first and second through-holes, and an eccentric distance exists between the bushing body axis and the central axis of the bushing through-hole, this eccentric distance being equal to the eccentric distance between the central axes of the through-holes of the first and second through-holes and the eccentric adjustment axis.

[0047] The bolt assembly includes a bolt 28 and a nut 29. The bolt 28 is configured to pass sequentially through a bushing through-hole of the first bushing 26, a lug hole, and a bushing through-hole of the second bushing 27, such that the bolt axis coincides with the eccentric adjustment axis. The bolt 28 is further configured to engage with the first bushing 26 and the second bushing 27 to form a single unit. The threaded end of the bolt 28 extends beyond the bushing through-hole of the second bushing 27, allowing the nut 29 to be screwed onto the threaded end from the second bushing side.

[0048] When the bolt 28 is rotated, since the bolt 28 is engaged with the first bushing 26 and the second bushing 27 to form a whole, the bushing assembly can rotate together with the bolt 28, so that the bolt axis can rotate around the central axis of the through hole of the first wing and the second wing.

[0049] The lateral support device 15 also includes a locking assembly disposed on the outer surface of the first wing and near the first through hole. The locking assembly is configured to engage with the bolt 28 to lock the rotational movement of the bolt 28.

[0050] The bolt 28 engages with the bushing assembly, allowing the eccentric adjustment component to be rotated simply by rotating the bolt 28. This enables continuous variation in the length of the lateral support device 15 until assembly errors between the lateral support device 15 and the rear fuselage horizontal stabilizer frame reinforcement beam or horizontal stabilizer suspension connecting plate 14 are eliminated. Then, the rotation of the locking assembly locks the bolt 28, thereby fixing the length of the lateral support device 15 and achieving a tight connection between the lateral support device 15 and the rear fuselage horizontal stabilizer frame reinforcement beam or horizontal stabilizer suspension connecting plate 14.

[0051] According to some embodiments, in addition to the bolt 28 and nut 29, the bolt assembly also includes a washer 30 disposed between the outer surfaces of the nut 29 and the second bushing 27, and configured such that the bolt 28 engages with the second bushing 27 via the washer 30.

[0052] The washer 30 is a standard connector. The washer 30 allows the bolt 28 and the second bushing 27 to snap together as a whole, which helps to reduce the difficulty of operation and improve the assemblability.

[0053] According to some embodiments, the first bushing 26 and the second bushing 27 each include a flange extending radially outward at the end of the bushing body in a direction perpendicular to the axis of the bushing body. When the first bushing 26 is received in the first through hole, the surface of its flange near the bushing body contacts the outer surface of the first wing, and when the second bushing 27 is received in the second through hole, the surface of its flange near the bushing body contacts the outer surface of the second wing.

[0054] By constructing the bushing to include a bushing body and a flange, the assemblability of the bushing can be improved. For example, the flange provides convenience when placing and removing the bushing. The flange also enables the bushing to be stably held within the through-hole of the lateral connecting rod wing.

[0055] According to some embodiments, the first bushing 26 has a boss 31 extending away from the bushing body along the axial direction of the bushing through hole at one end near the outer surface of the first wing. The bolt 28 includes an extension that extends radially away from the bolt axis at the connection between the head and the screw. The extension has an opening 32 that passes through the extension along the bolt axis. The opening 32 is configured to receive the boss 31 of the first bushing so that the bolt 28 is engaged with the first bushing 26.

[0056] The second bushing 27 has a recess 33 formed at one end of the outer surface of the bushing through hole near the second wing, which is provided along the edge of the bushing through hole. The bolt 28 also includes a slot 34 extending along the bolt axis on the threaded surface at the end of the thread. The washer 30 includes a protrusion 35 extending radially on the inner circumferential surface in a direction toward the center of the washer. The thickness of the protrusion 35 is greater than the thickness of the washer, and the protrusion 35 is configured to be received in the recess 33 of the second bushing 27 and the slot 34 of the bolt 28 so that the bolt 28 and the second bushing 27 form a snap-fit ​​engagement.

