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A Two-axis Vector Balanced Flap Tilt Rotor Aircraft

A technology of tilting rotors and aircrafts, which is applied to aircrafts, unmanned aircrafts, rotorcraft, etc., can solve the problems of bulky structure and low flight efficiency, and achieve the effect of powerful overall function, reasonable structure and low cost

Inactive Publication Date: 2018-06-01
左建章 +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

There are also fixed-wing UAVs that can take off and land vertically at air shows in China, but the principle is just to superimpose a three-axis multi-rotor aircraft on a fixed-wing aircraft. The technology is simple and the structure is cumbersome. down flight inefficiency

Method used

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  • A Two-axis Vector Balanced Flap Tilt Rotor Aircraft

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Embodiment Construction

[0014] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0015] see figure 1 , in an embodiment of the present invention, a two-axis vector balance flap tilt rotor aircraft includes a fuselage 1, the tail of the fuselage 1 is provided with an empennage and a rudder, and the left and right side walls of the fuselage 1 are respectively fixedly installed with The left wing 2 and the right wing 3, the lower surfaces of the left wing 2, the right wing 3 and the fuselage 1 are equipped with road wheels, and the outermost ...

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Abstract

The invention discloses a two-axis vector balanced flap tilt rotor aircraft, which comprises a fuselage, the tail of the fuselage is provided with an empennage and a rudder, and the left and right side walls of the fuselage are respectively fixedly installed with a left wing and a right wing. The left wing, the right wing and the lower surface of the fuselage are all equipped with walking wheels, and the outermost ends of the left wing and the right wing are respectively equipped with a left balance flap and a right balance flap. and the right wing are respectively installed with a left tilting servo mechanism and a right tilting servo mechanism, and the left tilting servo mechanism is connected to the left balance flap by transmission, and the right tilting servo mechanism is connected to the right balance flap by transmission, and the tilting servo mechanism is used to drive the balance flap Rotation, the invention has reasonable structure, low cost, simple overall use and control, can effectively realize the rotor flight of the fixed-wing aircraft, and the overall function is more powerful.

Description

technical field [0001] The invention relates to the field of unmanned aerial vehicles, in particular to a two-axis vector balanced flap tilt rotor aircraft. Background technique [0002] With the rapid development of science and technology, unmanned aerial vehicles have played an increasingly important role in various fields of military and civilian use. However, judging from the current development status, they can be roughly divided into helicopters, multi-rotors and fixed-wings. Helicopters are characterized by flexible takeoff and landing, large load capacity, mostly oil-powered engines, and a relatively long range compared to multi-rotors. However, its disadvantages are complex structure, difficult control, and high maintenance cost, while the main rotor is relatively dangerous due to its large diameter and fast rotation speed. Multi-rotors are the fastest-growing new type of aircraft in recent years. Due to their simple structure, easy operation, low cost, and vertic...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/22B64C3/38B64C9/00B64C13/16B64C13/24
CPCB64C3/38B64C9/00B64C13/16B64C13/24B64C27/22B64C2009/005B64U10/00
Inventor 左建章张军利李军杰
Owner 左建章
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