CN111891331A

CN111891331A - Transport airplane

Info

Publication number: CN111891331A
Application number: CN202010734255.6A
Authority: CN
Inventors: 吉飞; 王小军; 钱礼; 李梓衡
Original assignee: Xian Aircraft Design and Research Institute of AVIC
Current assignee: Xian Aircraft Design and Research Institute of AVIC
Priority date: 2020-07-27
Filing date: 2020-07-27
Publication date: 2020-11-06

Abstract

The application belongs to the field of airplane overall structures, and particularly relates to a transport airplane convenient for cargo handling. Including fuselage, wing and fin, the fuselage includes: the cargo hold structure comprises a front machine body (1), wherein a first cargo hold (61) is arranged inside the front machine body (1), and a first separation surface (31) is arranged at the rear end of the front machine body (1); the front end of the rear machine body (2) is provided with a second separation surface (32); back fuselage (2) with be provided with swivel pivot (5) between preceding fuselage (1), swivel pivot (5) can be controlled back fuselage (2) are realized opening or are closed, when being in the closed position, first parting surface (31) of preceding fuselage (1) with second parting surface (32) of back fuselage (2) are connected through fuselage lock (4) cooperation. This application is based on current conventional pneumatic general aircraft of overall arrangement, overcomes not enough that current mode brought, and convenient goods loading and unloading agrees with the use scene, promotes customer experience.

Description

Transport airplane

Technical Field

The application belongs to the field of airplane overall structures, and particularly relates to a transport airplane.

Background

Transport aircraft equipped with cargo holds are often designed on the basis of general-purpose aircraft, and often the cargo handling is carried out along the previous hatch door access, for example, in a hatch cover upturning manner, see fig. 1, in which the cargo handling passage is directed upwards and only has to be carried out by means of a spreader, and the cargo handling is at a certain risk. Meanwhile, the cabin door is opened upwards, the stability of the cabin cover is insufficient, and the cabin cover is sensitive to wind, so that the use condition is limited. The other is a newly added cabin door, for example, a mode that the cabin door is opened laterally is adopted, referring to fig. 2, a cargo loading and unloading channel is open, but a working area is positioned between a wing and an empennage, and the cargo is easy to collide with a machine body structure during loading and unloading; meanwhile, a process of pushing goods to the front part is required after the goods are loaded into the cargo hold, so that the manual burden of loading and unloading the goods is increased, and the use is inconvenient; the lateral hatch is also not conducive to the loading and unloading of longer cargo.

Accordingly, a technical solution is desired to overcome or at least alleviate at least one of the above-mentioned drawbacks of the prior art.

Disclosure of Invention

It is an object of the present application to provide a transport aircraft to address at least one of the problems of the prior art.

The technical scheme of the application is as follows:

a transport aircraft comprising a fuselage, wings and a tail, the fuselage comprising:

the cargo hold structure comprises a front machine body, a first cargo hold is arranged in the front machine body, and a first separation surface is arranged at the rear end of the front machine body;

the front end of the rear machine body is provided with a second separation surface;

the back fuselage with be provided with the pivot of rotation between the preceding fuselage, rotating assembly can control back fuselage realizes opening or closing, works as when back fuselage is in closed position, the front end of back fuselage with the rear end of preceding fuselage passes through the fuselage lock cooperation and connects, makes the second parting plane with first parting plane is closed.

Optionally, a second cargo compartment is provided inside the rear fuselage.

Optionally, first separation face department is provided with first separation face frame, second separation face department is provided with second separation face frame, there is annular seal through layering demountable installation on the second separation face frame, works as the second separation face with when first separation face is closed, annular seal is compressed and is realized sealedly.

Optionally, the rotating assemblies are arranged in two groups up and down along the rear machine body and the front machine body.

Optionally, the rotating assembly includes a double-lug joint, a single-lug joint, and a rotating pivot connecting the double-lug joint and the single-lug joint, the double-lug joint is disposed on the front body, the single-lug joint is disposed on the rear body, and the rear body can rotate around the rotating pivot by more than 120 degrees.

