CN111232192A

CN111232192A - Double-rotor aircraft

Info

Publication number: CN111232192A
Application number: CN201811445348.6A
Authority: CN
Inventors: 戴瑾
Original assignee: Individual
Current assignee: Individual
Priority date: 2018-11-29
Filing date: 2018-11-29
Publication date: 2020-06-05

Abstract

The invention discloses a double-rotor aircraft which comprises an aircraft body, a left engine, a right engine, a left rotor and a right rotor, wherein the left engine and the right engine are fixedly connected to the left side and the right side of the aircraft body, the left rotor is fixedly connected to a rotating shaft of the left engine, the right rotor is fixedly connected to a rotating shaft of the right engine, the left rudder and the right rudder are further arranged on the left side and the right side of the aircraft body, and the left rudder and the right rudder are respectively arranged below the left rotor and the right rotor. The invention has the advantages of higher pneumatic efficiency, less power consumption, longer flight time, simpler structure and easy realization of automatic and intelligent control.

Description

Double-rotor aircraft

Technical Field

The invention relates to a double-rotor aircraft, in particular to a double-rotor aircraft which is suitable for automatic control and is applied to aerial photography equipment.

Background

The rotor structure of the aircraft comprises a single rotor, a coaxial double rotor, a four rotor and the like. The helicopter is a typical single-rotor or coaxial dual-rotor aircraft, and if the flight attitude is to be controlled, the rotor must be capable of rotating while adjusting the rotating plane, so the aircraft adopting the structure has the disadvantages that: the design of the axle center part of the rotor wing is complex, and the weight and the cost of the machine body are increased.

An unmanned aerial vehicle for taking photo by plane requires automatic and intelligent control, requires a simpler mechanical structure, and generally adopts a four-rotor structure at present.

The four-rotor aircraft, also known as the quadcopter, only need increase or reduce the rotational speed of four rotors, just can realize tilting of arbitrary angle, and a pair of rotors on the diagonal of general design has the same direction of rotation, and the direction of rotation of two pairs of rotors is opposite, adjusts the rotational speed of two pairs of rotors, can also realize turning to.

For an aircraft given size constraints, the more rotors, the smaller the actual available rotor disk area, and the efficiency of generating lift decreases as the rotor disk area decreases, so the problem with current quad-rotor aircraft is that: the flying efficiency is not high, the electricity consumption is relatively high, and the flying time is short.

Disclosure of Invention

The invention aims to provide a novel dual-rotor aircraft which is low in power consumption, long in flight time, simple in structure and capable of being intelligently controlled.

The technical scheme adopted by the invention for solving the technical problem is to provide a dual-rotor aircraft, which comprises an aircraft body, a left engine, a right engine, a left rotor and a right rotor, wherein the left engine and the right engine are fixedly connected to the left side and the right side of the aircraft body, a rotating shaft of the left engine is fixedly connected with the left rotor, a rotating shaft of the right engine is fixedly connected with the right rotor, the left side and the right side of the aircraft body are also provided with a left rudder and a right rudder, and the left rudder and the right rudder are respectively arranged below the left rotor and the right rotor.

Preferably, the left rotor and the right rotor can be driven by a left engine and a right engine respectively to rotate, and the rotation directions of the left rotor and the right rotor are opposite.

Preferably, the left rotor and the right rotor have equal number of blades and same diameter.

Preferably, the rotation centers of the left rotor and the right rotor are respectively positioned on the same axis with the rotation centers of the left engine rotating shaft and the right engine rotating shaft.

Preferably, the connecting line of the rotating shafts of the left rudder and the right rudder and the left wing shaft and the right wing shaft is parallel, that is, the rotating direction of the left rudder and the right rudder is perpendicular to the connecting line of the left wing shaft and the right wing shaft.

Preferably, the left rudder and the right rudder are respectively provided with a steering engine, and the left rudder and the right rudder can rotate in the same direction or in opposite directions under the control of the steering engines.

Preferably, the machine body is also fixedly connected with a battery, a camera, a control circuit, a sensor, a communication circuit and a remote control circuit.

Preferably, the motor is an electric motor.

The invention has the following beneficial effects:

compared with the traditional four-rotor aircraft, the four-rotor aircraft has the advantages that the rotor is reduced, the area of the actually available rotor disk is increased, the structure is simpler, the aerodynamic efficiency is higher, the power consumption is less, the flight time is longer, and the automatic and intelligent control is easy to realize.

