CN118025498A

CN118025498A - Aircraft load cabin and aircraft

Info

Publication number: CN118025498A
Application number: CN202410193444.5A
Authority: CN
Inventors: 刘庆; 杨思文; 钟文; 马熊洪; 谭友德; 朱璇; 王巧云; 刘继承; 胡善刚
Original assignee: General Designing Institute of Hubei Space Technology Academy
Current assignee: General Designing Institute of Hubei Space Technology Academy
Priority date: 2024-02-21
Filing date: 2024-02-21
Publication date: 2024-05-14

Abstract

The application relates to an aircraft load cabin and an aircraft. An aircraft load compartment, comprising: the load assembly is provided with a bracket assembly, and two ends of the load assembly can be respectively in butt joint with the front cabin body and the rear cabin body through the bracket assembly; the load cabin shell is provided with a cavity, the load assembly is accommodated in the cavity, the load cabin shell is in floating connection with the bracket assembly in the axial direction, and is in restraining fit with the bracket assembly in the radial direction. The load assembly, the front section cabin body, the rear section cabin body and the load cabin shell are installed in a butt joint mode through the support, the main loads such as bending moment, axial force and overload in the flying process are borne by the loaded cabin body, and the cabin body only meets the dimension requirement. The excellent bearing capacity of the shell of the load is fully utilized, the bearing requirement of the cabin is greatly reduced, the mounting structure of the load is simplified, and the problems of light structure and space layout are solved. Meanwhile, the thermal deformation matching problem of the cabin body and the load is solved by adopting the mode of radially restraining and axially floating connection of the cabin body and the load.

Description

Aircraft load cabin and aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft load cabin and an aircraft.

Background

The load cabin is a device container for the aircraft to execute space tasks, is a key component for protecting the safety of effective load during launching and recovery, and needs to adapt to different working conditions of multiple stages of the aircraft. Wherein the payload cabin is positioned in the middle cabin section of the aircraft, and the front end and the rear end are respectively in butt joint with the two cabin sections. According to the mission profile requirement of the aircraft, the load cabin is required to have the characteristics of pneumatic bearing, heat protection, heat sealing, space protection and the like.

The load cabin is internally provided with an aircraft load, the aircraft load needs to be reliably installed in the aircraft cabin body to realize the functions of the aircraft load, and the load installation structure needs to meet the requirements of bearing, heat insulation, space coordination, assembly manufacturability and the like. The traditional load mounting structure is generally mounted on a flange of the cabin section shell by adopting a transfer bracket, loads such as overload of the load are borne by the cabin section shell, and loads such as bending moment and axial force in the flight process are borne by the cabin section shell. With the continuous improvement of the performance of an aircraft, the aircraft has put strict requirements on the light weight of the structure. When the effective load of the aircraft is larger and larger, the cabin body is required to meet the bearing requirement, so that the structural quality is often increased, and the light weight requirement of the aircraft is difficult to meet. In order to meet the requirements of compact installation of the large load of the aircraft and light weight of the structure, an innovative installation structure form is urgently needed for the large load of the aircraft.

Disclosure of Invention

In the related art, the load performance requirement of the load cabin of the aircraft is improved, so that the mass of the cabin shell is increased, and the light weight requirement of the aircraft is difficult to meet.

In a first aspect, an embodiment of the present application provides an aircraft load compartment comprising:

the load assembly is provided with a bracket assembly, and two ends of the load assembly can be respectively in butt joint with the front cabin body and the rear cabin body through the bracket assembly;

The load cabin shell is provided with a cavity, the load assembly is accommodated in the cavity, and the load cabin shell is in floating connection with the bracket assembly in the axial direction and is in restraining fit with the bracket assembly in the radial direction.

With reference to the first aspect, in one embodiment, one of the front end and the rear end of the load compartment housing is in constraint fit with the bracket assembly in the radial direction of the load compartment housing, and the other end of the front end and the rear end of the load compartment housing are in floating connection with the bracket assembly in the axial direction of the load compartment housing.

