Novel tilt-rotor unmanned aerial vehicle attitude control system

A tilt rotor and control system technology, applied in attitude control and other directions, can solve the problems of low speed and poor endurance, and achieve the effect of simple manufacture, controllable cost and guaranteed competitiveness

Inactive Publication Date: 2015-12-30
NORTHWEST A & F UNIV
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Problems solved by technology

[0006] The purpose of the present invention is to solve the problems of the above-mentioned prior art, to provide a novel tilt-rotor unmanned aerial vehicle attitude control system, the use of this system combines the high speed of fixed-wing aircraft, long range and multi-rotor unmanned aerial vehicles ( Helicopter) has the advantage

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  • Novel tilt-rotor unmanned aerial vehicle attitude control system
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  • Novel tilt-rotor unmanned aerial vehicle attitude control system

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[0028] The present invention will be further explained below in conjunction with the drawings.

[0029] Such as figure 1 As shown, in order to achieve full control of the UAV, the roll angle, pitch angle, heading angle and altitude of the UAV must be controlled. The specific method is: using a single-degree-of-freedom tilter that rotates along the pitch axis to rotate in the same direction and at the same angle to achieve the control of the UAV's pitch angle; using the tilter to rotate in the opposite direction at the same angle to achieve the control of the UAV's heading angle; The speed difference of the side rotors realizes the control of the UAV's roll angle; the rotation speed of the two sides of the rotor is increased or decreased by the same amount to realize the height control of the UAV. The above four control channels are independent of each other. Each control channel compares the actual posture calculated by the gyroscope and sensor with the expected posture given by ...

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Abstract

The invention discloses a novel tilt-rotor unmanned aerial vehicle attitude control system. The system comprises two parts of a hardware circuit and control software, wherein the hardware circuit comprises a main control chip, a gyroscope, a sensor, a remote controller, a heading attitude control mechanism and a tilt-rotor execution mechanism, the main control chip captures an instruction of the remote controller through wireless transmission, an expected attitude of the remote controlled instruction is compared with a real-time attitude monitored by the gyroscope, a compared result serves as controlled input quantity, and a corresponding control command is output after the input quantity is operated and processed by the main control chip. By means of close integration of software and hardware, an unmanned aerial vehicle can detects real-time attitudes of the vehicle and controls movement of the heading attitude control mechanism and the tilt-rotor execution mechanism according to the remote controller instruction, and the aircraft mode can be freely switched between a fixed wing aircraft and a rotorcraft. According to the novel tilt-rotor unmanned aerial vehicle attitude control system, great practical significance is achieved for development of tilt-rotor unmanned aerial vehicles, and high reference value is achieved for development of manned tilt rotorcrafts.

Description

technical field [0001] The invention relates to the field of novel unmanned aerial vehicles, in particular to a novel attitude control system for tilt-rotor unmanned aerial vehicles. Background technique [0002] In recent years, a new type of flying tool - multi-rotor aircraft has received extensive attention and rapid development in the field of science and technology. The multi-rotor aircraft can realize vertical take-off and landing, fixed-point hovering, forward and backward, rotation, side flight and other flight actions. As a flight carrier, it can carry imaging equipment, communication equipment, acquisition equipment, special equipment, etc. into the air, and can realize the operational needs that are difficult for aviation aircraft and remote-controlled aircraft to meet. Although multi-rotor aircraft are widely used in production and life and have achieved good results, factors such as too small load, low speed, and poor endurance of multi-rotor aircraft restrict ...

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Application Information

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IPC IPC(8): G05D1/08
Inventor 杨福增秦昊李长骏
Owner NORTHWEST A & F UNIV
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