[0057] By accommodating the boss 31 of the first bushing 26 within the opening 32 of the bolt 28 and the protrusion 35 of the washer 30 within the recess 33 of the second bushing 27 and the slot 34 of the bolt 28, the bolt 28 can be easily snapped into a whole with the first bushing 26 and the second bushing 27 without the aid of any tools, further improving assemblability.

[0058] According to some embodiments, the boss 31 of the first bushing 26 includes a pair of bosses that are radially opposite to each other relative to the bushing through hole and extend away from the bushing body along the axis of the bushing through hole, and the opening 32 of the extension includes a pair of openings that are radially arranged relative to the bolt axis, the pair of openings being configured to accommodate a corresponding boss of the pair of bosses of the first bushing 26.

[0059] Preferably, by configuring the bosses 31 of the first bushing 26 to be radially opposite each other relative to the bushing through-hole, and correspondingly configuring the openings 32 of the bolt extension to be radially opposite each other relative to the bolt axis, this configuration enhances the snap-fit ​​engagement between the bolt 28 and the first bushing 26, thereby improving operability. However, the number of the bosses 31 of the first bushing 26 and the corresponding openings 32 of the bolt extension is not limited to two; for example, there can be more than two.

[0060] According to some embodiments, the recess 33 of the second bushing 27 includes a pair of recesses arranged radially opposite each other along the edge of the bushing through hole, the bolt 28 includes a pair of slots 34 formed on the threaded surface at the thread end, extending along the bolt axis and arranged radially opposite each other, and the gasket 30 includes a pair of protrusions 35 extending radially opposite each other toward the center of the gasket on its inner circumferential surface, the thickness of the pair of protrusions 35 being greater than the thickness of the gasket, and configured to be received in corresponding recesses in the pair of recesses of the second bushing 27 and in corresponding slots in the pair of slots of the bolt 28.

[0061] Preferably, by configuring the recesses 33 of the second bushing 27 as a pair of recesses radially opposite to each other relative to the edge of the bushing through hole, correspondingly, the slots 34 at the ends of the bolt threads are also configured as a pair of slots radially opposite to the bolt axis, and the protrusions 35 of the washer 30 are also configured as a pair of protrusions radially opposite to each other on the inner circumferential surface, this configuration can enhance the snap-fit ​​engagement between the bolt 28 and the second bushing 27, thereby improving operability. However, the number of recesses 33 of the second bushing 27, slots 34 of the bolt 28, and protrusions 35 of the washer 30 is not limited to two, for example, it can be more than two.

[0062] According to some embodiments, a pair of bosses 31 are disposed on the flange of the first bushing 26. By disposing the bosses 31 on the bushing flange, the rotational torque of the bushing can be increased, improving the operability and assemblability of the device.

[0063] According to some embodiments, the extension of bolt 28 is configured as a gear 36 capable of engaging with a locking assembly, the opening 32 of the extension penetrating the spokes of gear 36 and communicating with the tooth groove. This configuration of the bolt extension can reduce manufacturing costs and improve operability and assemblability.

[0064] According to some embodiments, the locking assembly includes a toothed plate 37 that meshes with a gear on the bolt. This configuration of the locking assembly can further reduce manufacturing costs and improve operability and assemblability.

[0065] Preferably, the locking assembly includes a locking pin 38, a locking pin nut 39, a toothed plate 37, and a locking lever 40. Two locking pins are located near the through-hole of the first wing and have threads on their outer surfaces. The toothed plate 37 has a through-hole for receiving the locking pins to engage with the locking pin 38, and the toothed plate 37 has multiple teeth on the side near the gear 36 of the bolt 28 that mesh with the gear. The toothed plate 37 is fixedly connected to the lateral connecting rod 24 relative to the locking pin 38, the locking pin nut 39, and the locking lever 40. The locking pin nut 39 is threaded to the locking pin 38 and presses against the toothed plate 37. Both the locking pin 38 and the locking pin nut 39 have through-holes that can be aligned with each other. When the through-holes of the locking pin 38 and the locking pin nut 39 are aligned, the locking lever 40 is inserted into the through-hole to lock the rotational movement of the locking pin nut 39.

