CN115180172A - Method for producing a side wall panel in a load compartment, wall panel, arrangement, storage medium and installation - Google Patents
Method for producing a side wall panel in a load compartment, wall panel, arrangement, storage medium and installation Download PDFInfo
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- CN115180172A CN115180172A CN202210694764.XA CN202210694764A CN115180172A CN 115180172 A CN115180172 A CN 115180172A CN 202210694764 A CN202210694764 A CN 202210694764A CN 115180172 A CN115180172 A CN 115180172A
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/10—Bulkheads
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Abstract
The application discloses a method for manufacturing a side wall plate in a load compartment, the wall plate, a device, a storage medium and equipment, which relate to the technical field of aircraft manufacturing, and the method comprises the following steps: according to the position of the cabin door connector, a plurality of rotary shaft connectors are arranged on the inner side wall plate body; according to the overall strength and rigidity of the load compartment, a plurality of arched support beams are arranged on the inner side wall plate body; according to the distribution of missile hanging devices, a hanging frame is arranged on the inner side wall plate body; according to the position of an engine, a T-shaped beam and a thrust beam are arranged at one end of the inner side wall plate body close to the engine, the T-shaped beam is connected with a rotating shaft joint close to the T-shaped beam and a supporting beam, and the thrust beam is connected with two supporting beams close to the T-shaped beam. The functional requirements of the side wall plates in the load compartment and the main force transmission path of the integral structure are considered, the manufacturing method of the wall plates is optimized, and the structural stability of the wall plates after the wall plates are manufactured is ensured.
Description
Technical Field
The application relates to the technical field of aircraft manufacturing, in particular to a method, a wall plate, a device, a storage medium and equipment for manufacturing a side wall plate in a load cabin.
Background
As a novel material, compared with other materials, the composite material has the characteristics of high specific strength, high specific stiffness, strong mechanical property designability and the like, so that the composite material can obviously reduce the weight of an airplane when applied to a large-sized wallboard, and improve the safety and the economy.
Disclosure of Invention
The application mainly aims to provide a method for manufacturing a load compartment inner side wall plate, a device, a storage medium and equipment, and aims to solve the problem that the prior art lacks a method for manufacturing a load compartment inner side wall plate capable of ensuring the stability of the wall plate.
In order to achieve the above purpose, the embodiments of the present application adopt the following technical solutions:
in a first aspect, an embodiment of the present application provides a method for manufacturing a side wall plate in a load compartment, including the following steps:
according to the position of the cabin door connector, a plurality of rotary shaft connectors are arranged on the inner side wall plate body;
according to the overall strength and rigidity of the load compartment, a plurality of arched support beams are arranged on the inner side wall plate body;
according to the distribution of missile hanging devices, a hanging frame is arranged on the inner side wall plate body;
according to the position of an engine, a T-shaped beam and a thrust beam are arranged at one end of the inner side wall plate body close to the engine, the T-shaped beam is connected with a rotating shaft joint close to the T-shaped beam and a supporting beam, and the thrust beam is connected with two supporting beams close to the T-shaped beam.
In one possible implementation manner of the first aspect, after the T-shaped beam and the thrust beam are provided at one end of the inner side wall panel body close to the engine according to the engine position, and the T-shaped beam is connected to the rotating shaft joint and the support beam close thereto, and the thrust beam is connected to the two support beams close thereto, the method for manufacturing the load compartment inner side wall panel further includes:
and according to the position of the thrust beam, a cover is arranged on the inner side wall plate body close to the thrust beam.
In one possible implementation manner of the first aspect, after the T-shaped beam and the thrust beam are provided at one end of the inner side wall panel body close to the engine according to the engine position, and the T-shaped beam is connected to the rotating shaft joint and the support beam close thereto, and the thrust beam is connected to the two support beams close thereto, the method for manufacturing the load compartment inner side wall panel further includes:
and cap-shaped reinforcing ribs are arranged on the inner side wall plate body according to the positions of the supporting beam and the thrust beam.
In one possible implementation of the first aspect, the cap-shaped stiffener is wet-fitted with the inner side wall panel body.
In one possible implementation manner of the first aspect, before the plurality of rotary shaft joints are provided on the inside wall panel body according to the position of the door adapter, the method for manufacturing a side wall panel in a load compartment further includes:
and carrying out prepreg curing molding on the composite material to obtain the inner side wall plate body.
