Airplane control surface double-control three-lug rocker arm connecting structure

Abstract

The invention relates to an airplane mechanical transmission technology, in particular to an airplane control surface double-control three-lug rocker arm connecting structure which comprises a rocker arm (1), a shaft pin (2), a support (3), a first single-lug connector (4), a second single-lug connector (5), a bolt connecting assembly, a shaft assembly, a fixed connecting assembly, a radial limiting assembly and a bearing (21). The aircraft control surface dual-control channel control rocker arm connecting structure is small in occupied space, switching of dual control modes can be carried out on control surface deflection, system layouts such as control surface control and structure are not affected, and the function of the aircraft control surface dual control modes is achieved with low weight cost and space occupation. And the structure is stable, the weight increase is small, the occupied space is small, and the safety is high.

Description

TECHNICAL FIELD

[0001] The present application relates to aircraft mechanical transmission technology, and particularly provides a double-control three-earpiece rocker arm connecting structure for an aircraft control surface. BACKGROUND At present, with the continuous innovation and development of aircraft design, the control mode of the aircraft control surface has also changed. From the original single-control mode, it has developed into a double-control channel mode with unmanned / human control. Often, the space of the aircraft control surface control area is narrow, and it is impossible to install a control rocker arm for each control channel. Therefore, based on the existing control space, a control rocker arm connecting structure is needed to realize the control of the double-control mode.

[0002] The Chinese utility model patent with publication number CN 207292387U discloses a "single-input double-output control rocker arm". The utility model comprises a single input end, a rotating shaft, a first output port, a second output port, an actuator and left and right system pull rods. The utility model mainly adopts a T-shaped rocker arm, and one input end synchronously controls two output ends. The utility model patent has the advantages of simple structure and easy installation, but the method cannot meet the demand that both control input ends can control one output end.

[0003] The Chinese invention patent with publication number CN 103661923B discloses a "semi-hidden elevator rocker arm". The main body of the invention is an "S"-shaped rocker arm. The rocker arm directly connects the left and right elevators through a symmetrical joint to form a whole. The rocker arm is semi-hidden, and only the control earpiece part is exposed. The force transmission path of the invention is short, and the girder directly participates in the force, reducing the assembly parts, but the method cannot meet the demand that both control input ends can control one output end.

[0004] The Chinese utility model patent with publication number CN 207191399U discloses a "full-movement tail control rocker arm connecting structure", which comprises a control rocker arm, a tail beam, bolts, gaskets, lock nuts and split pins. The utility model adopts a uniform width hole shaft cooperation surface to realize the connection and installation of the control rocker arm and the tail beam. It meets the strength, rigidity and installation requirements, and reduces the overall weight, but the method cannot meet the demand that both control input ends can control one output end.

[0005] The above-mentioned inventions or utility models about the aircraft control surface control rocker arm are different in configuration and working principle, and cannot solve the demand proposed in the present application. SUMMARY

[0006] The purpose of the present application is: The existing aircraft control surface operating rocker arm connecting structure cannot meet the double control channel mode, two operating rocker arms need to be installed to control the control surface, however, the space is often limited, the two operating rocker arm connecting structures cannot be installed, the installation space is insufficient, the implementation is difficult, and the maintenance is low.

[0007] The technical scheme of the present application is: The present application provides a double control three-ear piece rocker arm connecting structure for aircraft control surface, which comprises a rocker arm (1), a shaft pin (2), a support (3), a first single-ear piece joint (4), a second single-ear piece joint (5), a bolt connecting assembly, a shaft assembly, a fixed connecting assembly, a radial limiting assembly and a bearing (21). The rocker arm has a hollow shaft and a radial branch, the end of the radial branch forms three layers of ear pieces, the middle layer ear piece and the upper layer ear piece form a first double-ear piece structure, the middle layer ear piece and the lower layer ear piece form a second double-ear piece structure, the first single-ear piece joint (4) cooperates with the first double-ear piece structure to form a first control, and the second single-ear piece joint (4) cooperates with the second double-ear piece structure to form a second control; the shaft assembly penetrates the ear piece holes of the three layers of ear pieces, the first single-ear piece joint 4 and the second single-ear piece joint 5; the first control and the second control correspond to different control mechanisms, respectively. The support (3) has a mounting end and a shaft sleeve, the bearing 21 is mounted in the shaft sleeve; the mounting end is fixedly connected with the aircraft base body through the fixed connecting assembly. The shaft pin is a stepped shaft, the large diameter part of the stepped shaft is inserted into one end of the hollow shaft and forms a clearance fit, the large diameter part and the hollow shaft are provided with a radial connecting through hole and are fixed as a whole through the shaft connecting assembly; the small diameter part of the stepped shaft is inserted into the shaft sleeve and is rotatably supported through the bearing, and the radial limiting assembly is installed on the small diameter part to limit the small diameter part in the radial direction. Further, the other end of the hollow shaft is fixed with the aircraft control surface through a flange connecting assembly, and the flange connecting assembly comprises a bolt (6), a washer (7), a nut (8) and a split pin (9).