[0066] According to some embodiments, the bushing assembly further includes a lateral connecting rod bushing 41. The lateral connecting rod bushing 41 includes a bushing body and a flange extending radially outward at one end of the bushing body, perpendicular to the axis of the bushing body. The bushing body of the lateral connecting rod bushing 41 is received in a first through-hole and a second through-hole. The flange of the lateral connecting rod bushing 41 is close to the axis of the lateral connecting rod 24 and contacts the inner surfaces of the first and second wings. The first bushing 26 and the second bushing 27 are respectively received in the bushing through-holes of the lateral connecting rod bushing 41.

[0067] The lateral connecting rod bushing 41 reduces wear on the lateral connecting rod flange during rotation of the first bushing 26 and the second bushing 27, thereby improving operability. Preferably, the axial length of the lateral connecting rod bushing 41 is equal to the length of the bushing body of the first bushing 26 or the second bushing 27, and when the bushing body of the lateral connecting rod bushing 41 is accommodated in the first through hole and the second through hole, the surface of the flange of the lateral connecting rod bushing 41 near the axis of the lateral connecting rod 24 is flush with the end face of the bushing body of the first bushing 26 or the second bushing 27.

[0068] According to some embodiments, the rear fuselage horizontal stabilizer suspension frame reinforcement beam and the horizontal stabilizer suspension inner connecting plate 17 are configured to have lugs for receiving the bearing 42, and the lateral support device 15 also includes the bearing 42 disposed between the first wing and the second wing, with bolts 28 passing sequentially through the first bushing 26, the bearing 42 and the second bushing 27.

[0069] The lateral support device 15 can be connected to the lug hole of the rear fuselage horizontal tail suspension frame reinforcement beam or the horizontal tail suspension connecting plate 14 via the bearing 42. Thus, the lateral support device 15 can rotate relative to the rear fuselage horizontal tail suspension frame reinforcement beam or the horizontal tail suspension connecting plate 14, thereby changing the orientation of the lateral support device 15, optimizing the load transmission path, and improving the operability of the device.

[0070] According to some embodiments, the bearing 42 can be a spherical plain bearing, for example, a lubricated radial spherical plain bearing. Figure 7 As shown, the spherical bearing allows the lateral connecting rod 24 to rotate clockwise or counterclockwise around the center of the spherical bearing to deviate from the plane containing the lugs of the rear fuselage horizontal stabilizer suspension frame reinforcement beam or the horizontal stabilizer suspension connecting plate 14, thereby improving the operability and assemblability of the device. For example, this directional adjustment function of the spherical bearing is particularly important when the lug holes of the rear fuselage horizontal stabilizer suspension frame reinforcement beam and the horizontal stabilizer suspension connecting plate 14 are not on the same plane.

[0071] According to some embodiments, the bearing 42 can be an eccentric bearing. An eccentric bearing can further enhance the length adjustment capability of the lateral support device 15. For example, when the eccentricity of the bushing assembly is insufficient to compensate for errors, a suitable eccentric bushing can be selected to further eliminate the errors.

[0072] According to some embodiments, the lateral support device 15 further includes a bearing limiting washer 43. The bearing limiting washer 43 is passed through by the bolt 28 and is respectively disposed between the first bushing 26 and the bearing 42, and between the bearing 42 and the second bushing 27. The bearing limiting washer 43 can limit the relative movement of the bearing 42 and the bolt 28 along the bolt axial direction, ensuring the coordination of the length adjustment of the lateral support device 15 and the load path, thereby improving operability.

[0073] According to some embodiments, as shown in the figure, bolt 28 is a countersunk head hex bolt. Countersunk head hex bolts can further reduce weight.