In one possible implementation manner of the first aspect, the rotating shaft joint at the non-main bearing frame position of the inner side wall plate body is connected with the supporting beam.
In a second aspect, embodiments of the present application provide a load compartment inner wall panel manufactured by the method for manufacturing a load compartment inner wall panel according to any one of the first aspect.
In a third aspect, an embodiment of the present application provides an apparatus for manufacturing a side wall plate in a load compartment, including:
the first execution module is used for arranging a plurality of rotary shaft joints on the inner side wall plate body according to the position of the cabin door joint device;
the second execution module is used for arranging a plurality of arched support beams on the inner side wall plate body according to the integral strength and rigidity of the load compartment;
the third execution module is used for arranging a hanging frame on the inner side wall plate body according to the distribution of the missile hanging devices;
and the fourth execution module is used for arranging a T-shaped beam and a thrust beam at one end of the inner side wall plate body close to the engine according to the position of the engine, connecting the T-shaped beam with a rotating shaft joint and a support beam close to the T-shaped beam, and connecting the thrust beam with two support beams close to the T-shaped beam.
In a fourth aspect, an embodiment of the present application provides a computer-readable storage medium, which stores a computer program, and when the computer program is loaded and executed by a processor, the method for manufacturing a side wall plate in a load compartment as provided in any one of the first aspect above is implemented.
In a fifth aspect, an embodiment of the present application provides an electronic device, which at least includes a processor and a memory, wherein,
the memory is used for storing a computer program;
the processor is adapted to load and execute a computer program to cause an electronic device to perform the method of manufacturing a side wall panel in a load compartment as provided in any of the above first aspects.
Compared with the prior art, the beneficial effects of this application are:
the embodiment of the application provides a method for manufacturing a side wall plate in a load compartment, the wall plate, a device, a storage medium and equipment, wherein the method comprises the following steps: according to the position of the cabin door joint device, a plurality of rotating shaft joints are arranged on the inner side wall plate body; according to the integral strength and rigidity of the load compartment, a plurality of arched support beams are arranged on the inner side wall plate body; according to the distribution of missile hanging devices, a hanging frame is arranged on the inner side wall plate body; according to the position of an engine, a T-shaped beam and a thrust beam are arranged at one end of the inner side wall plate body close to the engine, the T-shaped beam is connected with a rotating shaft joint and a support beam close to the T-shaped beam, and the thrust beam is connected with two support beams close to the thrust beam. According to the method, firstly, a rotating shaft joint is arranged at a position matched with a cabin door joint device to open and close the cabin door, secondly, a plurality of supporting beams are arranged according to the requirements of the integral strength and rigidity of a load cabin to increase the strength, the supporting beams are arched to match the shape of a wall plate and the shape of the load cabin formed by subsequent assembly, and then, a hanging frame is arranged on the wall plate according to the distribution of missile hanging devices to facilitate the installation and connection of the hanging devices; finally, according to the position of an engine, a T-shaped beam and a thrust beam are arranged to stabilize a local structure and ensure a force transmission path, the T-shaped beam is connected with a rotating shaft joint and a supporting beam which are close to the T-shaped beam, the thrust beam is connected with two supporting beams which are close to the thrust beam, the force transmission path is short, the construction on the force transmission path is small, the design can be simplified, the complexity that stress of a certain component in the force transmission path comes from all sides is avoided, the force transmission becomes more direct, the deformation types are few, the total deformation direction is single, the total deformation amount is small, the control is easier within an allowable range, the functional requirements of the side wall plate in the load cabin and the main force transmission path of the whole structure can be considered at the same time through the method, and the structural stability of the manufactured wall plate is ensured.
