CN217260636U - Horizontal tail supporting device for airplane - Google Patents

Abstract

The utility model discloses an aircraft flat tail support device, comprising: an arc-shaped frame, a lateral connecting rod and a flat tail body, wherein a vertical support rod is welded inside the arc-shaped frame, and the left and right sides of the vertical support rod are provided with There is a first support plate, the inner side of the first support plate is fixed with reinforcing ribs, the outer side of the first support plate is welded with a second support plate, the inside of the arc frame is provided with perforations, the lateral The connecting rod is fixed on the middle outer side of the vertical support rod, the end of the lateral connecting rod is fixed with a support beam, the flat tail body is located on the inner side of the arc frame, the front side of the flat tail body is fixed with a connecting piece, the The inner wall of the connecting piece is provided with a screw hole, and the inner end of the flat tail body is provided with an insertion rod. The aircraft flat tail support device utilizes a first support plate, a reinforcing rib and a second support plate to increase the strength of the support device and stably fix the flat tail body.

Description

An aircraft flat tail support device

technical field

The utility model relates to the technical field of aircraft flat tail support, in particular to an aircraft flat tail support device.

Background technique

The horizontal tail is one of the main parts of the aircraft, referred to as the horizontal tail, which is generally installed on the tail of the aircraft horizontally. The hinge is connected to the former, and the vertical tail and the horizontal tail are collectively called the tail, which can also be replaced by a set of V-shaped wings;

In the existing aircraft flat tail support device, the strength of the support device needs to be improved, and it is inconvenient to stably fix the flat tail body. Therefore, we propose an aircraft flat tail support device to solve the above problems.

SUMMARY OF THE INVENTION

The purpose of the present utility model is to provide an aircraft flat tail support device to solve the problem of the existing aircraft flat tail support device proposed in the above background technology, the strength of the support device needs to be improved, and it is inconvenient to stably fix the flat tail body.

In order to achieve the above-mentioned purpose, the utility model provides the following technical solutions: an aircraft horizontal tail support device, comprising:

An arc-shaped frame, a vertical support rod is welded inside the arc-shaped frame, a first support plate is arranged on the left and right sides of the vertical support rod, a reinforcing rib is fixed on the inner side of the first support plate, and the first support plate is fixed on the inner side of the first support plate. A second support plate is welded on the outer side of one plate, and the inside of the arc-shaped frame is provided with perforations;

a lateral connecting rod, the lateral connecting rod is fixed on the middle outer side surface of the vertical support rod, and the end of the lateral connecting rod is fixed with a support beam;

The flat tail body is located on the inner side of the arc frame, the front side of the flat tail body is fixed with a connecting piece, the inner wall of the connecting piece is provided with a screw hole, and the inner end of the flat tail body is provided with an insertion rod.

Preferably, the arc-shaped frame is symmetrically arranged with respect to the transverse centerline of the flat tail body, and both the first support plate and the second support plate are obliquely arranged inside the arc-shaped frame.

Preferably, the longitudinal section of the connecting piece is in a "U"-shaped structure, and the connecting piece is fixedly connected to the support beam by screws.

Preferably, the longitudinal section of the plunger is a "T"-shaped structure, and the plunger is located inside the perforation.

Compared with the prior art, the beneficial effect of the present utility model is: the aircraft flat tail support device utilizes the first support plate, the reinforcing rib and the second support plate to increase the strength of the support device, and stably fix the flat tail body;

1. An arc-shaped frame, a first support plate, a reinforcing rib and a second support plate are provided, the inner side of the arc-shaped frame is inclined with a first support plate and a second support plate, and the inner side of the first support plate is fixed with a reinforcing rib, Utilize the first support plate, the reinforcing rib and the second support plate to increase the strength of the support device;

2. A support beam, a flat tail body and a connecting piece are provided, and the connecting piece on the flat tail body is fixedly connected with the support beam by screws, which is convenient to use the connecting piece to connect the support beam;

3. A flat tail body and a plunger are provided, and the plunger is used to connect the flat tail body and the arc-shaped frame, thereby deepening the connection between the flat tail body and the arc-shaped frame, and stably fixing the flat tail body.

Description of drawings

Fig. 1 is the front view structure schematic diagram of the present utility model;

Fig. 2 is the front view sectional structure schematic diagram of the present utility model;

3 is a schematic diagram of the overall structure of the utility model;

FIG. 4 is a schematic diagram of the overall structure of the connector of the present invention.

In the figure: 1. Arc frame; 2. Vertical support rod; 3. First support plate; 4. Reinforcing rib; 5. Second support plate; 6. Support beam; 7. Perforation; 9. Flat tail body; 10. Connector; 11. Screw hole; 12. Insertion rod.