[0074] According to some embodiments, as shown in the figure, the body of the lateral connecting rod 24 includes a plurality of recesses 44 arranged along the axis of the lateral connecting rod. These recesses 44 can further reduce the weight of the lateral connecting rod 24.

[0075] Preferably, the cross-section of the lateral connecting rod can also be I-shaped, C-shaped, or circular hollow, etc.

[0076] According to some embodiments, the eccentric distance between the eccentric adjustment axis of the eccentric adjustment component 25 and the central axis of the through hole can be zero or non-zero. When the eccentric distance is zero, the lateral support device does not have a length adjustment function.

[0077] Preferably, the eccentricity of the bushing assembly can be zero or non-zero. The required eccentricity at the end of the lateral connecting rod 24 can vary; therefore, the eccentricity of the bushing assembly can be selected as needed. For example, the eccentricity of the bushing assembly at one end of the lateral connecting rod can be greater than, equal to, or less than the eccentricity of the bushing assembly at the other end of the lateral connecting rod, or it can be zero. Therefore, the lateral support device 15 of the present invention can achieve a more flexible and continuous length adjustment function.

[0078] As an example, such as Figure 8As shown, the center point of the through hole in the lateral connecting rod wing represents the central axis of the through hole, and the point offset from the center point of the through hole in the lateral connecting rod wing represents the eccentric adjustment axis of the eccentric adjustment component passing through the through hole of the lateral connecting rod wing. The distance between these two points represents the eccentric distance. As an example, the initial eccentric distances at both ends of the lateral connecting rod are a1 and a2. When the bolt assembly and bushing assembly are installed in the through hole of the lateral connecting rod 24, the bolt axis coincides with the eccentric adjustment axis. Therefore, when the bolt assembly and bushing assembly are rotated as a unit, the bolt axis will rotate around the central axis of the through hole of the lateral connecting rod, causing the bolt to periodically and continuously approach or move away from the rod body of the lateral connecting rod 24, thereby achieving a continuous length adjustment function. Preferably, the initial position of the eccentric adjustment axis at one end of the lateral connecting rod is directly above the central axis of the through hole of the wing, and the initial position of the eccentric adjustment axis at the other end of the lateral connecting rod is directly below the central axis of the through hole of the wing. This arrangement allows for rapid adjustment of the length of the lateral support device.

[0079] Figure 9 This diagram illustrates the motion trajectory of the eccentric adjustment axis rotating around the central axis of the wing-shaped through-hole of the lateral connecting rod. In this diagram, the center represents the central axis of the wing-shaped through-hole of the lateral connecting rod, the circle represents the motion trajectory of the eccentric adjustment axis rotating around the central axis of the wing-shaped through-hole of the lateral connecting rod, the radius 'a' represents the eccentric distance, and θ represents the angle of rotation of the eccentric adjustment axis around the wing-shaped through-hole axis. When the bolt assembly and bushing assembly are installed in the wing-shaped through-hole of the lateral connecting rod 24, the bolt axis coincides with the eccentric adjustment axis. As an example, the gear modules of the bolts at both ends of the lateral connecting rod are m1 and m2, and the number of teeth of the bolt gears has been adjusted n1 and n2 respectively. The number of teeth of the bolt gears g1 and g2 also needs to be adjusted respectively, where m1, m2, n1, n2, g1, and g2 are all positive integers. The angle θ of rotation of the eccentric adjustment axis around the wing-shaped through-hole axis is:

[0080]

[0081] The length adjustment range of the lateral support device is:

[0082]

[0083] This invention discloses a method for implementing the length adjustment function of a lateral support device. According to some embodiments, the method includes the following steps:

[0084] (1) Arrange the main hinge 20 of the horizontal tail section between the outer connecting plate 16 and the inner connecting plate 17 of the horizontal tail suspension frame, such as Figure 4 As shown;

[0085] (2) The main hinge 20 of the flat tail is connected to the outer connecting plate 16 and the inner connecting plate 17 of the flat tail suspension frame by means of the flat tail bolt 21, the flat tail nut 22 and the flat tail suspension connecting plate bushing 23, such as Figure 5 As shown;

