CN109263852B

CN109263852B - Aircraft flap fixing device

Info

Publication number: CN109263852B
Application number: CN201811007102.0A
Authority: CN
Inventors: 张伟宁; 赵艳林; 强博; 张宇; 王奡
Original assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Current assignee: Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date: 2018-08-31
Filing date: 2018-08-31
Publication date: 2022-02-22
Anticipated expiration: 2038-08-31
Also published as: CN109263852A

Abstract

The invention relates to the field of airplane design, in particular to an airplane flap fixing device. The device is designed to be used for fixing the airplane covering cap, so that the covering cap is prevented from being separated, and the surface coating of the airplane body structure is prevented from being scratched along with wind. The device comprises a first fixed base, a rocker arm, a plug and a second fixed base; the first fixed base is fixed on the airplane hatch cover; one end of the rocker arm is arranged on the first fixed base, and the rocker arm can rotate around the first fixed base; the plug is arranged at the other end of the rocker arm and can rotate along with the rocker arm, and a plug tongue is arranged on the plug; the second fixed base is fixed on a mouth cover frame of the machine body structure, and a fixed hole used for connecting the inserting tongue is formed in the second fixed base. The space occupied by the device can be reduced through the arrangement of the rotatable rocker arm, the aircraft covering cap is ensured to be completely opened, and the aircraft covering cap is ensured to be fixed and firm.

Description

Aircraft flap fixing device

Technical Field

The invention relates to the field of airplane design, in particular to an airplane flap fixing device.

Background

Due to the limited number of carrier-based aircraft contained in the aircraft hangar, many carrier-based aircraft are often parked on deck. The aircraft carrier loader has the advantages that the number and the types of aircraft carriers are large, the maintenance equipment and parts are various, along with the improvement of the maintenance requirement of the carrier-based aircraft on the ship surface, the detachable parts such as the cover cap need to be designed without separation, and the loss and the misloading of the parts are prevented. Conventional flaps typically employ hinges or cords to prevent the flap from disengaging. Because the existence of deck wind leads to the flap to shake with the wind usually, leads to the flap to collide with the paint layer on organism surface, especially to stealthy aircraft's coating, can lead to serious damage, and maintenance cost is big.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

One object of the present invention is to provide an aircraft door fixing device for fixing an aircraft door, ensuring that the door does not separate, and preventing the door from swaying with the wind and damaging the surface coating of the airframe structure.

The technical scheme of the invention is as follows:

an aircraft flap fixture for securing an aircraft flap, the aircraft flap fixture comprising:

the first fixed base is fixed on the airplane hatch cover;

one end of the rocker arm is mounted on the first fixed base, and the rocker arm can rotate around the first fixed base;

the plug is arranged at the other end of the rocker arm, and is provided with a plug tongue;

and the second fixing base is fixed on a mouth cover frame of the machine body structure and is provided with a fixing hole for connecting the inserting tongue.

Optionally, a first fixing base is provided with a first fixing groove, and a first mounting hole is formed in the first fixing groove; the one end that rocking arm and first unable adjustment base are connected is provided with the first fixed column of the circular shape of perpendicular to rocking arm main part, and first fixed column is installed in first mounting hole.

Optionally, one end of the first fixing column, which is far away from the rocker arm main body, is provided with a first fixing hole, and the first fixing column is limited in the first mounting hole by a first fixing pin penetrating through the first fixing hole.

The aircraft door retaining apparatus of claim, wherein the end of the rocker arm connected to the first retaining base is shaped to fit the first retaining groove.

Optionally, a first elastic sheet is installed between the first fixing pin and the first fixing base, and a gasket is further installed between the first elastic sheet and the first fixing pin.

Optionally, a second fixing groove is formed in one side, provided with the insertion tongue, of the plug, and the second fixing groove is matched with the shape of the contact end of the rocker arm.

Optionally, the other end of the rocker arm is provided with a second round fixing column, a second mounting hole in the same direction as the plug tongue is formed in the plug, and the plug is fixed to the second fixing column through the second mounting hole.

Optionally, the one end that the rocking arm main part was kept away from to the second fixed column is provided with the second fixed orifices, and the plug is spacing on the second fixed column through the second fixed pin that passes the second fixed orifices, and the plug can rotate around the second fixed column.

Optionally, a second elastic sheet is installed between the second fixing pin and the plug.

Optionally, a gasket is installed between the second elastic sheet and the second fixing pin.

The invention has the beneficial effects that:

according to the aircraft flap fixing device, the first fixing base is fixed on the aircraft flap; one end of the rocker arm is arranged on the first fixed base so as to rotate around the first fixed base; a plug is arranged at the other end of the rocker arm; when the aircraft flap was closed, fixing device was in aircraft flap within range completely, when opening the aircraft flap, rotated the rocking arm, with the erection plug with, fix the second unable adjustment base on the flap frame of organism structure and connect, prevented that the aircraft flap from rocking to the aircraft flap can be opened completely.

