Aircraft additive manufacturing method and aircraft manufactured thereby

Abstract

The present application provides an aircraft additive manufacturing method. The method comprises: designing a three dimensional digital model of an aircraft; setting a design separation interface on the three dimensional digital model so as to divide the three dimensional digital model into three dimensional digital models of modules; setting a process separation interface on the three dimensional digital models of the modules so as to divide the three dimensional digital models of the modules into three dimensional digital models of segments; performing slicing processing on the three dimensional digital models of the segments and setting printing parameters to generate printing data; using a 3D printer to perform printing on the basis of the printing data to generate segments; assembling the segments to form modules; and assembling the modules to form the aircraft. The present application further provides an aircraft.

Description

AIRCRAFT ADDITIVE MANUFACTURING METHOD AND AIRCRAFTMANUFACTURED THEREBY  FIELD OF THE INVENTION

[00001] The present application belongs to the field of aircraft manufacturing, and in particular relates to a method for additive manufacturing of an aircraft.BACKGROUND OF THE INVENTION

[00002] The description of background provided herein serves to provide an overall introduction of the background information of the present application.

[00003] Aircraft refers to apparatuses or devices capable of flying in the atmosphere. They have various shapes and sizes, ranging from small drones to massive passenger planes and spacecraft，all of which belong to aircraft. Airplanes are the most well-known aircraft, which fly in the atmosphere and typically consist of a fuselage, wings, a power system, and a control system. When taking off, the airplane relies on the thrust provided by the power system to generate a lift force, allowing it to leave the ground. Meanwhile, in the flying process, the airplane maintains itself in the air through the lift force acting on the wings. The shape of the wings can produce various aerodynamic forces, such as lift, drag and thrust. By adjusting the magnitudes and directions of these aerodynamic forces, the speed, direction and altitude of the airplane can be changed. Airplanes include manned airplanes and drones, where drones, also known as unmanned aircraft, are aircraft that fly through remote operation or preset routes without carrying personnel. Unmanned aircraft have experienced rapid development and widespread application in recent years.

[00004] During traditional processing and manufacturing of aircraft, subtractive manufacturing technology or equal-material manufacturing technology is typically used. The subtractive manufacturing technology is a manufacturing technology which removes material from a workpiece to manufacture products suitable for different applications, while the equal-material manufacturing technology is a technology which transforms materials into desired structures through methods such as mold shaping. However, traditional aircraft manufacturing technologies have several drawbacks, including low material utilization rate, poor processing environment, complex processes, long design and manufacturing cycles, difficulties in configuration iteration, high costs in small-batch processing, and high requirements for technical personnel. These drawbacks make traditional manufacturing technologies unable to meet the current rapid and efficient iterative development and production speed of aircraft.

[00005] Additive manufacturing technology, also commonly known as 3D printing technology, differs from traditional subtractive manufacturing and equal-material manufacturing methods. The core of additive manufacturing technology lies in the processing method of constructing and forming threedimensional objects by stacking or adding materials layer by layer which has advantages such as flexible design, short research and development cycles, rapid product iteration, high material utilization rate, good production predictability, and fewer assembly steps, thus avoiding the defects of subtractive manufacturing and equal-material manufacturing methods.

[00006] Therefore, it is desired to provide a technology for manufacturing aircraft using additive manufacturing method.SUMMARY OF THE INVENTION

[00007] This section provides an introduction of the concepts of the present application in a simplified form, which will be further elaborated in the detailed description below. This section is not intended to identify key or essential features of the claimed subject matter, nor is it intended to serve as an aid in determining the scope of the claimed subject matter.

[00008] According to a first aspect of the present application, a method for additive manufacturing of an aircraft is provided, which includes: designing a three dimensional digital model of the aircraft; setting a design separation interface on the three dimensional digital model to divide the three dimensional digital model into three dimensional digital models of modules; setting a process separation interface on the three dimensional digital models of modules to divide the three dimensional digital models of modules into three dimensional digital models of segments; slicing the three dimensional digital models of segments and setting printing parameters to generate printing data; using a 3D printer to print based on the printing data to generate segments; assembling the segments to form modules; and finally assembling the modules to form an aircraft.

[00009] In some embodiments, the segments and the modules are provided with installation holes.

