CN217260636U

CN217260636U - Horizontal tail supporting device for airplane

Info

Publication number: CN217260636U
Application number: CN202221169409.2U
Authority: CN
Inventors: 田丰; 马浩; 任世海
Original assignee: Harbin Qiangli Aviation Industry Co ltd
Current assignee: Harbin Qiangli Aviation Industry Co ltd
Priority date: 2022-05-16
Filing date: 2022-05-16
Publication date: 2022-08-23
Anticipated expiration: 2032-05-16

Abstract

The utility model discloses an aircraft horizontal tail strutting arrangement, include: arc frame, side direction connecting rod and horizontal tail body, the inside welding of arc frame has the vertical support pole, the left and right sides of vertical support pole all is provided with first extension board, the inboard of first extension board is fixed with the strengthening rib, the lateral surface welding of first extension board has the second extension board, the perforation has been seted up to the inside of arc frame, the middle part lateral surface at the vertical support pole is fixed to the side direction connecting rod, the end of side direction connecting rod is fixed with a supporting beam, the horizontal tail body is located the inboard of arc frame, the leading flank of horizontal tail body is fixed with the connecting piece, the screw has been seted up to the inner wall of connecting piece, the inner of horizontal tail body is provided with the inserted bar. This aircraft horizontal tail strutting arrangement utilizes first extension board, strengthening rib and second extension board to increase this strutting arrangement's intensity, and the stable fixed horizontal tail body.

Description

Horizontal tail supporting device for airplane

Technical Field

The utility model relates to an aircraft horizontal tail supports technical field, specifically is an aircraft horizontal tail strutting arrangement.

Background

The horizontal tail is one of the main large parts of the airplane, called as a horizontal tail fin for short, is generally horizontally arranged at the tail, the front half part of the horizontal tail is immovable and is a horizontal stabilizing surface, and plays a role in pitching stabilization, the rear half part of the horizontal tail is a lifting rudder for controlling the ascending and descending of the airplane, the horizontal tail and the vertical tail are connected by a hinge and are called as tail fins together, and the horizontal tail and the vertical tail can also be comprehensively replaced by a group of V-shaped wings;

the strength of the supporting device of the conventional horizontal tail supporting device of the airplane needs to be improved, and the horizontal tail body is inconvenient to fix stably, so that the supporting device of the horizontal tail of the airplane is provided, and the problems provided in the prior art are solved conveniently.

Disclosure of Invention

An object of the utility model is to provide an aircraft horizontal tail strutting arrangement to solve the current aircraft horizontal tail strutting arrangement who provides among the above-mentioned background art, strutting arrangement's intensity remains to improve, the problem of the fixed horizontal tail body of inconvenient stability.

In order to achieve the above object, the utility model provides a following technical scheme: an aircraft horizontal tail support device comprising:

the supporting device comprises an arc-shaped frame, wherein a vertical supporting rod is welded in the arc-shaped frame, first supporting plates are arranged on the left side and the right side of the vertical supporting rod, reinforcing ribs are fixed on the inner sides of the first supporting plates, second supporting plates are welded on the outer side faces of the first supporting plates, and through holes are formed in the arc-shaped frame;

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

the horizontal tail body is located on the inner side of the arc-shaped frame, a connecting piece is fixed to the front side face of the horizontal tail body, a screw hole is formed in the inner wall of the connecting piece, and an inserting rod is arranged at the inner end of the horizontal tail body.

Preferably, the arc-shaped frame is symmetrically arranged about a transverse center line of the horizontal tail body, and 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 of a U-shaped structure, and the connecting piece is fixedly connected with the supporting beam through a screw.

Preferably, the longitudinal section of inserted bar is "T" style of calligraphy structure, and the inserted bar is located fenestrate inside.