Optionally, the fuselage lock includes a double-lug joint, a single-lug joint, a connecting pin, a connecting rod, and a steering rocker arm, the double-lug joint is disposed on the rear fuselage, the single-lug joint is disposed on the front fuselage, the connecting pin connects the double-lug joint with the single-lug joint, the steering rocker arm is disposed at one end of the connecting pin through the connecting rod, when the rear fuselage is in a closed position, the steering rocker arm is rotated, and the connecting rod drives the connecting pin to connect the double-lug joint with the single-lug joint.

Optionally, the plurality of the body locks are arranged along the circumferential direction of the rear body and the front body.

Optionally, a plurality of connecting pins of the body lock share one steering rocker arm to form a link mechanism, and a handle is arranged on the link mechanism and can be used for synchronously opening and closing all the body locks.

Optionally, a release spring is provided on the pitman arm.

Optionally, the rear fuselage is locked with the ipsilateral wing when the rear fuselage is in an open position.

The invention has at least the following beneficial technical effects:

the transport plane is convenient for loading and unloading goods, after the rear body is opened, the cargo hold in the front body is exposed out of the first separating surface to form a natural cargo loading and unloading channel, the cargo is loaded and unloaded in one step, the transport plane is higher in convenience, and the cargo is loaded and unloaded without auxiliary tools such as hoisting tools; the working space is open, after the rear machine body is opened, the cargo loading and unloading working space is completely open at the other opened side of the rear machine body and in the opposite direction of the cargo compartment, and meanwhile, the space at the opened side of the rear machine body is also relatively open, so that the operation requirement can be met; the goods adaptability is high, the cargo hold rear part is adopted for loading, longer goods can be conveniently loaded in place at one time, and most goods types can be covered through the auxiliary design of a freight transportation system.

Drawings

FIG. 1 is a schematic illustration of the overall structure of one embodiment of a prior art transport aircraft;

FIG. 2 is a schematic illustration of the overall structure of another embodiment of a transport aircraft of the prior art;

FIG. 3 is a structural schematic view of an aft fuselage of a transport aircraft of an embodiment of the present application in a closed position;

FIG. 4 is a structural schematic view of an aft fuselage of a transport aircraft in an open position according to an embodiment of the subject application;

FIG. 5 is a schematic illustration of a parting plane seal configuration of a transport aircraft according to an embodiment of the present application;

FIG. 6 is a schematic illustration of a rotating assembly of a transport aircraft according to an embodiment of the present application;

fig. 7 is a schematic illustration of a fuselage lock configuration of a transport aircraft according to an embodiment of the present application.

Wherein:

1-a front fuselage; 2-rear fuselage; 31-a first separating surface; 32-second separating surface; 33-pressing strips; 34-an annular seal; 4-a fuselage lock; 5-a rotating assembly; 61-a first cargo compartment; 62-second cargo compartment.

Detailed Description

In order to make the implementation objects, technical solutions and advantages of the present application clearer, the technical solutions in the embodiments of the present application will be described in more detail below with reference to the drawings in the embodiments of the present application. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are a subset of the embodiments in the present application and not all embodiments in the present application. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present application and should not be construed as limiting the present application. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present application. Embodiments of the present application will be described in detail below with reference to the accompanying drawings.

In the description of the present application, it is to be understood that the terms "center", "longitudinal", "lateral", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are used merely for convenience in describing the present application and for simplifying the description, and do not indicate or imply that the referenced device or element must have a particular orientation, be constructed in a particular orientation, and be operated, and therefore should not be construed as limiting the scope of the present application.

The present application is described in further detail below with reference to fig. 3 to 7.

The application provides a transport aircraft, which comprises a fuselage, wings and a tail wing.