[00010] In some embodiments, the segments are assembled to form the modules by inserting rods into the installation holes of the segments to connect the segments, and the modules are finally assembled to form the aircraft by inserting rods into the installation holes of the modules to connect the modules.

[00011] In some embodiments, one end of the rod is bonded to the installation hole with adhesive and / or connected to the installation hole through interference fit.

[00012] In some embodiments, the segments are also connected through a tenon-and-mortise structure, and the modules are also connected through a tenon-and-mortise structure.

[00013] In some embodiments, the segments are also connected by threads, and the modules are also connected by threads.

[00014] In some embodiments, the tenon-and-mortise structure is connected through interference fit.

[00015] In some embodiments, mating surfaces of the tenon-and-mortise structure are bonded using an adhesive.

[00016] In some embodiments, the rods include spar, stringer and tensile bar.

[00017] In some embodiments, the method further includes: before assembling the segments to form the modules, pre-assembling the segments to inspect whether they are qualified, where if the segments are qualified, they are assembled to form the modules, and if the segments are unqualified, the parameters of the three dimensional digital models of segments and / or the printing parameters are adjusted, and the 3D printer is used again to generate the segments by printing.

[00018] In some embodiments, the method further includes: sealing gaps of the modules using a filler, and grinding and polishing the surfaces of the modules.

[00019] In some embodiments, the method further includes: performing thermal treatment on the segments after they are generated.

[00020] In some embodiments, the method further includes: installing accessory devices on the modules formed by assembly or the aircraft formed by final assembly, where the accessory devices are installed by threaded connection, snap-fit connection, or bonding.

[00021] In some embodiments, during the printing process, one or more materials from plastic, metal, and ceramic are used for printing, so as to meet different functional requirements.

[00022] In some embodiments, the modules include at least one of a nose module, a belly module, an inner wing module, a takeoff assembly module, an outer wing module, a landing gear module, a tail module, and a mission payload module.

[00023] In some embodiments, the segments are generated by remotely controlling the 3D printer to print.

[00024] In some embodiments, the installation holes on various modules for installing the spar, stringer and tensile bar each have the same size.

[00025] In some embodiments, the method further includes chamfering end faces of the rods before inserting them into the installation holes.

[00026] In some embodiments, the interior of the segment is one or more of a hollow structure, a grid structure, or a solid structure.

[00027] In another aspect, the present application provides an aircraft manufactured by using the 3D printing method according to the present application.BRIEF DESCRIPTION OF THE DRAWINGS

[00028] In the following detailed description of the embodiments, other or additional features, advantages and details are presented merely by way of example. In the drawings:

[00029] FIG. 1 exemplarily shows a flowchart of the method for additive manufacturing of an aircraft based on the principles of the present application.

[00030] FIG. 2 exemplarily shows a three dimensional digital model of an overall structure of the aircraft based on the principles of the present application.

[00031] FIG. 3 exemplarily shows three dimensional digital models of modules of the aircraft based on the principles of the present application.

[00032] FIG. 4 exemplarily shows the segments of the aircraft and the installation holes on them based on the principles of the present application.

[00033] FIG. 5 exemplarily shows the tenon-and-mortise structure on the segments and modules based on the principles of the present application.

[00034] It should be understood that throughout the drawings, similar or corresponding parts or features are denoted by corresponding reference signs. It should also be understood that the drawings are not necessarily drawn to scale, and they are merely schematic illustrations of exemplary embodiments of the present application, and are not intended to limit the present application.DETAILED DESCRIPTION OF THE EMBODIMENT(S) OF THE INVENTION

[00035] The exemplary embodiments of the present application will be described below in connection with the accompanying drawings. It should be understood that the following description is merely exemplary in nature, and is not intended to limit the present application, its application or use.

[00036] The present application will now be further elaborated. In the following paragraphs, different aspects of the present application are defined in more detail. Unless explicitly indicated to the contrary, each aspect so defined may be combined with any other aspect(s). In particular, any feature indicated as preferred or advantageous may be combined with any other feature(s) indicated as preferred or advantageous.

[00037] In view of the problems existing in the prior art, the present application provides a method for additive manufacturing of an aircraft based on 3D printing, which will be described in detail below with reference to the accompanying drawings.

[00038] Referring to FIG. 1, a flowchart of the method for additive manufacturing of an aircraft based on the principles of the present application is shown.

