阅读说明：本技术 一种v型尾翼多旋翼垂直起降布局的飞行器 (Aircraft with V-shaped empennage and multiple rotors in vertical take-off and landing layout ) 是由 杨小川 刘刚 付志 毛仲君 汪华松 于 2020-04-22 设计创作，主要内容包括：本发明涉及飞行器技术领域,公开了一种V型尾翼多旋翼垂直起降布局的飞行器,包括机身、固定侧翼、V型尾翼和提供飞行器前进拉力的动力机构,两侧固定侧翼靠近尖端的位置对称设置有翼尖旋翼,翼尖旋翼的旋转平面与所在的侧翼位于同一平面内；V型尾翼的两个翼段内对称设置有V尾旋翼,两个V尾旋翼的旋转平面与所在的V型尾翼翼段位于同一平面内。本发明采用四个旋翼分别内嵌于两侧机翼翼尖及V型尾翼的布局形式,该类飞行器的外形布局能在保证机体结构强度较高、动力充足前提下,提高多旋翼飞行器的抗风能力,减小阻力,并提高飞行速度。(The invention relates to the technical field of aircrafts, and discloses an aircraft with a V-shaped empennage and a multi-rotor vertical take-off and landing layout, which comprises an aircraft body, fixed side wings, a V-shaped empennage and a power mechanism for providing forward pulling force of the aircraft, wherein the fixed side wings on two sides are symmetrically provided with wingtip rotors close to the tip end, and the rotating planes of the wingtip rotors and the side wings are positioned in the same plane; the V-tail rotor wings are symmetrically arranged in the two wing sections of the V-shaped empennage, and the rotating planes of the two V-tail rotor wings and the wing sections of the V-shaped empennage are positioned in the same plane. The invention adopts the layout mode that four rotors are respectively embedded in wing tips of wings at two sides and a V-shaped empennage, and the appearance layout of the aircraft can improve the wind resistance of the multi-rotor aircraft, reduce the resistance and improve the flight speed on the premise of ensuring higher structural strength and sufficient power of the aircraft body.)

1. The utility model provides an aircraft of many rotors VTOL overall arrangement of V type fin, includes fuselage (1), fixed flank (2), V type fin (5) and provides the aircraft power unit that pulling force advances, its characterized in that: wing tip rotors (4) are symmetrically arranged at the positions, close to the tip, of the fixed side wings (2) on the two sides, and the rotating planes of the wing tip rotors (4) and the fixed side wings (2) are located in the same plane; v tail rotor wings (6) are symmetrically arranged in two wing sections of the V-shaped empennage (5), and the rotating plane of the V tail rotor wings (6) and the wing sections of the V-shaped empennage (5) are located on the same plane.

2. The aircraft of claim 1, wherein the V-tail multi-rotor vtol configuration comprises: the two wingtip rotors (4) are embedded in the positions, close to the wingtips, of the fixed side wings (2) respectively.

3. The aircraft of claim 2, wherein the V-tail multi-rotor vtol configuration comprises: the power mechanism is a propeller (3) and is positioned at the front end of the machine body (1).

4. The aircraft of claim 2, wherein the V-tail multi-rotor vtol configuration comprises: the power mechanism is a propeller (3) and is positioned at the tail part of the machine body (1).

5. The aircraft of claim 2, wherein the V-tail multi-rotor vtol configuration comprises: the power mechanism is a turbojet engine or a turbofan engine (7) arranged at the tail of the engine body (1).

6. The aircraft of claim 2, wherein the V-tail multi-rotor vtol configuration comprises: the power mechanism comprises two propellers (3), and the two propellers (3) are symmetrically arranged at the front positions of the windward sides of the fixed side wings (2) respectively.

7. The aircraft of claim 1, wherein the V-tail multi-rotor vtol configuration comprises: two wingtip rotor (4) are two tilting rotor, two tilting rotor symmetry respectively sets up in the most advanced outside position of two fixed flank (2).

Technical Field

The invention relates to the technical field of aircrafts, in particular to an aircraft with a V-shaped empennage and a plurality of rotors in vertical take-off and landing layout.

Background

The vertical take-off and landing fixed wing aircraft is an aviation fixed wing aircraft with vertical take-off and landing in a simple and small environment, has the characteristics of simplicity in take-off and landing, long endurance, long voyage distance and the like, and is one of aviation equipment which is mainly developed in various countries. A more common vtol unmanned aerial vehicle mainly includes a multi-rotor composite vtol aircraft, a tail-seated vtol aircraft, and a tilt-type vtol aircraft.

The multi-wingtip rotor wing of the existing multi-rotor wing combined type vertical take-off and landing aircraft is exposed like a multi-wingtip rotor wing and depends on multi-rotor wing reverse twist to carry out course control, and the existing multi-rotor wing combined type vertical take-off and landing aircraft has the defects of larger flight resistance, weaker wind resistance, poorer direction stability and the like; the fuselage of the tail-seated vertical take-off and landing aircraft is in a vertical state in a take-off and landing mode, and a horizontal flying mode is changed into a horizontal state, so that the problems of high gravity center, difficult take-off and landing, complex control and the like exist; and the tilting mechanism and the control system of the tilting type vertical take-off and landing aircraft are relatively complex and have high technical difficulty.