[0086] (3) Bearings are arranged in the lug holes of the upper half-frame 12, the lower half-frame 13, and the inner connecting plate 17 of the horizontal tail suspension frame, such as... Figure 7 As shown, and preferably, the distance from the center of the lug hole of the upper half frame 12 of the horizontal tail suspension to the center of the lug hole of the inner connecting plate 17 of the horizontal tail suspension frame is the same as the distance from the center of the lug hole of the lower half frame 13 of the horizontal tail suspension to the center of the lug hole of the inner connecting plate 17 of the horizontal tail suspension frame. This can be achieved, for example, by arranging an eccentric bearing in the lug hole.

[0087] (4) The lateral connecting rod is connected between the lugs of the upper half-frame reinforcing beam and the inner connecting plate of the horizontal tail suspension frame via the bushing assembly, bolt assembly, and bearing limiting washer. The bushing assembly and bolt assembly are snap-fitted together. Figure 7 As shown;

[0088] (5) The lateral connecting rod 24 is connected between the lugs of the lower half-frame reinforcing beam and the inner connecting plate 17 of the horizontal tail suspension frame via the bushing assembly, bolt assembly, and bearing limiting washer 43. The bushing assembly and bolt assembly are engaged with a snap-fit ​​mechanism. Figure 7 As shown;

[0089] (6) By rotating the bolt 28 with a tool and engaging it with the bushing assembly via a snap-fit, the bushing assembly rotates synchronously. The bolt 28 rotates around the central axis of the through hole in the lateral connecting rod wing, thereby causing the bolt stub of the bolt 28 to move closer to or further away from the rod body of the lateral connecting rod 24, thus adjusting the length of the lateral support device 15. Figure 7 and Figure 8 As shown;

[0090] (7) When the length of the lateral support device 15 reaches the ideal state, for example, the lateral support device 15 is tightly connected between the rear fuselage horizontal tail suspension frame reinforcing beam and the lug of the horizontal tail suspension frame inner connecting plate 17 without loosening, so that the toothed plate 37 meshes with the gear 36 of the bolt 28, tightens the locking nut 39 and passes the locking rod 40 through the through hole of the locking nut 39 and the locking rod 38, thereby locking the rotational movement of the bolt 28.

[0091] Specifically, when the lateral inertial load on the horizontal stabilizer is large or a large eccentricity is required, for example, when the cumulative manufacturing and assembly errors are large, the bushing assemblies at both ends of the lateral connecting rod are constructed as eccentric bushings with a non-zero or large eccentricity to reduce the stress on the lateral connecting rod. Conversely, when the lateral inertial load on the horizontal stabilizer is small or a small eccentricity is required, for example, when the cumulative manufacturing and assembly errors are small, the bushings at both ends of the lateral connecting rod are constructed as having a zero or small eccentricity.

[0092] The structure of the lateral support device described in this invention is not limited to the above embodiments. For example, the lateral connecting rod may include a rod body and a wing extending from both ends of the rod body along the axial direction of the rod body and away from the rod body, the wing having a through hole. Correspondingly, the rear fuselage horizontal stabilizer suspension frame reinforcing beam or horizontal stabilizer suspension connecting plate has two lugs to receive the wing of the lateral connecting rod. This configuration can also achieve the desired technical effect.

[0093] The lateral support device described in this invention has a simpler structure and lighter weight, reducing manufacturing difficulty and cost. The lateral support device of this invention allows for length adjustment via components such as eccentric bushings and bolt assemblies, thus eliminating the cumulative manufacturing and assembly errors of the rear fuselage horizontal stabilizer suspension frame and offering significant assembly advantages. The lateral support device of this invention allows for orientation adjustment via bearings, ensuring an optimal load path and further guaranteeing the length adjustment function of the lateral support device through bearings.

