WO2019076341A1

WO2019076341A1 - Flap retraction and releasing apparatus

Info

Publication number: WO2019076341A1
Application number: PCT/CN2018/110845
Authority: WO
Inventors: 潘立军; 吴大卫; 谭兆光; 杨慧; 方阳; 司江涛
Original assignee: 中国商用飞机有限责任公司; 中国商用飞机有限责任公司上海飞机设计研究院
Priority date: 2017-10-18
Filing date: 2018-10-18
Publication date: 2019-04-25
Also published as: CN107719644B; CN107719644A

Abstract

A flap retraction and releasing apparatus (100), comprising: a support base (3), which is arranged along an air flow and can be fixedly connected to a fixed trailing edge of an aircraft wing; a first rotating shaft (6), which is rotatably mounted to the support base; a swing arm (5), one end (51) of the swing arm being fixedly connected to the first rotating shaft; a connecting rod (4), one end (41) of the connecting rod being pivotedly connected to the other end (52) of the swing arm, and a spherical hinge (411) being provided at the other end (42) of the connecting rod; and an auxiliary bearing member (1), which is provided with three spherical hinges (111) distributed in a triangular shape, the auxiliary bearing member being connected to the support base by means of one of the three spherical hinges, wherein the spherical hinge on the connecting rod and the other two spherical hinges of the three spherical hinges on the auxiliary bearing member are all connected to the lower side of an aircraft flap. The flap retraction and releasing apparatus has a simple structure and is easy to control; the structure is compact, so that the apparatus is light; it can be ensured that a fairing is provided along the air flow, and the size of the fairing is effectively reduced.

Description

Flap retracting device

Technical field

The present invention relates to a lift system, and more particularly to an aircraft flap retracting device.

Background technique

At present, the common flap retracting mechanism mainly has three forms: a simple hinge mechanism, a link rail mechanism and a four-bar linkage mechanism.

Simple hinge mechanisms are commonly used for single-slit flaps with fixed Fuller's motion or double-slit flaps with fixed fins that rotate around a certain axis. This mechanism is simple, lightweight, reliable, and easy to control, but at the same time has certain limitations. Firstly, since the trajectory of the flap is a fixed arc, it is difficult to achieve the aerodynamic optimum for the take-off and landing positions. Secondly, the fixed hinge allows the Fuller motion to be smaller, and the required fairing is larger than other devices. There is a big discount on aerodynamic performance.

The link rail mechanism has a wide range of applications and can basically achieve any aerodynamic design. The flaps are attached to the pulley frame. During the take-off and landing, the pulley frame is driven by the connecting rod to move along the sliding rails, so that the flaps reach the raised position of each design. Depending on the trajectory, the slide rails can be roughly divided into three categories: linear slides, circular slides and hook slides. Among them, the arc slide rail and the hook type slide rail control the position and the off angle of the flap at the same time through the shape of the slide rail; the linear slide rail controls the flap position through the slide rail, and the deflection angle of the flap is controlled by the deflection of the drive rod. The connecting rod slide mechanism can make the flaps reach the optimal design position, but the mechanism is heavy in weight, complicated in structure, and troublesome in maintenance and repair.

The four-bar linkage mechanism has higher aerodynamic efficiency, but the structure is more complicated, and maintenance and repair are more troublesome.

In addition, in order to avoid interference when the inner and outer flaps are lowered, various mechanisms have to use complicated mechanism design, which pays a lot of pneumatic and weight.

Therefore, there is a need in the art for a flap retracting mechanism that is structurally simple and easy to control.

Summary of the invention

The invention provides an aircraft flap retracting device, which has the advantages of simple structure and easy control, compact structure and light weight, and the size of the fairing is effectively reduced while ensuring that the mechanism fairing can be arranged along the airflow. Specifically, the aircraft flap retracting device includes:

a support disposed in the airflow and fixedly coupled to the fixed trailing edge of the aircraft wing;

a first rotating shaft, the first rotating shaft is rotatably mounted to the support;

a rocker arm, one end of the rocker arm is coupled to the first rotating shaft;

a connecting rod, one end of the connecting rod is pivotally connected to the other end of the rocker arm, and the other end of the connecting rod is provided with a ball joint;

An auxiliary support member, wherein the auxiliary support member is provided with three ball joints arranged in a triangle shape, and the auxiliary support member is connected to the support through one of the three ball joints;

Wherein the ball joint on the link and the other two of the three ball joints on the auxiliary support are used to connect to the underside of the aircraft flap.

