CN220010068U - Connection fastening device for actuator joint of flight control system - Google Patents

Abstract

The utility model relates to a connection fastening device for an actuator joint of a flight control system, comprising: a structural support; an actuator joint comprising an anti-reverse mechanism and a bearing; the tail part of the bolt is provided with a positioning opening in a shape like a Chinese character 'mi'; a lock nut; a cotter pin; a stop bushing provided with a wear pad portion; a sliding bush, the stopper bush and the sliding bush fastening the bearing in a radial and an axial direction; the independent locking clamping plate is fixedly connected with the structural support, is positioned between the bolt and the structural support and is used for preventing the bolt from rotating around the axis of the bolt; and a gasket. The utility model adopts a double-insurance fastening design that the locking nut is matched with the cotter pin and the locking clamping plate for fastening, can prevent the actuator joint from falling off caused by falling off of the bolt, is suitable for the installation of the actuator joint of the mainstream aircraft, and has strong adaptability.

Description

Connection fastening device for actuator joint of flight control system

Technical Field

The utility model relates to the technical field of aircraft structural design, in particular to a connecting and fastening device for an actuator joint of a flight control system.

Background

In the flight control system, main control surfaces such as ailerons, elevators and rudders are all controlled by actuators, and the actuators are required to be fastened and connected with a frame of a frame structure or a movable surface when being mounted. The connection of the actuator joint and the structural support of the flight control system can realize the core functions of the control load transmission, the control surface flutter suppression loop and the like of the aircraft, is a key ring of the flight control system to the control loop of the movable surface of the aircraft, and meanwhile, the connection fastening of the actuator is also a main link of the installation/disassembly and maintenance of the actuator.

The main flight control actuator is generally installed in the wing and tail wing cabins, and the installation space is relatively narrow, so that the device for connecting the actuator connector has a compact installation requirement, and has high requirements on the reliability and maintainability of the connection of the actuator connector.

At present, a single-insurance fastening installation mode is generally adopted for the connection mode of the actuator connector, and as shown in fig. 1, the actuator connector and the structural support are installed together through bolts; the cotter pin is matched and fastened with the locking nut through the pin shaft hole so as to prevent the bolt from loosening; the bearing is fastened through a flange bushing; the wear pad is in contact with an anti-deflection mechanism of the actuator to prevent wear to the structural support.

However, the above design has the following problems:

1) Because of the large fixed force and small allowable range of the bolts used for the installation of the main flight control actuator, the lock nut and cotter pin are difficult to mate when installing the bolts of the main flight control actuator. During installation, cotter pins need to pass through the slotted nuts and bolt holes, and too small a torque range can cause hole sites to be difficult to align, resulting in installation difficulties. And the single pinhole of bolt also is difficult to satisfy less fixed force scope requirement, can appear elongating artifical man-hour, reduce the problem of installation effectiveness.

2) The main flight control actuator joint is designed with an anti-reversion mechanism, which allows the main flight control actuator joint to be worn with the structure, ensures that the actuator has a certain deflection range along the axis, and prevents the joint from being blocked. The anti-abrasion gasket of the current installation structure is an independent round complete gasket, the weight of an installation part can be increased, and the anti-abrasion gasket is easy to drop and difficult to maintain and replace.

3) The main flight control actuator is used as a control surface executing structure, and the falling off and the breakage of the actuator joint can influence the steering capability of the aircraft. According to the requirements of the civil aircraft CCAR25.607, two independent sets of locking devices are required for both flight and landing that interfere with the normal piloting skills of the aircraft. Therefore, the connecting bolts of the main flight control actuator connector are required to adopt two sets of independent locking devices so as to prevent the actuator connector from falling off due to the falling off of the bolts after the fastening failure of the nuts, and further the organism structure is damaged.

Therefore, in view of the above, it is apparent that how to design a connection fastening device for an actuator joint of a flight control system, which can solve the above-mentioned technical problems, is a technical problem that needs to be solved in the art.

