阅读说明：本技术 一种可垂直起降的飞行器 (Aircraft capable of vertically taking off and landing ) 是由 不公告发明人 于 2018-06-06 设计创作，主要内容包括：本发明公开一种可垂直起降飞行器,包括飞行舱,垂直方向动力模块,水平方向动力模块,操控平台,信号模块,电池或内燃机组成的动力模块,可折叠的机翼,应急模块,支撑模块。本发明还提供了该飞行器的实现方法,其分别利用垂直方向和水平方向螺旋桨旋转产生推力,实现垂直和水平方向运动,并且通过附加在螺旋桨上的控制气流的格栅实现该飞行器的稳定已经姿态控制。(The invention discloses an aircraft capable of vertically taking off and landing, which comprises a flight cabin, a vertical power module, a horizontal power module, an operation platform, a signal module, a power module consisting of a battery or an internal combustion engine, a foldable wing, an emergency module and a support module. The invention also provides a realization method of the aircraft, which respectively utilizes the rotation of the propellers in the vertical direction and the horizontal direction to generate thrust, realizes the movement in the vertical direction and the horizontal direction, and realizes the stable attitude control of the aircraft through the grille which is attached to the propellers and controls airflow.)

1. A vertical take-off and landing aircraft comprises (1) a flight cabin, (2) a vertical power module, (3) a horizontal power module, (4) a control platform, (5) a signal module, (6) a power module consisting of a battery or an internal combustion engine, (7) a foldable wing, (8) an emergency module and (9) a support module, and is characterized in that (1) the flight cabin is positioned in the middle of the aircraft and can carry 1-4 people without people, (2) the vertical power module consists of two propellers and an airflow control module, (3) the horizontal power module consists of two propellers and an airflow control module, (4) the control platform consists of a core control module, (5) the signal module and (6) the power module consisting of a battery or an internal combustion engine provides power for the vertical power module and the horizontal power module, (7) the foldable wings provide lift for the aircraft, (8) the emergency module provides safety protection for the aircraft in an emergency situation, and (9) the support module is used for supporting the aircraft during landing.

2. The VTOL aerial vehicle of claim 1, wherein the flight chamber comprises 1-4 seats, a control panel, a rudder, an automatic control system and a storage chamber, and further comprises a storage chamber and an automatic control system.

3. The VTOL aerial vehicle of claim 1, wherein the vertical power module and the horizontal power module are respectively composed of 2-4 propellers and a grille integrated on the upper and lower sides of the propellers for controlling airflow in one or both of front and rear directions.

4. The propeller as claimed in claim 3, wherein the air flow controlling grilles integrated on the upper and lower sides and the front and rear sides of the propeller and made of 2-20 solid or hollow blades having a length of 5-10000 mm, a width of 2-1000 mm, and a thickness of 0.2-50 mm made of carbon fiber, polymer material, metal or other composite material are formed by 2-20 grilles having a length of 5-10000 mm, a width of 2-1000 mm, and a thickness of 0.2-50 mm made of carbon fiber, polymer material, metal or other composite material, and are opened and closed by the control system to control the size and direction of the air flow.

5. The VTOL aerial vehicle of claim 1, wherein the control platform is manual or automatic, and can control the power system and the grid in horizontal and vertical directions by mechanical or electric current.

6. The VTOL aerial vehicle of claim 1, wherein the signal module is capable of transmitting and receiving signals.

7. The vtol aerial vehicle of claim 1, wherein the power module comprising a battery or an internal combustion engine provides power to the vertical power module and the horizontal power module via a conventional system or circuit.

8. The VTOL aerial vehicle of claim 1, wherein the foldable wings are made of carbon fiber, metal or other composite materials, and have a length of 5-10000 mm, a width of 5-2000 mm, and a thickness of 0.2-200 mm.

9. The VTOL aerial vehicle of claim 1, wherein the emergency module comprises an automatically or manually controlled parachute and a protection airbag.

Background

At present, automobiles are the most widely used vehicles in medium-distance traffic. Although automobiles greatly increase the convenience of life, with the popularization of automobiles, traffic congestion has become a difficult problem in cities. On the other hand, most automobiles consume fossil fuels, causing great damage to the environment and human health.

Electric vehicles are developed rapidly, but the problems of traffic jam and long-distance traffic cannot be solved. The demand for three-dimensional traffic in the traffic field has increased substantially.

In recent years, many vertical take-off and landing aircraft have appeared. The multi-axis unmanned aerial vehicle is widely applied as a tool which can help people to shoot in the air. But endurance becomes a problem.

In the field of manned flight, aircraft have emerged that employ four-axis propellers and battery power. However, the system has heavy weight and short cruising distance, and cannot solve the problem of medium-distance traffic.

The invention adopts the technologies of a power module comprising a vertical power module, a horizontal power module, a battery or an internal combustion engine, a foldable wing and the like, solves the problems of overlarge size, short flight distance and small load capacity of the aircraft, and is the aircraft with practical value.