[0094] The present invention also provides a rear fuselage horizontal stabilizer suspension frame 10, which includes a lateral support device 15 and a horizontal stabilizer main hinge 20 as described above.

[0095] The present invention also provides an aircraft comprising the rear fuselage horizontal stabilizer suspension frame 10 as described above.

[0096] Those skilled in the art will recognize that the present invention is not limited to the preferred embodiments described above. They will also recognize that modifications and variations are possible within the scope of the appended claims. Furthermore, through a study of the drawings, the disclosure, and the appended claims, those skilled in the art will be able to understand and implement variations of the disclosed embodiments.

Claims

1. A lateral support device for the rear fuselage horizontal stabilizer suspension frame of an aircraft, comprising: A lateral connecting rod is used to connect the reinforcing beam of the rear fuselage horizontal stabilizer suspension frame to the horizontal stabilizer suspension connecting plate, and includes a rod body and a first end and a second end located at both ends of the rod body, each of the first end and the second end having a first wing and a second wing extending parallel to each other and away from the rod body along the axial direction of the rod body, wherein the first wing has a first through hole and the second wing has a second through hole, and the first through hole and the second through hole are configured such that their through hole center axes are aligned with each other; An eccentric adjustment component is configured to pass through the first through hole and the second through hole, and the eccentric adjustment component has an eccentric adjustment axis, which is set such that there is an eccentric distance between the eccentric adjustment component and the central axis of the through hole when the eccentric adjustment component passes through the first through hole and the second through hole. The eccentric adjustment component is configured to be rotatable after passing through the first through hole, the lug hole on the lug of the reinforcing beam or the flat tail suspension connecting plate, and the second through hole, thereby causing the eccentric adjustment axis to rotate about the central axis of the through hole, thereby continuously adjusting the distance between the center of the lateral connecting rod and the center of the lug hole.

2. The lateral support device according to claim 1, wherein, The eccentricity adjustment component includes: A bushing assembly comprising a first bushing capable of being received in a first through-hole and a second bushing capable of being received in a second through-hole, the first bushing and the second bushing each comprising a bushing body and a bushing through-hole, the bushing body being configured such that the bushing body axis is aligned with the central axis of the through-hole, wherein the eccentricity between the bushing body axis and the central axis of the bushing through-hole is equal to the eccentricity between the central axis of the through-hole and the eccentricity adjustment axis; A bolt assembly comprising a bolt and a nut, the bolt being configured to pass sequentially through a bushing through-hole of a first bushing, a lug hole, and a bushing through-hole of a second bushing, such that the bolt axis coincides with the eccentric adjustment axis, and the bolt being configured to snap-fit ​​engage with the first and second bushings to form a single unit, wherein the threaded end of the bolt extends beyond the bushing through-hole of the second bushing, thereby allowing the nut to be screwed onto the threaded end from the second bushing side. When the bolt is rotated, the first bushing and the second bushing can rotate accordingly, allowing the bolt axis to rotate around the central axis of the through hole in the first and second wings. The lateral support device further includes a locking component disposed on the outer surface of the first wing, near the first through hole, and the locking component is configured to engage with the bolt to lock the rotational movement of the bolt.

3. The lateral support device according to claim 2, wherein, The bolt assembly also includes a washer disposed between the outer surfaces of the nut and the second bushing and configured such that the bolt engages with the second bushing via the washer.

4. The lateral support device according to claim 3, wherein, Both the first bushing and the second bushing include a flange extending radially outward at the end of the bushing body in a direction perpendicular to the axis of the bushing body. When the first bushing is accommodated in the first through hole, the surface of its flange near the bushing body contacts the outer surface of the first wing. When the second bushing is accommodated in the second through hole, the surface of its flange near the bushing body contacts the outer surface of the second wing.

