CN117622504A

CN117622504A - Aircraft vertical tail installation method

Info

Publication number: CN117622504A
Application number: CN202210991921.3A
Authority: CN
Inventors: 田瑜; 崔永强
Original assignee: Autoflight Kunshan Co Ltd
Current assignee: Autoflight Kunshan Co Ltd
Priority date: 2022-08-17
Filing date: 2022-08-17
Publication date: 2024-03-01

Abstract

The utility model relates to an aircraft technical field discloses an aircraft vertical fin installation method, is applied to the aircraft, and this aircraft is including detachable horn and the vertical fin of connection, and the one end protrusion of horn is provided with the linkage segment, and the vertical fin includes vertical fin one portion and vertical fin two portions, and one side that vertical fin one portion is close to vertical fin two portions is embedded to have coupling sleeve, and aircraft vertical fin installation method includes: the connecting section can be embedded in the connecting sleeve, and the horn is abutted with the two vertical tails. The mounting and dismounting modes of the horn and the vertical tail assembled by the aircraft vertical tail mounting method are convenient and quick, the connection rigidity of the horn and the vertical tail is good, and the connection reliability is high.

Description

Aircraft vertical tail installation method

Technical Field

The application relates to the technical field of aircrafts, in particular to an aircraft vertical tail installation method.

Background

The vertical tail on the aircraft can play a role in keeping the heading balance, stability and operation of the aircraft, and for the aircraft, the vertical tail needs to be quickly disassembled during transportation or maintenance. In the prior art, the vertical fin mounting structure is mostly a structure which is less detachable or non-detachable, so that the use flexibility is low; the vertical fin mounting structure is heavy, generally needs many people to work cooperatively, and the operation degree of difficulty is great, and the dismouting is comparatively troublesome, wastes time and energy.

Disclosure of Invention

Based on the above, the purpose of this application provides an aircraft vertical fin installation method, and horn and vertical fin easy dismounting is swift, and the connection rigidity of horn and vertical fin is better, and the connection reliability is higher.

In order to achieve the above purpose, the present application adopts the following technical scheme:

the utility model provides an aircraft vertical fin installation method, is applied to the aircraft, the aircraft includes horn and vertical fin that can dismantle the connection, the one end of horn is protruding to be provided with the linkage segment, the vertical fin includes vertical fin one portion and vertical fin two portions, one side that vertical fin one portion is close to vertical fin two portions is embedded to have the adapter sleeve; the aircraft vertical tail installation method comprises the following steps:

embedding the connection block in the connection sleeve;

and abutting the horn with the two vertical tail parts.

As a preferable scheme of the aircraft vertical tail installation method, a connecting hole is formed in one end of the two vertical tail parts, which is far away from one vertical tail part, and a positioning fastener is arranged on the horn corresponding to the connecting hole; the aircraft vertical fin installation method further comprises the following steps:

and connecting the positioning connecting piece with the positioning fastener through the connecting hole.

As a preferable scheme of the aircraft vertical tail installation method, the lower end part of the horn is provided with a first slope surface, and the upper end part of the vertical tail two parts is provided with a second slope surface; the said arm and said two vertical ends are abutted, comprising:

and abutting the first slope surface of the horn with the second slope surface of the two vertical tail parts, wherein the length directions of the first slope surface and the second slope surface are parallel to the length direction of the connecting sleeve.

As a preferable scheme of the aircraft vertical fin installation method, a vertical fin fastener is embedded on the second slope surface, and a horn fastener is embedded on the first slope surface; the aircraft vertical fin installation method further comprises the following steps: and connecting the vertical tail fastener of the second slope surface and the arm fastener of the first slope surface through a fastening connecting piece.

As an optimal scheme of the aircraft vertical fin installation method, the length of the vertical fin fastener extends along the length direction of the two vertical fin parts, the length of the horn fastener extends along the length direction of the horn, a plurality of fastening connectors are arranged, and the fastening connectors are arranged at intervals and are connected with the vertical fin fastener and the horn fastener.