With reference to the first aspect, in one embodiment, the bracket assembly includes:

The front bracket is assembled at the front end of the load assembly, at least one first screw is arranged in the front bracket, and the first screw radially extends along the load assembly and penetrates through the load cabin shell;

and the rear bracket is connected with the load cabin shell and the load assembly through at least one second screw and at least one third screw respectively.

In combination with the first aspect, in one embodiment, the front bracket is provided with a waist-shaped hole through which the first screw passes and a nut, the nut is connected with the first screw through a bolt, and the waist-shaped hole is arranged with the first screw in a clearance way in the axial direction of the load assembly.

With reference to the first aspect, in one embodiment, the load compartment housing includes:

A case main body;

and the mounting flange is mounted on the inner side surface of the rear end of the shell main body and is connected with the second screw bolt.

With reference to the first aspect, in one embodiment, the outer surface of the shell body is provided with a heat-resistant layer.

With reference to the first aspect, in one embodiment, a sealing ring is provided between the housing body and the bracket assembly.

With reference to the first aspect, in one embodiment, a cable network optical hole is provided at an end surface of the rear bracket.

With reference to the first aspect, in one embodiment, a front end surface of the load compartment housing is in clearance fit with a rear end surface of the front compartment housing.

In a second aspect, the present application provides an aircraft comprising: an aircraft load compartment according to any preceding claim.

The technical scheme provided by the embodiment of the application has the beneficial effects that at least:

The load assembly, the front section cabin body, the rear section cabin body and the load cabin shell are installed in a butt joint mode through the support, the main loads such as bending moment, axial force and overload in the flying process are borne by the loaded cabin body, and the cabin body only meets the dimension requirement. The excellent bearing capacity of the shell of the load is fully utilized, the bearing requirement of the cabin is greatly reduced, the mounting structure of the load is simplified, and the problems of light structure and space layout are solved. Meanwhile, the thermal deformation matching problem of the cabin body and the load is solved by adopting the mode of radially restraining and axially floating connection of the cabin body and the load.

Drawings

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for the description of the embodiments will be briefly described below, and it is apparent that the drawings in the following description are only some embodiments of the present application, and other drawings may be obtained according to these drawings without inventive effort for a person skilled in the art.

FIG. 1 is a cross-sectional view of a load compartment from a first perspective in accordance with an embodiment of the invention;

FIG. 2 is a partial schematic view of the area A of FIG. 1 of the present description;

FIG. 3 is a partial schematic view of region B of FIG. 1 of the present description;

FIG. 4 is a cross-sectional view of a second view of a load compartment in a docked condition with front and rear compartments in accordance with an embodiment of the present invention;

FIG. 5 is a partial schematic view of the area A of FIG. 4 of the present description;

FIG. 6 is a partial schematic view of region B of FIG. 4 of the present description;

FIG. 7 is an axial schematic view of a rear bracket according to an embodiment of the present invention;

fig. 8 is a cross-sectional view of a load assembly in an embodiment of the invention.

In the figure: 1. a load assembly; 11. a load front flange; 12. a load rear flange; 2. a bracket assembly; 21. a front bracket; 211. a waist-shaped hole; 212. a nut; 22. a rear bracket; 221. a cable network optical aperture; 222. a first opening; 223. a second opening; 224. a third opening; 23. a first screw; 24. a second screw; 25. a third screw; 3. a load compartment housing; 31. a case main body; 311. a front end face; 32. a mounting flange; 33. a heat-resistant layer; 4. a front cabin; 5. a rear cabin body; 6. a seal ring; 61. a first seal ring; 62. a second seal ring; 7. and (5) connecting bolts.

Detailed Description

In order that those skilled in the art will better understand the present application, a technical solution in the embodiments of the present application will be clearly and completely described below with reference to the accompanying drawings in which it is apparent that the described embodiments are only some embodiments of the present application, not all embodiments. All other embodiments, which can be made by those skilled in the art based on the embodiments of the application without making any inventive effort, are intended to be within the scope of the application.