In a preferred embodiment, the first shaft is coupled to the gearbox and is drivable by the gearbox.

In a preferred embodiment, the gearbox is mounted to the mount and is coupled to an output shaft of the motor.

In a preferred embodiment, the auxiliary support member is a "Y" shaped bracket, and three ball joints provided on the auxiliary support member are disposed at the ends of the three branches of the "Y" shaped bracket.

In a preferred embodiment, the auxiliary support member is a "V" shaped bracket, and three ball joints provided on the auxiliary support member are respectively disposed at a bottom apex and two branches of the "V" shaped bracket. Ends.

In a preferred embodiment, the support is provided with two support plates on the rocker arms and on both sides of the link.

In a preferred embodiment, at least two mutually spaced apart support blocks are fixedly connected to the support plate between the two support plates.

In a preferred embodiment, the first shaft is rotatably mounted to the two support plates.

In a preferred embodiment, the rocker arm and the link are pivotally connected by a second axis of rotation parallel to the first axis of rotation.

In a preferred embodiment, the auxiliary support member is pivotally coupled to the two support plates by a third rotational axis parallel to the first rotational axis, and the third rotational shaft and the auxiliary support member One of the three ball joints is fixedly connected.

In a preferred embodiment, the support is arranged in a gas flow.

In a preferred embodiment, the aircraft flap retracting mechanism is used to control the outer flaps of the aircraft.

In a preferred embodiment, the aircraft flap retracting device is used to control the inner flap of the aircraft.

In a preferred embodiment, the aircraft flap retracting device is used to control the control rudder surface at a large sweep angle.

An aircraft equipped with the above-described aircraft flap retracting device.

Additional features and advantages of the flap-retracting mechanism described herein will be set forth in the detailed description which follows, and will be appreciated by those skilled in the <RTIgt; These descriptions include the following detailed description, claims, and drawings.

It is to be understood that the foregoing general descriptions The drawings are included to provide a further understanding of the various embodiments and the accompanying drawings are incorporated in this specification. The drawings illustrate various embodiments of the invention, and, together with

DRAWINGS

The present invention is clearly described in the following claims, and the advantages thereof will be apparent from the following detailed description of the accompanying drawings The scope of the inventive concept is limited.

Figure 1 shows a perspective view of an aircraft flap retracting device in accordance with the present invention.

Figure 2 shows a schematic side view of the rocker arm and linkage assembly of the aircraft flap retracting device of Figure 1.

Figure 3 shows a schematic perspective view of the auxiliary support of the aircraft flap retracting device of Figure 1.

Figure 4 is a schematic illustration of the installation position of an aircraft flap retractor in accordance with the present invention.

Figure 5 shows an exploded view of an aircraft flap retracting device in accordance with the present invention.

List of reference signs

1 auxiliary support

2 third shaft

3 support

4 connecting rod

5 rocker arm

6 first shaft

7 support block

8 gearbox

9 second shaft

13 support plate

41 one end of the connecting rod

42 the other end of the connecting rod

51 One end of the rocker

52 the other end of the rocker

111,411 ball hinge

Detailed ways

Reference will now be made in detail to the various embodiments of the invention, While the invention will be described in conjunction with the exemplary embodiments, it is understood that the invention is not intended to limit the invention to those exemplary embodiments. Rather, the invention is intended to cover various alternatives, modifications, and equivalents, implementation plan. The terms "upper", "lower", "inner" and "outer" are used to refer to the positions of the features of the exemplary embodiments shown in the figures for the purpose of the description and the precise definition. Describe.

Because of the upper contra and the sweep angle, the outer flap of the aircraft has no fixed shaft when moving in the forward direction. It is a reciprocating and rotating composite motion, and there is also a displacement. Therefore, the motion of the outer flap is a six-degree-of-freedom motion. In the design of the mechanism, the complexity of the movement must be fully considered, and the reasonable constraints should be designed to ensure the normal operation of the flap movement. The motion of the trailing edge flap follows the principle of "equal percent chord length". Since the plane of the wing is roughly trapezoidal, the movement of the two actuators on the same flap rudder surface is not synchronized, and the design requires careful calculation and Analysis of sports relations. Pneumatically requires the inner and outer flaps to move synchronously. However, under the condition that the same set of torsion tubes transmit power, the same angle of the inner and outer flaps can be theoretically impossible to achieve, and the error can only be minimized when the design position is reached. Therefore, after installing the motion mechanism, it is necessary to check the aerodynamic performance to ensure that the aerodynamic performance error is within a reasonable design range. In view of these factors, the aircraft flap retracting device of the present invention has been made.