[00039] In step S100, referring to FIG. 2, a three dimensional digital model 100 of the overall structure of the aircraft is designed using computer-aided design software. During the design process, systems such as appropriate flight control systems and power systems that meet different functions need to be selected based on the performance requirements of the aircraft, and these systems are designed into the three dimensional digital model of the aircraft, or installation positions for these systems are reserved in the three dimensional digital model of the aircraft. On this basis, the overall three dimensional digital model of the aircraft is completed with consideration of the aerodynamic shape and force-bearing structure of the aircraft. The present application does not limit the type of auxiliary software used to design the three dimensional digital model of the aircraft, which can for example be commonly used modeling software in the art, such as CAD and CATIA.

[00040] After the three dimensional digital model design of the overall structure of the aircraft is completed, in step S200, a design separation interface 101 is set on the three dimensional digital model of the aircraft, as shown in FIG. 3. Different modules can be located on two sides of each separation interface 101, thereby allowing the three dimensional digital model of the aircraft to be segmented / divided into three dimensional digital models of multiple modules. When segmenting the modules, the segmentation can be performed based on the overall size and shape of the aircraft, or the functions of various parts. For example, according to the functions of various parts, the aircraft 100 can be segmented into a nose module 110, a belly module 120, an inner wing module 130, a takeoff assembly module 140, an outer wing module 150, a landing gear module 160, a tail module 170, a mission payload module (not shown), etc. In the present application, the segmented modules may include at least one of the aforementioned modules. However, the division of the aforementioned modules is merely exemplary. It can be easily understood by those skilled in the art that for different types of aircraft, due to the differences in their shapes and / or sizes, the segmentation of modules can be different. For example, for some rotary-wing unmanned aircraft, there may not be inner wing module or outer wing module. After the three dimensional digital model of the aircraft is segmented into digital models of multiple modules, the method can proceed to step S300. In step S300, a process separation interface can be set on the three dimensional digital model of each module, thereby segmenting the three dimensional digital model of each module into three dimensional digital models of multiple segments for subsequent 3D printing based on the segments. For example, referring to FIG. 4, taking the outer wing module 150 of the aircraft as an example, a process separation interface 102 can be set on it, thereby allowing it to be at least divided / segmented into a first segment 151 and a second segment 152. Those skilled in the art will understand that when segmenting the module into segments, it is appropriate to determine the sizes and number of the segments to be segmented based on the size of the module and the working size of the 3D printer used (i.e., the maximum printing size), while considering the forming directions of the segments. The segments printed according to the present application have the function of supporting the overall structure of the aircraft, and their outer surfaces also have a shape that conforms to the principles of fluid mechanics, thus having both the characteristics of the aircraft structure and skin. Therefore, they can be referred to as structural skin, which omits the process of skin treatment for various parts of the aircraft required in the prior art.

[00041] It can be easily understood by those skilled in the art that in some embodiments, the modules may not be segmented into segments. For example, for some small-sized unmanned aircraft, if their modules can be fully printed by a 3D printer, there is no need to segment the modules, and thus it is possible to directly print them based on the design separation interface without setting a process separation interface. In some other embodiments, it is also possible to segment only some modules for 3D printing, while other modules can be obtained through other processing methods or procurement.

[00042] The method then proceeds to step S400. In step S400, the three dimensional digital model of each segment is sliced using computer-aided software, and printing parameters are set to generate printing data. During slicing, the three dimensional digital models of segments can be converted into a file in a format such as STL or STP for transmission to the slicing software, and the three dimensional digital model is cut into a series of stacked two-dimensional graphics along the same direction in the slicing software for the 3D printer to print layer by layer, and the working path of the print head is generated. When setting the printing parameters, parameters such as the layer height of the two-dimensional graphics, the filling density of the segment, and the wall thickness can be set in the slicing software. However, other parameters such as the scanning speed and the curing time of each layer can also be set according to requirements, as would be easily understood by those skilled in the art. After slicing the models of segments and setting the printing parameters, the data including slicing data and printing parameters is exported as a file such as GCODE for transmission to the 3D printer.