Disclosure of Invention

Based on the above-mentioned problems existing in the prior art, the present utility model aims to provide a dual-safety connection fastening device with simple structure, high reliability and convenient installation and disassembly, which can overcome the defects of the prior art to ensure the load transmission, flutter suppression, life safety and the like of an actuator joint of a flight control system.

The above object of the present utility model is achieved by providing a connection fastening device for an actuator joint of a flight control system, which adopts the following technical scheme:

the connection fastening device provided by the utility model comprises: the lug of the structural support is provided with a through hole; an actuator joint comprising an anti-reverse mechanism and a bearing; a bolt; a lock nut; the cotter pin is in fastening fit with the lock nut so as to prevent the lock nut from rotating relative to the bolt; a stop bushing; and a sliding bush, the stop bush and the sliding bush radially and axially fastening the bearing, the anti-reverse mechanism being engaged with the stop bush,

wherein the bolt tail may be provided with a locating opening in the shape of a Chinese character 'mi' and the stop bushing may be an integral stop bushing provided with a wear washer portion to prevent the anti-reverse mechanism of the actuator joint from wearing the structural bracket while tightening the bearing of the actuator joint.

According to the technical scheme, the connecting and fastening device provided by the utility model has the following beneficial technical effects: the self-made rice-shaped positioning opening at the tail part of the bolt in the connecting and fastening device can ensure that the bolt is in a smaller rotation range, so that the cotter pin and the bolt are matched conveniently, thereby facilitating fixed force.

Preferably, in some embodiments, the connection fastening device may further include a separate locking clip, where the locking clip is fixedly connected to the structural support, and the locking clip is located between the bolt and the structural support, so as to prevent the bolt from rotating around the axis of the bolt.

According to the technical scheme, the connecting and fastening device provided by the utility model has the following beneficial technical effects: the connecting and fastening device provided by the utility model has the advantages that the locking nut and the bolt can be prevented from rotating relatively by the fastening mode of matching the locking nut with the cotter pin, the independent locking clamping plate can further fix the bolt, and the locking clamping plate is simple in structure and convenient to install.

Preferably, in some embodiments, the wear pad portion of the stop bushing may be of a non-complete circular design to reduce component weight.

Preferably, in some embodiments, a washer may be provided between the lock nut and the structural support for preventing wear of the structural support.

Preferably, in some embodiments, the bolt may be a hex bolt and the lock nut may be a hex nut.

Preferably, in some embodiments, the diameter of the wear pad portion of the stop bushing corresponds to the anti-backup mechanism of the actuator joint, and the wear pad portion may contact the anti-backup mechanism of the actuator joint to prevent mutual wear of the anti-backup mechanism and the structural bracket.

Preferably, in some embodiments, the sliding bush is in clearance fit with the structural support, the stop bush is in interference fit with the structural support, and the bolt is in clearance fit with the bearing.

Preferably, in some embodiments, the bolt may be passed through the through-hole in the tab of the structural bracket, the through-hole of the actuator connector, the sliding bushing, the stop bushing and the washer to be in a tightening engagement with the lock nut to securely connect the actuator connector to the structural bracket, with the hexagonal head center of the locking clip being determined to be coaxial with the axis of the actuator connector during installation.

And in a more preferred embodiment, the bolt is not rotated until the threaded portion of the bolt does not pass completely through the sliding bush, the stopper bush or the bearing during installation to prevent scratches from being generated on the inner surface of the sliding bush, the stopper bush or the bearing.

Preferably, in some embodiments, the connection fastening device is used for actuator joint mounting of an aircraft.

In summary, the beneficial effects of the utility model are as follows:

because the connecting and fastening device adopts two independent locking devices, one is an independent locking clamping plate, and the other is a fastening mode of matching the locking nut with the cotter pin, the installation reliability of the actuator joint is greatly improved;

in addition, the self-designed bolt is adopted in the utility model, wherein the bolt is usually a hexagon bolt, and the tail part of the bolt is provided with a self-made positioning opening in a shape like a Chinese character 'mi', which is beneficial to matching of cotter pins and the bolt in a smaller rotation range, thereby facilitating fixed force and improving installation efficiency;

in addition, the utility model also adopts an autonomous design integrated stop bushing, the bushing has an anti-wear function, and an anti-wear gasket is not needed to be additionally added, so that the number of parts can be reduced and the maintainability can be improved.

