Manufacturing method

Abstract

To provide a manufacturing method which improves the efficiency of a manufacturing process of a flight vehicle.SOLUTION: A manufacturing method of a flight vehicle 10 comprises: an assembly process which assembles the flight vehicle 10; and a measurement process which measures weight of the flight vehicle 10 and gravity center position thereof by a weight sensor 20. The measurement process starts at the time of performing the assembly process.SELECTED DRAWING: Figure 1

Description

[Technical Field]

[0001] The present disclosure relates to manufacturing methods. [Background technology]

[0002] Patent Document 1 discloses an assembly line for a flying object factory. [Prior art documents] [Patent documents]

[0003] [Patent Document 1] Japanese Patent Publication No. 2022-081433 Summary of the Invention [Problem to be solved by the invention]

[0004] Conventionally, the weight and center of gravity of a flying object are measured after the assembly of the flying object is completed, which results in an inefficient manufacturing process for the flying object.

[0005] The objective of this disclosure is to streamline the manufacturing process of air vehicles. [Means for solving the problem]

[0006] The manufacturing method according to the present disclosure includes: A method for manufacturing an aircraft, comprising: an assembly process for assembling the aircraft; a measuring step of measuring the weight and center of gravity of the aircraft using a weight sensor; Including, The measuring step starts when the assembling step is performed. [Effects of the Invention]

[0007] The present disclosure improves the efficiency of the air vehicle manufacturing process. [Brief explanation of the drawings]

[0008] [Figure 1]FIG. 1 is a schematic plan view of an air vehicle and a weight sensor according to an embodiment of the present disclosure. [Figure 2] FIG. 1 is a schematic front view of an air vehicle and a weight sensor according to an embodiment of the present disclosure. [Figure 3] 1 is a flowchart illustrating a manufacturing method according to an embodiment of the present disclosure. DETAILED DESCRIPTION OF THE INVENTION

[0009] Hereinafter, an embodiment of the present disclosure will be described with reference to the drawings.

[0010] In each drawing, the same or corresponding parts are denoted by the same reference numerals. In the description of this embodiment, the description of the same or corresponding parts will be omitted or simplified as appropriate.

[0011] The configuration of an aircraft 10 according to this embodiment will be described with reference to FIGS.

[0012] In this embodiment, the air vehicle 10 is a vertical take-off and landing (eVTOL) aircraft that obtains lift and thrust using one or more electric rotors, but may be another type of air vehicle, such as an airplane, helicopter, or glider. "eVTOL" is an abbreviation for electric vertical take-off and landing. The air vehicle 10 can accommodate one or more crew members in its cabin. The air vehicle 10 is operated at least in part under VFR. "VFR" is an abbreviation for visual flight rules. The air vehicle 10 may also be operated under IFR. "IFR" is an abbreviation for instrument flight rules.

[0013] The aircraft 10 comprises a main body 11, main wings 12, and one or more rotors 13. The main wings 12 are attached to the top of the main body 11. In addition to the main wings 12, various other components are attached to the main body 11, such as doors, seats, and wheels 14. The main wings 12 and the tail fins attached to the rear of the main body 11 each have one or more nacelles. Each nacelle is attached with a rotor 13 and contains a drive mechanism including a motor for driving the rotor 13. The rotor 13 corresponds to an electric rotor. The rotor 13 may be of a tilt type. The number of rotors 13 may be any number sufficient to obtain the required thrust. In this embodiment, there are four rotors 13 in total, two on each of the main wings 12 and the tail fin. The number of nacelles is the same as the number of rotors 13. The main wings 12 contain one or more batteries that supply power to the drive mechanism. Similar batteries may also be contained in one or more nacelles. The number of wheels 14 may be four or more, but in this embodiment, there are three. The aircraft 10 may further include known equipment such as avionics and actuators, electrical components such as wire harnesses, and equipment components such as air conditioning ducts and other piping. The avionics includes, for example, a computer, a flight recorder, and radar.

[0014] In this embodiment, the weight and center of gravity position of the aircraft 10 are measured by the weight sensor 20. The center of gravity position of the aircraft 10 is specifically the position of the center of gravity in the horizontal direction, but may also include the position of the center of gravity in the vertical direction. The number of weight sensors 20 may be four or more, but in this embodiment there are three.

[0015] The weight sensor 20 may be any sensor capable of measuring the weight and center of gravity of an object placed thereon. The weight sensor 20 may be, for example, a mattress-type or sheet-type sensor. The weight sensor 20 is placed on the floor of a factory assembly line. The weight sensor 20 may be at least partially embedded in the floor. On the assembly line, the weight and center of gravity of the air vehicle 10 can be measured by placing each of the three wheels 14 of the air vehicle 10 on the corresponding weight sensor 20.