Specifically, a separating surface is arranged at the middle rear part of the fuselage to divide the fuselage into a front fuselage and a rear fuselage. A first cargo hold 61 is arranged in the front body 1, and a first separation surface 31 is arranged at the rear end of the front body 1; the front end of the rear machine body 2 is provided with a second separation surface 32; be provided with rotating assembly 5 between back fuselage 2 and the preceding fuselage 1, rotating assembly 5 can control back fuselage 2 and realize opening or closing, and when back fuselage 2 was in the closed position, the front end of back fuselage 2 passed through fuselage lock 4 cooperations with the rear end of preceding fuselage 1 and is connected for second parting surface 32 and first parting surface 31 are closed.

In an embodiment of the present application, a first cargo hold 61 is provided inside the front body 1, a second cargo hold 62 is also provided inside the rear body 2, cargo loading is realized through the front and rear cargo holds, the body parting plane is a cargo hold loading and unloading channel, and cargo loading systems can be additionally installed inside the cargo holds according to customer requirements, so that cargo loading and fixing can be more conveniently performed.

In one embodiment of the present application, a sealing structure is disposed between the first separating surface 31 and the second separating surface 32, a second separating surface frame is disposed at the second separating surface 32, an annular sealing member 34 is mounted on the second separating surface frame through a bead 33, and when the second separating surface 32 is closed with the first separating surface 31, the annular sealing member 34 is compressed, and a sealing effect is generated to achieve sealing. In this embodiment, the bead 33 is used to fix the ring seal 34 to the second separating surface 32, and is removable to facilitate installation and replacement of the ring seal 34.

In one embodiment of the present application, the rotating assemblies 5 are disposed on the sides of the first separating surface 31 of the front body 1 and the second separating surface 32 of the rear body 2, and the rotating assemblies 5 are disposed in two sets up and down along the rear body 2 and the front body 1. Rotating assembly 5 is single ears hinge structure, connects including the ears, the monaural connects to and connect the rotation pivot that the ears connect and the monaural connects, and the ears connect the setting in the front on fuselage 1, and the monaural connects the setting on fuselage 2 at the back, and back fuselage 2 can rotate to one side of fuselage around rotation pivot, and when fuselage 2 was in the open position after, the angle that back fuselage 2 opened was greater than 120 degrees. Advantageously, in this embodiment, the rear fuselage 2 is locked with the same side wing or other structure when the rear fuselage 2 is in the open position.

In an embodiment of the application, preceding fuselage 1 docks the locking through fuselage lock 4 with back fuselage 2, fuselage lock 4 includes that the ears connect, the monaural connects, the connecting pin, connecting rod and steering rocker, the ears connect and set up on back fuselage 2, the monaural connects the setting on fuselage 1 in the front, the connecting pin connects the ears to be connected with the monaural, steering rocker passes through the connecting rod setting in the one end of connecting pin, when back fuselage 2 is in closed position, rotate the steering rocker, it connects the ears to be connected with the monaural through the connecting rod drive connecting pin. Advantageously, a plurality of body locks 4 may be arranged along the circumferential direction of the rear body 2 and the front body 1, and a plurality of connecting pins of the body locks 4 share a steering rocker arm to form a link mechanism, and the connecting pins are connected in common through a link mechanism, and a handle is provided on the link mechanism to enable synchronous opening and closing of all the body locks 4. In this embodiment, the single-lug and double-lug connectors are butted by controlling the connecting pins of the 6 body locks 4 through a single handle, so that the opening and locking of the rear body 4 are facilitated. Advantageously, in this embodiment, a release spring is also provided on the steering rocker arm.

