阅读说明：本技术 一种飞行器用双向调节旋翼 (Bidirectional adjusting rotor wing for aircraft ) 是由 顾文彬 王震 何雷 毛益明 陆鸣 谢兴博 钟明寿 胡云昊 陈裕田 韩阳明 符磊 于 2019-07-30 设计创作，主要内容包括：本发明涉及一种飞行器用双向调节旋翼,包括：U形支架,铰接在所述U形支架开口的圆环支架,可转动的安装在所述圆环支架中的驱动轴和安装在所述驱动轴上的桨叶；所述U形支架两侧具有铰轴安装孔；所述桨叶的底端具有L形安装臂,所述L形安装臂铰接在所述驱动轴上。本发明提供的双向调节旋翼应用到飞行器一体化巡飞弹上,综合集成巡航探测、追踪攻击、悬停打击等多种功能。(The invention relates to a bidirectional adjusting rotor wing for an aircraft, which comprises: the device comprises a U-shaped bracket, a circular ring bracket hinged at the opening of the U-shaped bracket, a driving shaft rotatably arranged in the circular ring bracket and a paddle arranged on the driving shaft; hinge shaft mounting holes are formed in two sides of the U-shaped support; the bottom end of the paddle is provided with an L-shaped mounting arm which is hinged on the driving shaft. The two-way adjusting rotor wing provided by the invention is applied to an integrated cruise missile of an aircraft, and integrates multiple functions of cruise detection, tracking attack, hovering striking and the like comprehensively.)

1. A two-way adjustable rotor for an aircraft, comprising: the device comprises a U-shaped bracket, a circular ring bracket hinged at the opening of the U-shaped bracket, a driving shaft rotatably arranged in the circular ring bracket and a paddle arranged on the driving shaft; hinge shaft mounting holes are formed in two sides of the U-shaped support; the end part of the driving shaft obliquely extends to form a mounting arm, and the bottom end of the paddle is hinged to the mounting arm.

2. A bi-directionally adjustable rotor for an aircraft according to claim 1, wherein: the twist angle of the blade decreases from 15 degrees to 4 degrees from the root to the tip.

3. A bi-directionally adjustable rotor for an aircraft according to claim 1, wherein: the paddles are a pair and are symmetrically arranged on the driving shaft.

4. A bi-directionally adjustable rotor for an aircraft according to claim 1, wherein: the hinge shaft mounting hole is formed in an 8-shaped bracket; the 8-shaped bracket is fixed with the U-shaped bracket; the axis of the hinge shaft mounting hole is perpendicular to the axis of the hinge shaft of the circular ring support.

Technical Field

The invention relates to a bidirectional adjusting rotor wing for an aircraft, and belongs to the technical field of unmanned aerial vehicles.

Background

Along with rotor unmanned aerial vehicle technique promotes, unmanned aerial vehicle can carry on equipment weight and promote, can play more and more important effect in the modernization war. However, the existing rotor unmanned aerial vehicle flies by using a rotor, the speed of the existing rotor unmanned aerial vehicle is extremely low, and the existing rotor unmanned aerial vehicle cannot effectively meet the requirement of hitting a maneuvering target, namely, the existing rotor unmanned aerial vehicle hits a ground target, and because the speed of the existing rotor unmanned aerial vehicle is too low, a long reaction time is formed for an opponent, so that attack failure is caused.

Disclosure of Invention

The invention aims to solve the technical problems that: overcome the shortcoming of above-mentioned technique, thereby provide one kind and can adjust the rotor orientation and change the aircraft of unmanned aerial vehicle flight mode and use two-way regulation rotor.

In order to solve the technical problems, the technical scheme provided by the invention is as follows: a dual-adjustment rotor for an aircraft, comprising: the device comprises a U-shaped bracket, a circular ring bracket hinged at the opening of the U-shaped bracket, a driving shaft rotatably arranged in the circular ring bracket and a paddle arranged on the driving shaft; hinge shaft mounting holes are formed in two sides of the U-shaped support; the end part of the driving shaft obliquely extends to form a mounting arm, and the bottom end of the paddle is hinged to the mounting arm.

The scheme is further improved in that: the twist angle of the blade decreases from 15 degrees to 4 degrees from the root to the tip.

The scheme is further improved in that: the paddles are a pair and are symmetrically arranged on the driving shaft.

The scheme is further improved in that: the hinge shaft mounting hole is formed in an 8-shaped bracket; the 8-shaped bracket is fixed with the U-shaped bracket; the axis of the hinge shaft mounting hole is perpendicular to the axis of the hinge shaft of the circular ring support.

The two-way adjusting rotor wing for the aircraft provided by the invention realizes the change of two horizontal and vertical axes through the design of two vertical hinge shafts, and is assisted by the fixed wing, thereby realizing the mutual conversion from the lift force provided by the rotor wing to the power flight provided by the rotor wing, and further realizing the rapid flight, hovering and other various attitude changes of the unmanned aerial vehicle.

Drawings

the invention will be further explained with reference to the drawings.

Fig. 1 is a schematic structural diagram of an application state of a preferred embodiment of the present invention.

Fig. 2 is a schematic view of the fully folded mode structure of fig. 1.

Fig. 3 is a schematic structural view of the front fly mode of fig. 1.

fig. 4 is a schematic structural diagram of a preferred embodiment of the present invention.

Detailed Description