[0016] The weight sensor 20 may be a sensor capable of measuring the weight and center of gravity of a suspended object. In such a modified example, the weight sensor 20 is placed on the ceiling of a factory assembly line. The weight sensor 20 may be at least partially embedded in the ceiling. By hanging the aircraft 10 at three points on the assembly line, the weight and center of gravity of the aircraft 10 can be measured.

[0017] The manufacturing method according to this embodiment will be described with reference to FIG.

[0018] The manufacturing method according to this embodiment includes an assembly process for assembling the aircraft 10 and a measurement process for measuring the weight and center of gravity of the aircraft 10 using a weight sensor 20. The series of steps S1 to S3 shown in FIG. 3 correspond to the assembly process, but step S3 also includes a measurement process.

[0019] In S1, the main body 11 of the aircraft 10 is assembled. Specifically, the main body 11 is assembled by workers, robots, or a combination of workers and robots. The assembled main body 11 is then transported by a conveyor to a location on the assembly line where one or more components, including the main wings 12, are prepared. Alternatively, if wheels 14 are already attached to the main body 11, the main body 11 may move to that location by itself.

[0020] In S2, one or more parts including the main wings 12 are attached to the main body 11. Specifically, a worker, a robot, or a collaboration between a worker and a robot attaches the one or more parts to the main body 11. For example, the main wings 12 are riveted to the top of the main body 11. Thereafter, the main body 11 with the one or more parts including the main wings 12 attached is transported by a conveyor to a location on the assembly line where other parts including the rotors 13 are prepared. Alternatively, if wheels 14 are already attached to the main body 11, the main body 11 may move to that location by itself.

[0021] In S3, other parts including the rotor 13 are attached to the main body 11, to which one or more parts including the main wing 12 have been attached, thereby completing the aircraft 10. Specifically, a worker or a robot, or a worker and a robot working together, attaches the other parts to the main body 11, to which one or more parts have been attached. For example, the rotor 13 is attached to a nacelle of the main wing 12 and a nacelle of the tail provided at the rear of the main body 11.

[0022] In S3, the weight and center of gravity position of the aircraft 10 are further measured by the weight sensor 20. The measurement results obtained by the weight sensor 20 are acquired, stored, and output by a computer. For example, the weight sensor 20 transmits the measured values ​​of the weight and center of gravity position to the computer. Upon receiving the measured values, the computer stores the received measured values ​​in storage and displays them on a display.

[0023] In S4, the flying vehicle 10 is towed and moved from the assembly line to the inspection space. Alternatively, the flying vehicle 10 may move from the assembly line to the inspection space by self-propelling.

[0024] In S5, the aircraft 10 is inspected. Specifically, the aircraft 10 is inspected by a worker or a robot, or by a worker and a robot working together.

[0025] As described above, in this embodiment, the measurement process begins when the assembly process is being performed, rather than after the assembly process is completed, which improves the efficiency of the manufacturing process of the air vehicle 10.

[0026] The measurement process may be started at any timing during the assembly process. For example, the weight sensor 20 may begin measuring the weight and center of gravity of the aircraft 10 being assembled at S1 or S2. During the assembly process, the measurement results obtained by the weight sensor 20 may be sequentially stored by the computer. The computer may then compare the progress of the assembly process, i.e., which parts are to be attached at what point in time, with changes in the stored measurement results to determine whether any parts have been left attached.

[0027] For example, before the start of S2 or S3, a measuring device having a weight sensor 20 may be attached to the air vehicle 10 under assembly, and the device may be moved along with the air vehicle 10 under assembly while taking measurements.

[0028] The present disclosure is not limited to the above-described embodiments. For example, two or more blocks shown in the block diagrams may be integrated, or one block may be divided. Two or more steps shown in the flowcharts may be executed in parallel or in a different order, instead of being executed in chronological order as described, depending on the processing capabilities of the device executing each step, or as needed. Other modifications are possible within the scope of the present disclosure. [Explanation of symbols]

[0029] 10 Flying Objects 11 Main unit 12 Main wing 13 Rotor 14 wheels 20 Weight Sensor

Claims

[Claim 1] A method for manufacturing an aircraft, comprising: an assembly process for assembling the aircraft; a measuring step of measuring the weight and center of gravity of the aircraft using a weight sensor; Including, A manufacturing method in which the measuring step starts when the assembly step is performed.

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