Detailed ways

The technical solutions in the embodiments of the present utility model will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the implementations. example. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work fall within the protection scope of the present invention.

1-4, the present utility model provides a technical solution: an aircraft flat tail support device, comprising an arc frame 1, a vertical support rod 2, a first support plate 3, a reinforcing rib 4, a second support plate 5, Support beam 6, through hole 7, lateral connecting rod 8, flat tail body 9, connecting piece 10, screw hole 11 and insert rod 12, as shown in Figure 1, Figure 2 and Figure 3, the inner side of the arc frame 1 is vertically welded with The vertical support rod 2, the inner side of the first support plate 3 is fixed with a reinforcing rib 4, the reinforcing rib 4 is arranged on the inner side of the first support plate 3 in an “X” shape, and the inside of the arc frame 1 is inclined with a first support plate. 3 and the second support plate 5;

The first support plate 3 and the second support plate 5 are located on the outer side of the central frame of the vertical support rod 2, and the first support plate 3 and the second support plate 5 are used for auxiliary support, and the inclined first support plate 3 and the second support plate 5 are used. Improve the strength of the arc frame 1;

The flat tail body 9 is placed between the upper and lower sets of arc-shaped frames 1. As shown in FIG. 4, the longitudinal section of the connecting piece 10 is in a "U" shape, and the interior of the connecting piece 10 is provided with screw holes 11. The connector 10 of the "U"-shaped structure is stuck on the outside of the support beam 6, the screw holes 11 on the support beam 6 are aligned with the screw holes 11 inside the connector 10, and then the connector 10 and the support beam 6 are fixed by screws;

As shown in Figure 2, the longitudinal section of the plunger 12 is in a "T" shape, insert the plunger 12 with a "T" shape in the longitudinal section into the through hole 7 and the flat tail body 9, and then insert the screw through the flat tail The interior of the main body 9 and the insertion rod 12, thereby fixing the flat tail body 9 on the inner side of the arc frame 1, and stably installing the flat tail body 9, the above will complete a series of operations of the aircraft flat tail support device, which is not described in detail in this description The content belongs to the prior art known to those skilled in the art.

The standard parts used in the utility model can be purchased from the market, the special-shaped parts can be customized according to the description in the specification and the drawings, and the specific connection method of each part adopts the mature bolts, rivets and welding in the prior art. and other conventional means, the machinery, parts and equipment all adopt the conventional models in the prior art, and the circuit connection adopts the conventional connection manner in the prior art, which will not be described in detail here.

Although the present invention has been described in detail with reference to the foregoing embodiments, for those skilled in the art, it is still possible to modify the technical solutions described in the foregoing embodiments, or perform equivalent replacements for some of the technical features. Within the spirit and principle of the present utility model, any modifications, equivalent replacements, improvements, etc. made shall be included within the protection scope of the present utility model.

Claims (4)

1. The utility model provides an aircraft horizontal tail strutting arrangement which characterized in that: the method comprises the following steps:

the novel arc-shaped frame comprises an arc-shaped frame (1), wherein a vertical supporting rod (2) is welded inside the arc-shaped frame (1), first supporting plates (3) are arranged on the left side and the right side of the vertical supporting rod (2), reinforcing ribs (4) are fixed on the inner sides of the first supporting plates (3), second supporting plates (5) are welded on the outer side surfaces of the first supporting plates (3), and through holes (7) are formed inside the arc-shaped frame (1);

the lateral connecting rod (8) is fixed on the outer side surface of the middle part of the vertical supporting rod (2), and a supporting beam (6) is fixed at the tail end of the lateral connecting rod (8);

the horizontal tail body (9), the horizontal tail body (9) is located the inboard of arc frame (1), the leading flank of horizontal tail body (9) is fixed with connecting piece (10), screw (11) have been seted up to the inner wall of connecting piece (10), the inner of horizontal tail body (9) is provided with inserted bar (12).

2. An aircraft horizontal tail support device according to claim 1, wherein: the arc-shaped frame (1) is symmetrically arranged relative to the transverse center line of the horizontal tail body (9), and the first support plate (3) and the second support plate (5) are obliquely arranged inside the arc-shaped frame (1).

3. An aircraft horizontal tail support device according to claim 1, wherein: the longitudinal section of the connecting piece (10) is of a U-shaped structure, and the connecting piece (10) is fixedly connected with the supporting beam (6) through a screw.

4. The aircraft horizontal tail supporting device according to claim 1, wherein: the longitudinal section of the inserted bar (12) is of a T-shaped structure, and the inserted bar (12) is positioned inside the through hole (7).

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