Drawings

FIG. 1 is a schematic structural view of a dual rotor aircraft in an embodiment of the present invention;

fig. 2 is a bottom view of a schematic structural view of a dual rotor aircraft in an embodiment of the invention.

Detailed Description

The following detailed description of specific embodiments of the invention refers to the accompanying drawings.

Referring to fig. 1 and 2, the invention discloses a dual-rotor aircraft, which comprises an aircraft body 1, a left engine 2, a right engine 3, a left rotor 4, a right rotor 5, a left rudder 6 and a right rudder 7, wherein the left engine 2 and the right engine 3 are fixedly connected to the left side and the right side of the aircraft body 1, the left rotor 4 is fixedly connected to a rotating shaft of the left engine 2, the right rotor 5 is fixedly connected to a rotating shaft of the right engine 3, the left rudder 6 and the right rudder 7 are further arranged on the left side and the right side of the aircraft body 1, and the left rudder 6 and the right rudder 7 are respectively arranged below the left rotor 4 and the right rotor 5.

The power of the aircraft is provided by a left engine 2 and a right engine 3. The left engine 2 and the right engine 3 are in the form of motors and drive the left rotor wing 4 and the right rotor wing 5 to rotate in opposite directions; the blades of the left rotor wing 4 and the right rotor wing 5 are equal in number and same in diameter, and the rotating centers of the left rotor wing 4 and the right rotor wing 5 are located on the same axis with the rotating centers of the rotating shafts of the left engine 2 and the left engine 3 respectively.

The attitude control of the aircraft is realized by the deflection of the left rudder 6 and the right rudder 7, the left rudder 6 and the right rudder 7 are arranged below the

rotary wings

4 and 5, and when the control surface deflects, the control of the airframe 1 is realized by utilizing the airflow generated by the rotary wings and generating the moment. The connecting lines of the rotating shafts of the left rudder 6 and the right rudder 7 and the shafts of the

rotors

4 and 5 are parallel, namely the rotating directions of the left rudder 6 and the right rudder 7 are vertical to the connecting lines of the shafts of the

rotors

4 and 5; said

rudders

6, 7 must be kept at a distance from the

rotors

4, 5, approximately equal to the diameter of the rotor disc, in order to generate a sufficient tilting moment; the left rudder 6 and the right rudder 7 are respectively provided with a steering engine, the steering engines can control the left rudder 6 and the right rudder 7 to rotate in the same direction or in the opposite direction, the machine body 1 tilts when rotating in the same direction, and the machine body 1 can turn when rotating in the opposite direction.

Still fixedly connected with battery, camera, control circuit and sensor on the organism 1 to and communication and remote control circuit for realize the automatic intelligent control of aircraft and the realization of the function of taking photo by plane.

Although the present invention has been described with respect to the preferred embodiments, it will be understood by those skilled in the art that various changes in form and details may be made therein without departing from the spirit and scope of the invention as defined by the appended claims.

Claims

1. The utility model provides a dual rotor aircraft, includes organism, left engine, right engine, left rotor, dextrorotation wing, left engine and right engine fixed connection be in the left and right sides of organism, fixedly connected with left rotor in the pivot of left engine, fixedly connected with right rotor in the pivot of right engine, its characterized in that, the left and right sides of organism still is provided with left rudder and right rudder, left rudder and right rudder set up respectively in the below of left rotor and dextrorotation wing.

2. A twin rotor aircraft as defined in claim 1 in which the left and right rotors are driven to rotate by left and right motors respectively, the left and right rotors rotating in opposite directions.

3. A twin rotor aircraft according to claim 1, wherein the left and right rotors have equal numbers of blades and the same diameter.

4. A twin rotor aircraft according to claim 1, wherein the centre of rotation of the left and right rotors are co-axial with the centre of rotation of the left and right engine shafts respectively.

5. A twin rotor aircraft as defined in claim 1 wherein the axes of rotation of the left and right rudders are parallel to the line joining the left and right wing axes, i.e. the direction of rotation of the left and right rudders is perpendicular to the line joining the left and right wing axes.

6. A twin rotor aircraft as defined in claim 1 wherein the left and right rudders are each provided with a steering engine, and the left and right rudders can rotate in the same direction or in opposite directions under the control of the steering engines.

7. A twin rotor aircraft as defined in claim 1, wherein the body further has fixedly attached thereto a battery, a camera, control circuitry and sensors, and communication and remote control circuitry.

8. A twin rotor aircraft as defined in claim 1, wherein said engines are electric motors.