[00043] After the printing data is generated, the method can proceed to step S500. In step S500, the 3D printer can print based on the received printing data, thereby generating various segments. According to the present application, the printing data can be transmitted to the 3D printer through a network, such as through a wireless network, or can be copied and transmitted to the 3D printer via a mobile hard disk. During the printing process, the printing process of the 3D printer can be remotely controlled and monitored by a computer, thereby realizing real-time control and monitoring of different types of printers in different areas, and the printing progress and problems that arise during the printing process can be known at any time. In case of problems, printing can be suspended or restarted at any time, ensuring print quality while also reducing operational costs. The interior of each printed segment can be a hollow structure, a grid structure, or a solid structure to meet the mechanical performance requirements of different segments.

[00044] After each segment is generated, the method can proceed to step S600. In step S600, the generated segments can be assembled to form corresponding modules. Referring to FIGS. 4 and 5, the segments manufactured by using the manufacturing method according to the principles of the present application are all provided with installation holes 180, so that rods can be inserted into the installation holes 180 to connect multiple segments, thereby forming each module by assembly. In step S700, the modules can be connected by inserting rods into the installation holes 180 of the modules to form an aircraft by final assembly.

[00045] Alternatively or additionally, the segments can be provided with tenon-and-mortise structures 190. Referring to FIGS. 4 and 5, each tenon-and-mortise structure 190 includes a tenon 191 and a corresponding mortise 192 located on two segments respectively, which allows the segments can be connected through the tenon-and-mortise structure and the modules can be connected through the tenon-and-mortise structure. The tenon-and-mortise structures 190 not only strengthen the connection between the segments and the connection between the modules of the aircraft, but also provide the aircraft with certain anti-vibration performance, thereby reducing the damage to the aircraft structure caused by vibration during the flight or when taking off and landing. Advantageously, the tenon 191 and the mortise 192 can be connected through interference fit, and the mating surfaces between them can also be bonded using an adhesive, such as glue, so that the connection and bonding between them become firmer. Advantageously, the segments can also be provided with a snap-fit structure. For example, a tongue 193 and a groove 194 can be provided on the tenon 191 and the corresponding mortise 192 respectively, thereby further enhancing the connection strength between segments or modules. The snap-fit structure can be provided on the separation interface, or at the surface of the segment or module. Advantageously, the segments can also be connected through threads. For example, threaded holes 195 can be provided on the tenon 191 and the mortise 192 so as to connect the segments or modules through bolts.

[00046] The installation holes 180 can have different shapes for installing rods with different cross-sectional shapes, which may be designed in any of steps S100, S200, or S300. The tenon-and-mortise structure 190 may be designed in step S200 or step S300, where the mating surfaces of the tenon and the mortise form part of the process separation interface 102.

[00047] In steps S600 and S700, when connecting the segments or modules through rods, one end of the rod can be inserted into the installation hole of at least one segment, and adhesive such as glue can be injected into the installation hole to bond the one end of the rod with the installation hole, while the other end of the rod can be inserted into the installation hole of at least one segment through interference fit. Alternatively, both ends of the rod can be bonded to the installation holes of the segments through adhesive, such as glue, or connected to the installation holes of the segments through interference fit. Through bonding and interference fit, the connection between the rod and the segments is made firmer, thereby enhancing the stability of the connection.

[00048] The rods in the present application may include spar, stringer, and tensile bar. The cross-sectional area of the spar is larger than that of the stringer; it serves to connect various modules and segments of the aircraft, and is the main connector between various modules. The stringer has a smaller cross-sectional area and is mainly used to connect various segments. The spar and the stringer can be located near the middle of the cross section of the segment or module, or near the surface of the segment or module.

[00049] Advantageously, a tensile bar can also be arranged at the edge position of the cross section of the module or its segment, that is, near an outer surface of the module, so as to enhance the strength at the surface. The cross-sectional size of the tensile bar is much smaller than its length size, and its cross-sectional area is also smaller than that of the spar and the stringer. Both ends of the tensile bar are inserted into the installation holes of at least two segments that make up the module, and they can also be bonded to the installation holes of the segments with adhesive, such as glue, so as to enhance their stability.

[00050] According to the present application, the spar, the stringer, and the tensile bar may have a rectangular, circular, “工”-shaped or “匚”-shaped cross section, or other regular-shaped cross sections, and may be made of materials such as carbon fiber, glass fiber, aluminum alloy, alloy steel, wood, etc. Referring to FIG. 4, the segment or module may be provided with a first installation hole 180a for installing the spar, a second installation hole 180b for installing the stringer, and a third installation hole 180c for installing the tensile bar, collectively referred to as installation holes 180. Although the installation holes are shown as circular in the figure, they may also be rectangular, “工”-shaped, or “匚”-shaped, or have other regular shapes. Advantageously, the first installation hole, the second installation hole, and the third installation hole on various modules may have the same size, which allows the spar, stringer, and tensile bar used for different modules to be interchangeable and facilitates the subsequent installation of updated and iterated modules on the aircraft.