Drawings
Fig. 1 is a schematic structural diagram of an electronic device in a hardware operating environment according to an embodiment of the present application;
FIG. 2 is a schematic flow chart illustrating a method for manufacturing a side wall panel in a load compartment according to an embodiment of the present application;
FIG. 3 is a functional block diagram of an apparatus for manufacturing a side wall panel in a load compartment according to an embodiment of the present application;
FIG. 4 is a schematic structural view of a side wall panel in the load compartment according to an embodiment of the present application;
FIG. 5 is a schematic structural view of an inner side wall panel body of the inner side wall panel of the load compartment according to the embodiment of the present application;
FIG. 6 is a schematic structural view of the inner side wall plate body after the rotating shaft joint is arranged thereon;
FIG. 7 is a schematic structural view of the inner side wall plate body after the support beams are arranged thereon;
FIG. 8 is a schematic view of the structure of the inner panel body after the hanger is installed thereon;
FIG. 9 is a partial schematic view of the T-beam disposed on the inboard wall body;
FIG. 10 is a partial schematic view of the inside panel body after the hat stiffener has been provided;
the labels in the figure are: 101-processor, 102-communication bus, 103-network interface, 104-user interface, 105-memory, 1-inner side wall plate body, 2-rotating shaft joint, 3-supporting beam, 4-hanging rack, 5-T-shaped beam, 6-thrust beam, 7-cover and 8-cap-shaped reinforcing rib.
Detailed Description
It should be understood that the specific embodiments described herein are merely illustrative of the present application and are not intended to limit the present application.
The main solution of the embodiment of the application is as follows: a method for manufacturing a side wall plate in a load compartment, the wall plate, a device, a storage medium and equipment are provided, wherein a plurality of rotating shaft joints are arranged on an inner side wall plate body according to the position of a cabin door joint device; according to the overall strength and rigidity of the load compartment, a plurality of arched support beams are arranged on the inner side wall plate body; according to the distribution of missile hanging devices, a hanging frame is arranged on the inner side wall plate body; according to the position of an engine, a T-shaped beam and a thrust beam are arranged at one end of the inner side wall plate body close to the engine, the T-shaped beam is connected with a rotating shaft joint close to the T-shaped beam and a supporting beam, and the thrust beam is connected with two supporting beams close to the T-shaped beam.
With the continuous development of modern high-tech technology, the industry of medium-sized and large-sized unmanned aerial vehicles is continuously expanded, the competition is fierce, the cabin space of the unmanned aerial vehicles is efficiently and reasonably distributed according to the task requirements, and under the conditions that the quality is ensured and the requirements of functions are met, the weight and the cost are maximally reduced, and the use and maintenance performance is improved, so that one of the targets for developing the unmanned aerial vehicles is provided. The structural layout of the airplane is to ensure the structural strength of the load cabin, firstly, the functional requirements in the cabin section are considered, and secondly, the arrangement of a main force transmission path of the integral structure is considered; thirdly, the structural layout design in a limited space is considered. Two embedded task load cabins which are bilaterally symmetrical are arranged at the abdomen of the unmanned aerial vehicle, the inner side wall plates of the task load cabins are in a bow shape, the forming of the task load cabins is a technical difficulty due to the complex profile, the large size, the large longitudinal span and the heavy structural load bearing capacity, the stability of the wall plates after other components are connected on the task load cabins is difficult to control, the layout requirements in the three aspects can be met only when the components are added at the positions, and no systematic method is used for manufacturing guidance.
Therefore, the application provides a solution, a plurality of rotating shaft joints are arranged on the inner side wall plate body according to the position of the cabin door joint device; according to the integral strength and rigidity of the load compartment, a plurality of arched support beams are arranged on the inner side wall plate body; according to the distribution of missile hanging devices, a hanging frame is arranged on the inner side wall plate body; according to the position of an engine, a T-shaped beam and a thrust beam are arranged at one end of the inner side wall plate body close to the engine, the T-shaped beam is connected with a rotating shaft joint and a support beam close to the T-shaped beam, and the thrust beam is connected with two support beams close to the thrust beam. Can satisfy the basic function demand in the cabin, carry out rational overall arrangement according to intensity needs and biography power route to the position that sets up of each functional component in narrow and small under-deck space simultaneously, compromise the functional demand and the overall structure owner of the inboard wall panel of load cabin and pass the power route, can effectively guide the wallboard that manufacturing stability is good, intensity, rigidity all satisfy needs.
Referring to fig. 1, fig. 1 is a schematic structural diagram of an electronic device in a hardware operating environment according to an embodiment of the present application, where the electronic device may include: a processor 101, such as a Central Processing Unit (CPU), a communication bus 102, a user interface 104, a network interface 103, and a memory 105. Wherein the communication bus 102 is used for enabling connection communication between these components. The user interface 104 may comprise a Display screen (Display), an input unit such as a Keyboard (Keyboard), and the optional user interface 104 may also comprise a standard wired interface, a wireless interface. The network interface 103 may optionally include a standard wired interface, a WIreless interface (e.g., a WIreless-FIdelity (WI-FI) interface). The Memory 105 may be a storage device independent from the processor 101, and the Memory 105 may be a high-speed Random Access Memory (RAM) Memory or a Non-Volatile Memory (NVM), such as at least one disk Memory; the processor 101 may be a general-purpose processor including a central processing unit, a network processor, etc., and may also be a digital signal processor, an application specific integrated circuit, a field programmable gate array or other programmable logic device, discrete gate or transistor logic, discrete hardware components.