Additional features and advantages of the connection fastening devices described herein will be set forth in the detailed description which follows, and in part will be readily apparent to those skilled in the art from that description or recognized by practicing the embodiments described herein, including the detailed description which follows, the claims, as well as the appended drawings.

It is to be understood that both the foregoing general description and the following detailed description present various embodiments and are intended to provide an overview or framework for understanding the nature and character of the claimed subject matter. The accompanying drawings are included to provide a further understanding of the various embodiments and are incorporated in and constitute a part of this specification. The drawings illustrate various embodiments described herein and, together with the description, serve to explain the principles and operation of the claimed subject matter.

Drawings

Technical features of the present utility model are clearly described in the following claims with reference to the above objects, and advantages thereof are apparent from the following detailed description with reference to the accompanying drawings, which illustrate preferred embodiments of the present utility model by way of example, without limiting the scope of the inventive concept.

FIG. 1 is a schematic cross-sectional view of a single-safety connection fastening apparatus employed in prior art actuator joints.

Fig. 2 is a schematic cross-sectional view of a preferred embodiment of a connection fastening device according to the present utility model.

Fig. 3 is a schematic perspective view of a bolt in a preferred embodiment of a connection fastening device according to the utility model.

Fig. 4 is a schematic view of the tail of a bolt in a preferred embodiment of a connection fastening device according to the utility model.

Fig. 5 is a schematic perspective view of a stop bushing in a preferred embodiment of a connection fastening device according to the utility model.

Fig. 6 is a schematic perspective view of a preferred embodiment of a connection fastening device according to the utility model mounted to a structural support.

List of reference numerals

1 structural support

2 actuator joint

3 bolt

4 lock nut

5 cotter pin

6 stop bushing

7 sliding bushing

8 bearing

9 locking clamp plate

10 anti-reversion mechanism

Detailed Description

Reference will now be made in detail to the various embodiments of the utility model, examples of which are illustrated in the accompanying drawings and described below.

While the utility model will be described in conjunction with the exemplary embodiments, it will be appreciated that the present description is not intended to limit the utility model to those exemplary embodiments. On the contrary, the utility model is intended to cover not only these exemplary embodiments, but also various alternatives, modifications, equivalents and other embodiments, which may be included within the spirit and scope of the utility model as defined by the appended claims.

For convenience in explanation and accurate definition in the appended claims, the terms "upper", "lower", "inner" and "outer" are used to describe features of the exemplary embodiments with reference to the positions of such features as displayed in the figures.

Fig. 2 shows a schematic cross-sectional structural view of a preferred embodiment of a connection fastening device for a flight control system according to the utility model. Wherein, this connection fastener mainly includes:

the structure bracket 1 is provided with through holes on lugs of the structure bracket 1;

an actuator joint 2, the actuator joint 2 comprising an anti-reverse mechanism 10 and a bearing 8;

a bolt 3, wherein the bolt 3 is preferably a hexagon bolt, and a positioning opening in a shape of a Chinese character 'mi' is arranged at the tail part of the bolt;

a lock nut 4, the lock nut 4 preferably being a hexagonal nut;

a cotter pin 5, the cotter pin 5 is tightly matched with the lock nut 4 to prevent the lock nut 4 and the bolt 3 from generating relative rotation;

a stop bush 6, the stop bush 6 preferably being an integrated stop bush provided with a wear-resistant pad portion to prevent the anti-reverse mechanism 10 of the actuator joint 2 from wearing the structural bracket 1 while tightening the bearing 8 of the actuator joint 2;

a slide bush 7, a stopper bush 6 and the slide bush 7 fasten the bearing 8 in the radial and axial directions;

an independent locking clamping plate 9, wherein the locking clamping plate 9 is fixedly connected with the structural support 1, and the locking clamping plate 9 is positioned between the bolt 3 and the structural support 1 so as to prevent the bolt 3 from rotating around the axis of the bolt; and

a washer is preferably provided between the lock nut 4 and the structural support 1 for preventing wear of the structural support 1.

