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Deformation aircraft

A technology of aircraft and wing rotation, applied in the field of aircraft, can solve the problems of poor flight reliability and safety, large torque of folding wing actuators, etc., and achieve the effect of ensuring reliability and safety

Pending Publication Date: 2020-02-28
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to provide a deformable aircraft to solve the technical problems of large torque of the folding wing actuator of the vertical take-off and landing aircraft and poor flight reliability and safety in the prior art

Method used

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  • Deformation aircraft
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  • Deformation aircraft

Examples

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Embodiment 1

[0035] A deformed aircraft provided in this embodiment, such as Figure 1-Figure 6 As shown, a deformable aircraft includes a fuselage 1, a fixed wing 2 and a rotating wing 3. The fixed wings 2 are symmetrically installed on both sides of the fuselage 1, and the center position of the rotating wing 3 is connected to the fixed wing through a rotating mechanism. The wing 2 is away from the end of the fuselage 1, and the rotating wing 3 can rotate relative to the fixed wing 2 around its connection point. The deformed aircraft of the present embodiment is connected to the end of the fixed wing 2 away from the fuselage 1 by the central position of the rotating wing 3, so that the rotating wing 3 can rotate relative to the fixed wing 2, because the rotating wing 3 and the fixed wing The connecting point of the wing 2 is the central point of the rotating wing 3, so that the static force on both sides of the rotating mechanism is the same, so the rotating moment of the rotating wing 3...

Embodiment 2

[0041] This embodiment is used as a kind of specific implementation manner of embodiment 1, such as Figure 7-Figure 8 As shown, the fixed wing 2 includes a fixed section 21 and a rotating section 22, the fixed section 21 is connected to both sides of the fuselage 1, one end of the rotating section 22 is connected to the end of the fixed section 21 away from the fuselage 1, and the rotating section 22 can Rotate relative to the fixed section 21 with the centerline of the end of the fixed section 21 away from the fuselage as the center, the other end of the rotating section 22 is connected to the center of the rotating wing 3, and the rotating wing 3 can rotate relative to the rotating section 22 The edge of the end of the segment 22 away from the fixed segment 21 is pivoted. When the deformation aircraft of this embodiment takes off vertically, as Figure 7 As shown, the fuselage 1 and the fixed section 21 of the fixed wing 2 are parallel to the ground, and the rotating secti...

Embodiment 3

[0045] This embodiment is used as a kind of specific implementation manner of embodiment 1, such as Figure 9-Figure 12 As shown, the fixed wing 2 includes an ascending section 23 and a descending section 24. The ascending section 23 is connected to the fuselage 1 and is inclined upward at an angle c. One end of the descending section 24 is connected with an end of the ascending section 23 away from the fuselage, and the descending section The inclination angle of 24 relative to the horizontal plane is b, the other end of the descending section 24 is connected to the center of the rotating wing 3, and the rotating wing 3 can rotate relative to the descending section 24 with the vertical line of the descending section 24 as the center. When the deformed aircraft in this embodiment is taking off vertically, as Figure 12 As shown, the angle b between the descending section 24 and the horizontal plane, the plane of the rotating wing 3 and the centerline of the rotor 4 are also in...

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Abstract

The invention relates to a deformation aircraft, and relates to the technical field of aircrafts to solve the technical problems that in the prior art, the force moment of a folding wing execution mechanism of a vertical takeoff and landing aircraft is large and flying reliability and safety are poor. The deformation aircraft comprises a machine body, fixed wings and rotation wings. The fixed wings are symmetrically installed on the two sides of the machine body. The center positions of the rotation wings are connected to the ends, away from the machine body, of the fixed wings through rotation mechanisms, and the rotation wings can rotate relative to the fixed wings with connection points as the centers. According to the deformation aircraft, the center points of the rotation wings are used as the connection points of the rotation wings and the fixed wings, and therefore the static stress of the two sides of each rotation mechanism can be the same; and the rotation force moment required by the rotation wings is smaller compared with the rotation force moment required by the fixed wings, and therefore the angle of the rotation wings can be freely regulated in the flying process ofthe deformation aircraft, and reliability and safety of the rotation wings of the deformation aircraft in the rotation process can be ensured.

Description

technical field [0001] The invention relates to the technical field of aircraft, in particular to a deformable aircraft. Background technique [0002] Vertical take-off and landing fixed-wing aircraft, combining fixed-wing aircraft and rotorcraft, can realize vertical take-off and landing, hovering in the air and fixed-wing cruise. The main features of the aircraft are: (1) The aircraft has the advantages of both rotorcraft and fixed-wing aircraft, which can realize vertical take-off and landing and vertical hovering, and can be transformed into a fixed-wing aircraft that can fly for a long time. Convert between the two. (2) During cruising flight, the two rotors can be rotated 90° to be parallel to the longitudinal axis of the aircraft to provide power for cruising flight, with relatively low energy consumption, high flight speed and large flight radius. With the continuous provision of aircraft automatic control technology, there are more and more application scenarios f...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64C27/26B64C27/28
CPCB64C27/26B64C27/28
Inventor 缪顺文缪培钰缪佩琪
Owner 缪顺文