In a first aspect, as shown in fig. 1 and 4, the present application provides an aircraft load compartment comprising: a load assembly 1 and a load compartment housing 3; wherein,

The load assembly 1 is provided with a bracket assembly 2, and two ends of the load assembly 1 can be respectively in butt joint with the front cabin body 4 and the rear cabin body 5 through the bracket assembly 2; the load compartment housing 3 is provided with a cavity, the load assembly 1 is accommodated in the cavity, and the load compartment housing 3 is in floating connection with the bracket assembly 2 in the axial direction and is in restraining fit with the bracket assembly 2 in the radial direction.

It will be appreciated that the conventional load mounting structure is typically mounted on the flange of the cabin shell using an adapter bracket, and that loads such as overload of the load are borne by the cabin shell, and that loads such as bending moment and axial force during flight are also borne by the cabin shell. With the continuous improvement of the performance of an aircraft, the aircraft has put strict requirements on the light weight of the structure. The payload of the aircraft is bigger and bigger, and the cabin body is used for meeting the bearing requirement, so that the structural quality is large, and the lightweight requirement of the aircraft is difficult to meet. In the embodiment, the load assembly 1 is in butt joint with the front cabin body 4 and the rear cabin body 5 through the bracket assembly 2 and is installed with the load cabin shell 3, the load cabin shell is used for bearing main loads such as bending moment, axial force and overload in the flying process, and the cabin body only meets the dimension requirement. Further, the thermal deformation matching problem of the cabin body and the load is solved by means of radial constraint and axial floating connection of the cabin body and the load.

In some embodiments, one of the front and rear ends of the load compartment housing 3 is engaged with the bracket assembly 2 in a radial constraint manner of the load compartment housing 3, and the other end is in floating connection with the load compartment housing 3 in the axial direction, and the other end is fixedly connected with the bracket assembly 2 in the axial direction of the load compartment housing 3.

It should be noted that, the load cabin shell 3 is easy to deform and elongate under the pneumatic heating when the aircraft flies, in order to meet the requirement of structural matching, one end of the load cabin shell 3 and the bracket assembly 2 are limited only radially, and a gap is arranged in the axial direction so as to adapt to the extension deformation.

In some specific embodiments, as shown in fig. 1, 2 and 3, the bracket assembly 2 includes: a front bracket 21 and a rear bracket 22; wherein,

The front bracket 21 is assembled at the front end of the load assembly 1, at least one first screw 23 is arranged in the front bracket 21, and the first screw 23 extends along the radial direction of the load assembly 1 and penetrates through the load compartment housing 3. A rear bracket 22 connected to the load compartment housing 3 and the load assembly 1 by at least one second screw 24 and at least one third screw 25, respectively.

It should be noted that, the second screw 24 passes through the opening of the rear bracket 22 and is screwed and fixed with the mounting flange 32 of the load compartment housing 3, so that the axial fixing constraint of the load assembly 1, the rear bracket 22 and the load compartment housing 3 is realized, and the second screw 24 must not protrude out of the rear end surface of the rear bracket 22 after being mounted. The present embodiment employs 12 sets of second screws 24 altogether to achieve fixation of both. Further, the rear bracket 22 is provided with a countersunk slot, the third screw 25 passes through a light hole on the rear bracket 22 to be connected with a threaded hole of the load rear flange 12, the third screw 25 does not protrude out of the rear end surface of the rear bracket 22 after being mounted, and the load assembly 1 and the rear bracket 22 are connected through 12 groups of third screws 25 in the embodiment.

In some preferred embodiments, as shown in fig. 2, the front bracket 21 is provided with a waist-shaped hole 211 through which the first screw 23 passes, and a nut 212, where the nut 212 is connected with the first screw 23 by a bolt, and the waist-shaped hole 211 is disposed with a gap between the first screw 23 in the axial direction of the load assembly 1. Further, the front end surface 311 of the load compartment case 3 and the front end surface of the front bracket 21 leave a gap in the axial direction.

Optionally, the front end 311 of the load compartment housing 3 is in clearance fit with the rear end of the front compartment 4.

It will be appreciated that, since a sufficient axial clearance is left between the first screw 23 and the waist-shaped hole 211, when the load compartment housing 3 is axially deformed, the first screw 23, the load compartment housing 3 and the nut 212 slide together relative to the front bracket 21, and are ensured not to be constrained by the structure during the deformation of the load compartment housing 3, so as to meet the requirement of matching the axial deformation of the load compartment housing 3.

