CN115556916A

CN115556916A - Foldable nose, aircraft and overhauling method

Info

Publication number: CN115556916A
Application number: CN202211238720.2A
Authority: CN
Inventors: 许兴; 赖志伟; 邴富强
Original assignee: Xiamen Tengxi Aviation Technology Co ltd
Current assignee: Xiamen Tengxi Aviation Technology Co ltd
Priority date: 2022-09-28
Filing date: 2022-09-28
Publication date: 2023-01-03

Abstract

The invention relates to a foldable nose which is arranged at the front part of a body of an aircraft and comprises a nose top plate and a nose shell, wherein the nose shell is connected to the lower part of the nose top plate; the nose top plate and the inside nose shell form a nose cabin, and the nose cabin is internally provided with the avionic equipment. The invention also provides an aircraft which comprises the foldable nose. The invention also provides a method for overhauling the aircraft by using the foldable nose, wherein the aircraft comprises the foldable nose. The nose can be turned over in this case design, with the avionics equipment setting of aircraft can turn over the nose cabin of turning over the inside of nose. When the maintenance, dismantle can turn over the fixed back of rolling over a nose and can directly turn up the nose, greatly increased maintenance efficiency.

Description

Foldable nose, aircraft and overhauling method

Technical Field

The invention relates to a foldable nose and an aircraft with the foldable nose. The invention also relates to a method for overhauling the aircraft by using the turnover nose.

The invention belongs to the technical field of aircraft nose structures in a narrow sense.

Background

The autorotation rotorcraft is a rotor type aviation aircraft taking autorotation rotors as lifting surfaces and propeller thrust as advancing power. The rotor of the rotorcraft provides lift force and attitude control moments such as pitching and rolling, so that the rotor of the rotorcraft is always in a self-rotating state by blowing in front of the rotor in case of the engine parking in the air, and the rotorcraft still can safely land by means of the self-rotating of the rotor, unlike a helicopter which drives the rotor by means of the power of the engine.

The body shell of the autorotation rotorcraft is generally made of glass fiber reinforced plastics, carbon fibers and the like, and the upper part of the body shell is provided with an opening to form a related manned cabin body and the like, so that when the autorotation rotorcraft is overhauled, equipment such as seats in the manned cabin body and the like are generally required to be firstly dismantled and then overhauled. And when the staff overhauls, the engine body shell can not be dismantled and surrounds the staff, so that the range of motion of the staff is small, and the overhauling efficiency is low.

Disclosure of Invention

In order to solve the problems, the invention aims to provide a foldable nose which is convenient for aircraft maintenance.

The embodiment of the invention is realized by adopting the following scheme: the foldable nose is arranged at the front part of the aircraft body and comprises a nose top plate and a nose shell, the nose shell is connected to the lower part of the nose top plate, the nose top plate is connected to the aircraft body in a foldable manner, and the nose shell is detachably connected with the aircraft body;

the nose top plate and the inside of the nose shell form a nose cabin, and the avionic equipment is installed in the nose cabin.

Preferably, the nose top plate is a D-shaped plate, wherein an arc-shaped edge of the D shape is positioned at the front part of the machine body and is used for installing the nose shell; the straight edge of the D shape is positioned at the middle front part of the machine body, and the straight edge is connected with the machine body through a hinge.

Preferably, a plurality of mounting holes are formed in the two sides of the nose casing, which are connected with the machine body.

Preferably, a cross beam is arranged in the machine body, and the bottom surface of the nose top plate is abutted against the cross beam.

Preferably, the nose cabin is communicated with the inner cavity of the fuselage.

In addition, the invention also provides an aircraft which comprises the foldable nose.