As a preferred scheme of the aircraft vertical fin installation method, the face of two vertical fins and the horn butt joint is provided with first step face, the horn with the face of two vertical fins butt joint is provided with the second step face, the aircraft vertical fin installation method still includes: and matching and abutting the second step surface with the first step surface.

As a preferable scheme of the aircraft vertical fin installation method, the connecting hole and the vertical fin fastener are respectively positioned at two sides of the first step surface, and the vertical fin fastener is positioned between the first step surface and one part of the vertical fin.

As a preferable scheme of the vertical fin mounting method of the aircraft, the first step surface and the second step surface are obliquely arranged, and the first step surface is inclined upwards towards one part of the vertical fin.

As a preferable scheme of the aircraft vertical tail installation method, the horn is convexly provided with a positioning bulge towards the two vertical tail parts;

the aircraft vertical fin installation method further comprises the following steps: and the positioning protrusion is abutted against the end surface of the two vertical tail parts, which is far away from one part of the vertical tail.

As a preferable scheme of the method for installing the vertical tail of the aircraft, the end face of the two vertical tail parts, which is far away from the first vertical tail part, is provided with a first inclined plane, and the surface of the positioning protrusion, which is abutted with the two vertical tail parts, is provided with a second inclined plane;

the positioning protrusion is abutted to the end face of the two vertical tail parts, which is far away from the one vertical tail part, specifically comprises:

the beneficial effects of the application are that the first inclined plane of the vertical tail two parts is matched and abutted with the second inclined plane of the positioning protrusion are as follows:

the utility model provides an aircraft vertical fin installation method, this aircraft vertical fin installation method inserts in the adapter sleeve of vertical fin one portion through the linkage segment, realizes the butt joint location of horn and vertical fin, can effectively guarantee the axiality of horn and vertical fin, and can restrict the vertical fin in two ascending degrees of freedom. Under the structure, the installation is simple and convenient, and the connection can be realized by pushing the horn towards the vertical tail after aligning the connecting section and the connecting sleeve.

Drawings

In order to more clearly illustrate the technical solutions in the embodiments of the present application, the following description will briefly explain the drawings needed in the descriptions of the embodiments of the present application, and it is obvious that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to the contents of the embodiments of the present application and these drawings without inventive effort for a person of ordinary skill in the art.

FIG. 1 is a flow chart of an aircraft vertical tail installation method according to an embodiment of the present application

FIG. 2 is a schematic illustration of an assembly of a horn and a vertical tail of an aircraft provided by an embodiment of the present application;

FIG. 3 is an enlarged view of portion A of FIG. 2;

FIG. 4 is a schematic view of a partial structure of an aircraft provided in an embodiment of the present application;

FIG. 5 is a schematic view of a partial structure of a vertical fin according to an embodiment of the present disclosure;

fig. 6 is a schematic partial structure of a horn according to an embodiment of the present application;

fig. 7 is a schematic diagram of a separation state of a horn and a vertical fin according to an embodiment of the present application;

fig. 8 is a schematic diagram of a separation state of the other side face of the horn and the vertical fin according to the embodiment of the present application.

Detailed Description

The present application is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the application and not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present application are shown in the drawings.

In the description of the present application, unless explicitly stated and limited otherwise, the terms "connected," "connected," and "fixed" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally formed; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communicated with the inside of two elements or the interaction relationship of the two elements. The specific meaning of the terms in this application will be understood by those of ordinary skill in the art in a specific context.

In this application, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, and may also include the first and second features not being in direct contact but being in contact with each other by way of additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.

In the description of the present embodiment, the terms "upper", "lower", "left", "right", and the like are orientation or positional relationships based on those shown in the drawings, merely for convenience of description and simplicity of operation, and do not indicate or imply that the apparatus or element in question must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the present application. In the description of the present application, unless otherwise indicated, the meaning of "a plurality" is two or more. Furthermore, the terms "first," "second," and the like, are used merely for distinguishing between descriptions and not for distinguishing between them.