Preferably, as shown in fig. 2, the first screw 23 is designed with a heat shielding layer to meet the heat shielding requirements.

In some specific embodiments, as shown in fig. 1 and 4, the load compartment housing 3 comprises: a case main body 31 and a mounting flange 32; wherein,

And a mounting flange 32 mounted on an inner side surface of the rear end of the case main body 31, wherein the mounting flange 32 is screw-coupled to the second screw 24.

Preferably, in order to enhance the heat insulation effect, the outer surface of the case main body 31 is provided with a heat-proof layer 33.

In some alternative embodiments, in order to meet the sealing requirements of the load compartment housing 3, a sealing ring 6 is provided between the housing body 31 and the bracket assembly 2.

Specifically, as shown in fig. 6 and 5, 1 first seal ring 61 is provided between the load compartment case 3 and the front bracket 21. Between the load compartment housing 3 and the rear support 22, 1 second sealing ring 62 is arranged radially. Also, the abutting surfaces of the front bracket 21 and the front cabin body 4 and the abutting surfaces of the rear bracket 22 and the rear cabin body 5 are sealed.

In some alternative embodiments, as shown in fig. 7, the rear bracket 22 is designed with 4 groups of holes, the first hole 222 is a hole for connecting the rear bracket 22 with the load compartment housing 3, the second hole 223 is a threaded hole for connecting the rear bracket 22 with the rear part of the load compartment housing 3, and the third hole 224 is a hole for connecting the rear bracket 22 with the load component 1. Further, a cable network hole 221 is arranged at the end face of the rear bracket 22, the cable network hole 221 is a cable network hole channel of the rear bracket 22, and the cable network hole 221 is designed to be arranged at the long axis position of the special-shaped load compartment housing 3, so that the requirement of space coordination is met, and the mounting structure of the rear bracket 22 and the load compartment housing 3, the load component 1 and the load compartment housing 3 is required to meet the requirement of space coordination, bearing and operation manufacturability.

It will be appreciated that after the load assembly 1 and the load compartment housing 3 are assembled into a module, the front end of the module is connected with the front compartment body 4 by bolts through the threaded holes on the front bracket 21, and the rear end of the module is connected with the rear compartment body 5 by bolts through the threaded holes on the rear bracket 22, and an end face sealing ring is designed between the abutting faces of the compartment bodies to meet the sealing requirement. It can be seen that the transfer of force of the aircraft in the load compartment position is achieved by the housing of the load assembly 1, the load compartment housing 3 only functioning as a pneumatic dimension. As shown in fig. 8, the load assembly 1 comprises a main housing, and a load front flange 11 and a load rear flange 12 mounted on the main housing for interfacing with the front and rear brackets.

In the second embodiment provided by the application, for the short-axis section of the abnormal cabin body, the connecting structure of the rear support 22 and the load cabin shell 3 is designed in a radial direction without a space, so that the section of the part only considers the connecting design of the load assembly 1 and the rear support 22, and the connecting structure of the load cabin shell 3 and the rear support 22 is required to be arranged according to the actual space during the specific design.

In a second aspect, the present application provides an aircraft comprising: an aircraft load compartment, the aircraft load compartment comprising: a load assembly 1 and a load compartment housing 3; wherein,

In a third aspect, the present application provides a method for assembling the aircraft described above: firstly, the butt joint of the load assembly 1 and the rear bracket 22 is completed; secondly, the module is in butt joint with the load cabin shell 3; the front bracket 21 is used for connecting the load assembly 1 with the front end of the load cabin shell 3 again; finally, the whole module is in butt joint with the front cabin body 4 and the rear cabin body 5.

In summary, the load assembly, the front cabin body, the rear cabin body and the load cabin shell are installed in a butt joint mode through the support, the main loads such as bending moment, axial force and overload in the flying process are borne by the loaded shell, and the cabin body only meets the dimension requirement. The excellent bearing capacity of the shell of the load is fully utilized, the bearing requirement of the cabin is greatly reduced, the mounting structure of the load is simplified, and the problems of light structure and space layout are solved. Meanwhile, the thermal deformation matching problem of the cabin body and the load is solved by adopting the mode of radially restraining and axially floating connection of the cabin body and the load.

