CN110606188A

CN110606188A - Large-wing airplane

Info

Publication number: CN110606188A
Application number: CN201910861405.7A
Authority: CN
Inventors: 成立
Original assignee: Qingdao Hillock New Energy Technology Co Ltd
Current assignee: Qingdao Hillock New Energy Technology Co Ltd
Priority date: 2019-09-12
Filing date: 2019-09-12
Publication date: 2019-12-24

Abstract

The invention relates to a large-wing aircraft, which comprises an aircraft body, wherein two sides of the aircraft body are provided with enlarged wings; the aircraft body top is equipped with the support column of erectting, the symmetry is provided with a plurality of stay cord on the support column, the stay cord is connected to on the wing. The invention supports the wings at two sides through the upright support columns and the pull ropes, so that the wings can be freely lengthened, widened and weighted. The lengthening of the wings is increased, so that the airplane can fly more stably; the volume of the wing is increased, so that the space inside the wing is increased, and the increase of the cargo capacity of the airplane is facilitated.

Description

Large-wing airplane

Technical Field

The invention relates to the technical field of aircraft manufacturing, in particular to a large-wing aircraft.

Background

The wings are important components of the airplane and are main components used for generating lift force on the airplane, and the wings generate the lift force to support the airplane to fly in the air. It also serves a certain stabilizing and handling function. The area and size of the wing has a certain influence on the stable operation of the aircraft. Because the wings are arranged on the two sides of the fuselage, the supporting effect of the fuselage on the wings can be influenced due to the overlarge area or overlong length of the wings, so that the area and size of the conventional wings can be limited, and the airplane with the large wings is developed for improving the flying stability of the airplane and the supporting effect on the wings.

Disclosure of Invention

The invention aims to provide a large-wing aircraft which has strong flight stability and stable support to wings.

In order to solve the technical problems, the technical scheme of the invention is as follows: a large-wing airplane comprises a fuselage, wherein both sides of the fuselage are provided with enlarged wings; the aircraft body top is equipped with the support column of erectting, the symmetry is provided with a plurality of stay cord on the support column, the stay cord is connected to on the wing.

Preferably, the number of the pull ropes is even and the pull ropes are symmetrically arranged on two sides of the pull rope.

Preferably, the pull ropes are in an annular array with the support column as a center.

As a preferred technical scheme, the number of the support columns is multiple, the support columns are arranged on the top of the airplane from front to back, and the support columns are all provided with pull ropes connected to the wings.

According to a preferable technical scheme, a fuselage extension body is arranged at the top of the fuselage, two sides of the fuselage extension body extend to the upper portion of the wing, and the fuselage extension body covers the outer sides of the supporting columns and the pull ropes.

Due to the adoption of the technical scheme, the invention has the beneficial effects that: the invention supports the wings at two sides through the upright support columns and the pull ropes, so that the wings can be freely lengthened, widened and weighted. The lengthening of the wings is increased, so that the airplane can fly more stably; the volume of the wing is increased, so that the space inside the wing is increased, and the increase of the cargo capacity of the airplane is facilitated;

because the fuselage extension body is arranged on the fuselage, the height of the airplane is increased, the internal space is enlarged, the loading capacity of the airplane is increased, and the stability and the safety of the airplane in operation are improved; compared with the airplane with the same loading capacity, the airplane body has greatly reduced weight.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

FIG. 1 is a schematic structural diagram of a first embodiment of the present invention;

FIG. 2 is a left side view of FIG. 1;

FIG. 3 is a schematic structural diagram of a second embodiment of the present invention;

fig. 4 is a schematic structural diagram of a third embodiment of the present invention.

Detailed Description

The first embodiment is as follows:

as shown in fig. 1 and 2, a large-wing aircraft comprises a fuselage 1, wherein both sides of the fuselage 1 are provided with enlarged wings 2; the top of the fuselage 1 is provided with a vertical supporting column 3, the supporting column 3 is symmetrically provided with a plurality of pulling ropes 4, the pulling ropes 4 are connected to the wings 2, and the pulling ropes 4 are preferably steel cables.

In this embodiment, the number of the support columns 3 is 1, two pull ropes 4 are symmetrically connected to the support columns 3, and the two pull ropes 4 are symmetrically connected to the wing 2 to support the wing 2. In this embodiment, the quantity of stay cord 4 is not restricted and 2, and the quantity of stay cord can be even number and symmetry setting in the both sides of stay cord 4, makes the pulling force of support column both sides keep balance.

The top of the machine body 1 is provided with a machine body extending body 5, and the machine body extending body 5 covers the outer sides of the supporting columns 3 and the pull ropes 4.

In this embodiment, two sides of the fuselage extension 5 extend to the top of the wing 2, the support columns 3 and the pull ropes 4 are both located inside the fuselage extension 5, and the top of the airplane extends a support grid structure into the fuselage extension and is integrated with the fuselage

The fuselage extension body 5 encloses a storage space at the top of the fuselage, and can be used for carrying goods or loading equipment, so that the cargo carrying capacity of the airplane is improved.

In the invention, the fuselage extension body 5 is not arranged, the supporting columns and the pull ropes are exposed, the fuselage extension body 5 is only raised at the top of the fuselage 1, and the fuselage extension body 5 is provided with a through hole for the pull rope 4 to extend out and be connected with the wing 2.

Example two:

as shown in fig. 3, in this embodiment, the aircraft is long, the wings are widened and lengthened, the number of the support columns 3 is 2 or more than 2, two support columns 3 are arranged at the top of the aircraft from front to back, pull ropes 4 connected to the wings 2 are mounted on the support columns 3, and the wings 2 have two support points.

In the invention, the number of the support columns can be more than 2, and the support columns are sequentially arranged on the top of the fuselage 1 from front to back, so that the wing 2 has multi-point support.

Example three:

as shown in fig. 4, in this embodiment, a support column 3 is disposed at the top of the fuselage 1, a plurality of pull ropes 4 connected to the wings 2 are disposed on the support column 3, and the pull ropes 4 are in an annular array with the support column 3 as a center, so that the pull forces applied to the support column 3 are kept balanced, and the wings 2 can be supported in a multi-point balanced manner.

The foregoing shows and describes the general principles, essential features, and advantages of the invention. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.

Claims

1. A large-wing aircraft, comprising a fuselage, characterized in that: enlarged wings are arranged on two sides of the fuselage; the aircraft body top is equipped with the support column of erectting, the symmetry is provided with a plurality of stay cord on the support column, the stay cord is connected to on the wing.

2. A large-wing aircraft according to claim 1, wherein: the number of the pull ropes is even and the pull ropes are symmetrically arranged on two sides of the pull ropes.

3. A large-wing aircraft according to claim 1 or claim 2, wherein: the pull ropes are in an annular array by taking the support column as a center.

4. A large-wing aircraft according to claim 1, wherein: the aircraft comprises an aircraft body, a plurality of supporting columns, a plurality of wing supporting plates and a plurality of wing supporting plates, wherein the supporting columns are arranged on the top of the aircraft from front to back, and pull ropes connected to the wings are mounted on the supporting columns.

5. A large-wing aircraft according to claim 1, wherein: the top of fuselage is equipped with the fuselage extension body, the both sides of fuselage extension body extend to the wing top, the fuselage extension body cover is established the outside of support column and stay cord.