Drawings

FIG. 1 is an exploded view of the aircraft door securement device of the present invention;

FIG. 2 is an isometric view of the aircraft flap retainer of the present invention;

FIG. 3 is a top view of the aircraft door securement device of the present invention;

FIG. 4 is a half sectional view of the aircraft door securement device of FIG. 2 in accordance with the present invention;

FIG. 5 is a view of the rocker arm structure of the aircraft flap retainer of the present invention;

FIG. 6 is a plug configuration view of the aircraft flap retainer of the present invention;

FIG. 7 is a view showing a first fixing base of the fixing device for an aircraft door of the present invention;

FIG. 8 is a schematic view showing the opening of the aircraft door fastening device of the present invention.

Wherein:

1-aircraft flap; 2-a first fixed base; 3-a gasket; 4-a spring plate; 5-a rocker arm; 6-a plug; 7-a second stationary base; 21-a first fixation groove; 22-a first mounting hole; 41-a second elastic sheet; 51-a first fixed column; 52-first fixation hole; 53-second fixed column; 54-a second fixation hole; 61-tongue insertion; 62-a second mounting hole; 63-second fixation groove.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present invention clearer, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are illustrative and intended to be illustrative of the invention and are not to be construed as limiting the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention. Embodiments of the present invention will be described in detail below with reference to the accompanying drawings.

In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present invention and for simplifying the description, and do not indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore, should not be taken as limiting the scope of the present invention.

The present invention will be described in further detail with reference to fig. 1 to 8.

As shown in fig. 1 to 8, the aircraft flap fixing device provided by the present invention is used for fixing an aircraft flap, and the aircraft flap fixing device may include a first fixing base, a rocker arm, a plug, and a second fixing base.

First unable adjustment base 2 includes two backup pads and spans the fixed plate between two backup pads, and first unable adjustment base 2 is fixed on aircraft flap 1 face inside the aircraft through two backup pads, and the fixed plate forms first fixed slot 21 with two backup pads and is used for laying the rocking arm to be provided with the first mounting hole 22 that is used for fixed rocking arm on the fixed plate.

The rocker arm 5 comprises a rocker arm main body and a first fixed column 51 and a second fixed column 53 arranged at two ends of the rocker arm main body, wherein

The one end that rocking arm 5 and first unable adjustment base 2 are connected is provided with the circular shape first fixed column 51 of perpendicular to rocking arm 5 main part, and the one end that rocking arm 5 main part was kept away from to first fixed column 51 is provided with first fixed orifices 52, and first fixed column 51 is spacing in first mounting hole 22 through the first fixed pin that passes at first fixed orifices 52, and rocking arm 5 can rotate around first fixed orifices 52. And the main body of this end of the swing arm 5 is dropped in the first fixing groove 21 of the first fixing base 2, and the shape is matched with the shape of the first fixing groove 21, so that the stability of the swing arm 5 can be ensured in a fixed state.

When aircraft flap 1 seals, rocking arm 5 is in aircraft flap 1's within range completely, can reduce the space that aircraft flap fixing device occupy, opens the back when aircraft flap 1, can be through rotating rocking arm 5 for the other end of rocking arm 5 is in the marginal position of aircraft flap 1.

The other end of the rocker arm 5 is provided with a circular second fixing column 53, the axial direction of the second fixing column 53 is consistent with the axial direction of the rocker arm 5, and one end, away from the main body of the rocker arm 5, of the second fixing column 53 is provided with a second fixing hole 54.

Further, install gasket 3 between the fixed plate of first fixed pin and first unable adjustment base 2, install shell fragment 4 between gasket 3 and the fixed plate of first unable adjustment base 2, when rocking arm 5 needs to rotate, at first exert external force and upwards mention rocking arm 5 for rocking arm 5 breaks away from first fixed slot 21, then with rocking arm 5 around the fixed column rotate can, reach preset position, remove external force, just can resume firm connected state between rocking arm 5 and the first unable adjustment base 2.

The plug 6 is installed at the other end of the rocker arm 5, a plug tongue 61 is arranged on the plug 6, a second fixing groove 63 is further formed in one face provided with the plug tongue 61, the shape of the contact end of the second fixing groove 63 and the rocker arm 5 is matched, a second mounting hole 62 identical to the plug tongue 61 in direction is formed in the plug 6, the second mounting hole 62 of the plug 6 is limited on the second fixing column 53 through a second fixing pin penetrating through the second fixing hole 54, the end of the main body portion of the rocker arm 5 is clamped in the second fixing groove 63, stable connection can be guaranteed, and the plug 6 can rotate around the second fixing column 53.