Those skilled in the art will appreciate that the configuration shown in fig. 1 does not constitute a limitation of the electronic device and may include more or fewer components than those shown, or some components may be combined, or a different arrangement of components.
As shown in fig. 1, the memory 105, which is a storage medium, may include therein an operating system, a data storage module, a network communication module, a user interface module, and an electronic program.
In the electronic device shown in fig. 1, the network interface 103 is mainly used for data communication with a network server; the user interface 104 is mainly used for data interaction with a user; the processor 101 and the memory 105 in the present invention may be provided in an electronic device, and the electronic device calls the load compartment inner side wall plate manufacturing apparatus stored in the memory 105 through the processor 101, and executes the load compartment inner side wall plate manufacturing method provided in the embodiment of the present application.
Referring to fig. 2, an embodiment of the present application provides a method for manufacturing a side wall panel in a load compartment, based on the hardware device of the foregoing embodiment, including the steps of:
s10: and performing prepreg curing molding on the composite material to obtain the inner side wall plate body 1.
In the specific implementation process, the composite material is a composite material and is used as a raw material for manufacturing the inner side wall plate body 1, the prepreg refers to a uniform pre-cured material formed by soaking fiber bundles or fiber cloth with resin, and the pre-cured material can be directly used for manufacturing a composite material structure. Classifying according to physical states, wherein the prepreg is divided into unidirectional prepreg, bidirectional prepreg and three-way prepreg; the prepreg is divided into thermosetting resin prepreg and thermoplastic resin prepreg according to different resin matrixes; according to different reinforced materials, the reinforced composite material is divided into carbon fiber prepreg, glass fiber prepreg and aramid prepreg; according to different curing temperatures, the prepreg can be divided into a medium-temperature curing (120 ℃) prepreg, a high-temperature curing (180 ℃) prepreg, a prepreg with the curing temperature exceeding 200 ℃ and the like.
Further, the inner side wall plate body 1 is divided into discrete areas according to the boundary of the lost layer by applying a composite material lost layer optimization design technology, the original multiple-to-fewer layer losing process of the composite material is replaced by a fewer-to-more inserting mode, the adjacent conditions of all the areas are considered in the inserting mode, and the adding rule is adjusted, so that a more specific layer laying sequence is given, the thickness of an assembly area is enhanced, the thickness of a non-connection area is weakened, and the inner side wall plate which is the composite material layer laying sequence scheme with the lightest structural weight and meets the strength requirement and all the process conditions is obtained through composite material optimization design.
S20: according to the position of the hatch jointer, a plurality of rotating shaft joints 2 are arranged on the inner side wall plate body 1.
In the specific implementation process, the inner side wall plate body 1 is connected with the cabin door after being processed to form a complete load cabin, so that the stable butt joint between the inner side wall plate body and the cabin door is considered, the opening and closing of the butted cabin door are smooth, and the installation position of the rotating shaft joint 2 correspondingly matched with the cabin door joint device is determined according to the position of the cabin door joint device.
S30: according to the integral strength and rigidity of the load compartment, a plurality of arched support beams 3 are arranged on the inner side wall plate body 1.
In the specific implementation process, the whole structure of the load compartment can be obtained through simulation or design parameters, so that the whole strength and rigidity of the load compartment can be obtained, a plurality of arched supporting beams 3 are arranged at weak positions needing to be enhanced and fit with the section shape of the inner side wall plate body 1, and arched keels distributed along the axis of the load compartment are formed to enhance the structural strength and rigidity of the whole compartment.
S40: according to the distribution of missile hanging devices, a hanging frame 4 is arranged on the inner side wall plate body 1.
In the concrete implementation process, special unmanned aerial vehicle need possess certain operational capacity, need set up corresponding structure of carrying on the weapon, because the weapon of fighting is mostly the guided missile, can set up two sets of stores pylons 4 under the general condition at least, stores pylon 4 adopts the embedded type barrel nut with linkage to be connected, realizes convenient dismouting and does not influence the wallboard appearance.