Disclosure of Invention

The invention aims to solve the problems of the existing vehicles and provides a manned or unmanned aircraft which does not need a runway, can take off and land vertically and can realize medium and long distance traffic.

In order to achieve the purpose, the technical scheme adopted by the invention comprises the following steps: the aircraft comprises (1) a flight cabin, (2) a vertical direction power module for providing lift force in the processes of takeoff, landing and flight, (3) a horizontal direction power module for providing forward or backward speed and direction of the aircraft and adjusting various flight attitudes, (4) a control platform for controlling the speed of takeoff or landing, the forward or backward speed and adjusting various flight attitudes, (5) a signal module for transmitting or receiving signals, (6) a power module consisting of a battery or an internal combustion engine for providing power for takeoff, landing and flight, and (7) a foldable wing for providing lift force required by long-distance flight. (8) The emergency module is used for providing emergency protection for personnel materials and the aircraft when the aircraft breaks down, and the support module is used for providing support for the aircraft on land (9).

Specifically, the flying cabin can be composed of 1-4 seats, a control panel, a rudder, a control system and a storage bin, and can also be composed of the storage bin and an automatic control system because the aircraft can be manned or unmanned. In manned situations, flight pods have openable and closable viewing windows. In addition, the flight cabin is also provided with an air conditioning system for regulating the temperature in the cabin.

Specifically, the vertical power module is composed of two propellers and a grille integrated with the propellers and used for controlling airflow above and below or above and below the propellers. The two propellers may consist of 3-20 solid or hollow blades made of carbon fibre, metal or other composite material, with a length of 10-10000 mm, a width of 2-1000 mm and a thickness of 0.2-50 mm. The paddle is driven by an electric motor or an internal combustion engine and is used for providing lift force during taking off, landing and flying. The grille integrated with the upper part and the lower part of the propeller or the upper part and the lower part of the propeller for controlling the airflow is made of 3-20 carbon fiber, metal or other composite materials with the length of 10-10000 mm, the width of 2-1000 mm and the thickness of 0.2-50 mm, and the opening and closing of the grille are controlled by a pull rod connected to the grille so as to control the size and the direction of the inlet and outlet airflow. The grille can be divided into a plurality of parts, and the plurality of parts can be independently controlled to open and close, so that the size and the direction of airflow can be adjusted, and the power of each part of the airplane body can be adjusted to further keep the airplane body stable or adjust the flying attitude.

The horizontal direction power module consists of two large-size propellers and a grid integrated with the upper part and the lower part of the propellers or the upper part and the lower part of the propellers for controlling airflow. The propeller can be driven by an electric motor or an internal combustion engine, and can provide horizontal power for the aircraft and adjust the flight attitude.

The propellers and the grille are controlled by the control platform. The control platform is manual or automatic, and can control a power system and a grid in the horizontal and vertical directions in a mechanical or current mode so as to control the takeoff, landing, flying speed and flying attitude of the aircraft.

The signal module can transmit and receive signals to learn about air traffic, weather conditions and can transmit location or distress signals as well as auto cruise signals.

The power module consisting of batteries or internal combustion engines provides power to the vertical direction power module and the horizontal direction power module through conventional systems or circuits. When the power of the aircraft is battery power, the vertical and horizontal propellers and the grid are achieved by the battery through a circuit control motor. When the aircraft uses an internal combustion engine, the vertical and horizontal propellers can be driven either directly by the internal combustion engine or by a central internal combustion engine via a conventional system. The grid can be controlled by a battery via a line-controlled motor.

For short distance flight or in small spaces, the aircraft may be provided with lift during flight by vertically oriented propellers. Because the vertical propeller consumes a large amount of energy, when flying for a long distance, the foldable wing can provide lift force for the aircraft so as to achieve the purpose of saving fuel and realizing long-distance flight. The foldable wing is made of carbon fiber, metal or other composite materials, is 10-10000 mm long, 5-2000 mm wide and 0.2-200 mm thick, and can be folded or unfolded freely through an electric motor.

In the flight process, if the battery is short-circuited, the emergency module provides safety guarantee for passengers or cargoes under the condition that the internal combustion engine is flamed out or other faults occur. The emergency module consists of an automatic or manual control parachute and a personnel and material protection air bag. Under the dangerous condition, the safety landing can be realized by manually controlling the ejection or automatically ejecting through the button.

In addition to the above modules, the aircraft may also be provided with headlights or direction signal lights, fog lights and velocimeters, to the front and to the rear. In addition, the aircraft may have a collapsible support structure with solid or pneumatic tires and landing gear or may have no tires and use the landing gear structure directly as a support.

The invention can be implemented by other embodiments having the necessary technical features. Accordingly, the above-disclosed embodiments are illustrative, but not exclusive. All changes which come within the scope of the invention or the range of equivalents thereto are intended to be embraced therein.