CN210479052U

CN210479052U - Novel aircraft engine installing support

Info

Publication number: CN210479052U
Application number: CN201821561991.0U
Authority: CN
Inventors: 霍甜; 欧阳星; 徐强; 张文祺; 曾晓康
Original assignee: Zhuoer Aircraft Manufacturing Wuhan Co ltd
Current assignee: Zhuoer Aircraft Manufacturing Wuhan Co ltd
Priority date: 2018-09-25
Filing date: 2018-09-25
Publication date: 2020-05-08
Anticipated expiration: 2028-09-25

Abstract

The utility model discloses a novel aircraft engine mounting bracket, which comprises a first round pipe, a large cylindrical ring, a support plate, a second round pipe, a third round pipe, a fourth round pipe, a fifth round pipe, a sixth round pipe, a first small cylindrical ring and a second small cylindrical ring, wherein the third round pipe and the fourth round pipe have the same size and shape, and the third round pipe and the fourth round pipe are horizontally arranged; two ends of the third circular tube and the fourth circular tube are fixedly welded with large cylindrical rings, two large cylindrical rings fixedly welded with the third circular tube are fixedly welded with six circular tubes which are arranged downwards and outwards in an inclined mode, and the six circular tubes are arranged in a trisymmetrical mode relative to the circular tubes; the two large cylindrical rings which are fixedly welded with the circular tube I are fixedly welded with a circular tube I which is arranged downwards and outwards in an inclined mode; the utility model discloses the engine mounting bracket adopts the position that firm spatial structure designed to fix the engine, this utility model invention, simple structure, and safe firm fixes a position accurately, simple to operate, and it is easy to dismantle, facilitates for the assembly of engine.

Description

Novel aircraft engine installing support

Technical Field

The utility model relates to a mounting bracket specifically is a novel aircraft engine installing support.

Background

At present, civil aviation fixed wing aircrafts at home and abroad are developed more and more rapidly, the types of the aircrafts are more and more diverse, and the installation requirements on aircraft engines are more and more strict. The engine is the core part of the aircraft, and good installation can not only ensure the performance of the aircraft, but also avoid potential safety hazard. The engine type of conventional civil aviation fixed wing aircraft only has several kinds, but present engine installing support is safe firm inadequately, and its location is accurate inadequately for the assembly of engine is comparatively difficult, thereby influences the practicality of device.

Disclosure of Invention

An object of the utility model is to provide a novel aircraft engine installing support to solve the problem that proposes among the above-mentioned background art.

In order to achieve the above object, the utility model provides a following technical scheme:

a novel aircraft engine mounting bracket comprises a first round pipe, a large cylindrical ring, a support plate, a second round pipe, a third round pipe, a fourth round pipe, a fifth round pipe, a sixth round pipe, a first small cylindrical ring and a second small cylindrical ring, wherein the third round pipe and the fourth round pipe are the same in size and shape, and are horizontally arranged; two ends of the third circular tube and the fourth circular tube are fixedly welded with large cylindrical rings, two large cylindrical rings fixedly welded with the third circular tube are fixedly welded with six circular tubes which are arranged downwards and outwards in an inclined mode, and the six circular tubes are arranged in a trisymmetrical mode relative to the circular tubes; the two large cylindrical rings welded and fixed with the first circular tube are welded and fixed with the first circular tube which is arranged downwards and outwards in an inclined mode, the two first circular tubes are arranged symmetrically with respect to the fourth circular tube, and the first circular tube and the sixth circular tube which are positioned on the same side are welded and fixed with the first small cylindrical ring; the circular tube III is welded with two circular tubes II which are arranged downwards and outwards in an inclined mode, the two circular tubes II are symmetrically arranged relative to the circular tube III, and one ends, far away from the circular tube III, of the two circular tubes II are welded and fixed with the supporting plate; six welding of pipe have two pipes five that set up downwards and lean out, and two pipes five keep away from the equal welded fastening of one end of pipe four and have small circle post ring two, and two pipes five set up about pipe four-way external symmetry.

As a further aspect of the present invention: the supporting plate is provided with a plurality of threaded holes.

As a further aspect of the present invention: the first two small cylindrical rings and the second two small cylindrical rings are located on the same plane.

As a further aspect of the present invention: the four large cylindrical rings are positioned on the same plane.

Compared with the prior art, the beneficial effects of the utility model are that: the utility model discloses the engine mounting bracket adopts the position that firm spatial structure designed to fix the engine, this utility model invention, simple structure, and safe firm fixes a position accurately, simple to operate, and it is easy to dismantle, facilitates for the assembly of engine.

Drawings

FIG. 1 is a schematic top view of a novel aircraft engine mounting bracket.

Fig. 2 is a schematic diagram of an axial structure of a novel aircraft engine mounting bracket.

FIG. 3 is a side view schematic diagram of a novel aircraft engine mounting bracket.

In the figure: the device comprises a first round pipe 1, a large cylindrical ring 2, a supporting plate 3, a second round pipe 4, a third round pipe 5, a fourth round pipe 6, a fifth round pipe 7, a sixth round pipe 8, a first small cylindrical ring 9 and a second small cylindrical ring 10.

