阅读说明：本技术 一种襟翼整流罩机构 (Wing flap fairing mechanism ) 是由 陈炎 袁坚锋 林启洲 董萌 黄海峰 于 2021-08-31 设计创作，主要内容包括：一种用于飞机襟翼的整流罩机构包括：滑轨部,该滑轨部形成有轨道,轨道沿着飞机的前后方向且倾斜地延伸,在轨道上设置有滑动件,滑动件能够沿着轨道滑动；整流罩,该整流罩的前部具有至少一个前接头,其中,前接头可铰转地连接于滑轨部,且整流罩还包括至少一个中接头；以及至少一个拉杆,拉杆的一端可铰转地连接于滑动件,另一端可铰转地连接于中接头。该整流罩机构结构简化,在提高驱动机构运行可靠性的同时降低了加工和安装的难度。(A fairing mechanism for an aircraft flap comprising: a rail portion formed with a rail extending obliquely along a fore-and-aft direction of the aircraft, on which a slider is provided, the slider being slidable along the rail; a fairing having at least one forward joint at a forward portion thereof, wherein the forward joint is hingedly connected to the slide rail portion and the fairing further includes at least one intermediate joint; and at least one pull rod, one end of which is connected with the sliding part in an articulated way, and the other end of which is connected with the middle joint in an articulated way. The structure of the fairing mechanism is simplified, and the difficulty of processing and installation is reduced while the operation reliability of the driving mechanism is improved.)

1. A fairing mechanism for an aircraft flap, the fairing mechanism comprising:

a rail portion formed with a rail extending obliquely along a fore-and-aft direction of the aircraft, the rail being provided with a slider that is slidable along the rail;

a fairing having at least one forward joint at a forward portion thereof, wherein the forward joint is hingedly connected to the slide rail portion and the fairing further comprises at least one mid joint; and

and one end of the pull rod is connected with the sliding piece in a hinged mode, and the other end of the pull rod is connected with the middle joint in a hinged mode.

2. The fairing mechanism of claim 1 including two said front joints, one of said front joints being a front left joint connected to said runner section on a left side of said runner section and the other of said front joints being a front right joint connected to said runner section on a right side of said runner section.

3. The fairing mechanism of claim 1 wherein said slider is a pulley yoke.

4. The fairing mechanism as recited in claim 1, further comprising at least one aft joint at an aft portion of said fairing, a strut assembly hingedly connected between said aft joint and said skid rail portion.

5. The fairing mechanism of claim 4 including one said aft joint, said aft joint being located at an intermediate position in a direction perpendicular to a longitudinal direction of said fairing.

6. The fairing mechanism of claim 5 wherein said strut assembly comprises a first strut and a second strut, wherein one end of said first strut is hingably connected to said slide rail portion, the other end of said first strut is hingably connected to one end of said second strut, and the other end of said second strut is hingably connected to said aft joint.

Technical Field

The invention relates to the field of aircraft, in particular civil aircraft, and in particular to the structure of a flap fairing of an aircraft wing.

Background

Aircraft, in particular civil aircraft, are provided with flaps on their leading and trailing edges. The flaps may deflect downward and/or slide forward and backward, thereby increasing lift to the aircraft during flight of the aircraft. The flaps arranged on the trailing edge of the wing are subjected to a so-called fuller movement, in particular, they lie against the lower surface of the wing at ordinary times, and in use they are retracted along a slide rail mounted on the lower surface of the wing and are deflected downward. To achieve this fuller movement, the aircraft is also provided with a drive mechanism for driving the flaps into fuller movement.

The drive mechanisms used to drive the flap movement are irregularly shaped and can negatively impact the aerodynamic characteristics of the aircraft wing, such as increased aerodynamic drag. Therefore, flap fairings are required to house the drive mechanism. Through setting up the wing flap radome fairing, can reduce the aerodynamic drag because of actuating mechanism causes, moreover, this wing flap radome fairing still can play the effect that the actuating mechanism of protection wing flap does not receive external object impact damage.

When the flap performs the fuller movement, the flap fairing also moves along with the flap to avoid interfering with the flap and its drive mechanism. Also, the envelope of the flap fairing during motion is also as small as possible to reduce drag.

An existing fairing includes a shell and a tail cone, with a hinge assembly disposed between the shell and the tail cone, which interface assembly moves the tail cone during a fuller movement of the flap and shapes the fairing into a streamlined shape, thereby reducing drag during movement of the fairing with the flap.

However, such hinge assemblies are relatively complex and have a relatively high risk of jamming during movement. Once stuck, the fairing cannot follow the predetermined trajectory. Moreover, the attached hinge assembly also results in an increase in the weight of the aircraft, reducing the overall economy of the aircraft.

Accordingly, there is a need for an improved cowl structure that overcomes the problems with the prior art discussed above.

Disclosure of Invention

The present invention has been made to solve the above-mentioned problems occurring in the prior art. It is an object of the invention to provide a structurally improved flap fairing mechanism which is simple in construction and which reliably enables the flap fairing to follow the movement of the flap fairing in a fullerene manner.

The fairing mechanism for an aircraft flap of the invention comprises: a rail portion formed with a rail extending obliquely along a fore-and-aft direction of the aircraft, on which a slider is provided, the slider being slidable along the rail; a fairing having at least one forward joint at a forward portion thereof, wherein the forward joint is hingedly connected to the slide rail portion and the fairing further includes at least one intermediate joint; and at least one pull rod, one end of which is connected with the sliding part in an articulated way, and the other end of which is connected with the middle joint in an articulated way.

The fairing mechanism with the structure can simplify the structure of the driving mechanism of the fairing, improve the operational reliability of the driving mechanism and reduce the difficulty of processing and installation.