In addition, the invention also provides a method for overhauling the aircraft by using the foldable nose, wherein the aircraft comprises the foldable nose, and the method comprises the following steps:

diagnosing the fault position of the aircraft, and determining the avionics equipment of which the fault position is positioned in the nose cabin;

the nose shell is detached from the machine body, the nose shell is turned upwards, the nose shell drives the nose top plate to turn, the nose top plate is turned along the joint of the nose shell and the machine body, the nose cabin is turned over to the upper side of the machine body, and the avionic equipment in the nose cabin is directly exposed outside;

and (4) overhauling the avionic equipment, turning the avionic equipment back to the nose cabin, fixing the connection between the nose shell and the aircraft body, and completing the overhauling of the aircraft.

The nose can be turned over in this case design, with the avionics equipment setting of aircraft can turn over the nose cabin of turning over the inside of nose. When the maintenance, dismantle can turn over the fixed back of rolling over a nose and can directly turn up the nose, greatly increased maintenance efficiency. The nose that turns up makes inside avionics equipment directly expose externally, the going on of the work of being convenient for overhaul.

The invention provides a method for overhauling an aircraft by using a foldable nose, which greatly simplifies the maintenance steps and improves the maintenance efficiency compared with the prior art.

Drawings

FIG. 1 is a perspective view of the present invention;

FIG. 2 is a first structural diagram of the present invention;

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

FIG. 4 is a third schematic structural diagram of the present invention;

FIG. 5 is a flow chart of a method of servicing an aircraft of the present invention.

Description of reference numerals: the foldable nose-10, the body-100, the nose top plate-1, the nose shell-2, the nose cabin-3, the mounting hole-20, the cross beam-101 and the avionic device-200.

Detailed Description

The invention is further described with reference to the following figures and specific embodiments.

Referring to fig. 1 to 5, the foldable nose 10 is disposed at the front of a fuselage 100 of an aircraft, and includes a nose top plate 1 and a nose casing 2, the nose casing 2 is connected to the lower portion of the nose top plate 1, the nose top plate 1 is connected to the fuselage 100 in a foldable manner, and the nose casing 2 is detachably connected to the fuselage 100;

the nose top plate 1 and the interior of the nose shell 2 form a nose cabin 3, and the avionic device 200 is installed in the nose cabin 3. The foldable nose 10 is mainly used for arranging the avionics equipment 200 of the aircraft in the nose cabin 3 inside the foldable nose 10. When in maintenance, the nose can be directly turned up after the disassembly can turn over the nose 10 to be fixed, thereby greatly increasing the maintenance efficiency. The turned nose enables the avionics device 200 inside to be directly exposed outside, and therefore maintenance work is facilitated.

Further, when the nose top plate 1 and the nose casing 2 are combined into an undetachable member, it can be considered that the solution of the present invention is modified. The nose is split into a nose top plate 1 and a nose shell 2 in the scheme, and the assembly of the aircraft is only facilitated.

The nose top plate 1 is a D-shaped plate, wherein a D-shaped arc edge is positioned at the front part of the machine body 100 and is used for installing the nose shell 2; the straight side of the "D" shape is located at the middle front portion of the body 100, and the straight side is connected to the body 100 by a hinge. The reason why the D-shaped plate is adopted at the top of the nose is that the aircraft related to the scheme is more particularly used as a rotary rotorcraft for freight transportation. The top adopts "D" font plate, has both satisfied the pneumatic design needs of aircraft, can place the goods again at the plate top.

A plurality of mounting holes 20 are formed on two sides of the nose casing 2 connected with the machine body 100. In the present case, the nose casing 2 and the body 100 are connected by fitting screws into the mounting holes 20.

A cross beam 101 is arranged in the fuselage 100, and the bottom surface of the nose top plate 1 is abutted against the cross beam 101. The nose top plate 1 is supported by a cross beam 101 at the bottom and has certain bearing capacity.

The nose cabin 3 is communicated with the inner cavity of the fuselage 100.

In addition, the invention also provides an aircraft which comprises the foldable nose. It can be considered that the aircraft which is provided with the avionics device 200 in the nose and can realize the inspection of the avionics device by designing the foldable nose is designed in relation to the present case.