Fig. 3 shows a schematic perspective view of a bolt 3 in a preferred embodiment of a connection fastening device according to the utility model, and fig. 4 shows a schematic view of a tail of a bolt 3 in a preferred embodiment of a connection fastening device according to the utility model. Wherein, this bolt 3 is preferably hexagon bolt to be equipped with the location opening of rice font at the bolt afterbody, this location opening of rice font has reduced at cotter 5 and the matching in-process pivoted angle scope of bolt 3, can reduce the cooperation degree of difficulty of bolt hole and nut when satisfying the less fixed force requirement of scope, thereby makes things convenient for the fixed force and improves installation and dismantlement efficiency.

Fig. 5 shows a schematic perspective view of a stop bushing 6 in a preferred embodiment of a connection fastening device according to the utility model. The stop bush 6 is preferably provided with an anti-wear pad portion, which integrates a conventional stop bush with an anti-wear pad, reduces the number of parts and at the same time can prevent the anti-reverse mechanism 10 of the actuator joint 2 from wearing the structural bracket 1 while fastening the bearing 8 of the actuator joint 2, and preferably the diameter of the anti-wear pad portion of the stop bush 6 corresponds to the distance of the anti-reverse mechanism 10 of the actuator joint 2 to the axis of the bolt 3, which is brought into contact with the anti-reverse mechanism 10 of the actuator joint 2 when the actuator joint 2 is subjected to vibration or slight left-right sliding, to prevent the anti-reverse mechanism 10 of the actuator joint 2 from rubbing against the structural bracket 1.

In a more preferred embodiment, the wear pad portion of the integrated stop bushing 6 may be of a non-complete circular design, minus the portion that would not contact the anti-backup mechanism 10 of the actuator joint 2, resulting in a lighter weight stop bushing 6.

Fig. 6 shows a schematic perspective view of a preferred embodiment of a connection fastening device according to the utility model mounted to a structural support. The installation steps of the connection fastening device are as follows:

firstly, it is determined that the center of the hexagonal head of the locking clamping plate 9 is coaxial with the axis of the actuator joint 2 so as to ensure that the hexagonal head of the bolt 6 does not interfere with the locking clamping plate 9 after the bolt 3 is installed;

then, the bolt 3 is fastened and matched with the lock nut 4 through the lug through hole of the structural bracket 1, the through hole of the actuator joint 2, the sliding bush 7, the stop bush 6 and the gasket, so as to fasten and connect the actuator joint 2 with the structural bracket 1, and the bolt guide pin installation method is used to enable the bolt to be installed smoothly;

meanwhile, it should be noted that during the installation, the bolt 3 is not rotated until the threaded portion of the bolt 3 does not completely pass through the sliding bush 7, the stopper bush 6 or the bearing 8, to prevent scratches from being generated on the inner surface of the sliding bush 7, the stopper bush 6 or the bearing 8. In addition, a fixed force wrench is needed during bolt installation, so that the requirement of connecting the actuator joint with fixed force is met.

Furthermore, it should be noted that during installation of the preferred embodiment, the sliding bushing 7 is in a clearance fit with the structural bracket 1, the stop bushing 6 is in an interference fit with the structural bracket 1, and the bolt 3 is in a clearance fit with the bearing 8 to better accommodate and absorb the vibrations that the actuator joint may encounter.

In a preferred embodiment, the connection fastening device may be used for actuator joint mounting of an aircraft and has structural advantages such as, but not limited to:

due to the double-insurance fastening design, the fastening mode of the locking nut matched with the opening pin and the locking clamping plate adopted by the actuator joint can effectively prevent the actuator joint from falling off caused by falling off of the bolt;

an integrated wear-resistant stop bushing which prevents the actuator joint from striking and causing wear to the tabs of the structural support and reduces the weight burden on the overall structure; and

the tail part is provided with the bolt with the opening in the shape of the Chinese character 'mi', which meets the requirement of small fixed force range of the bolt in the connecting and fastening device for the actuator joint, improves the mountability of the parts, reduces the mounting difficulty of workers and saves the operation time.

