CN219215381U

CN219215381U - Aircraft vertical stabilizer upset frock

Info

Publication number: CN219215381U
Application number: CN202223270972.1U
Authority: CN
Inventors: 高慧
Original assignee: South China Aircraft Industry Co Ltd of China Aviation Industry General Aircraft Co Ltd
Current assignee: South China Aircraft Industry Co Ltd of China Aviation Industry General Aircraft Co Ltd
Priority date: 2022-12-05
Filing date: 2022-12-05
Publication date: 2023-06-20
Anticipated expiration: 2032-12-05

Abstract

The utility model discloses an aircraft vertical stabilizer overturning tool which comprises an overturning frame, a vertical tail joint assembly and two groups of supporting frames, wherein two ends of the overturning frame are respectively and rotatably connected with the two groups of supporting frames, and the vertical tail joint assembly is connected with the overturning frame and comprises a positioning piece, a supporting plate and a pressing plate. When the vertical stabilizer is used, the positioning piece is inserted into the vertical butt joint hole of the vertical stabilizer, the pressing plate and the supporting plate are respectively positioned on the upper side and the lower side of the vertical stabilizer, the pressing plate moves relative to the supporting plate, the vertical stabilizer is pressed between the pressing plate and the supporting plate, and finally the overturning frame rotates relative to the supporting frame, so that the vertical stabilizer is driven to overturn upwards, and the vertical stabilizer is convenient to hoist. Therefore, the tool can provide good fixing and positioning for the vertical stabilizer in the process of overturning the vertical stabilizer, and can provide balanced and stable overturning acting force for the vertical stabilizer, so that the vertical stabilizer can be prevented from generating larger shearing force to a stacking position while being convenient to overturn the vertical stabilizer.

Description

Aircraft vertical stabilizer upset frock

Technical Field

The utility model relates to the technical field of aircraft assembly, in particular to an aircraft vertical stabilizer overturning tool.

Background

The tail wing is a structure arranged at the tail part of the aircraft, is an important component of a flight control system, can be used for controlling the pitching, the yawing and the tilting of the aircraft so as to change the flight attitude of the aircraft, and can enhance the flight stability. Most of the tails include a horizontal tail and a vertical tail, which is called a vertical tail for short, which has the function of maintaining the course balance, stability and operation of the aircraft, and the principle is similar to that of the horizontal tail. Like a horizontal tail, the front half of the trailing airfoil is typically fixed, called the vertical stabilizer, and the rear half is hinged to the rear of the vertical stabilizer for steering deflection, called the rudder.

At present, in the butt joint process of the vertical tail and the horizontal tail of a large amphibious aircraft, the assembly requirement of overturning and positioning of a vertical stabilizer is generally required to be met. During assembly, one side of the vertical stabilizer is put on the bracket, and then the other side of the vertical stabilizer is lifted by a crane so as to realize the overturning of the vertical stabilizer. The overturning mode is inconvenient to operate, and in the overturning process, the vertical stabilizer is easy to slide or separate from the bracket, so that the overturning is difficult. In the lifting process, the vertical stabilizer is easy to generate larger shearing force on the placing position, so that the placing position is deformed.

Disclosure of Invention

In order to overcome the defects in the prior art, the utility model aims to provide an aircraft vertical stabilizer overturning tool which can facilitate overturning of a vertical stabilizer.

In order to solve the problems, the technical scheme adopted by the utility model is as follows: an aircraft vertical stabilizer upset frock includes: two sets of support frames; the two ends of the turnover frame are respectively and rotatably connected with the two groups of support frames; and the vertical tail joint assembly is connected to the turnover frame and comprises a positioning piece, a supporting plate and a pressing plate, wherein the positioning piece is used for positioning a vertical tail butt joint hole on the vertical stabilizer, and the pressing plate can move towards the supporting plate so as to press the vertical stabilizer between the pressing plate and the supporting plate.

Compared with the prior art, the utility model has the beneficial effects that: when the vertical stabilizer is used, the positioning piece is inserted into the vertical tail butt joint hole of the vertical stabilizer, the pressing plate and the supporting plate are respectively positioned on the upper side and the lower side of the vertical stabilizer, the pressing plate moves relative to the supporting plate, the vertical stabilizer is pressed between the pressing plate and the supporting plate, and finally the overturning frame rotates relative to the supporting frame, so that the vertical stabilizer is driven to upwards overturn. After the overturning of the vertical stabilizer is completed, the vertical stabilizer is hoisted by adopting a crane, the vertical stabilizer is loosened by the pressing plate and the supporting plate, and the vertical stabilizer can be hoisted to the vertical tail butt joint table for vertical tail butt joint by pulling out the positioning piece. Therefore, the tool can provide good fixing and positioning for the vertical stabilizer in the process of overturning the vertical stabilizer, and can provide balanced and stable overturning acting force for the vertical stabilizer, so that the vertical stabilizer can be prevented from generating larger shearing force to a stacking position while being convenient to overturn the vertical stabilizer.

