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Aircraft fuselage and aircraft including same

A technology for aircraft and fuselage, applied in the field of aircraft, can solve the problems of poor fuselage strength, heavy fuselage weight, laborious installation of aircraft, etc., and achieve the effects of increasing fuselage strength, reducing dead weight, and facilitating transportation

Active Publication Date: 2020-10-02
YUNEEC TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The technical problem to be solved by the present invention is to overcome the weight of the fuselage, the poor strength of the fuselage, and the difficulty of the aircraft caused by the installation of the power system first and then closing the upper and lower fuselages in the prior art, and the use of screw connections to connect the upper and lower fuselages of the aircraft. With defects such as laborious and laborious installation, an aircraft fuselage and an aircraft including it are provided

Method used

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  • Aircraft fuselage and aircraft including same
  • Aircraft fuselage and aircraft including same
  • Aircraft fuselage and aircraft including same

Examples

Experimental program
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Embodiment 1

[0034] figure 1 An aircraft fuselage 1 is shown comprising an upper fuselage 2 and a lower fuselage 3 . The upper fuselage and the lower fuselage are connected by ultrasonic welding. Such as Figure 4 As shown, the interior of the aircraft fuselage 1 has a cavity 4 communicating with at least one opening 5 on the lower fuselage. A power system (not shown in the figure) is disposed in the cavity through the opening.

[0035] The interior of the aircraft fuselage of the present invention has a relatively large cavity, and the cavity communicates with the outside through the opening on the lower fuselage. In this way, the power system can be installed on the fuselage after the fuselage of the aircraft is made. Openings in the lower fuselage provide ample space for rear-mounted powertrains. In this embodiment, the power system includes a main control board and a battery. The main control board can drive the rotor motor to rotate to provide flight power, and the battery suppl...

Embodiment 2

[0047] The aircraft in this embodiment is a remote control aircraft, refer to Figure 5 and Image 6 as shown ( Figure 5 , 6 Both mainly show the lower part of the aircraft fuselage), the fuselage structure includes an aircraft fuselage. The fuselage of the aircraft has a battery slot 12, an inner cavity, an antenna port, two wiring ports 15 and 16, a wiring port cover, a baffle plate 13, and a landing gear interface 14 together.

[0048] Wherein, the battery slot 12 is arranged at the lower part of the aircraft fuselage and is used for accommodating the battery assembly, and the inner accommodating cavity is arranged inside the battery slot and is located inside the aircraft fuselage, and the inner accommodating cavity is used for accommodating a main The control board 11 (that is to say, the inner cavity is located Figure 5 In the main control board 11), the opening of the battery slot allows the main control board to enter the inner cavity through the battery slot. I...

Embodiment 3

[0056] This embodiment is an aircraft, which includes the aircraft fuselage described in any one of the above-mentioned embodiments 1-2.

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Abstract

The present invention provides an aerocraft fuselage and an aerocraft comprising the aerocraft fuselage. The aerocraft fuselage comprises an upper fuselage and a lower fuselage, wherein the upper fuselage and the lower fuselage are connected by using ultrasonic welding, a cavity is arranged inside the aerocraft fuselage and is communicated to at least an opening on the lower fuselage, and a power system is arranged inside the cavity through the opening. According to the present invention, the upper fuselage and the lower fuselage of the aerocraft are connected by using the ultrasonic welding process, such that the one-time molding is achieved, and the yield is high; and the upper fuselage and the lower fuselage of the aerocraft fuselage using the welding process form the seamless connection, the force is applied on the contact surface, and the strength is substantially improved.

Description

technical field [0001] In particular, the invention relates to an aircraft fuselage and an aircraft comprising it. Background technique [0002] In the aircraft of the prior art, the power system needs to be installed in the upper fuselage or the lower fuselage first, and then the upper and lower fuselages are closed and fixedly connected after the installation is completed. Moreover, the upper and lower fuselages of the aircraft are often connected by screw connection, and the screw fixing points are used as stress points, but the overall fuselage strength is relatively low. If the number of screws is increased in order to enhance the strength of the fuselage, excessive weight will be added to the aircraft, which is not conducive to the improvement of the performance of the aircraft. At the same time, it is difficult to assemble by screw connection. The fuselage of medium to large aircraft locks generally requires dozens of screws of different sizes, which leads to high la...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C1/00
Inventor 田瑜江文彦
Owner YUNEEC TECH CO LTD