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 to 3, in an embodiment of the present invention, a novel aircraft engine mounting bracket includes a first circular tube 1, a large cylindrical ring 2, a support plate 3, a second circular tube 4, a third circular tube 5, a fourth circular tube 6, a fifth circular tube 7, a sixth circular tube 8, a first small cylindrical ring 9 and a second small cylindrical ring 10, where the third circular tube 5 and the fourth circular tube 6 have the same size and shape, and the third circular tube 5 and the fourth circular tube 6 are both horizontally disposed; two ends of the circular tube III 5 and two ends of the circular tube IV 6 are respectively fixedly welded with a large cylindrical ring 2, the two large cylindrical rings 2 which are fixedly welded with the circular tube III 5 are respectively fixedly welded with a circular tube VI 8 which is arranged downwards and outwards in an inclined mode, and the two circular tubes VI 8 are symmetrically arranged around the circular tube III 5; the two large cylindrical rings 2 welded and fixed with the circular tube four 6 are respectively welded and fixed with a circular tube I1 which is arranged downwards and outwards in an inclined mode, the two circular tubes I1 are symmetrically arranged relative to the circular tube four 6, and the circular tube I1 and the circular tube six 8 which are positioned on the same side are respectively welded and fixed with the small cylindrical ring I9; the two circular tubes II 4 which are arranged downwards and outwards in an inclined mode are welded on the circular tube III 5, the two circular tubes II 4 are symmetrically arranged about the circular tube III 5, one ends, far away from the circular tube III 5, of the two circular tubes II 4 are welded and fixed with the supporting plate 3, the supporting plate 3 is provided with two symmetrically arranged threaded holes, and locking screws which are arranged in a matched mode can be inserted into the threaded holes, so that the supporting plate 3 is fixed with the airplane body; the support is characterized in that two circular tubes five 7 which are arranged downwards and outwards in an inclined mode are welded on the circular tube six 8, small cylindrical rings two 10 are welded and fixed at one ends, far away from the circular tube four 6, of the two circular tubes five 7, the two circular tubes five 7 are symmetrically arranged outwards relative to the circular tube four 6, the whole support forms a space mechanism and is symmetrical left and right, so that the strength and the connection stability of the support are guaranteed, the two small cylindrical rings one 9 and the two small cylindrical rings two 10 are matched with a positioning piece on the airplane body, so that the mounting position of the support is positioned, after the positioning is completed, the support plate 3 is fixedly connected with the airplane body, the two small cylindrical rings one 9 and the two small cylindrical rings two 10 are fixed with the positioning piece on the airplane body through a locking device, the locking device is the prior art, and the details are omitted; when the engine is in the switching, four big cylindricality rings 2 are inserted respectively to the setting element on the engine, carry out the location of earlier stage, fix a position the back, fix on the installing support through locking device, and locking device is prior art, and it is unnecessary to describe here.

The two first small cylindrical rings 9 and the two second small cylindrical rings 10 are located on the same plane.

The four large cylindrical rings 2 are located on the same plane.

In the description of the present invention, it should be noted that the terms "vertical", "horizontal", "inner", "outer", "front", "back", and the like indicate the orientation or positional relationship based on the drawings, and are only for convenience of describing the present invention and simplifying the description, but do not indicate or imply that the device or element indicated must have a specific orientation, be constructed and operated in a specific orientation, and thus cannot be understood as a limitation to the present invention.

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. A novel aircraft engine mounting bracket comprises a first round pipe (1), a large cylindrical ring (2), a support plate (3), a second round pipe (4), a third round pipe (5), a fourth round pipe (6), a fifth round pipe (7), a sixth round pipe (8), a first small cylindrical ring (9) and a second small cylindrical ring (10), and is characterized in that the size and the shape of the third round pipe (5) and the fourth round pipe (6) are the same, and the third round pipe (5) and the fourth round pipe (6) are horizontally arranged; two ends of the circular tube III (5) and two ends of the circular tube IV (6) are fixedly welded with large cylindrical rings (2), two large cylindrical rings (2) which are fixedly welded with the circular tube III (5) are fixedly welded with circular tubes VI (8) which are arranged downwards and outwards in an inclined mode, and the two circular tubes VI (8) are symmetrically arranged relative to the circular tube III (5); the two large cylindrical rings (2) welded and fixed with the four circular tubes (6) are respectively welded and fixed with a first circular tube (1) which is arranged downwards and outwards in an inclined mode, the two first circular tubes (1) are symmetrically arranged relative to the four circular tubes (6), and the first circular tube (1) and the sixth circular tube (8) which are positioned on the same side are respectively welded and fixed with a first small cylindrical ring (9); the round pipe III (5) is welded with two round pipes II (4) which are arranged downwards and outwards in an inclined mode, the two round pipes II (4) are symmetrically arranged relative to the round pipe III (5), and one ends, far away from the round pipe III (5), of the two round pipes II (4) are welded and fixed with the supporting plate (3); six (8) welding of pipe have two pipes five (7) that set up downwards and lean out, and the equal welded fastening of one end that pipe four (6) were kept away from in two pipes five (7) has small circle post ring two (10), and two pipes five (7) set up about pipe four (6) outside symmetry.

2. A novel aircraft engine mounting bracket according to claim 1, characterised in that the support plate (3) is provided with a plurality of threaded holes.

3. A novel aircraft engine mounting bracket as defined in claim 1, wherein the two first small cylindrical rings (9) and the two second small cylindrical rings (10) are located in the same plane.

4. A novel aircraft engine mounting bracket according to claim 1, characterised in that the four large cylindrical rings (2) lie in the same plane.