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A rotary retractable variable torque quadrotor aircraft

A rotorcraft and variable torque technology, applied in the direction of aircraft, rotorcraft, propellers, etc., can solve the problems of unstable flight capability, weakened aircraft attitude control ability, small aircraft load, etc., to achieve convenient storage and transportation, and operational performance Improve, improve the effect of the payload

Active Publication Date: 2018-10-19
WUHAN UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0002] The four-rotor aircraft connects the front, rear and left and right groups of four rotors through the support arm. The direction of rotation of each group of rotors is the same, and the two groups of rotors are respectively forward and reverse rotors. The body is balanced, and the lift is changed by changing the rotor speed, thereby changing the attitude and position of the quadrotor helicopter. The support arm of the common quadrotor aircraft is fixed with the body, resulting in a large geometric size and inconvenient storage and transportation. And other issues
This kind of flight control principle is inefficient, the load of the aircraft is small, and the flight capability is unstable. Especially during the landing process of the aircraft, the rotor speed must be reduced to reduce the lift of the rotor. The reduction of lift means that the ability to control the attitude of the aircraft is weakened. , the flight stability of the aircraft is reduced or even out of control

Method used

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  • A rotary retractable variable torque quadrotor aircraft
  • A rotary retractable variable torque quadrotor aircraft
  • A rotary retractable variable torque quadrotor aircraft

Examples

Experimental program
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Effect test

Embodiment 1

[0019] control Figure 1-8 The implementation process of the present invention is described.

[0020] Rotary variable moment quadrotor aircraft ( figure 1 ), comprising: a fuselage, connected with the fuselage, 4 rotor arms symmetrically distributed, and rotors positioned on the rotor arms, among the 4 rotors, the rotation directions of two adjacent rotors are opposite; the blades of each rotor 21 through the variable torque mechanism ( figure 2 ), using a space link mechanism and a cam mechanism, so that the rotor can be controlled by the steering gear to shrink, adjust the movement and the distance from the body, and then change the torque to achieve the purpose of adjusting the lift, and realize the adjustment function of the attitude of the aircraft.

[0021] Described rotor is driven by motor 20, and the rotational speed of each motor keeps consistent. This mechanism comprises: 4 motors 20 controlled by the inertial navigator, the fourth connecting rod 19, the third c...

Embodiment 2

[0031] The hardware is as follows:

[0032] The stm32F103T8 control chip with a main frequency of 72MHz is used.

[0033] The MPU6050 with a three-axis gyroscope and a three-axis acceleration sensor is used.

[0034] The integrated Bluetooth communication system can realize the communication between the quadrotor and the computer / mobile phone.

[0035] The integrated lithium battery charging system can be directly charged using the micro-USB interface.

[0036] Reserve the installation position of the electromagnetic sensor HMC5883L chip, which is convenient for users to expand.

[0037] I2C interface is reserved for expanding modules such as electromagnetic sensor HMC5883L and altimeter BMP085.

[0038] Reserved SPI interface for expanding 2.4G NRF24L01+ wireless communication module

[0039] Flight control process:

[0040] The system structure is based on stm32F103T8 as the main flight controller to control the system. The microcontroller implements sampling, processi...

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PUM

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Abstract

The invention relates to a torque variable aircraft and further relates to a rotary contract type torque variable four-rotor aircraft. The rotary contract type torque variable four-rotor aircraft comprises a fuselage, four rotor arms connected with the fuselage and evenly distributed and four rotors located on the rotor arms, and every two neighboring rotors rotate in opposite directions. Distance between the paddle of each rotor and the fuselage can be adjusted through motion of a torque variable mechanism, lift force is adjustable, and posture of the aircraft can be adjusted.

Description

technical field [0001] The present invention relates to a variable moment rotor aircraft, and further relates to a rotating retractable variable moment rotor aircraft. Background technique [0002] The four-rotor aircraft connects the front, rear and left and right groups of four rotors through the support arm. The direction of rotation of each group of rotors is the same, and the two groups of rotors are respectively forward and reverse rotors. The body is balanced, and the lift is changed by changing the rotor speed, thereby changing the attitude and position of the quadrotor helicopter. The support arm of the common quadrotor aircraft is fixed with the body, resulting in a large geometric size and inconvenient storage and transportation. And other issues. [0003] The power plant of the quadrotor aircraft is composed of propellers and four independent motors. The opposite direction on the aircraft is a pair of identical propellers and the adjacent rotors rotate in opposi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C27/08B64C11/32B64C1/30
CPCB64C1/30B64C11/32B64C27/08
Inventor 雷斌孙璟左继洲陈满意徐鹏成易文周亮陈浩蒋林
Owner WUHAN UNIV OF SCI & TECH
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