Compared with the prior art, the beneficial effects of the utility model are that: the airplane horizontal tail supporting device utilizes the first supporting plate, the reinforcing ribs and the second supporting plate to increase the strength of the supporting device and stably fix the horizontal tail body;

1. the supporting device is provided with an arc-shaped frame, a first support plate, a reinforcing rib and a second support plate, wherein the first support plate and the second support plate are obliquely arranged on the inner side of the arc-shaped frame;

2. the connecting piece on the horizontal tail body is fixedly connected with the supporting beam through a screw, so that the supporting beam can be conveniently connected by the connecting piece;

3. be provided with horizontal tail body and inserted bar, utilize the inserted bar to connect horizontal tail body and arc frame to deepen being connected of horizontal tail body and arc frame, stably fixed horizontal tail body.

Drawings

FIG. 1 is a schematic front view of the present invention;

FIG. 2 is a front view of the cutting structure of the present invention;

FIG. 3 is a schematic view of the overall structure of the present invention;

fig. 4 is the overall structure schematic diagram of the connecting piece of the present invention.

In the figure: 1. an arc frame; 2. a vertical support bar; 3. a first support plate; 4. reinforcing ribs; 5. a second support plate; 6. a support beam; 7. perforating; 8. a lateral connecting rod; 9. a horizontal tail body; 10. a connecting member; 11. a screw hole; 12. and (4) inserting the rod.

Detailed Description

The technical solutions in the embodiments of the present invention will be described clearly and completely with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative work belong to the protection scope of the present invention.

Referring to fig. 1-4, the present invention provides a technical solution: an airplane horizontal tail supporting device comprises an arc-shaped frame 1, a vertical supporting rod 2, a first supporting plate 3, a reinforcing rib 4, a second supporting plate 5, a supporting beam 6, a through hole 7, a lateral connecting rod 8, a horizontal tail body 9, a connecting piece 10, a screw hole 11 and an inserting rod 12, wherein as shown in figures 1, 2 and 3, the vertical supporting rod 2 is vertically welded on the inner side of the arc-shaped frame 1, the reinforcing rib 4 is fixed on the inner side of the first supporting plate 3, the reinforcing rib 4 is arranged on the inner side of the first supporting plate 3 in an X shape, and the first supporting plate 3 and the second supporting plate 5 are obliquely arranged inside the arc-shaped frame 1;

the first support plate 3 and the second support plate 5 are positioned on the outer side of the central framework of the vertical support rod 2, the first support plate 3 and the second support plate 5 are used for assisting in supporting, and the strength of the arc-shaped frame 1 is improved by the aid of the first support plate 3 and the second support plate 5 which are obliquely arranged;

placing a horizontal tail body 9 between the upper and lower 2 groups of arc-shaped frames 1, wherein the longitudinal section of a connecting piece 10 is in a U-shaped structure, a screw hole 11 is formed in the connecting piece 10, the connecting piece 10 with the longitudinal section in the U-shaped structure is clamped on the outer side of the supporting beam 6, the screw hole 11 in the supporting beam 6 is aligned with the screw hole 11 in the connecting piece 10, and then the connecting piece 10 and the supporting beam 6 are fixed through screws;

as shown in fig. 2, the longitudinal section of the insertion rod 12 is "T" shaped, the insertion rod 12 with the longitudinal section being "T" shaped is inserted into the through hole 7 and the inner part of the horizontal tail body 9, and then the screw is inserted into the horizontal tail body 9 and the insertion rod 12, so that the horizontal tail body 9 is fixed on the inner side of the arc-shaped frame 1, the horizontal tail body 9 is stably installed, and thus a series of operations of the aircraft horizontal tail supporting device are completed.

The utility model discloses the standard part that uses all can purchase from the market, and dysmorphism piece all can be customized according to the description with the record of drawing of description, and the concrete connection mode of each part all adopts conventional means such as ripe bolt, rivet, welding among the prior art, and machinery, part and equipment all adopt prior art, and conventional model, including circuit connection adopts conventional connection mode among the prior art, does not detailed here again.

Although the present invention has been described in detail with reference to the foregoing embodiments, it will be apparent to those skilled in the art that modifications may be made to the embodiments or portions thereof without departing from the spirit and scope of the invention.

Claims

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).