Exemplary embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

An aircraft flap retracting device 100 in accordance with the present invention is shown in FIG. The aircraft flap retracting device 100 includes a support 3, a first rotating shaft 6, a rocker arm 5, a connecting rod 4, and an auxiliary support member 1. The support 3 is disposed along the airflow and can be fixedly coupled to the fixed trailing edge of the aircraft wing to support other components of the flap retractor 100. The first rotating shaft 6 is rotatably mounted to the support 3 such that the first rotating shaft 6 is rotatable about its own axis within the support 3.

Referring also to Figures 2 and 4, the rocker arm 5 is fixedly coupled at its one end 51 to the first shaft 6 to be rotatable with the first shaft 6. The link 4 is pivotally coupled at its one end 41 to the other end 52 of the rocker arm 5 such that one end 41 of the link 4 is pivotable relative to the other end 52. And the other end 42 of the connecting rod 4 is provided with a ball joint 411 for connecting to the lower side of the flap of the aircraft, so that when the first rotating shaft 6 is driven to rotate, the rocking arm 5 is driven to rotate, thereby driving the connecting rod 4 Apply thrust or tension to the underside of the flap.

The auxiliary support member 1 is provided with three ball joints 111 arranged in a triangular shape. One of the three ball hinges 111 is coupled to the support 3, and the other two ball hinges 111 are both connected to the underside of the aircraft flap. Due to the arrangement of the auxiliary support member 1, when the link 4 exerts a thrust on the flap for deployment, the flap has a function of the three ball joints 111, so that the flap has a displacement outward in the downward bias. When the device is used for the outer flap, the interference with the inner flap can be effectively avoided, and the gap between the inner and outer flaps can be effectively reduced.

Specifically, the first rotating shaft 6 is coupled to the gear case 8 and is drivable by the gear case 8 for rotational movement. Alternatively, the first shaft 6 can also be the output shaft of the gearbox 8. The gearbox 8 can be mounted on the support 3 or mounted to the fuselage and connected to the output shaft of the motor for rotation by the motor.

The auxiliary support 1 may be configured in different forms as long as the three ball joints 111 arranged in a triangle shape can be arranged and the ball joints 111 are respectively connected to the support 3 and the lower side of the flaps. In the embodiment shown in Fig. 3, the auxiliary support 1 is a "Y" shaped bracket, and the three ball joints 111 of the auxiliary support 1 are respectively disposed at the ends of the three branches of the "Y" shaped bracket. Of course, it is conceivable that the auxiliary support 1 can also be formed as a "V" shaped bracket, and the three ball joints 111 of the auxiliary support 1 are respectively arranged at the bottom apex of the "V" shaped bracket and the ends of the two branches. In this case, in order to facilitate the mounting of the two ball hinges 111 to the underside of the flaps, it is preferable that the ball joint 111 provided at the bottom apex of the "V" shaped bracket is connected to the holder 3, and the other two ball hinges 111 Connect the underside of the flap.

Preferably, the support 3 is provided with two support plates 13 respectively located on both sides of the rocker arm 5 and the link 4. At least two mutually spaced apart support blocks 7 fixedly connected to the support plate are arranged between the two support plates 13 to reinforce the support 3.

The first rotating shaft 6 is rotatably mounted to the two support plates 13.

Preferably, the rocker arm 5 and the connecting rod 4 are pivotally connected by a second rotating shaft 9 parallel to the first rotating shaft 6, thereby changing the rotational speed and direction transmitted by the drive shaft. It is also preferred that the auxiliary support 1 is pivotally connected to the two support plates 13 by a third rotary shaft 2 parallel to the first rotary shaft 6, and the third rotary shaft 2 and the three ball joints 111 on the auxiliary support member A ball hinge is fixedly connected.

The aircraft flap retracting device according to the invention is particularly suitable for controlling the outer flap of an aircraft. The advantage is obvious when controlling the outer flaps of the aircraft, but the device can also be used to control the inner flaps of the aircraft and the control rudder surface with a large sweep angle. The mounting position of the aircraft flap retracting device 100 on the flap of the aircraft is shown in FIG.