The method for installing the vertical tail of the aircraft, as shown in fig. 1, comprises the following steps:

s1: the connection block is embedded in the connection sleeve.

The embodiment provides an aircraft vertical fin installation method, is applied to an aircraft, and as shown in fig. 2 to 8, the aircraft comprises a detachable connection horn 1 and a vertical fin 2, one end of the horn 1 is provided with a connecting section 3 in a protruding mode, the vertical fin 2 comprises a vertical fin first part 21 and a vertical fin second part 22, one side, close to the vertical fin second part 22, of the vertical fin first part 21 is embedded with a connecting sleeve 7, the connecting section 3 is embedded in the connecting sleeve 7, butt joint positioning of the horn 1 and the vertical fin 2 is achieved, and coaxiality of the horn 1 and the vertical fin 2 is effectively guaranteed. It should be noted that, the connecting section 3 is partially inserted in the horn 1 and is fixedly connected with the structure in the horn 1, so as to ensure the structural strength and stability of the connecting section 3, and the other part protrudes out of the end face of the horn 1 and is inserted in the connecting pipe groove, so as to realize the positioning of the vertical fin 2. Preferably, the connection section 3 is hollow and cylindrical, and the internal harness of the aircraft can pass through the connection section 3, so that the arrangement of the harness is facilitated.

S2: the arm is abutted with the two vertical ends.

After the connecting section 3 is embedded in the connecting sleeve 7 in the previous step, the two vertical tail parts 22 are abutted with the horn 1. Specifically, the lower end portion of the arm 1 is provided with a first slope surface 100, the upper end portion of the vertical tail two portions 22 is provided with a second slope surface 220, and the length directions of the first slope surface 100 and the second slope surface 220 are parallel to the length direction of the connecting sleeve. During the insertion of the connection section 3 into the connection sleeve 7, the first ramp surface 100 of the horn 1 is in sliding engagement with the second ramp surface 220 of the two vertical tail sections 22 until fully abutting against each other. Under the above structure, the first slope surface 100 and the second slope surface 220 play a guiding role, so that the connection section 3 and the connection sleeve 7 are smoothly spliced, and the first slope surface 100 and the second slope surface 220 are mutually abutted, so that the rotation of the connection section 3 relative to the connection sleeve 7 can be effectively limited, the connection stability of the connection section 3 and the connection sleeve 7 is ensured, and the swinging of the vertical fin 2 is effectively lightened.

According to the vertical tail installation method of the aircraft, the connecting section 3 is inserted into the connecting sleeve 7 of the first vertical tail part 21, the second vertical tail part 22 is abutted against the horn 1, the butt joint positioning of the horn 1 and the vertical tail 2 is achieved, the coaxiality of the horn 1 and the vertical tail 2 can be effectively ensured, and the swing of the vertical tail 2 is effectively lightened. Under the structure, the installation is simple and convenient, and the connection can be realized only by pushing the horn 1 towards the vertical tail 2 after aligning the connecting section 3 and the connecting sleeve 7. At the same time, the connecting sleeve 7 plays a guiding and protecting role for the connecting section 3. In this embodiment, the connection section 3 is clamped with the connection sleeve, that is, the peripheral dimension of the connection section 3 is adapted to the inner diameter of the connection sleeve, so that the connection section 3 can be inserted into the connection sleeve and also can be fixed with the connection sleeve.

Further, as shown in fig. 5 and 6, the second slope surface 220 is embedded with a vertical tail fastener 5, the first slope surface 100 is embedded with a horn fastener 6, and the aircraft vertical tail installation method in the embodiment of the present application further includes: the vertical tail fastener 5 and the horn fastener 6 are connected through a fastening connection piece. The vertical tail fastener 5 and the arm fastener 6 have larger friction force, and the connecting section 3 can be effectively limited to rotate relative to the connecting sleeve 7 after being inserted into the connecting sleeve 7. The vertical tail fastener 5 and the horn fastener 6 are connected through the fastening connecting piece, the vertical tail 2 and the horn 1 are further fastened, and the connection strength and stability of the vertical tail 2 and the horn 1 are improved. I.e. the rigid connection of the horn 1 and the tail 2 is ensured by the shearing resistance and the contact surface of the fastening connection. Meanwhile, after the vertical fin 2 is installed, the installation state of the fastening connecting piece can be directly observed, and the connection reliability of the vertical fin 2 and the horn 1 can be judged, so that the fastening connecting piece can be timely adjusted or replaced, and the connection firmness of the vertical fin 2 and the horn 1 is ensured.