[00051] According to the present application, various parts of the aircraft can be printed using plastic materials, metal materials, or ceramic materials based on the specific requirements of the molded parts. The plastic materials can be divided into polymer materials and composite materials. The polymer materials have the characteristics of low density and high strength, such as ABS (Acrylonitrile Butadiene Styrene plastic, ABS plastic), nylon, etc. The composite materials are usually composed of a polymer matrix and reinforcement materials. The reinforcement materials can be carbon fibers, glass fibers, or metal particles, etc., which can enhance or alter the mechanical properties of the polymer to meet the functional requirements of parts in different positions. The plastic materials are typically used in applications where weight control is required. The metal materials can be stainless steel, titanium alloy, and aluminum alloy, etc., which are usually used in applications where high strength and high corrosion resistance are required. The ceramic materials can be alumina and zirconia, etc., which are typically used in applications where high heat resistance, high strength, and high stiffness are required.

[00052] According to the present application, when designing the process separation interface based on the working size of the 3D printer used and the forming directions of the segments, it is highly suitable to meet the following situations:

[00053] (1) the main force-bearing direction of the segment is not perpendicular to the forming direction, so as to avoid fractures between the printed layers of the formed segment due to excessive force during use;

[00054] (2) during the printing and forming process, the bottom and top surfaces of the segments serve as the process separation interface for the connection between segments;

[00055] (3) an outer wall of the segment formed perpendicular to the forming direction during the printing and forming process serves as the conformal surface of the aircraft; and

[00056] (4) during the printing and forming process, overhangs are minimized to ensure the surface finish of the parts; that is, while ensuring the stability of the segments during the printing process, the overhangs used to support the segments are reduced as much as possible, such as using only one overhang or no overhangs.

[00057] According to the method of the present application, after printing and generating the segments, a step of performing thermal treatment on the segments can also be included, such as annealing or tempering the printed segments, thereby eliminating the stress of the segments and enhancing their mechanical properties.

[00058] Preferably, the method of the present application may further include a step of pre-assembling the segments before assembling multiple segments to form a module, in order to inspect whether each segment is qualified, that is, whether each segment meets the assembly requirements. During the pre-assembly process, it is possible to use only rods, tenon and mortise, or buckles to connect the segments, without using any adhesive such as glue. If the segments pass the inspection, the multiple segments are assembled into a module. If the segments fail to pass the inspection, for example, if the amount of interference fit does not meet the requirements, the parameters of the three dimensional digital models of segments and / or the printing parameters are adjusted, followed by step S500 to reprint the segments. Advantageously, the method of the present application may further include a step of chamfering end faces of the rods before inserting them into the installation holes, so as to prevent the rods from scratching personnel during the assembly process and facilitate the insertion of the rods into the installation holes.

[00059] Also advantageously, after assembling the segments to form the module, the method of the present application may further include a sealing step. In the sealing step, the gaps of the module, that is, the gaps at the connecting surfaces of the segments, can be sealed using a filler, such as a mixture of putty and quartz powder, so as to enhance the connection stability between the segments. After the sealing is completed, sandpaper or other tools can be used to grind and polish the surface of the module to meet the smoothness requirements, thereby reducing the drag during the flight of the aircraft. Further, it is also possible to choose whether to paint the surface of the module according to requirements. Alternatively or additionally, after finally assembling the functional modules to form the aircraft, the gaps of the aircraft can be sealed, and its surface can be ground, polished, or painted.

[00060] According to the present application, in step S600 or step S700, the method may further include installing accessory devices on the modules formed by assembly or the aircraft formed by final assembly. The accessory devices refer to devices installed on the aircraft and having specific functions, such as controllers used to form a control system, electronic devices such as battery packs used to form a power system, lifting devices used to transport cargo, and carrying devices such as seats used to transport personnel. The accessory devices can be designed during the design of the three dimensional digital model of the aircraft, and printed during the printing of segments, or installation positions can be reserved during the design and printing process. The accessory devices can be obtained through procurement or processed through other processing methods. The accessory devices can be installed on the modules or aircraft by threaded connection, snap-fit connection, or bonding. Threaded holes for threaded connection, buckles for snap-fit connection, and bonding surfaces for bonding can be designed and printed together with the design of the three dimensional digital model of the aircraft, or processed through other processing methods after the segments are printed.