The main benefits of the present invention are:

1. Due to the arrangement of four ball hinges, the four ball joints can make the outer flaps have a displacement along the outward direction during the downward deflection process, which effectively avoids the interference with the inner flaps. And effectively reduce the gap between the inner and outer flaps;

2. Due to the setting of the auxiliary support member, it can effectively carry three ball joints, so that the structure is compact and the weight is reduced;

3. Due to the arrangement of the airflow of the support, the size of the fairing can be effectively reduced while ensuring that the fairing can be arranged along the flow;

4. Due to the simple ball hinge mechanism, the flap retracting device has a simple structure and easy control;

5. Due to the setting of the shifting and shifting gearbox, the speed and direction transmitted by the drive shaft can be effectively changed.

While the structure and working principles of the present invention have been described in connection with the preferred embodiments thereof, those skilled in the art will understand that the above examples are only illustrative and not limiting. Therefore, it is intended that the present invention cover the modifications and modifications of the inventions

Claims

An aircraft flap retracting device comprising:

a support (3), the support (3) is arranged in a gas flow and can be fixedly connected to a fixed trailing edge of the aircraft wing;

a first rotating shaft (6), the first rotating shaft (6) is rotatably mounted to the support (3);

a rocker arm (5), one end (51) of the rocker arm (5) is fixedly connected to the first rotating shaft (6);

a connecting rod (4), one end (41) of the connecting rod (4) is pivotally connected to the other end (52) of the rocker arm (5), and the other end of the connecting rod (4) 42) provided with a ball joint (411);

An auxiliary support (1), the auxiliary support (1) is provided with three ball joints (111) arranged in a triangle, and the auxiliary support (1) passes through the three ball joints (111) One of the connections to the support (3);

The ball joint (411) on the link and the other two ball joints (111) of the three ball joints (111) on the auxiliary support are both connected to the underside of the aircraft flap.
The aircraft flap retracting mechanism according to claim 1, wherein

The first shaft (6) is coupled to the gearbox (8) and is drivable by the gearbox (8).
The aircraft flap retracting mechanism according to claim 1, wherein

The gearbox is mounted to the mount (3) and is coupled to an output shaft of the motor.
The aircraft flap retracting mechanism according to claim 1, wherein

The auxiliary support (1) is a "Y" shaped bracket, and three ball joints (111) provided on the auxiliary support (1) are disposed at the ends of the three branches of the "Y" shaped bracket.
The aircraft flap retracting mechanism according to claim 1, wherein

The auxiliary support member (1) is a "V" shaped bracket, and three ball joints (111) provided on the auxiliary support member (1) are respectively disposed at a bottom vertex and two branches of the "V" shaped bracket The end.
The aircraft flap retracting mechanism according to claim 1, wherein

The support (3) is provided with two support plates (13) respectively located on both sides of the rocker arm (5) and the connecting rod (4).
The aircraft flap retracting mechanism according to claim 6 wherein:

Between the two support plates (13) there are provided at least two mutually spaced support blocks (7) fixedly connected to the support plates.
The aircraft flap retracting mechanism according to claim 6 wherein:

The first rotating shaft (6) is rotatably mounted to the two support plates (13).
The aircraft flap retracting mechanism according to claim 1, wherein

The rocker arm (5) and the connecting rod (4) are pivotally connected by a second rotating shaft (9) parallel to the first rotating shaft (6).
The aircraft flap retracting mechanism according to claim 6 wherein:

The auxiliary support (1) is pivotally connected to the two support plates (13) by a third rotating shaft (2) parallel to the first rotating shaft (6), and the third rotating shaft (2) is One of the three ball joints (111) on the auxiliary support is fixedly coupled.
The aircraft flap retracting mechanism according to claim 1, wherein

The support (3) is arranged in a gas flow.
The aircraft flap retracting mechanism according to claim 1, wherein

The aircraft flap retracting device is used to control the outer flap of the aircraft.
The aircraft flap retracting mechanism of claim 1 wherein said aircraft flap retracting means is for controlling an inner flap of the aircraft.
The aircraft flap retracting mechanism of claim 1 wherein said aircraft flap retracting means is for controlling a control rudder surface having a large sweep angle.
An aircraft characterized in that the aircraft is equipped with an aircraft flap retracting device according to any one of claims 1-14.