In addition, the invention also provides a method for overhauling an aircraft by using the foldable nose, wherein the aircraft comprises the foldable nose, and the method comprises the following steps:

the first step is as follows: diagnosing the fault position of the aircraft, and determining the avionics device 200 of which the fault position is positioned inside the nose cabin 3;

the second step is that: the nose shell 2 of the aircraft is detached from the aircraft body 100, the nose shell 2 is turned upwards, the nose shell 2 drives the nose top plate 1 to turn, the nose top plate 1 is turned along the joint of the nose top plate and the aircraft body 100, the nose cabin 3 is turned over above the aircraft body 100, and the avionic device 200 in the nose cabin 3 is directly exposed outside;

the third step: and (4) overhauling the avionics equipment 200, turning back the nose cabin 3, fixing the nose shell 2 to be connected with the aircraft body 100, and completing the overhauling of the aircraft.

Compared with the existing aircraft maintenance, the method for maintaining the aircraft by using the turnover nose has the advantages that the maintenance steps are greatly simplified and the maintenance efficiency is improved by combining the turnover nose 10 structure.

The points to be explained are: first, in the description of the present application, it should be noted that, unless otherwise specified and limited, the terms "mounted," "connected," "connecting," and "connecting" should be understood broadly, and may be a mechanical connection or an electrical connection, or a communication between two elements, and may be directly connected, and "upper," "lower," "left," and "right" are used only to indicate a relative positional relationship, and when an absolute position of an object to be described is changed, the relative positional relationship may be changed.

Secondly, the method comprises the following steps: in the drawings of the disclosed embodiments of the invention, only the structures related to the disclosed embodiments are referred to, other structures can refer to common designs, and the same embodiment and different embodiments of the invention can be combined mutually without conflict.

Finally, the above description is only a preferred embodiment of the present invention, and the scope of the present invention is not limited to the above examples, and all technical solutions belonging to the idea of the present invention belong to the scope of the present invention.

Claims

1. Can turn over a nose (10), set up in fuselage (100) front portion of aircraft, its characterized in that: the nose-mounted aircraft nose comprises a nose top plate (1) and a nose shell (2), wherein the nose shell (2) is connected to the lower part of the nose top plate (1), the nose top plate (1) is connected to an aircraft body (100) in a turnover manner, and the nose shell (2) is detachably connected with the aircraft body (100);

the nose top plate (1) and the nose shell (2) form a nose cabin (3), and the nose cabin (3) is internally provided with avionic equipment.

2. The foldable nose of claim 1, wherein: the nose top plate (1) is a D-shaped plate, wherein the D-shaped arc edge is positioned at the front part of the nose body (100), and the arc edge is used for installing the nose shell (2); the straight edge of the D shape is positioned in the middle front part of the machine body (100), and the straight edge is connected with the machine body (100) through a hinge.

3. The foldable nose of claim 1, wherein: a plurality of mounting holes (20) are formed in the two sides of the nose shell (2) connected with the machine body (100).

4. The foldable nose of claim 1, wherein: a cross beam (101) is arranged in the machine body (100), and the bottom surface of the nose top plate (1) is abutted against the cross beam (101).

5. The foldable nose of claim 1, wherein: the nose cabin (3) is communicated with the inner cavity of the machine body (100).

6. An aircraft comprising a foldable nose according to claims 1-5.

7. A method of servicing an aircraft that includes a foldable nose according to claims 1-5, using the foldable nose, the method comprising the steps of:

diagnosing the fault position of the aircraft, and determining the avionics equipment of which the fault position is positioned in the nose cabin (3);

the nose shell (2) of the aircraft is detached from the aircraft body (100), the nose shell (2) is turned upwards, the nose shell (2) drives the nose moving top plate (1) to turn, the nose moving top plate (1) is turned along the joint of the nose moving top plate and the aircraft body (100), the nose cabin (3) is turned over above the aircraft body (100), and the avionic equipment in the nose cabin (3) is directly exposed outside;

the avionics equipment is overhauled, the nose cabin (3) is folded back, the nose shell (2) is fixed to be connected with the aircraft body (100), and the aircraft is overhauled.