In the above embodiments, the connection fastening means for the actuator joint of a flight control system have been described, which are intended to be exemplary, not exhaustive or limiting.

It will be apparent to those skilled in the art that various modifications can be made in the full scope indicated by the broad general meaning of the terms expressed in the appended claims, especially in matters of structure, material, elements, components, shapes, sizes and arrangements of parts, including combinations of parts within the principles described herein. To the extent that such modifications do not depart from the spirit and scope of the appended claims, they are intended to be included therein.

The present utility model can be freely combined with each other, or can be appropriately modified and omitted within the scope of the present utility model.

Claims (10)

1. A connection fastening device for an actuator joint of a flight control system, comprising:

the structure comprises a structure bracket (1), wherein through holes are formed in lugs of the structure bracket (1);

an actuator joint (2), the actuator joint (2) comprising an anti-reverse mechanism (10) and a bearing (8);

a bolt (3);

a lock nut (4);

a cotter pin (5), wherein the cotter pin (5) is tightly matched with the lock nut (4) to prevent the lock nut (4) from rotating relative to the bolt (3);

a stop bush (6);

and a sliding bush (7), the stop bush (6) and the sliding bush (7) radially and axially fastening the bearing (8), the anti-reverse mechanism (10) being engaged with the stop bush (6),

characterized in that the tail part of the bolt (3) is provided with a positioning opening in a shape like a Chinese character 'mi' and

the stop bushing (6) is an integrated stop bushing provided with a wear-resistant gasket portion to prevent the anti-reverse mechanism (10) of the actuator joint (2) from wearing the structural bracket (1) while tightening the bearing (8) of the actuator joint (2).

2. The connection fastening device according to claim 1, further comprising a separate locking catch plate (9), said locking catch plate (9) being fixedly connected to the structural support (1), said locking catch plate (9) being located between the bolt (3) and the structural support (1) to prevent rotation of the bolt about the bolt axis.

3. The connection fastening device according to claim 1 or 2, characterized in that the wear pad portion of the stop bushing (6) is of a non-complete circular design to reduce component weight.

4. The connection fastening device according to claim 1 or 2, characterized in that a washer is provided between the lock nut (4) and the structural support (1).

5. The connection fastening device according to claim 1 or 2, characterized in that the bolt (3) is a hexagonal bolt and the lock nut (4) is a hexagonal nut.

6. The connection fastening device according to claim 1 or 2, characterized in that the diameter of the anti-wear pad portion of the stop bushing (6) corresponds to the anti-reverse mechanism (10) of the actuator joint (2), which anti-wear pad portion is in contact with the anti-reverse mechanism (10).

7. The connection fastening device according to claim 1 or 2, characterized in that the sliding bush (7) is in a clearance fit with the structural support (1), the stop bush (6) is in an interference fit with the structural support (1), and the bolt (3) is in a clearance fit with the bearing (8).

8. The connection fastening device according to claim 1 or 2, characterized in that, during installation, the bolt (3) is passed through the lug-on through hole of the structural bracket (1), the through hole of the actuator joint (2), the sliding bush (7), the stop bush (6) and a washer into a fastening fit with the lock nut (4) with the hexagonal head center of the locking catch plate (9) being determined coaxial with the axis of the actuator joint (2) to fasten the actuator joint (2) to the structural bracket (1).

9. The connection fastening device according to claim 1 or 2, characterized in that during installation, the bolt (3) is not rotated until the threaded portion of the bolt has not passed completely through the sliding bush (7), the stop bush (6) or the bearing (8) in order to prevent scratches from being produced on the inner surface of the sliding bush (7), the stop bush (6) or the bearing (8).

10. The connection fastening device of claim 1 or 2, wherein the connection fastening device is used for actuator joint installation of an aircraft.