An aircraft control surface suspension structure

Abstract

The application belongs to the technical field of aircraft control surface suspension structure design, and particularly relates to an aircraft control surface suspension structure, which comprises a force-bearing support arm, a control surface support arm, a suspension bolt, a bushing and a ball bearing. A single lug is formed on the force-bearing support arm, and the mounting hole on the single lug has an annular stop edge on one side and an annular press-fitting edge on the other side. Double lugs are formed on the control surface support arm and are located on both sides of the single lug. The suspension bolt passes through the mounting holes on the single lug and the double lugs, is matched with a nut threaded on the suspension bolt, and clamps the double lugs from the outside. The bushing has two bushings, is sleeved on the suspension bolt, and is located in the mounting holes of the double lugs. The ball bearing is sleeved on the suspension bolt and is located in the mounting hole on the single lug. The annular stop edge and the annular press-fitting edge are clamped at both ends of the outer ring of the ball bearing, and the annular press-fitting edge is in inclined contact with the corresponding end of the outer ring of the ball bearing in an outwardly inclined state.

Description

Technical Field

[0001] This application belongs to the field of aircraft control surface suspension structure design technology, and specifically relates to an aircraft control surface suspension structure. Background Technology

[0002] Aircraft control surfaces are typically suspended using a lunette-mounted self-lubricating bushing design. This allows the suspension bolts to effectively bear radial loads. However, some control surfaces generate loads not only radially but also axially, such as the gravitational load on the aircraft's vertical tail rudder. In existing lunette suspension systems, this load is balanced by the compression of the lunette end faces. During control surface rotation, this compression friction occurs between the lunette end faces and the bushings, leading to wear on both the lunettes and bushings. Figure 1 As shown, this can affect the positioning accuracy of the control surface, and in severe cases, it can even cause the control surface to jam.

[0003] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0004] The purpose of this application is to provide an aircraft control surface suspension structure to overcome or mitigate at least one of the known technical defects.

[0005] The technical solution of this application is:

[0006] An aircraft control surface suspension structure includes a load-bearing arm, a control surface arm, a suspension bolt, a bushing, and a ball bearing.

[0007] The load-bearing arm is formed with a single lug, and the mounting hole on the single lug has an annular stop edge on one side and an annular press-fit edge on the other side.

[0008] The rudder support arm has two lugs formed on both sides of the single lug;

[0009] The suspension bolts pass through the mounting holes on the single and double ear pieces and engage with the nuts connected to their threads to clamp the double ear pieces from the outside.

[0010] There are two bushings, which are fitted onto the suspension bolts and located in the mounting holes of the double lugs;

[0011] The ball bearing is fitted onto the suspension bolt and installed in the mounting hole on the single lug. The annular retaining edge and the annular press-fit edge are clamped at both ends of the outer ring of the ball bearing. The annular press-fit edge and the corresponding end of the outer ring of the ball bearing are in beveled contact and are in an outward inclined state.

[0012] According to at least one embodiment of this application, in the above-described aircraft control surface suspension structure, the outer end face of the nut has a serrated structure.

[0013] The suspension bolt is equipped with a stop pin, which is located in a corresponding serrated groove of the serrated structure.

[0014] According to at least one embodiment of this application, in the above-described aircraft control surface suspension structure, the inward end of each of the two bushings has an outward annular folded edge.

[0015] The two outward-facing annular flanges are located between the two ends of the ball bearing and the double lugs.

[0016] According to at least one embodiment of this application, in the above-described aircraft control surface suspension structure, the side of the single lug with an annular press-fit edge has an annular press-fit groove surrounding the annular press-fit edge.

[0017] According to at least one embodiment of this application, in the above-described aircraft control surface suspension structure, the annular press-fit edge is inclined outward at 45°.

[0018] According to at least one embodiment of this application, the above-described aircraft control surface suspension structure further includes a gasket;

[0019] The washer is fitted onto the suspension bolt, positioned between the nut and the double lugs. Attached Figure Description

[0020] Figure 1 This is a schematic diagram showing the location of wear caused by the squeezing friction between the end face of the lug and the bushing in the existing aircraft control surface suspension structure.

[0021] Figure 2 This is a schematic diagram of the aircraft control surface suspension structure provided in the embodiments of this application;

[0022] Figure 3 yes Figure 2 A partial schematic diagram;

[0023] Figure 4 This is a schematic diagram of the ball bearing being assembled into the mounting hole on the single lug provided in an embodiment of this application;

[0024] in:

[0025] 1-Support arm; 2-Rudder arm; 3-Suspension bolt; 4-Bushing; 5-Shim; 6-Ball bearing.

[0026] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0027] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0028] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0029] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0030] An aircraft control surface suspension structure, such as Figures 2-3 As shown, it includes a load-bearing arm 1, a rudder arm 2, a suspension bolt 3, a bushing 4, a gasket 5, and a ball bearing 6.

[0031] The load-bearing arm 1 is a load-bearing structure installed on the control surface of an aircraft. It has a single lug formed on it. The mounting hole on the single lug has an annular stop edge on one side and an annular press-fit edge on the other side, as well as an annular press-fit groove with a ring around the annular press-fit edge.