S50: according to the position of an engine, a T-shaped beam 5 and a thrust beam 6 are arranged at one end of an inner side wall plate body 1 close to the engine, the T-shaped beam 5 is connected with a rotating shaft joint 2 and a support beam 3 close to the T-shaped beam, and the thrust beam 6 is connected with two support beams 3 close to the T-shaped beam.
In the specific implementation process, the engine is the core part of the whole unmanned aerial vehicle, power is provided for the whole unmanned aerial vehicle, the structural layout is particularly important, on one hand, the installation of the engine needs to be avoided, on the other hand, the structural rigidity and the force transmission path of the important stressed part need to be considered, the thrust beam 6 and the T-shaped beam 5 are arranged by adopting the method, the structural rigidity of the internal side wall plate of the engine installation part is enhanced, the force transmission path of the stressed part is short, the parts passing through in the force transmission process are reduced, the stress is prevented from passing through the wall plate with a complex and changeable structure due to the fact that the force transmission follows the principle of the shortest path, and the overall stability of the wall plate is ensured.
S60: the inner side wall plate body 1 is provided with a hat-shaped bead 8 depending on the positions of the support beam 3 and the thrust beam 6.
In the specific implementation process, the hat-shaped reinforcing ribs 8 are reinforcing ribs with approximately trapezoidal sections, the structure has natural damage tolerance performance, the requirement of a multi-path load transmission path can be met, high structural efficiency can be guaranteed under a complex stress state, the strength of the connection part of the supporting beam 3 and the thrust beam 6 is enhanced after the supporting beam is connected with the thrust beam, the hat-shaped reinforcing ribs 8 are arranged on weak webs between the supporting beam and the thrust beam to increase the structural rigidity, multi-path load transmission can be integrated, and the requirements of the transmission path are met through the hat-shaped reinforcing ribs 8.
According to the manufacturing method of the side wall plate in the load cabin, firstly, the rotating shaft joint 2 is arranged at the position matched with the cabin door joint device to realize the opening and closing of the cabin door, secondly, a plurality of supporting beams 3 are arranged according to the requirements of the integral strength and rigidity of the load cabin to increase the strength, the supporting beams 3 are arched to match the shape of the wall plate body 1 and the shape of the load cabin formed by subsequent assembly, and then, the hanging frame 4 is arranged on the wall plate according to the distribution of missile hanging devices to facilitate the installation and connection of the hanging devices; finally, according to the position of an engine, a T-shaped beam 5 and a thrust beam 6 are arranged to stabilize a local structure and ensure a force transmission path, the T-shaped beam 5 is connected with a rotating shaft joint 2 and a supporting beam 3 which are close to the T-shaped beam 5, the thrust beam 6 is connected with two supporting beams 3 which are close to the thrust beam 6, the force transmission path is short, the construction on the force transmission path is less, the design can be simplified, the complexity that stress of a certain component in the force transmission path comes from all parties is avoided, the force transmission becomes more direct, the deformation types are few, the total deformation direction is single, the total deformation amount is small, the control is easier within an allowable range, the functional requirements of the side wall plate in the load cabin and the main force transmission path of the whole structure can be considered at the same time through the method, and the structural stability after the manufacture of the wall plate is ensured.
In one embodiment, in step S50: according to the position of the engine, after the T-shaped beam 5 and the thrust beam 6 are arranged at one end of the inner side wall plate body close to the engine, the T-shaped beam 5 is connected with the rotating shaft joint 2 and the support beam 3 close to the T-shaped beam 5, and the thrust beam 6 is connected with the two support beams 3 close to the T-shaped beam, the manufacturing method of the inner side wall plate of the load compartment further comprises the following steps:
a flap 7 is provided on the inner side wall plate body 1 near the thrust beam 6 according to the position of the thrust beam 6.
In the specific implementation in-process, for the engine of later stage in to the load cabin overhauls, need consider simultaneously thrust beam 6 position and engine position, the position that the flap 7 that had just made to offer can be convenient for operate the engine, will avoid thrust beam 6 again, still can not reduce wallboard intensity, offers flap 7 on the interior lateral wall body 1 of the below of thrust beam 6.