5. The lateral support device according to claim 4, wherein, The first bushing has a boss at one end near the outer surface of the first wing, extending away from the bushing body along the axial direction of the bushing through hole. The bolt includes an extension extending radially away from the bolt axis at the connection between the head and the shank. The extension has an opening penetrating the extension along the bolt axis. The opening is configured to receive the boss of the first bushing so that the bolt engages with the first bushing. The second bushing has a recess formed at one end of the outer surface of the bushing through hole near the second wing, which is provided along the edge of the bushing through hole. The bolt also includes a slot extending along the bolt axis on the threaded surface at the thread end. The washer includes a protrusion extending radially toward the center of the washer on its inner circumferential surface. The thickness of the protrusion is greater than the thickness of the washer, and the protrusion is configured to be received in the recess of the second bushing and the slot of the bolt so that the bolt and the second bushing form a snap-fit ​​engagement.

6. The lateral support device according to claim 5, wherein, The first bushing has a pair of bosses that are radially opposite each other relative to the bushing through hole and extend away from the bushing body along the axis of the bushing through hole, and the opening of the extension includes a pair of openings radially disposed relative to the bolt axis, the pair of openings being configured to accommodate a corresponding boss of the pair of bosses of the first bushing.

7. The lateral support device according to claim 5, wherein, The second bushing has a pair of recesses arranged radially opposite each other along the edge of the bushing through hole. The bolt has a pair of slots formed on the threaded surface at the thread end, extending along the bolt axis and arranged radially opposite each other. The washer has a pair of protrusions arranged radially opposite each other on its inner circumferential surface toward the center of the washer. The thickness of the pair of protrusions is greater than the thickness of the washer, and they are configured to be received in corresponding recesses in the pair of recesses of the second bushing and in corresponding slots in the pair of slots of the bolt.

8. The lateral support device according to claim 6, wherein, A pair of bosses of the first bushing are disposed on the flange of the first bushing.

9. The lateral support device according to claim 5, wherein, The extension of the bolt is configured as a gear capable of engaging with the locking assembly, the opening penetrating the spokes of the gear and communicating with the tooth groove.

10. The lateral support device according to claim 9, wherein, The locking assembly includes a toothed plate that meshes with the gear.

11. The lateral support device according to claim 2, wherein, The bushing assembly further includes a lateral connecting rod bushing, the lateral connecting rod bushing including a bushing body and a flange extending radially outward at one end of the bushing body perpendicular to the axis of the bushing body, wherein the bushing body of the lateral connecting rod bushing is received in the first through hole and the second through hole, the flange of the lateral connecting rod bushing is close to the axis of the lateral connecting rod and contacts the inner surfaces of the first wing and the second wing, and the first bushing and the second bushing are respectively received in the bushing through hole of the lateral connecting rod bushing.

12. The lateral support device according to claim 2, wherein, The lateral support device also includes a bearing disposed between the first wing and the second wing, and the bolt passes through the first bushing, the bearing and the second bushing in sequence.

13. The lateral support device according to claim 12, wherein, The bearing in question is a spherical plain bearing.

14. The lateral support device according to claim 12 or 13, wherein, The bearing in question is an eccentric bearing.

15. The lateral support device according to claim 12, wherein, The lateral support device further includes bearing limiting shims, which are bolted through and respectively disposed between the first bushing and the bearing, and between the bearing and the second bushing.

16. The lateral support device according to claim 2, wherein, The bolt is a countersunk head hex bolt.

17. The lateral support device according to claim 1, wherein, The lateral connecting rod includes a plurality of notches arranged along the axis of the lateral connecting rod.

18. The lateral support device according to claim 1, wherein, The eccentricity distance between the eccentric adjustment axis of the eccentric adjustment component and the central axis of the through hole is zero.

19. A rear fuselage horizontal stabilizer suspension frame, the rear fuselage horizontal stabilizer suspension frame comprising a lateral support device and a horizontal stabilizer main hinge according to any one of the preceding claims, the horizontal stabilizer main hinge being disposed between horizontal stabilizer suspension connecting plates to connect the horizontal stabilizer.

20. An aircraft comprising a rear fuselage horizontal stabilizer suspension frame as claimed in claim 19.

Images