Control system and method for oil-drive variable-pitch multi-rotor aircraft

A technology for a multi-rotor aircraft and a control system, which is applied to the control system and control field of an oil-dynamic variable-pitch multi-rotor aircraft, and can solve the problems of unstable output power, drastic changes in rotational speed, and inability of the pitch system to achieve control effects.

Inactive Publication Date: 2017-11-07
XIAN TANVEN INTELLIGENT TECH CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

In the existing pitch control system, the output torque of the engine is increased or decreased by changing the pitch, resulting in unstable output power and drastic changes in speed, which will make the pitch control system unable to achieve the desired control when operating Effect

Method used

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  • Control system and method for oil-drive variable-pitch multi-rotor aircraft
  • Control system and method for oil-drive variable-pitch multi-rotor aircraft
  • Control system and method for oil-drive variable-pitch multi-rotor aircraft

Examples

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Embodiment Construction

[0078] The present invention will be further described below in conjunction with the accompanying drawings.

[0079] The structure of the control system of the oil-operated variable-pitch multi-rotor aircraft:

[0080] according to figure 1 As shown, M0 is the engine, including the electric motor and the fuel engine, responsible for providing the power to drive the whole machine. The fuel mixing amount of the fuel engine is controlled by the carburetor or the electronic injection system, and its power output is controlled by the damper or the throttle.

[0081] M1, M2, M3, and M4 are an even number of rotors (the number of rotors in this example is four), which provide lift to maintain height and traction (component force) required for speed and position changes, and are generated by pitch changes and rotational speed changes The different lift forces provide the moment required for attitude change.

[0082] M0 outputs the power to each shaft through the transmission system...

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Abstract

The invention discloses a control system and method for an oil-drive variable-pitch multi-rotor aircraft. The aircraft employs an oil-drive motor to drive a plurality of propellers, and the propellers have the same rotating speed. The aerodynamic force and aerodynamic moment of the aircraft are changed through the changing of the pitch of each propeller, thereby achieving the posture and position control. Compared with a conventional multi-rotor aircraft, the aircraft is long in endurance, is large in carrying capacity, is low in fault rate, is good in maneuvering performances, and is smaller in mass. The control method solves a problem of cooperation of pitch control and the control of the rotating speed of an engine, greatly improves the sensitivity of oil-drive multi-rotor power output, solves a problem, caused by the time delay of the engine, of the control of the whole aircraft, and enables the maneuverability and control accuracy of the oil-drive variable-pitch multi-rotor aircraft to be guaranteed.

Description

【Technical field】 [0001] The invention relates to the field of aircraft control, in particular to a control system and a control method for an oil-driven variable-pitch multi-rotor aircraft. 【Background technique】 [0002] Most of the existing multi-rotor aircraft are driven by electric motors. The motor configuration is one electric motor for one propeller. The pitch of the propeller is fixed. The attitude control and position control of the aircraft are changed by changing the speed of each motor. Due to the limitation of battery energy density, the electric multi-rotor aircraft has the disadvantages of short flight time and low load. [0003] There are few existing oil-powered multi-rotor aircraft, and the motor configuration, attitude, and position control principles of the few oil-operated multi-rotor aircraft are the same as those of electric multi-rotor aircraft, that is, one propeller is equipped with an oil-driven motor, and the paddle of the propeller The distance...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G05D1/08G05D1/10
CPCG05D1/0808G05D1/101
Inventor 程靖吕京兆左盘飞刘喜龙王新升
Owner XIAN TANVEN INTELLIGENT TECH CO LTD
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