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Rotor-wing craft with two tilting flaps with balanced axial vector

A technology for tilting rotors and aircraft, applied in aircraft, unmanned aircraft, rotorcraft, etc., can solve the problems of cumbersome structure and low flight efficiency, and achieve the effect of powerful overall function, reasonable structure, and simple use and control.

Inactive Publication Date: 2016-06-29
左建章 +2
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  • Abstract
  • Description
  • Claims
  • Application Information

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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 thr

Method used

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  • Rotor-wing craft with two tilting flaps with balanced axial vector

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[0014] The technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative work shall fall within the protection scope of the present invention.

[0015] See figure 1 In the 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 a tail and a rudder, and the left and right side walls of the fuselage 1 are respectively fixedly installed The left wing 2 and the right wing 3, the left wing 2, the right wing 3, and the lower surface of the fuselage 1 are all equipped with walking wheels, ...

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Abstract

The invention discloses a rotor-wing craft with two tilting flaps with balanced axial vector. The rotor-wing craft comprises a craft body, wherein a tail wing and a rudder are arranged at the tail part of the craft body; a left wing and a right wing are respectively and fixedly arranged on the left side wall and the right side wall of the craft body; traveling wheels are respectively arranged on the lower surfaces of the left wing, the right wing and the craft body, and a left balancing flap and a right balancing flap are respectively and movably arranged at the outermost ends of the left wing and the right wing; a left tilting servo mechanism and a right tilting servo mechanism are respectively arranged in the left wing and the right wing, the left tilting servo mechanism is connected with the left balancing flap in a transmission manner, and the right tilting servo mechanism is connected with the right balancing flap in a transmission manner; and the balancing flaps are driven to rotate by utilizing the tilting servo mechanisms. The rotor-wing craft disclosed by the invention has the advantages that the structure is reasonable, simultaneously the cost is lower, the whole use and control are simple, the rotor-wing flying of the fixed-wing craft can be effectively realized and the whole 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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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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