[00061] The present application also provides an aircraft, which is manufactured by using the manufacturing method based on the principles of the present application. The aircraft based on the principles of the present application may be a manned aircraft or an unmanned aircraft.

[00062] The manufacturing method based on the principles of the present application reduces the assembly steps of the aircraft, thereby shortening the manufacturing process of the aircraft and accelerating the processing of the aircraft. This improves the predictability of the product and the utilization rate of materials, while reducing costs. Further, the manufacturing method based on the principles of the present application also shortens the research and development cycle of the aircraft and the iteration cycle of the product. Moreover, the aircraft based on the principles of the present application allows designers to modify the three dimensional model according to specific needs before putting it into process when iteration or modification is required. This can eliminate the process of changing molds and processing devices in traditional manufacturing; compared to traditional manufacturing, 3D printing does not require excessive consideration of processing techniques, while also improving the flexibility of design and manufacturing.

[00063] Although at least one exemplary embodiment has been described in the above detailed description, it should be understood that there are numerous variations. It should also be understood that the one or more exemplary embodiments described herein are merely examples, and are not intended to limit the scope, applicability, or construction of the present application in any way. Instead, the above detailed description will provide convenient guidance for those skilled in the art to implement one or more exemplary embodiments. It should be understood that various changes, modifications, or alterations can be made to the functions and arrangement of the elements without departing from the scope of the present application as set forth in the appended claims and their equivalent solutions. 

Claims

1. A method for additive manufacturing of an aircraft, comprising:designing a three dimensional digital model of the aircraft; setting a design separation interface on the three dimensional digital model to divide the three dimensional digital model into three dimensional digital models of modules; setting a process separation interface on the three dimensional digital models of modules to divide the three dimensional digital models of modules into three dimensional digital models of segments; slicing the three dimensional digital models of segments and setting printing parameters to generate printing data; using a 3D printer to print based on the printing data to generate segments; assembling the segments to form modules; and finally assembling the modules to form an aircraft.

2. The method according to claim 1, wherein the segments and the modules are provided with installation holes.

3. The method according to claim 2, wherein the segments are assembled to form the modules by inserting rods into the installation holes of the segments to connect the segments, and the modules are finally assembled to form the aircraft by inserting rods into the installation holes of the modules to connect the modules.

4. The method according to claim 3, wherein the rod is bonded to the installation hole with adhesive and / or connected to the installation hole through interference fit.

5. The method according to claim 4, wherein the segments are also connected through a tenon-and-mortise structure, and the modules are also connected through a tenon-and-mortise structure.

6. The method according to claim 5, wherein the segments are also connected by threads, and the modules are also connected by threads.

7. The method according to claim 6, wherein the tenon-and-mortise structure is connected through interference fit.

8. The method according to claim 7, wherein mating surfaces of the tenon-and-mortise structure are bonded using an adhesive.

9. The method according to claim 8, wherein the rods comprise spar, stringer and tensile bar.

10. The method according to claim 5, further comprising: before assembling the segments to form the modules, pre-assembling the segments to inspect whether they are qualified, wherein if the segments are qualified, they are assembled to form the modules, and if the segments are unqualified, the parameters of the three dimensional digital models of segments and / or the printing parameters of segments are adjusted, and the 3D printer is used again to generate the segments by printing.

11. The method according to claim 5, further comprising: sealing gaps of the modules using a filler, and grinding and polishing the surfaces of the modules.

12. The method according to claim 5, further comprising: installing accessory devices on the modules formed by assembly or the aircraft formed by final assembly, wherein the accessory devices are installed by threaded connection, snap-fit connection, or bonding.

13. The method according to claim 5, wherein during the printing process, one or more materials from plastic, metal, and ceramic are used for printing, so as to meet different functional requirements.

14. The method according to claim 13, wherein the modules comprise at least one of a nose module, a belly module, an inner wing module, a takeoff assembly module, an outer wing module, a landing gear module, a tail module, and a mission payload module.

15. An aircraft, characterized in that the aircraft is manufactured by using the method according to claim 1.

Images