Disclosure of Invention

Based on the problems, the invention provides the aircraft with the V-shaped empennage and the multi-rotor vertical take-off and landing layout, the four rotors are respectively embedded in wing tips of the two sides of the aircraft and the V-shaped empennage, and the appearance layout of the aircraft can improve the wind resistance of the multi-rotor aircraft, reduce the resistance and improve the flight speed on the premise of ensuring higher structural strength and sufficient power of the aircraft body.

In order to solve the technical problems, the invention provides an aircraft with a V-shaped empennage and a multi-rotor-wing vertical take-off and landing layout, which comprises an aircraft body, fixed side wings, a V-shaped empennage and a power mechanism for providing forward pulling force of the aircraft, wherein the fixed side wings on two sides are symmetrically provided with wingtip rotors close to the tip end, and the rotating planes of the wingtip rotors and the fixed side wings are positioned in the same plane; the V-tail rotor wings are symmetrically arranged in the two wing sections of the V-shaped empennage, and the rotating planes of the two V-tail rotor wings and the wing sections of the V-shaped empennage are positioned in the same plane.

Furthermore, two wingtip rotors are respectively embedded in the positions of the fixed side wings close to the wingtips.

Furthermore, the power mechanism is a propeller and is positioned at the front end of the machine body.

Furthermore, the power mechanism is a propeller and is positioned at the tail part of the machine body.

Further, the power mechanism is a turbojet engine or a turbofan engine arranged at the tail of the engine body.

Furthermore, the power mechanism comprises two propellers which are respectively and symmetrically arranged at the front positions of the windward sides of the fixed side wings at the two sides.

Further, two wingtip rotors are two tilting rotors, and the two tilting rotors are respectively and symmetrically arranged at the outer side positions of the tips of the two fixed side wings.

Compared with the prior art, the invention has the beneficial effects that:

1) the flight resistance during cruise is reduced: the vertical take-off and landing aircraft composed of two fixed side wing wingtip rotary wings and a V-shaped tail rotary wing of a V-shaped tail wing has the advantages that the hovering power or posture auxiliary arrangement mode can obviously reduce the resistance of the aircraft, and under the condition of ensuring the same propelling efficiency, because the multiple rotary wings are embedded, the fixed wings have small resistance and longer flight time;

2) enhancing the wind resistance of the aircraft: compared with a combined vertical takeoff device which is operated by means of multi-rotor wing reverse-twisting course, the wing tip rotor wings of the fixed side wings on the two sides and the V-shaped tail rotor wing of the V-shaped tail wing are embedded, and the course operation is still directly driven by the tension of the V-shaped tail rotor wing of the V-shaped tail wing, so that the wind resistance of the aircraft can be obviously improved;

3) the control of the vertical lifting is simple: the hovering control mode of the layout is similar to a combined type vertical take-off and landing mode, and the difficulty in designing a flight control strategy and a control law is low;

4) compatible with various power arrangements: the aircraft adopts a vertical layout form of wingtip rotors of wingtips of two fixed side wings and V-shaped tail rotors of a V-shaped tail wing, the aircraft has a simple structure, the problem of blade interference of forward pulling and backward pushing power does not exist, and the aircraft can be compatible with various power layouts;

5) applicable high-speed configuration: the aircraft adopts the embedded mode rotor layout, does not have other parts that expose, and the area of facing the wind is little, can be applicable to high-speed overall arrangement configuration.

Drawings

FIG. 1 is a schematic structural view of an aircraft in a V-tail multi-rotor VTOL layout in embodiment 1;

FIG. 2 is a front view of the arrangement of the V-shaped flight of FIG. 1;

FIG. 3 is a schematic view showing a multi-rotor VTOL layout of the V-type empennage in which propellers are installed at the front ends of wings on both sides in embodiment 2;

FIG. 4 is a schematic view showing a multi-rotor VTOL layout with a V-shaped tail and propellers mounted on the tail of a fuselage in accordance with embodiment 2;

FIG. 5 is a schematic view showing a V-type empennage multi-rotor VTOL layout with a turbofan engine added to the tail of the fuselage in embodiment 2;

fig. 6 is a schematic view of a V-type empennage multi-rotor vertical take-off and landing layout of a tip-tilt rotor according to embodiment 3;

wherein: 1. a body; 2. fixing the side wings; 3. a propeller; 4. a wingtip rotor; 5. a V-shaped tail; 6. a tail rotor wing V; 7. turbofan engine.

Detailed Description

In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail below with reference to examples and accompanying drawings, and the exemplary embodiments and descriptions thereof are only used for explaining the present invention and are not meant to limit the present invention.