The transport aircraft is convenient for cargo loading and unloading, after the rear aircraft body 2 is opened, the first cargo hold 61 in the front aircraft body 1 is exposed out of the first separating surface 31, and the second cargo hold 62 in the rear aircraft body 2 is exposed out of the second separating surface 32, so that a natural cargo loading and unloading channel is formed, cargo loading and unloading are completed in one step, convenience is higher, and auxiliary tools such as hoisting tools and the like are not needed for loading and unloading of the cargo; the working space is open, after the rear machine body 2 is opened, the cargo loading and unloading working space is completely open at the other side of the rear machine body and in the opposite direction of the cargo compartment, meanwhile, the opening angle of the rear machine body 2 is greater than 120 degrees, and the rear space at the opening side is also relatively open, so that the operation requirement can be met; the goods adaptability is high, and the structure of front and back fuselage can be convenient once load longer goods and put in place, can also cover most goods types through the auxiliary design of freight transportation system. This application is based on current conventional general aircraft of pneumatic overall arrangement, overcomes the current not enough that the goods in-process brought of loading and unloading are opened to the mode through upper portion and lateral part hatch door, further facilitates the goods loading and unloading, agrees with the use scene, promotes customer experience.

The above description is only for the specific embodiments of the present application, but the scope of the present application is not limited thereto, and any changes or substitutions that can be easily conceived by those skilled in the art within the technical scope of the present application should be covered within the scope of the present application. Therefore, the protection scope of the present application shall be subject to the protection scope of the claims.

Claims

1. A transport aircraft comprising a fuselage, wings and a tail, wherein the fuselage comprises:

the cargo hold structure comprises a front machine body (1), wherein a first cargo hold (61) is arranged inside the front machine body (1), and a first separation surface (31) is arranged at the rear end of the front machine body (1);

the front end of the rear machine body (2) is provided with a second separation surface (32);

back fuselage (2) with be provided with swivel pivot (5) between preceding fuselage (1), rotating assembly (5) can be controlled back fuselage (2) are realized opening or are closed, work as when back fuselage (2) are in the closed position, the front end of back fuselage (2) with the rear end of preceding fuselage (1) passes through fuselage lock (4) cooperation and connects, makes second parting surface (32) with first parting surface (31) are closed.

2. A transport aircraft as claimed in claim 1, characterized in that the interior of the rear fuselage (2) is provided with a second cargo compartment (62).

3. A transport aircraft as claimed in claim 1, characterized in that a first separating surface frame is provided at the first separating surface (31), a second separating surface frame is provided at the second separating surface (32), a ring seal (34) is detachably mounted on the second separating surface frame by means of a bead (33), the ring seal (34) being compressed for sealing when the second separating surface (32) is closed with the first separating surface (31).

4. A transport aircraft according to claim 1, characterized in that the rotating assemblies (5) are arranged in two groups one above the other along the rear fuselage (2) and the front fuselage (1).

5. A transport aircraft as claimed in claim 4, characterized in that the swivel assembly (5) comprises a binaural joint, a monaural joint and a swivel pivot connecting the binaural joint and the monaural joint, the binaural joint being arranged on the front fuselage (1) and the monaural joint being arranged on the rear fuselage (2), the rear fuselage (2) being rotatable about the swivel pivot by more than 120 degrees.

6. A transport aircraft as claimed in claim 1, characterized in that the fuselage lock (4) comprises a binaural joint, a monaural joint arranged on the rear fuselage (2), a connecting pin arranged on the front fuselage (1), a connecting rod connecting the binaural joint with the monaural joint, and a steering rocker arranged at one end of the connecting pin by means of the connecting rod, the steering rocker being rotated when the rear fuselage (2) is in the closed position, the connecting pin being carried by means of the connecting rod to connect the binaural joint with the monaural joint.

7. A transport aircraft as claimed in claim 6, characterized in that the fuselage locks (4) are arranged in a plurality in the circumferential direction of the rear fuselage (2) and the front fuselage (1).

8. A transport aircraft as claimed in claim 7, characterized in that the connecting pins of a plurality of fuselage locks (4) share one steering rocker, constituting a linkage mechanism, which is provided with a handle enabling the simultaneous opening and closing of all the fuselage locks (4).

9. A transporting aircraft as claimed in claim 8, characterised in that a release spring is provided on the steering arm.

10. A transport aircraft as claimed in claim 1, characterized in that the rear fuselage (2) is locked with the same-side wing when the rear fuselage (2) is in the open position.