In one embodiment, all the components in the above embodiments are connected with the inner side wall plate body 1 by detachable bolts, the cap-shaped reinforcing ribs 8 and the wall plate are in wet assembly, namely, the normal temperature glue and the bolts are in mixed connection, the reinforcing ribs are formed independently, the quality is better than that of co-glued parts, and the wet assembly is more reliable; the assembling mode on the machine body mainly takes the fabrication hole and the intersection point hole on the main stressed component as the assembling reference, and other parts are assembled and connected by adopting the self-positioning hole system definition of part assembly, so that the assembling and disassembling can be realized quickly, the use and the maintenance are simple and convenient, the positioning tool is reduced, the assembly of a small number of frames is realized, and the tool cost is reduced.
In one embodiment, based on the consideration of the force transmission path, the rotating shaft joint 2 is assembled on the supporting beam 3 at the position of the non-main force bearing frame of the inner side wall plate body 1, so that the layout is reasonable, the structure is simplified, the force transmission path of the structure is ensured, and the structural strength and the rigidity of the wall plate are enhanced.
Referring to fig. 4, based on the same inventive concept as that in the previous embodiment, the embodiment of the present application further provides a load compartment inner side wall panel manufactured by the method for manufacturing a load compartment inner side wall panel provided by the present application. In this embodiment, a main bearing member of an inner side wall plate with a length of 4.5 m and a height of 0.8 m is taken as an example for explanation:
as shown in fig. 5, the inner side wall panel body 1 is obtained by curing and molding a prepreg.
As shown in fig. 6, the intersection point of the cabin door of the mission load cabin is located on the inner side wall plate body 1, and 7 sets of rotating shaft joints 2 matched with the cabin door joint device are arranged on the inner side wall plate body 1 and can be connected with the cabin door joint device to realize the opening and closing of the cabin door.
As shown in the attached figure 7, 5 groups of supporting beams 3 are arranged on the inner side wall plate body 1, the supporting beams 3 are arched, the strength and the rigidity of the whole cabin body are ensured, and 3 groups of rotating shaft joints 2 are assembled on the supporting beams 3 at the position of a non-main bearing frame, so that the reasonable layout is realized, the structure is simplified, and the force transmission path of the structure is ensured.
As shown in the attached figure 8, according to the distribution of missile hanging devices, 2 groups of hanging devices are arranged on the inner side wall plate body 1 for fixing, and in order to facilitate installation and disassembly, the hanging devices and the hanging devices 4 are connected at bosses by adopting embedded cylindrical nuts.
As shown in figure 9, a T-shaped beam 5 and a thrust beam 6 are arranged on an inner side wall plate body 1 at a position close to an engine, three end parts of the T-shaped beam 5 are connected with 1 group of rotating shaft joints 2 and supporting beams 3, the thrust beam 6 is connected with 2 groups of supporting beams 3, the structural rigidity and a force transmission path of an important stressed position are ensured, and a detachable cover cap 7 is arranged on the inner side wall plate body 1 below the thrust beam 6, so that the maintenance of the internal engine is facilitated.
As shown in fig. 10, in the non-connection region of the inner panel body 1 where the deformation is large, some longitudinal composite hat-shaped reinforcing ribs 8 are added to increase the structural rigidity of the web portion of the inner panel and to fit the force transmission path in the axial direction.
After the arrangement is completed, the inner side wall plate shown in fig. 4 can be obtained through relevant processing and assembly.
In addition, based on the same inventive concept as that in the previous embodiment, the embodiment of the present application further provides an unmanned aerial vehicle, the unmanned aerial vehicle includes two load compartments symmetrically arranged on the abdomen of the unmanned aerial vehicle, and the inner side wall plate of the load compartment is manufactured by the manufacturing method of the inner side wall plate of the load compartment provided by the embodiment of the present application.
Referring to fig. 3, based on the same inventive concept as the previous embodiment, the present embodiment further provides a manufacturing apparatus of a side wall panel in a load compartment, including:
the first execution module is used for arranging a plurality of rotating shaft joints on the inner side wall plate body according to the position of the cabin door joint device;
the second execution module is used for arranging a plurality of arched support beams on the inner side wall plate body according to the integral strength and rigidity of the load compartment;
the third execution module is used for arranging a hanging frame on the inner side wall plate body according to the distribution of the missile hanging devices;
and the fourth execution module is used for arranging a T-shaped beam and a thrust beam at one end of the inner side wall plate body close to the engine according to the position of the engine, connecting the T-shaped beam with a rotating shaft joint and a support beam close to the T-shaped beam, and connecting the thrust beam with two support beams close to the T-shaped beam.
