阅读说明：本技术 侧倾纵列双桨电动直升机 (Side-tipping longitudinal-row double-propeller electric helicopter ) 是由 罗灿 于 2020-06-11 设计创作，主要内容包括：本发明侧倾纵列双桨电动直升机,包括机身、两副旋翼、两个倾转机构、推进桨、电动机和操控系统等。两副旋翼的转动方向相反,旋翼通过调节旋翼转速来调节旋翼拉力,设置铰支座,每副旋翼可以被控制围绕着铰支座轴线向左侧及向右侧倾转,倾转受倾转机构控制；推进桨通过调节正转反转转速来调节推进力；电动机为旋翼和推进桨提供动力；操控系统操控五套电机的转速,五套电机即前顶桨旋翼电动机、前顶桨旋翼倾转机构伺服电机、后顶桨旋翼电动机、后顶桨旋翼倾转机构伺服电机和推进桨电动机。(The invention relates to a side-tipping longitudinal double-propeller electric helicopter which comprises a helicopter body, two pairs of rotor wings, two tilting mechanisms, a propelling propeller, a motor, an operation system and the like. The rotating directions of the two pairs of rotors are opposite, the rotors adjust the pulling force of the rotors by adjusting the rotating speed of the rotors, the hinged support is arranged, each pair of rotors can be controlled to tilt to the left side and the right side around the axis of the hinged support, and the tilting is controlled by the tilting mechanism; the propulsion paddle adjusts the propulsion force by adjusting the forward rotation speed and the reverse rotation speed; the motor provides power for the rotor wing and the propelling paddle; the control system controls the rotating speed of five sets of motors, namely a front top propeller rotor motor, a front top propeller rotor tilting mechanism servo motor, a rear top propeller rotor tilting mechanism servo motor and a propulsion propeller motor.)

1. Electronic helicopter of tandem double-oar heels, including fuselage, two pairs of rotors, two mechanisms of verting, propulsion oar, motor and control system etc. its characterized in that: the body bears all devices, mechanisms and equipment of the electric helicopter; the two pairs of rotors are arranged in the fuselage in tandem along the longitudinal axis of the fuselage, the rotors comprise rotor shafts, blades and hinged supports, the rotating directions of the two pairs of rotors are opposite, the distance between the two rotor shafts is greater than the radius of the rotors, the rotors adjust the tension of the rotors by adjusting the rotating speed of the rotors, the hinged supports are arranged, the fixed parts of the hinged supports are connected with the fuselage, the rotating parts of the hinged supports are connected with a bearing of the rotor shafts, the rotating axes of the hinged supports are parallel to the longitudinal axis of the fuselage, each pair of rotors can be controlled to tilt to the left side and the right side around the axis of the hinged supports, and the tilting is controlled by a tilting mechanism; the two tilting mechanisms are mechanisms for respectively controlling the two pairs of rotors to tilt, are electric control mechanisms and comprise a base, a servo motor and a moving part, the base is connected with the aircraft body, the moving part is connected with a part to be controlled to tilt, the servo motor is controlled by an operation system, and energy comes from a power supply; the propelling propeller is a propeller which generates forward and backward propelling force to the machine body and comprises a propelling propeller shaft, blades and the like, the propelling propeller adjusts the propelling force by adjusting the forward and reverse rotating speeds, the propelling propeller is arranged at the head part of the machine body or the tail part of the machine body, and the axis of the propelling propeller shaft is parallel to the longitudinal axis of the machine body; the motor provides power for the rotor wing and the propelling paddle, the front rotor wing and the rear rotor wing are respectively provided with the motor, the output shafts of the motors are respectively connected with the rotor wing shafts of the motors and tilt together with the rotor wing shafts of the motors, the motors capable of rotating forwards, stopping and rotating backwards are arranged, the output shafts of the motors are connected with the propelling paddle shafts, the motors are controlled by the control system, and energy comes from a power supply; the control system controls five sets of motors to adjust the rotating speed of the five sets of motors, namely a front top propeller rotor motor, a front top propeller rotor tilting mechanism servo motor, a rear top propeller rotor tilting mechanism servo motor and a propulsion propeller motor.

Technical Field

The invention relates to an electric helicopter, in particular to an electric helicopter which is provided with two pairs of rotors in sequence along the longitudinal axis of a helicopter body, wherein each pair of rotors can tilt towards the left side and the right side and is provided with a propulsion paddle.

Background

The traditional electric helicopter is a four-rotor helicopter, a control system controls the rotating speed of four rotors, the horizontal flight resistance is large, the flight efficiency is low, the flight speed is low, and the crosswind resistance performance is poor. In order to reduce the horizontal flight resistance of the helicopter, improve the flight efficiency, improve the flight speed and improve the crosswind resistance. The invention provides an electric helicopter structure, wherein two pairs of rotor wings are sequentially arranged along the longitudinal axis of a helicopter body, each pair of rotor wings can tilt towards the left side and the right side, the tilting is controlled by a tilting mechanism, and a propelling paddle is arranged.

Disclosure of Invention

The invention relates to a side-tipping longitudinal double-propeller electric helicopter which comprises a helicopter body, two pairs of rotor wings, two tilting mechanisms, a propelling propeller, a motor, an operation system and the like.