Preferably, the length of the vertical tail fastener 5 extends along the length direction of the vertical tail two parts 22, the length of the horn fastener 6 extends along the length direction of the horn 1, a plurality of fastening connectors are arranged, and a plurality of fastening connectors are arranged at intervals and are connected with the vertical tail fastener 5 and the horn fastener 6. Namely, the area of the vertical tail fastener 5 covering the two vertical tail parts 22 is larger, the area of the horn fastener 6 covering the horn 1 is larger, and the uniformity and the connection strength of the connection stress of the vertical tail 2 and the horn 1 can be improved; and under the structure, the connection of the fastening connecting piece is convenient, so that the contact parts of the horn 1 and the vertical tail two parts 22 are fastened and connected, the connection rigidity of the horn 1 and the vertical tail 2 is improved, and the swing of the vertical tail 2 is lightened.

Illustratively, the vertical fin fastener 5 and the horn fastener 6 are metal plates with a plurality of threaded holes 20 formed thereon, the fastening connection member is a bolt, and the bolt is sequentially in threaded connection with the threaded holes 20 on the vertical fin fastener 5 and the threaded holes 20 on the horn fastener 6, or sequentially in threaded connection with the threaded holes 20 on the horn fastener 6 and the threaded holes 20 on the vertical fin fastener 5, so as to realize the fastening connection of the horn 1 and the vertical fin 2. The installation and the dismantlement are convenient, and the cost is lower, and connection structure intensity is higher. Optionally, the vertical tail fastener 5 and the arm fastener 6 are aluminum alloy fasteners, and the structural strength is high.

In some embodiments, as shown in fig. 3 and 5, a connecting hole 10 is formed at an end of the second vertical tail portion 22 away from the first vertical tail portion 21, a positioning fastener 4 is disposed on the horn 1 corresponding to the connecting hole 10, and the aircraft vertical tail installation method further includes: a positioning connector is connected with the positioning fastener 4 through the connecting hole 10. After the connecting section 3 and the connecting pipe sleeve 7 are positioned, the connecting strength of the horn 1 and the vertical tail 2 is reinforced through the positioning connecting piece, and the connecting stability of the horn 1 and the vertical tail 2 is improved. And after the installation is finished, the positioning connecting piece is convenient to observe, and the installation condition and the fastening reliability of the vertical fin 2 and the horn 1 are timely judged.

Preferably, the connecting hole 10 is embedded to be equipped with the stand pipe, and the locating connection piece passes the stand pipe and is connected with the locating fastener 4, and the setting of stand pipe is convenient for wear to establish of locating connection piece for the locating connection piece is comparatively stable, and can avoid locating connection piece and the pore wall of connecting hole 10 to take place to interfere the damage that causes the pore wall of connecting hole 10.

Illustratively, the positioning connecting piece is a bolt, the positioning fastening piece 4 is a fastening nut, the fastening nut is embedded on the horn 1, the guide tube is a bolt guide hole, and the bolt passes through the bolt guide hole to be in threaded connection with the fastening nut, so that the fixed connection of the horn 1 and the vertical fin 2 is realized. The bolt and the fastening nut have higher connection strength, convenient operation, simplicity, easy obtainment and lower cost. Of course, in other embodiments, the positioning connector and positioning fastener 4 may be other structures, such as a snap-fit structure, etc.

