Motor vector control method and device and aircraft
A technology of vector control and control mode, which is applied in the direction of vector control system, motor generator control, AC motor control, etc., can solve problems such as out-of-control fuselage and severe vibration, and achieve the solution of out-of-control and severe vibration of the fuselage and reduce vibration and noise, reducing the effect of torque ripple
Active Publication Date: 2018-02-02
GUANGZHOU XAIRCRAFT TECH CO LTD
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Problems solved by technology
[0008] For this reason, the first object of the present invention is to propose a kind of electric motor vector control method, this method adopts the mode of direct voltage given to carry out maximum torque control to electric motor, not only can reduce the torque ripple that adopts square wave control to produce, Reduce vibration and noise, and solve the problems of loss of control and severe vibration of the fuselage caused by the speed closed-loop control
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[0061] Embodiments of the present invention are described in detail below, examples of which are shown in the drawings, wherein the same or similar reference numerals designate the same or similar elements or elements having the same or similar functions throughout. The embodiments described below by referring to the figures are exemplary and are intended to explain the present invention and should not be construed as limiting the present invention.
[0062] The motor vector control method, device and aircraft proposed by the embodiments of the present invention are described below with reference to the accompanying drawings.
[0063] figure 1 is a flowchart of a motor vector control method according to an embodiment of the present invention. Such as figure 1 As shown, the motor vector control method includes the following steps:
[0064] S1, receiving a pulse position modulated PPM signal.
[0065] Specifically, in an aircraft application, the flight controller may output...
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The invention discloses a motor vector control method and device and an aircraft. The method comprises the following steps: receiving a pulse position modulation PPM signal; acquiring the first givenvoltage signal of a motor according to the PPM signal; acquiring the d-axis voltage of the motor by adopting the control mode that the d-axis given current is 0; computing q-axis voltage of the motorat the next moment according to the first given voltage signal and the d-axis voltage of the motor, and carrying out vector control on the motor according to the d-axis voltage of the motor and the q-axis voltage of the motor at the next moment. According to the method, maximum torque control is carried out on the motor by adopting a direct voltage given manner, and the torque ripple generated byadopting square wave control can be reduced, so that the vibration and noise are reduced, and the problems of out-of-control and violent airframe shaking caused when speed closed-loop control is adopted are solved.
Description
technical field [0001] The invention relates to the technical field of motor control, in particular to a motor vector control method, device and aircraft. Background technique [0002] Most of the existing motors used in drones are three-phase brushless DC motors, which are controlled by electronic governors. [0003] At present, a six-beat square wave speed controller is mostly used in the market to control the motor, that is, the input pulse width signal is converted into a duty cycle of a PWM (Pulse Width Modulation, pulse width modulation) signal to regulate the speed of the motor. However, since there are only six commutations in one electrical angle cycle, and the current waveform is a square wave, a large torque pulsation will be generated, which will cause the vibration of the propeller of the aircraft (such as a UAV), thereby affecting the overall stability of the aircraft. Sexuality has a certain impact, and it will generate a lot of noise. [0004] In addition, ...
Claims
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Login to View More IPC IPC(8): H02P21/00H02P21/05
CPCH02P21/0021H02P21/05H02P21/00H02P21/22H02P21/0003H02P21/14H02P27/08H02P21/18B64D31/00
Inventor 于江涛
Owner GUANGZHOU XAIRCRAFT TECH CO LTD