The aircraft vertical stabilizer overturning tool comprises the locating piece, the connecting bolt and the safety bolt, wherein the locating piece is provided with a U-shaped groove, the connecting bolt is detachably connected in the U-shaped groove in a penetrating mode and is used for being inserted into a vertical tail butt joint hole, the safety bolt is vertically distributed with the connecting bolt, and the safety bolt is detachably inserted into a notch of the U-shaped groove.

According to the aircraft vertical stabilizer overturning tool, the plurality of groups of vertical fin connector assemblies are arranged, and the plurality of groups of vertical fin connector assemblies are distributed along the length direction of the overturning frame.

The aircraft vertical stabilizer overturning tool is characterized in that two groups of locating pieces are arranged in each group of vertical tail joint assembly, the two groups of locating pieces are distributed along the width direction of the overturning frame, and the two groups of locating pieces are located between the supporting plate and the pressing plate.

According to the aircraft vertical stabilizer overturning tool, the index plate is arranged at the rotating connection position of the overturning frame and the supporting frame.

According to the aircraft vertical stabilizer overturning tool, the upper side part of the supporting frame is provided with the limiting support, and after the overturning frame overturns upwards, the side part of the overturning frame abuts against the limiting support.

According to the aircraft vertical stabilizer overturning tool, the bottom of the supporting frame is fixedly connected with the embedded steel plate.

According to the aircraft vertical stabilizer overturning tool, the end face of the embedded steel plate is provided with the spare part storage box.

The utility model is described in further detail below with reference to the drawings and the detailed description.

Drawings

Fig. 1 is a schematic diagram of the overall structure of a turnover tool according to an embodiment of the present utility model;

FIG. 2 is an enlarged view of a portion of FIG. 1 at A;

fig. 3 is a partial enlarged view at B in fig. 1.

Reference numerals illustrate: 100 supporting frames, 200 overturning frames, 300 vertical tail joint assemblies, 310 positioning pieces, 311 positioning seats, 312 connecting bolts, 313 safety bolts, 314U-shaped grooves, 320 supporting plates, 330 pressing plates, 400 dividing plates, 500 limiting supports, 700 embedded steel plates and 800 parts storage boxes.

Detailed Description

Referring to fig. 1 to 3, an embodiment of the present utility model provides an aircraft vertical stabilizer overturning tool, which includes an overturning frame 200, a vertical tail joint assembly 300 and two sets of supporting frames 100, wherein two ends of the overturning frame 200 are respectively connected with the two sets of supporting frames 100 in a rotating manner; the vertical tail joint assembly 300 is connected to the turnover frame 200, and comprises a positioning member 310, a supporting plate 320 and a pressing plate 330, wherein the positioning member 310 is used for positioning a vertical tail butt joint hole on the vertical stabilizer, and the pressing plate 330 can move towards the supporting plate 320 so as to press the vertical stabilizer between the pressing plate 330 and the supporting plate 320.

When the vertical stabilizer is turned over, the vertical stabilizer is horizontally placed on the bracket, the positioning piece 310 of the turning tool is inserted into the vertical tail butt joint hole of the vertical stabilizer, the pressing plate 330 and the supporting plate 320 are respectively positioned on the upper side and the lower side of the vertical stabilizer, the pressing plate 330 moves relative to the supporting plate 320, the vertical stabilizer is pressed between the pressing plate 330 and the supporting plate 320, and finally the turning frame 200 is turned upwards relative to the supporting frame 100, so that the vertical stabilizer is driven to turn over. After the overturning of the vertical stabilizer is completed, the vertical stabilizer is in a vertical state, and can be hoisted by a crane, the vertical stabilizer is loosened by the pressing plate 330 and the supporting plate 320, and the positioning piece 310 is pulled out, so that the vertical stabilizer can be hoisted to the vertical tail docking station for vertical tail docking. Therefore, the tool can provide good fixing and positioning for the vertical stabilizer in the process of overturning the vertical stabilizer, and can provide balanced and stable overturning acting force for the vertical stabilizer, so that the vertical stabilizer can be prevented from generating larger shearing force to a stacking position while being convenient to overturn the vertical stabilizer.

Further, referring to fig. 2, the positioning member 310 includes a positioning seat 311, a connection pin 312 and a safety pin 313, the positioning seat 311 has a U-shaped slot 314, the connection pin 312 is detachably connected in the U-shaped slot 314 in a penetrating manner, the connection pin 312 is used for being inserted into a vertical butt hole, the safety pin 313 is vertically distributed with the connection pin 312, and is detachably inserted into a notch of the U-shaped slot 314. The vertical fin joint assemblies 300 are provided with a plurality of groups, and the plurality of groups of vertical fin joint assemblies 300 are distributed along the length direction of the roll-over frame 200. Two sets of positioning members 310 are provided in each set of vertical tail joint assembly 300, the two sets of positioning members 310 are distributed along the width direction of the turnover frame 200, and the two sets of positioning members 310 are located between the supporting plate 320 and the pressing plate 330. When the vertical stabilizer is turned over, the supporting plate 320 and the pressing plate 330 are respectively positioned at the upper side and the lower side of the vertical stabilizer, the connecting bolt 312 is inserted into the vertical tail butt joint hole, and then the safety bolt 313 is inserted, so that the fixing and positioning effects are ensured. After the overturning is completed, the safety plug 313 is pulled out, the connecting plug 312 is pulled out, and the vertical stabilizer can be hoisted for butt joint by loosening the supporting plate 320 and the pressing plate 330.