The helicopter body is a mechanical structure for bearing all devices, mechanisms and equipment of the electric helicopter and adopts a mature technology. The fuselage is generally longitudinally long cylindrical streamline.

The two pairs of rotors are arranged in the fuselage in tandem along the longitudinal axis of the fuselage. The rotor comprises a rotor shaft, a blade and a hinged support, and the rotor adopts mature technology. The rotation directions of the two pairs of rotors are opposite. The distance between the two rotor shafts is greater than the rotor radius. The rotor adjusts the rotor pulling force through adjusting the rotor rotational speed, adjusts and adopts ripe technique. A hinged support is arranged, the fixed part of the hinged support is connected with the machine body, the rotating part of the hinged support is connected with the rotor shaft bearing, and the rotating axis of the hinged support is parallel to the longitudinal axis of the machine body. Each rotor can be controlled to tilt to the left and right around the hinge support axis. The tilting is controlled by a tilting mechanism.

Two mechanisms that vert control two pairs of rotors respectively and vert, are electric control mechanism, including base, servo motor and motion, all adopt mature technique. The base is connected with the machine body, the moving part is connected with the part to be controlled to incline, the servo motor is controlled by the control system, and energy comes from the power supply.

The propeller is a propeller which can generate forward and backward propelling force to the airframe, comprises a propeller shaft, blades and the like, and adopts a mature technology. The propulsion paddle adjusts the propulsion force by adjusting the forward rotation speed and the reverse rotation speed, and the adjustment adopts a mature technology. The propulsion paddle is arranged at the head of the machine body or the tail of the machine body. The propeller shaft axis is parallel to the longitudinal axis of the fuselage.

The motor provides power for the rotor wing and the propelling paddle and adopts a mature technology. The front rotor and the rear rotor are respectively provided with an electric motor, and the output shafts of the electric motors are respectively connected with the rotor shafts of the electric motors. A motor capable of rotating forwards, stopping and rotating reversely is arranged, and an output shaft of the motor is connected with the propeller shaft. The motor is controlled by the control system, and energy comes from the power supply.

The control system adopts a mature technology to control five sets of motors and adjust the rotating speed of the five sets of motors, wherein the five sets of motors are a front jacking propeller rotor motor, a front jacking propeller rotor tilting mechanism servo motor, a rear jacking propeller rotor tilting mechanism servo motor and a propulsion propeller motor.

The connection is a well-established technique in which the rotational speeds of objects to be connected are equalized by a connection machine, for example, by cementing, bolting, riveting, mechanical engagement, coupling, or the like. The rotor and the propulsion propeller are respectively provided with a propeller, a duct type propeller and the like, and are mature technologies.

The flight action of the electric helicopter of the invention is as follows: when the propulsion oar does not rotate, the effect is equal to that the propulsion oar is not arranged, and the electric helicopter can realize various flight actions except high-speed flight by controlling the two pairs of rotors. When the two pairs of rotors do not tilt and the tension of the rotors is synchronously adjusted, the electric helicopter is lifted. When the two pairs of rotors do not tilt and the tension of the rotors is asynchronously adjusted, the helicopter pitches, and the electric helicopter can horizontally fly forwards and backwards on the basis of pitching action. When two pairs of rotors synchronously adjust and increase the rotor pulling force and incline to different directions respectively, the electric helicopter turns to. When the two rotors synchronously adjust the tension of the rotors and tilt in the same direction, the electric helicopter rolls, and can horizontally fly leftwards and rightwards on the basis of the rolling action. When the propelling propeller rotates, the two pairs of rotors do not tilt, forward blades of the two pairs of rotors respectively provide lift force for the electric helicopter to form rolling torque which is mutually offset and balanced, and the electric helicopter horizontally flies at high speed forwards and backwards under the pushing of the propelling propeller. Various actions may be superimposed. The above-mentioned flight action is based on the premise that two pairs of rotors are both located above the fuselage, and the flight action may be different when two pairs of rotors are not both located above the fuselage.

The invention discloses a side-tipping longitudinal double-propeller electric helicopter, which has the advantages that: the aircraft is provided with two pairs of rotors longitudinally arranged along the aircraft body, the rotors can tilt towards the left side and the right side, and the tilting is controlled by a tilting mechanism. Because the rotor wing tensile horizontal component is very big when verting, and electronic helicopter steering torque is very big, and electronic helicopter turns to soon, and the fuselage front portion can point to crosswind fast and come to the direction, and anti crosswind performance is good. The electric helicopter has small resistance in longitudinal flight, high flight efficiency and high flight speed compared with a four-rotor electric helicopter in horizontal flight. The electric helicopter can fly at high speed in a rolling torque balance manner by arranging the propelling propeller.

Drawings

FIG. 1 is a schematic view of example 1 of the present invention. In the figure, 1 is a fuselage, 2 is a rotor shaft of a front rotor, 3 is a rotor shaft of a rear rotor, and 4 is a propulsion paddle.

Fig. 2 is a schematic tilting view of a rotor according to the invention, wherein 1 is a longitudinal axis in the fuselage, 2 is an electric motor, 3 is a hinged support, and 4 is a rotor shaft.

The components in the drawings are only schematic in relation to each other, and do not reflect actual shapes and dimensions.

Detailed Description