It should be understood by those skilled in the art that the division of each module in the embodiment is only a division of a logic function, and all or part of the division may be integrated onto one or more actual carriers in actual application, and all of the modules may be implemented in a form called by a processing unit through software, may also be implemented in a form of hardware, or implemented in a form of combination of software and hardware.
Based on the same inventive concept as in the previous embodiments, embodiments of the present application further provide a computer-readable storage medium, which stores a computer program, and when the computer program is loaded and executed by a processor, the method for manufacturing the side wall plate in the load compartment, as provided in the embodiments of the present application, is implemented.
In addition, based on the same inventive concept as the foregoing embodiments, the embodiments of the present application further provide an electronic device, which at least includes a processor and a memory, wherein,
the memory is used for storing a computer program;
the processor is used for loading and executing a computer program to enable the electronic equipment to execute the manufacturing method of the side wall plate in the load compartment, which is provided by the embodiment of the application.
In some embodiments, the computer-readable storage medium may be memory such as FRAM, ROM, PROM, EPROM, EEPROM, flash, magnetic surface memory, optical disk, or CD-ROM; or may be various devices including one or any combination of the above memories. The computer may be a variety of computing devices including intelligent terminals and servers.
In some embodiments, the executable instructions may be in the form of a program, software module, script, or code written in any form of programming language, including compiled or interpreted languages, or declarative or procedural languages, and it may be deployed in any form, including as a stand-alone program or as a module, component, subroutine, or other unit suitable for use in a computing environment.
By way of example, executable instructions may, but need not, correspond to files in a file system, and may be stored in a portion of a file that holds other programs or data, such as in one or more scripts in a hypertext Markup Language (HTML) document, in a single file dedicated to the program in question, or in multiple coordinated files (e.g., files that store one or more modules, sub-programs, or portions of code).
By way of example, executable instructions may be deployed to be executed on one computing device or on multiple computing devices at one site or distributed across multiple sites and interconnected by a communication network.
It should be noted that, in this document, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that a process, method, article, or system 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 system. Without further limitation, an element defined by the phrases "comprising a," "8230," "8230," or "comprising" does not exclude the presence of other like elements in a process, method, article, or system comprising the element.
The sequence of the embodiments of the present application is merely for description, and does not represent the advantages and disadvantages of the embodiments.
Through the above description of the embodiments, those skilled in the art will clearly understand that the method of the above embodiments can be implemented by software plus a necessary general hardware platform, and certainly can also be implemented by hardware, but in many cases, the former is a better implementation manner. Based on such understanding, the technical solutions of the present application may be embodied in the form of a software product, which is stored in a storage medium (e.g., a rom/ram, a magnetic disk, an optical disk) and includes instructions for enabling a multimedia terminal (e.g., a mobile phone, a computer, a television receiver, or a network device) to execute the method of the embodiments of the present application.
In summary, according to the method for manufacturing the inner side wall plate of the load compartment, the wall plate, the device, the storage medium and the equipment, the plurality of rotary shaft joints are arranged on the inner side wall plate body according to the position of the compartment door joint device; according to the overall strength and rigidity of the load compartment, a plurality of arched support beams are arranged on the inner side wall plate body; according to the distribution of missile hanging devices, a hanging frame is arranged on the inner side wall plate body; according to the position of an engine, a T-shaped beam and a thrust beam are arranged at one end of the inner side wall plate body close to the engine, the T-shaped beam is connected with a rotating shaft joint close to the T-shaped beam and a supporting beam, and the thrust beam is connected with two supporting beams close to the T-shaped beam. The functional demand and the overall structure owner of load under-deck lateral wall board are compromise to this application and pass the power route, the component that need lay on the wallboard uses this as the basis to carry out reasonable layout, it is shorter to ensure to pass the power route, the construction on passing the power route is less, can simplify the design, the complexity that certain component stress comes from each side in having avoided passing the power route, it becomes more direct to pass power, the kind of deformation is few, total deformation direction is single, the total amount of deformation is little, it is in the tolerance to control more easily, can produce the light of structure weight, and satisfy the intensity requirement and the interior lateral wall board of the combined material shop layer sequence scheme of all technological conditions.