In some embodiments, as shown in fig. 3 and 5, the horn 1 is provided with a positioning protrusion 12 protruding toward the two vertical tail parts 22, and the aircraft vertical tail installation method of the embodiment of the application further includes: the positioning protrusion 12 is abutted against the end surface of the vertical tail two parts 22, which is far away from the vertical tail one part 21. After inserting the linkage segment 3 in the connecting tube groove, the end face that arm 1 was provided with linkage segment 3 is provided with the terminal surface butt of connecting tube groove with perpendicular to tail one portion 21, and at this moment, the terminal surface butt of perpendicular to tail two portions 22 keeping away from perpendicular to tail one portion 21 is protruding 12 to the location also, has further restricted perpendicular to tail 2 and has rolled the degree of freedom, has played good limiting displacement to arm 1 and perpendicular to tail 2, guarantees the connection precision and the structural strength of arm 1 and perpendicular to tail 2.

Preferably, the end surface of the second vertical tail portion 22 far away from the first vertical tail portion 21 is set to be a first inclined surface 222, and a second inclined surface 121 is disposed on a surface of the positioning protrusion 12 abutting against the second vertical tail portion 22. The first inclined surface 222 of the vertical tail two parts 22 is matched and abutted with the second inclined surface 121 of the positioning protrusion 12. Through the cooperation butt with first inclined plane 222 and second inclined plane 121, can play limiting displacement to vertical fin 2, also can play certain guide effect when vertical fin 2 and horn 1 are installed for linkage segment 3 is connected smoothly and stably with the connecting tube groove. More preferably, the first inclined surface 222 is inclined upward toward the vertical end portion 21, i.e., the inclined directions of the first inclined surface 222 and the second inclined surface 121 are consistent with the direction of inserting the connecting section 3 into the connecting pipe groove, so as to facilitate guiding.

Still further, the face that two portions 22 of perpendicular to the tail are in butt joint with horn 1 is provided with first step face 221, and the face that horn 1 is in butt joint with two portions 22 of perpendicular to the tail is provided with second step face 11, and the aircraft perpendicular to the tail installation method of this application still includes: the second step surface 11 is fitted to and abutted against the first step surface 221. The matching and abutting of the first step surface 221 and the second step surface 11 can limit the free rolling of the vertical fin 2, and a certain positioning effect is achieved on the horn 1 and the vertical fin 2.

Preferably, the first step surface 221 and the second step surface 11 are both inclined, and the first step surface 221 is inclined upward toward the vertical one portion 21. That is, the inclined surface of the first step surface 221 is consistent with the direction of inserting the connecting section 3 into the connecting pipe groove, so that the horn 1 and the vertical tail 2 are connected smoothly, and the first step surface 221 and the second step surface 11 are mutually abutted to provide positioning and limiting effects, so that the vertical tail fastener 5 and the horn fastener 6 are convenient to face directly, and the fastening connecting piece is fast and convenient to install.

In the present embodiment, the attachment hole 10 and the vertical tail fastener 5 are located on both sides of the first step surface 221, respectively, and the vertical tail fastener 5 is located between the first step surface 221 and the vertical tail portion 21. Positioning and preliminary fastening of the vertical fin 2 and the horn 1 are realized through a positioning connecting piece, and simultaneously, the vertical fin 2 and the horn 1 are fixed through a fastening connecting piece; and under the above-mentioned structure, the setting of the vertical fin fastener 5 of being convenient for, vertical fin fastener 5 and connecting hole 10 are located the both sides of first step face 221 respectively promptly, can effectively improve horn 1 and vertical fin 2's joint strength for the equal fixed connection of contact part of horn 1 and vertical fin 2 improves horn 1 and vertical fin 2's connection reliability.

Note that the above is only a preferred embodiment of the present application and the technical principle applied. Those skilled in the art will appreciate that the present application is not limited to the particular embodiments described herein, but is capable of numerous obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the present application. Therefore, while the present application has been described in connection with the above embodiments, the present application is not limited to the above embodiments, but may include many other equivalent embodiments without departing from the spirit of the present application, the scope of which is defined by the scope of the appended claims.