Further, referring to fig. 3, an index plate 400 is provided at the rotational connection of the roll-over frame 200 and the support frame 100 to facilitate observation of the roll-over angle. Further, a limiting support 500 is provided on the upper side of the support 100, and after the turnover frame 200 is turned upwards, the side of the turnover frame 200 abuts against the limiting support 500, and the turnover frame 200 is limited by the limiting support 500. When the vertical stabilizer is fixed, the turnover frame 200 is positioned in a vertical state, and after the vertical stabilizer is fixed, the turnover frame 200 is turned by 90 degrees and positioned in a horizontal state, and the vertical stabilizer is positioned in a vertical state.

Further, with continued reference to fig. 1, the bottom of the support frame 100 is fixedly connected with a pre-buried steel plate 700, the support frame 100 can be supported and fixed by three feet, and the end surface of the pre-buried steel plate 700 is provided with a spare part storage box 800 so as to be convenient for placing spare parts. Specifically, the flipping of the flipping frame 200 may be driven by a motor.

It should be noted that, in the description of the present utility model, if an azimuth or positional relationship is referred to, for example, upper, lower, front, rear, left, right, etc., the azimuth or positional relationship is based on the azimuth or positional relationship shown in the drawings, it is merely for convenience of describing the present utility model and simplifying the description, and it is not indicated or implied that the referred device or element must have a specific azimuth, be configured or operated in a specific azimuth, and should not be construed as limiting the present utility model.

In the description of the present utility model, a plurality means one or more, and a plurality means two or more, and it is understood that greater than, less than, exceeding, etc. does not include the present number, and it is understood that greater than, less than, within, etc. include the present number. If any, first or second, etc. are described for the purpose of distinguishing between technical features only and not for the purpose of indicating or implying a relative importance or implicitly indicating the number of technical features indicated or implicitly indicating the precedence of the technical features indicated.

In the description of the present utility model, unless explicitly defined otherwise, terms such as arrangement, installation, connection, etc. should be construed broadly and the specific meaning of the terms in the present utility model can be reasonably determined by a person skilled in the art in combination with the specific contents of the technical scheme.

The above embodiments are only preferred embodiments of the present utility model, and the scope of the present utility model is not limited thereto, but any insubstantial changes and substitutions made by those skilled in the art on the basis of the present utility model are intended to be within the scope of the present utility model as claimed.

Claims

1. An aircraft vertical stabilizer upset frock, characterized in that includes:

two sets of support frames (100);

the two ends of the turnover frame (200) are respectively and rotatably connected with the two groups of support frames (100); and

the vertical tail joint assembly (300) is connected to the turnover frame (200) and comprises a positioning piece (310), a supporting plate (320) and a pressing plate (330), wherein the positioning piece (310) is used for positioning a vertical tail butt joint hole on the vertical stabilizer, and the pressing plate (330) can move towards the supporting plate (320) so as to press the vertical stabilizer between the pressing plate (330) and the supporting plate (320).

2. The aircraft vertical stabilizer overturning tooling according to claim 1, wherein the positioning piece (310) comprises a positioning seat (311), a connecting bolt (312) and a safety bolt (313), the positioning seat (311) is provided with a U-shaped groove (314), the connecting bolt (312) is detachably connected in the U-shaped groove (314) in a penetrating manner and is used for being inserted into a vertical butt joint hole, and the safety bolt (313) is vertically distributed with the connecting bolt (312) and is detachably inserted into a notch of the U-shaped groove (314).

3. The aircraft vertical stabilizer overturning tooling of claim 1, wherein the vertical fin connector assemblies (300) are provided with a plurality of groups, and the plurality of groups of vertical fin connector assemblies (300) are distributed along the length direction of the overturning frame (200).

4. An aircraft vertical stabilizer turning tool according to claim 3, wherein two sets of positioning members (310) in each set of vertical tail joint assemblies (300) are provided, the two sets of positioning members (310) are distributed along the width direction of the turning frame (200), and the two sets of positioning members (310) are located between the supporting plate (320) and the pressing plate (330).

5. The aircraft vertical stabilizer overturning tool according to claim 1, wherein an index plate (400) is arranged at the rotating connection part of the overturning frame (200) and the supporting frame (100).

6. The aircraft vertical stabilizer overturning tool according to claim 1, wherein a limiting support (500) is arranged on the upper side portion of the supporting frame (100), and after the overturning frame (200) is overturned upwards, the side portion of the overturning frame (200) abuts against the limiting support (500).

7. The aircraft vertical stabilizer overturning tool according to claim 1, wherein an embedded steel plate (700) is fixedly connected to the bottom of the supporting frame (100).

8. The aircraft vertical stabilizer overturning tooling according to claim 7, wherein the end face of the pre-buried steel plate (700) is provided with a part storage box (800).