When the aircraft flap 1 is closed, the plug tongue 61 is positioned between the rocker arm 5 and the aircraft flap 61, so that the occupied volume can be reduced, after the aircraft flap 1 is opened, the plug 6 is rotated 180 degrees around the second fixing column 53, so that the plug tongue 61 of the plug 6 is positioned on the side, away from the aircraft flap 61, of the rocker arm 5, and the distance between the plug 61 and the main body of the rocker arm 5 is larger than the thickness of the aircraft flap frame.

Further, a second elastic sheet 41 is installed between the second fixing pin and the plug 6, and a gasket 3 is installed between the second elastic sheet 41 and the second fixing pin. Can guarantee to be connected stably between plug 6 and the rocking arm 5 through second shell fragment 41, simultaneously, when needs rotate plug 6, only need apply external force to plug 6 and make the end of the main part of rocking arm 5 break away from second fixed slot 63, then alright in order to rotate plug 6, reach preset position, remove external force, just can resume firm connected state between plug 6 and the rocking arm 5.

The second fixed base 7 is fixed on the face of the cover frame of the airframe structure facing the interior of the aircraft, and the second fixed base 7 is provided with a fixed hole for connecting the insert tongue.

When the airplane flap is used, when the airplane flap 1 is in a closed state, the rocker arm 5 is fixed on the airplane flap 1 through the first fixing base 2, and parts such as a rocker arm part and a plug of the device are located in the range of the airplane flap, so that other redundant space occupied by the device can be reduced; when the aircraft flap is opened 1, rotate 180 around the pivot of base with rocking arm 5 for the plug rotates to flap edge, rotates 180 around the erection column on the rocking arm with the plug, rotates the inserted tongue of plug to rocking arm 5 and keeps away from on the face of aircraft flap 1, then, removes aircraft flap 1, inserts the inserted tongue in the mounting hole of unable adjustment base, can make the aircraft flap open completely, and realizes the fixed of flap.

The above description is only for the specific embodiment of the present invention, but the scope of the present invention is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present invention are included in the scope of the present invention. Therefore, the protection scope of the present invention shall be subject to the protection scope of the appended claims.

Claims

1. An aircraft flap fixture for securing an aircraft flap, the aircraft flap fixture comprising:

the first fixing base (2) is fixed on the airplane flap (1);

the rocker arm (5) is mounted on the first fixed base (2) at one end, and the rocker arm (5) can rotate around the first fixed base (2);

the plug (6) is installed at the other end of the rocker arm (5), and a plug tongue (61) is arranged on the plug (6);

the second fixing base (7) is fixed on a mouth cover frame of the machine body structure, and a fixing hole for connecting the inserting tongue (61) is formed in the second fixing base (7);

a first fixing groove (21) is formed in the first fixing base (2), and a first mounting hole (22) is formed in the first fixing groove (21); one end of the rocker arm (5) connected with the first fixing base (2) is provided with a circular first fixing column (51) perpendicular to the main body of the rocker arm (5), and the first fixing column (51) is installed in the first installation hole (22).

2. The aircraft door fixing device according to claim 1, wherein a first fixing hole (52) is formed in one end of the first fixing column (51) far away from the main body of the rocker arm (5), and the first fixing column (51) is limited in the first mounting hole (22) by a first fixing pin penetrating through the first fixing hole (52).

3. An aircraft flap fixing device according to claim 1, characterized in that the shape of the end of the rocker arm (5) connected to the first fixing base (2) is adapted to the shape of the first fixing groove (21).

4. The aircraft door fixing device of claim 2, wherein a first spring (4) is mounted between the first fixing pin and the first fixing base (2), and a gasket is further mounted between the first spring (4) and the first fixing pin.

5. An aircraft flap fixing device according to claim 1, characterized in that a second fixing groove (63) is provided on the side of the plug (6) provided with the tongue (61), the second fixing groove (63) being adapted to the shape of the contact end of the rocker arm (5).

6. The aircraft door fixing device of claim 1, wherein a second fixing pillar (53) with a circular shape is arranged at the other end of the rocker arm (5), a second mounting hole (62) with the same direction as the inserting tongue (61) is arranged on the plug (6), and the plug (6) is fixed on the second fixing pillar (53) through the second mounting hole (62).

7. The aircraft door fixing device of claim 6, wherein a second fixing hole (54) is formed in one end, away from the main body of the rocker arm (5), of the second fixing column (53), the plug (6) is limited on the second fixing column (53) through a second fixing pin penetrating through the second fixing hole (54), and the plug (6) can rotate around the second fixing column (53).

8. The aircraft flap fixing device according to claim 7, characterized in that a second spring (41) is mounted between the second fixing pin and the plug (6).

9. The aircraft flap retainer as defined in claim 8, wherein a gasket is mounted between the second resilient tab (41) and the second retainer pin.