Claims

1. The utility model provides an aircraft vertical fin installation method which is characterized in that is applied to the aircraft, the aircraft includes horn (1) and vertical fin (2) that can dismantle the connection, the one end of horn (1) is protruding to be provided with linkage segment (3), vertical fin (2) include vertical fin one portion (21) and vertical fin two portion (22), vertical fin one portion (21) is close to one side of vertical fin two portion (22) is embedded has adapter sleeve (7); the aircraft vertical tail installation method comprises the following steps:

embedding the connecting section (3) in the connecting sleeve (7);

and abutting the horn (1) with the vertical tail two parts (22).

2. The aircraft vertical tail installation method according to claim 1, wherein a connecting hole (10) is formed in one end of the vertical tail two parts (22) away from the vertical tail one part (21), and a positioning fastener (4) is arranged on the horn (1) corresponding to the connecting hole (10); the aircraft vertical fin installation method further comprises the following steps:

and connecting the positioning connecting piece with the positioning fastener (4) through the connecting hole (10).

3. The aircraft vertical mounting method according to claim 1, characterized in that the lower end portion of the horn (1) is provided with a first ramp surface (100) and the upper end portion of the vertical two-part (22) is provided with a second ramp surface (220); the abutting of the horn (1) and the vertical tail two parts (22) specifically comprises:

and abutting a first slope surface (100) of the horn (1) and a second slope surface (220) of the vertical tail two parts (22), wherein the length directions of the first slope surface (100) and the second slope surface (220) are parallel to the length direction of the connecting sleeve (7).

4. A method of installing a vertical tail of an aircraft according to claim 3, wherein the second ramp surface (220) is embedded with a vertical tail fastener (5), and the first ramp surface (100) is embedded with a horn fastener (6); the aircraft vertical fin installation method further comprises the following steps: and connecting a vertical tail fastener (5) of the second slope surface (220) and a horn fastener (6) of the first slope surface (100) through a fastening connecting piece.

5. The aircraft vertical mounting method according to claim 4, wherein the length of the vertical fastener (5) extends along the length direction of the vertical two parts (22), the length of the horn fastener (6) extends along the length direction of the horn (1), and a plurality of fastening connectors are arranged at intervals and are connected with the vertical fastener (5) and the horn fastener (6).

6. The aircraft vertical fin mounting method according to claim 4, wherein a face of the vertical fin two portion (22) abutting against the horn (1) is provided with a first step face (221), a face of the horn (1) abutting against the vertical fin two portion (22) is provided with a second step face (11), the aircraft vertical fin mounting method further comprising: the second step surface (11) is matched and abutted with the first step surface (221).

7. The aircraft vertical mounting method according to claim 6, characterized in that the connection hole (10) and the vertical fastening piece (5) are located on both sides of the first step surface (221), respectively, the vertical fastening piece (5) being located between the first step surface (221) and the vertical portion (21).

8. The aircraft vertical mounting method according to claim 6, characterized in that the first step surface (221) and the second step surface (11) are both arranged obliquely, the first step surface (221) being inclined upwards in the direction of the vertical one part (21).

9. The aircraft vertical tail installation method according to claim 1, characterized in that the horn (1) is provided with a positioning projection (12) protruding towards the vertical tail two parts (22);

the aircraft vertical fin installation method further comprises the following steps: and the positioning bulge (12) is abutted against the end surface of the two vertical tail parts (22) far away from the first vertical tail part (21).

10. The aircraft vertical mounting method according to claim 9, wherein the end surface of the vertical second part (22) away from the vertical first part (21) is provided with a first inclined surface (222), and the surface of the positioning protrusion (12) abutting against the vertical second part (22) is provided with a second inclined surface (121);

the positioning protrusion (12) is abutted to the end face of the two vertical tail parts (22) far away from the first vertical tail part (21), and specifically comprises:

the first inclined surface (222) of the vertical tail two parts (22) is matched and abutted with the second inclined surface (121) of the positioning bulge (12).