[0008] Further, the shaft assembly comprises a coupling shaft 11, a washer (12), a nut (13) and a split pin (14); the front end of the coupling shaft is a screw rod which cooperates with the nut, the washer is located between the nut and the ear piece, and the split pin penetrates the connecting shaft in the radial direction to form a limiting part.

[0009] Further, the fixed connecting assembly comprises a bolt (15), a washer (16) and a nut (17).

[0010] Further, the clearance amount of the clearance fit is 0.093mm-0.02mm.

[0011] Further, the radial limiting assembly comprises a washer (18), a nut (19) and a split pin (20).

[0012] Further, the bolt connecting assembly comprises a conical bolt (10), an arc washer (22), a nut (23) and a split pin (24). When the radial connecting hole is worn, the nut (23) can be rotated to be re-tightened with the conical bolt.

[0013] Further, the lug hole of the three-layer lug and the single lug is provided with a shoulder bushing (25).

[0014] Further, the first single lug joint 4 and the second single lug joint 5 are connected with a pull rod or a cable.

[0015] Further, the radial branch is two and is symmetrically arranged relative to the hollow shaft.

[0016] When the control mode of the first control is used, the first control drives the three-layer lug to rotate the rocker arm around the bearing (21) in the support (3), and drives the control surface to deflect through the rotation of the radial branch. In this process, the second control is in a relaxed state (free state / force-free state), and follows the rocker arm to perform load-free following; when the control mode of the second control is used, the second control drives the three-layer lug of the radial branch to rotate the rocker arm around the bearing (21) in the support (3), and drives the control surface to deflect through the rotation of the rocker arm (1). In this process, the first control is in a relaxed state, and follows the rocker arm (1) to perform load-free following.

[0017] The advantages of the present application are: The aircraft control surface double-control passage operating rocker arm connecting structure of the present application has small space occupation, can switch the double-control mode of the control surface deflection, does not affect the control, structure and other system layout of the control surface, realizes the function of the double-control mode of the aircraft control surface with small weight cost and space occupation, and has high safety. BRIEF DESCRIPTION OF DRAWINGS

[0018] Figure 1 : the structure schematic view of the present application; Figure 2 : the structure schematic view of the present application; Figure 3 : the installation schematic view of the present application; Figure 4 : the structure schematic view of the rocker arm; Figure 5 : the structure schematic view of the shaft pin; Figure 6 : the structure schematic view of the support; Reference signs: 1 - rocker, 2 - shaft pin, 3 - support, 4 - first single lug joint, 5 - second single lug joint, 6 - bolt, 7 - washer, 8 - nut, 9 - cotter pin, 10 - conical bolt, 11 - bolt, 12 - washer, 13 - nut, 14 - cotter pin, 15 - bolt, 16 - washer, 17 - nut, 18 - washer, 19 - nut, 20 - cotter pin, 21 - bearing, 22 - arc washer, 23 - nut, 24 - cotter pin, 25 - shoulder bushing. DETAILED DESCRIPTION

[0019] The disclosed examples will be described more fully hereinafter with reference to the accompanying drawings, in which some, but not all, of the disclosed examples are shown. Indeed, these examples can be described and should be viewed in the context of various other examples that can be described. These examples are described in order to provide what is believed to be the most useful and readily understood description of the examples covered, and no limitation of the scope of the examples is intended by illustrating the examples in this way. In fact, it will be apparent to those skilled in the art that various modifications can be made to the examples described without departing from the scope of the examples.

[0020] An aircraft control surface double control three-lug rocker connecting structure is provided, comprising a rocker (1), a shaft pin (2), a support (3), a first single lug joint (4), a second single lug joint (5), a bolt connecting assembly, a shaft assembly, a fixed connecting assembly, a radial limiting assembly, and a bearing (21); The rocker has a hollow shaft and a radial arm, the end of the radial arm forms three layers of lugs, the middle layer of lugs and the upper layer of lugs form a first double-lug structure, the middle layer of lugs and the lower layer of lugs form a second double-lug structure, the first single lug joint (4) cooperates with the first double-lug structure to form a first control, and the second single lug joint (4) cooperates with the second double-lug structure to form a second control; the shaft assembly passes through the lug holes of the three layers of lugs, the first single lug joint 4, and the second single lug joint 5; the first control and the second control correspond to different control mechanisms, respectively; The support (3) has a mounting end and a shaft sleeve, the bearing 21 is mounted in the shaft sleeve; the mounting end is fixedly connected with the aircraft base body through the fixed connecting assembly; The shaft pin is a stepped shaft, the large-diameter part of the stepped shaft is inserted into one end of the hollow shaft and forms a clearance fit, the large-diameter part and the hollow shaft are provided with a radial connecting through hole and are fixed as a whole through the shaft connecting assembly; the small-diameter part of the stepped shaft is inserted into the shaft sleeve and is rotatably supported through the bearing, and the radial limiting assembly is installed on the small-diameter part to limit the small-diameter part in the radial direction; The other end of the hollow shaft is fixed with the aircraft control surface through a flange connecting assembly, and the flange connecting assembly comprises a bolt (6), a washer (7), a nut (8), and a cotter pin (9).