[0032] The control surface support arm 2 is a connection structure between the control surface and the load-bearing structure on the aircraft. It has double lugs formed on it, located on both sides of the single lug.

[0033] The suspension bolt 3 passes through the mounting holes on the single and double lugs and engages with the nuts connected to its threads to clamp the double lugs from the outside, thereby connecting the single and double lugs, that is, connecting the load-bearing arm 1 and the control surface arm 2, and realizing the suspension installation of the control surface on the aircraft.

[0034] The outer end face of the nut has a serrated structure to facilitate tightening of the nut, and a stop pin is provided on the suspension bolt 3. The stop pin is located in a corresponding serrated groove of the serrated structure to prevent the nut from loosening.

[0035] There are two bushings 4, which are fitted onto the suspension bolts 3 and are located in the mounting holes of the double lugs. The inward end has an outward annular folded edge.

[0036] The washer 5 is fitted onto the suspension bolt 3, positioned between the nut and the double lugs.

[0037] The ball bearing 6 is sleeved on the suspension bolt 3 and is set in the mounting hole on the single lug. The annular stop edge and the annular press-fit edge are clamped at both ends of the outer ring of the ball bearing 6. The two outward annular folded edges are located between the two ends of the ball bearing 6 and the double lugs. The annular press-fit edge is in contact with the corresponding end of the outer ring of the ball bearing 5 with a beveled fit and is in an outward tilted state, specifically, it can be tilted outward by 45°.

[0038] Before assembling the ball bearing 5 into the mounting hole on the single lug, the annular press-fit edge can be folded outwards and placed in the annular press-fit groove in an open state. This allows the ball bearing 5 to be placed into the mounting hole on the single lug without obstruction. After the ball bearing 5 is placed into the mounting hole on the single lug, the annular press-fit edge can be pressed inwards using a press-fit tool, pressing the annular press-fit edge onto the corresponding end of the outer ring of the ball bearing 5. The annular press-fit edge and the corresponding end of the outer ring of the ball bearing 5 will make beveled contact, thus completing the assembly of the ball bearing 5 into the mounting hole on the single lug.

[0039] The design incorporates a beveled contact between the annular press-fit edge and the corresponding end of the outer ring of the ball bearing 5, which is in an outward tilted state. On the one hand, this avoids large-angle compression and bending of the annular press-fit edge, which could cause damage. On the other hand, the outward tilt of the annular press-fit edge makes it easier to apply an outward folding force to fold it outward into the annular press-fit groove, thus facilitating the disassembly of the ball bearing 5.

[0040] In the aircraft control surface suspension structure disclosed in the above embodiments, ball bearings 5 ​​are used to suspend the control surface. This fully utilizes the characteristic of ball bearings 5 ​​to bear axial loads. Through the contact between the inner and outer rings of the ball bearings 5, the load generated by the control surface along the bolt axis is balanced. Furthermore, the relative rotation between the inner and outer rings of the ball bearings 5 ​​directly bears the extrusion friction, replacing the extrusion friction between the lugs and bushings. Since there is lubrication friction between the contact surfaces of the inner and outer rings of the ball bearings 5, wear is not easily generated, which can effectively ensure the positioning accuracy of the control surface and avoid control surface jamming.

[0041] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. An aircraft control surface suspension structure, characterized in that, Includes load-bearing arm (1), rudder arm (2), suspension bolt (3), bushing (4), and ball bearing (6); A single lug is formed on the load-bearing arm (1). The mounting hole on the single lug has an annular stop edge on one side and an annular press-fit edge on the other side. The rudder support arm (2) has two lugs formed on both sides of the single lug; The suspension bolt (3) is set through the mounting hole on the single ear piece and the double ear piece, and cooperates with the nut connected to its thread to clamp the double ear piece from the outside. There are two bushings (4), which are fitted onto the suspension bolts (3) and are located in the mounting holes of the double lugs; The ball bearing (6) is fitted onto the suspension bolt (3) and is set in the mounting hole on the single lug. The annular stop edge and the annular press-fit edge are clamped at both ends of the outer ring of the ball bearing (6). The annular press-fit edge and the corresponding end of the outer ring of the ball bearing (6) are in contact with each other by a bevel and are in an outward tilted state.

2. The aircraft control surface suspension structure according to claim 1, characterized in that, The outer end face of the nut has a serrated structure; The suspension bolt (3) is provided with a stop pin, which is located in a corresponding sawtooth groove of the sawtooth structure.

3. The aircraft control surface suspension structure according to claim 2, characterized in that, The two bushings (4) have outward-facing annular folds at their inward ends; The two outward-facing annular folds are located between the two ends of the ball bearing (6) and the double lugs.

4. The aircraft control surface suspension structure according to claim 3, characterized in that, One side of the single ear piece with an annular pressing edge has an annular pressing groove surrounding the annular pressing edge.

5. The aircraft control surface suspension structure according to claim 4, characterized in that, The annular pressing edge is tilted outward at 45°.

6. The aircraft control surface suspension structure according to claim 5, characterized in that, It also includes gaskets (5); The washer (5) is fitted onto the suspension bolt (3) and is located between the nut and the double lugs.

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