In the description of the present application, it should be noted that the azimuth or positional relationship indicated by the terms "upper", "lower", etc. are based on the azimuth or positional relationship shown in the drawings, and are merely for convenience of describing the present application and simplifying the description, and are not indicative or implying that the apparatus or element in question must have a specific azimuth, be constructed and operated in a specific azimuth, and thus should not be construed as limiting the present application. Unless specifically stated or limited otherwise, the terms "mounted," "connected," and "coupled" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, or integrally connected; can be mechanically or electrically connected; can be directly connected or indirectly connected through an intermediate medium, and can be communication between two elements. The specific meaning of the above terms in the present application can be understood by those of ordinary skill in the art according to the specific circumstances.

It should be noted that in the present application, relational terms such as "first" and "second" and the like are used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Moreover, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements does not include only those elements but may include other elements not expressly listed or inherent to such process, method, article, or apparatus. Without further limitation, an element defined by the phrase "comprising one … …" does not exclude the presence of other like elements in a process, method, article, or apparatus that comprises the element.

The foregoing is only a specific embodiment of the application to enable those skilled in the art to understand or practice the application. Various modifications to these embodiments will be readily apparent to those skilled in the art, and the generic principles defined herein may be applied to other embodiments without departing from the spirit or scope of the application. Thus, the present application is not intended to be limited to the embodiments shown herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. An aircraft load compartment, comprising:

The load assembly (1) is provided with a bracket assembly (2), and two ends of the load assembly (1) can be respectively in butt joint with the front cabin body (4) and the rear cabin body (5) through the bracket assembly (2);

The load cabin shell (3) is internally provided with a cavity, the load assembly (1) is accommodated in the cavity, and the load cabin shell (3) is in floating connection with the bracket assembly (2) in the axial direction and is in constraint fit with the bracket assembly (2) in the radial direction.

2. The aircraft load compartment of claim 1, wherein: one of the front end and the rear end of the load cabin shell (3) is in radial constraint fit with the support assembly (2) in the load cabin shell (3), the front end and the rear end of the load cabin shell (3) are in floating connection in the axial direction of the load cabin shell (3), and the other end of the load cabin shell is in fixed connection with the support assembly (2) in the axial direction of the load cabin shell (3).

3. The aircraft load compartment according to claim 2, wherein the bracket assembly (2) comprises:

the front support (21) is assembled at the front end of the load assembly (1), at least one first screw (23) is arranged in the front support (21), and the first screw (23) extends along the radial direction of the load assembly (1) and penetrates through the load cabin shell (3);

-a rear bracket (22) connected to the load compartment housing (3) and the load assembly (1) by means of at least one second screw (24) and at least one third screw (25), respectively.

4. An aircraft load compartment according to claim 3, wherein: the front support (21) is provided with a waist-shaped hole (211) and a nut (212) which are used for the first screw (23) to pass through, the nut (212) is connected with the first screw (23) through bolts, and the waist-shaped hole (211) is arranged with the first screw (23) in a clearance way in the axial direction of the load assembly (1).

5. An aircraft load compartment according to claim 3, wherein the load compartment housing (3) comprises:

A case main body (31);

And a mounting flange (32) mounted on the inner side surface of the rear end of the housing main body (31), wherein the mounting flange (32) is connected with the second screw (24) through bolts.

6. The aircraft load compartment of claim 5, wherein: the outer surface of the shell main body (31) is provided with a heat-proof layer (33).

7. The aircraft load compartment of claim 5, wherein: a sealing ring (6) is arranged between the shell main body (31) and the bracket component (2).

8. An aircraft load compartment according to claim 3, wherein: a cable network optical hole (221) is formed in the end face of the rear support (22).

9. The aircraft load compartment of claim 1, wherein: the front end face (311) of the load cabin shell (3) is in clearance fit with the rear end face of the front cabin body (4).

10. An aircraft, comprising: an aircraft load compartment according to any one of claims 1 to 9.