[0021] The shaft assembly comprises a coupling shaft 11, a washer (12), a nut (13) and a cotter pin (14); the front end of the coupling shaft is a screw rod, which cooperates with the nut, the washer is located between the nut and the lug, and the cotter pin is radially penetrated through the coupling shaft to form a limit.

[0022] The fixed connection assembly comprises a bolt (15), a washer (16) and a nut (17).

[0023] The clearance of the clearance fit is 0.093mm-0.02mm.

[0024] The radial limit assembly comprises a washer (18), a nut (19) and a cotter pin (20).

[0025] The bolt connection assembly comprises a tapered bolt (10), an arc washer (22), a nut (23) and a cotter pin (24). When the radial connection hole is worn, the nut (23) can be rotated to be tightened with the tapered bolt again.

[0026] The lug hole of the three-layer lug and the single lug is provided with a shoulder bushing (25).

[0027] The first single lug joint 4 and the second single lug joint 5 are connected with a pull rod or a cable.

[0028] The radial branch is two and is symmetrically arranged relative to the hollow shaft.

[0029] The description of the different advantageous arrangements has been presented for purposes of illustration and description, but is not intended to be exhaustive or limited to the examples disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. Moreover, different advantageous examples can provide different advantages as compared to other advantageous examples. The chosen examples are selected to best explain the principles of the example, a practical application, and to enable others skilled in the art to best exploit the disclosure for a variety of embodiments and with various modifications as suitable for particular situations.

Claims

1. A dual-control, three-ear rocker arm connection structure for aircraft control surfaces, characterized in that: Includes rocker arm (1), shaft pin (2), support (3), first single-ear joint (4), second single-ear joint (5), bolt connection assembly, shaft assembly, fixed connection assembly, radial limiting assembly and bearing (21). The rocker arm has a hollow shaft and a radial support arm. The end of the radial support arm forms three layers of lugs. The middle lug and the upper lug form a first double lug structure, and the middle lug and the lower lug form a second double lug structure. The first single lug connector (4) cooperates with the first double lug structure to form a first control path, and the second single lug connector (4) cooperates with the second double lug structure to form a second control path. The shaft assembly passes through the lug holes of the three layers of lugs, the first single lug connector 4, and the second single lug connector 5. The first control path and the second control path correspond to different control mechanisms. The support (3) has an installation end and a bushing, and the bearing is installed in the bushing; the installation end is fixedly connected to the aircraft base through a fixed connection assembly; The shaft pin is a stepped shaft. The large-diameter part of the stepped shaft is inserted into one end of the hollow shaft and forms a clearance fit. The large-diameter part and the hollow shaft have radial connecting through holes and are fixed together by a shaft connecting assembly. The small-diameter part of the stepped shaft is removed into the bushing and is rotatably supported by the bearing. The radial limiting assembly is installed on the small-diameter part to radially limit the small-diameter part.

2. The aircraft control surface dual-control three-ear rocker arm connection structure according to claim 1, characterized in that: The other end of the hollow shaft is fixed to the aircraft control surface via a flange connection assembly, which includes bolts (6), washers (7), nuts (8), and cotter pins (9).

3. The aircraft control surface dual-control three-ear rocker arm connection structure according to claim 1, characterized in that: The shaft assembly includes a connecting shaft 11, a washer (12), a nut (13), and a cotter pin (14); the front end of the connecting shaft is a screw that cooperates with the nut, the washer is located between the nut and the lug, and the cotter pin radially penetrates the connecting shaft to form a limit.

4. The aircraft control surface dual-control three-ear rocker arm connection structure according to claim 1, characterized in that: The fixed connection assembly includes bolts (15), washers (16) and nuts (17).

5. The aircraft control surface dual-control three-ear rocker arm connection structure according to claim 1, characterized in that: The clearance for clearance fits is between 0.093 mm and 0.02 mm.

6. The aircraft control surface dual-control three-ear rocker arm connection structure according to claim 1, characterized in that: The radial limiting assembly includes a washer (18), a nut (19), and a cotter pin (20).

7. The aircraft control surface dual-control three-ear rocker arm connection structure according to claim 1, characterized in that: The bolted connection assembly includes a tapered bolt (10), an arc washer (22), a nut (23), and a cotter pin (24).

8. The aircraft control surface dual-control three-ear rocker arm connection structure according to claim 1, characterized in that: A shoulder bushing (25) is installed in the ear hole of both the three-layer ear piece and the single ear piece.

9. The aircraft control surface dual-control three-ear rocker arm connection structure according to claim 1, characterized in that: The first single-ear connector (4) and the second single-ear connector (5) are connected to the pull rod or cable.

10. The aircraft control surface dual-control three-ear rocker arm connection structure according to claim 1, characterized in that: There are two radial arms, which are arranged symmetrically with respect to the hollow axis.

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