In a preferred embodiment, the front joint comprises two front joints, one of the front joints is a front left joint, the front left joint is connected to the slide rail part at the left side of the slide rail part, the other of the front joints is a front right joint, and the front right joint is connected to the slide rail part at the right side of the slide rail part.

In another specific structure, the sliding member is a pulley yoke.

To increase the structural rigidity of the fairing, the fairing may further comprise at least one rear joint at the rear of the fairing, between which a strut assembly is hingeably connected.

In a particular arrangement, an aft joint is included, the aft joint being located at an intermediate position in a direction perpendicular to the longitudinal direction of the fairing.

Further, the stay bar assembly comprises a first stay bar and a second stay bar, wherein one end of the first stay bar is hingably connected to the sliding rail part, the other end of the first stay bar is hingably connected to one end of the second stay bar, and the other end of the second stay bar is hingably connected to the rear joint.

Drawings

The embodiments of the invention will become more apparent from the structure illustrated in the accompanying drawings, in which:

FIG. 1 shows a bottom perspective view of an aircraft with the fairing mechanism of the present invention installed.

FIG. 2 illustrates a perspective view of the fairing mechanism of the present invention.

FIG. 3 illustrates a side view of the fairing mechanism shown in FIG. 2 in a stowed state.

FIG. 4 illustrates a side view of the fairing mechanism shown in FIG. 2 in a lowered position.

Detailed Description

The following detailed description of embodiments of the invention refers to the accompanying drawings. It is to be understood that the preferred embodiments of the present invention are shown in the drawings only, and are not to be considered limiting of the scope of the invention. Various obvious modifications, changes and equivalents of the embodiments of the invention shown in the drawings can be made by those skilled in the art, and all of them are within the scope of the invention.

In the following detailed description of the present invention, terms indicating directions and orientations such as "upper", "lower", "front", "rear", "left", "right", and the like are used with reference to an orientation generally adopted by an aircraft, for example, an orientation during flight, and it is understood that the orientation of the aircraft may be changed as necessary.

Fig. 1 shows a perspective bottom view of an aircraft 1. The aircraft 1 includes a wing 10, a flap 20 provided at a trailing edge of the wing 10, and a cowling mechanism 100 provided below the flap 20, the cowling mechanism 100 being movable with movement of the flap 20.

Fig. 2 illustrates a perspective view of the fairing mechanism 100, the fairing mechanism 100 including a slide rail portion 110 and a fairing 120. The fairing 120 is movable relative to the slide 110 by means of a drive mechanism as will be described in detail below.

As shown in fig. 2 to 4, the rail portion 110 is formed with a rail 111, and the rail 111 extends along the front-rear direction of the aircraft and is inclined. A slider, a specific example of which is a pulley frame 131, is provided on the rail 111. The pulley frame 131 can slide along the obliquely extending rail 111, thereby changing its position in the front-rear direction and in the up-down direction.

Two joints, i.e., a front left joint 121 and a front right joint 122, are respectively provided at both sides of the front portion of the cowl 120, and the front left joint 121 and the front right joint 122 are hinged at both sides of the rail portion 110 by, for example, a hinge lever 112.

A center joint 123 is provided at a substantially middle position of the cowl 120, and the center joint 123 is connected to the pulley frame 131 by a tie rod 132. The pull rod 132 is hingedly connected to the pulley holder 131 at one end and to the center joint 123 at the other end. In fig. 2, only the center joint 123 and the tie rod 132 provided on one side, i.e., the left side, of the rail portion 110 are shown. It is contemplated by those skilled in the art that the middle joint 123 and the corresponding tie rod 132 may be provided on the other side, i.e., the right side, of the rail part 110.

An aft joint 124 is also provided at the aft portion of the cowl 120, and in the structure shown in the drawings, the aft joint 124 is located at a middle position in a direction perpendicular to the longitudinal direction of the cowl 120. The rear joint 124 is connected to the shoe portion 110 by a strut assembly. Specifically, in the particular structure shown in the figures, the strut assembly includes a first strut 133 and a second strut 134, the first strut 133 being hingedly connected at one end to the track portion 110 and at the other end to one end of the second strut 134, and the second strut 134 being hingedly connected at the other end to the rear joint 124.

The operation of the fairing mechanism 100 of the present invention will now be described in conjunction with fig. 3 and 4.

When the flap 20 of the aircraft 1 starts to move, for example to deflect downwards, the pulley yoke 131 is driven to move backwards and downwards along the track 111 of the slide rail portion 110. In the process, the sliding of the pulley frame 131 moves the tie rod 132, which in turn transmits the movement to the middle joint 123, so that the cowling 120 pivots about the axis at the front left joint 121 and the front right joint 122.

During pivoting of the fairing 120, the strut assembly first and second struts 133, 134 also rotate and maintain the connection between the slide rail portion 110 and the aft joint 124 of the fairing 120 during rotation. Thereby, the overall rigidity of the cowl mechanism 100 is increased.

It can be seen that, compared with the existing flap fairing structure, the present invention realizes the corresponding movement of the fairing 120 along with the movement of the flap 20 through a simpler structure, the operational reliability is higher, and the difficulty of processing and installing the fairing structure can be reduced.

It will be apparent to those skilled in the art that obvious modifications may be made to the above-described arrangements without departing from the scope of the invention.

For example, instead of the above-described front left joint 121 and front right joint 122, only one front joint may be included, which may be located at a middle position in a direction perpendicular to the longitudinal direction of the cowl and may be hingedly connected to the rail portion 110 from below the rail portion 110.

As another example, the pulley yoke 131 can be replaced by a simple slider, which is connected to the pull rod 132 in a pivotable manner.