The above description is only exemplary of the present application and should not be taken as limiting the present application, as any modification, equivalent replacement, or improvement made within the spirit and principle of the present application should be included in the protection scope of the present application.
Claims (10)
1. A method for manufacturing a side wall plate in a load compartment, which is characterized by comprising the following steps:
according to the position of the cabin door joint device, a plurality of rotating shaft joints are arranged on the inner side wall plate body;
according to the overall strength and rigidity of the load compartment, a plurality of arched support beams are arranged on the inner side wall plate body;
according to the distribution of missile hanging devices, a hanging frame is arranged on the inner side wall plate body;
according to the position of an engine, a T-shaped beam and a thrust beam are arranged at one end, close to the engine, of the inner side wall plate body, the T-shaped beam is connected with two rotating shaft joints close to the T-shaped beam and the support beams, and the thrust beam is connected with two support beams close to the thrust beam.
2. The method for manufacturing a load compartment inner side wall panel according to claim 1, wherein after the T-shaped beam and the thrust beam are provided at the end of the inner side wall panel body close to the engine in accordance with the engine position and the T-shaped beam is connected to the two pivot joints and the support beams close thereto, and the thrust beam is connected to the two support beams close thereto, the method for manufacturing a load compartment inner side wall panel further comprises:
and according to the position of the thrust beam, a cover is arranged on the inner side wall plate body close to the thrust beam.
3. The method for manufacturing a load compartment inner side wall panel according to claim 1, wherein after the T-shaped beam and the thrust beam are provided at the end of the inner side wall panel body close to the engine in accordance with the engine position and the T-shaped beam is connected to the two pivot joints and the support beams close thereto, and the thrust beam is connected to the two support beams close thereto, the method for manufacturing a load compartment inner side wall panel further comprises:
and cap-shaped reinforcing ribs are arranged on the inner side wall plate body according to the positions of the supporting beam and the thrust beam.
4. The method for manufacturing a side wall panel in a load compartment according to claim 3, wherein the hat stiffener is wet-fitted to the inner wall panel body.
5. The method of manufacturing a load compartment inner side wall panel according to claim 1, wherein before the providing of the plurality of pivot joints on the inner side wall panel body according to the position of the door adapter, the method of manufacturing a load compartment inner side wall panel further comprises:
and carrying out prepreg curing molding on the composite material to obtain the inner side wall plate body.
6. The method for manufacturing a load compartment inner side wall panel according to claim 1, wherein the pivot joints at the non-main load-bearing frame positions of the inner side wall panel body are connected to the support beams.
7. A load compartment inner side wall panel manufactured by the method of manufacturing a load compartment inner side wall panel according to any one of claims 1 to 6.
8. An apparatus for manufacturing a side wall panel in a load compartment, comprising:
the first execution module is used for arranging a plurality of rotary shaft joints on the inner side wall plate body according to the position of the cabin door joint device;
the second execution module is used for arranging a plurality of arched support beams on the inner side wall plate body according to the overall strength and rigidity of the load compartment;
the third execution module is used for arranging a hanging rack on the inner side wall plate body according to the distribution of the missile hanging devices;
and the fourth execution module is used for arranging a T-shaped beam and a thrust beam at one end of the inner side wall plate body close to the engine according to the position of the engine, connecting the T-shaped beam with the two rotating shaft joints close to the T-shaped beam and the supporting beams, and connecting the thrust beam with the two supporting beams close to the T-shaped beam.
9. A computer-readable storage medium, in which a computer program is stored which, when being loaded into execution by a processor, carries out the method for manufacturing a side wall panel in a load compartment according to any one of claims 1-6.
10. An electronic device at least comprising a processor and a memory, wherein,
the memory is used for storing a computer program;
the processor is adapted to load and execute the computer program to cause the electronic device to perform the method of manufacturing a side wall panel in a load compartment according to any of claims 1-6.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210694764.XA CN115180172A (en) | 2022-06-20 | 2022-06-20 | Method for producing a side wall panel in a load compartment, wall panel, arrangement, storage medium and installation |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210694764.XA CN115180172A (en) | 2022-06-20 | 2022-06-20 | Method for producing a side wall panel in a load compartment, wall panel, arrangement, storage medium and installation |
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| CN115180172A true CN115180172A (en) | 2022-10-14 |
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