Low-speed-section position-sensorless control method of permanent magnet fault-tolerant motor system based on envelope detection and non-orthogonal phase-locked loop
A technology of permanent magnet fault tolerance and control method, which is applied in the direction of single motor speed/torque control, motor control, high-speed motor control, etc., and can solve the problems of unable to realize permanent magnet fault tolerant motor without position sensor control, difficult coordinate transformation, etc.
Active Publication Date: 2020-06-23
BEIHANG UNIV
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Problems solved by technology
However, when the permanent magnet fault-tolerant motor is in fault operation, the remaining non-fault phase windings are in an asymmetrical operating state, and it is difficult to perform coordinate transformation. Therefore, the traditional high-frequency injection method cannot realize the position sensorless control of the permanent magnet fault-tolerant motor in fault operation.
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[0068] Attached below Figure 1-6 A specific embodiment of the technical solution of the present invention is described in detail.
[0069] figure 1 Shown is a block diagram of a permanent magnet fault-tolerant motor high-reliability drive controller for an airborne electric actuator provided by the present invention, including a floating-point high-speed DSP system, a large-scale programmable logic gate array FPGA system, an isolated drive circuit, A fault-tolerant power drive circuit and a signal detection circuit. Described DSP system adopts floating-point type high-speed DSPTMS320F28335, main frequency 150MHz, has single-precision floating-point number processing unit; Described FPGA system is made up of FPGA chip and peripheral circuit thereof, and wherein FPGA chip selects Cyclone II series FPGA EP2C35F484 of U.S. ALTERA Company, The main frequency is up to 100MHz, with 33216 logic units, 35 multipliers, and 322 configurable I / O pins. The MOSFET device in the fault-to...
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The invention discloses a low-speed-section position-sensorless control method of a permanent magnet fault-tolerant motor system based on envelope detection and a non-orthogonal phase-locked loop. A high-frequency voltage signal is injected into any non-fault two-phase winding of the motor, a digital band-pass filter is used for extracting high-frequency response current of a high-frequency injection phase, differential mode inductance of a two-phase winding is calculated through envelope detection and signal processing, rotor position and rotating speed signals in estimated inductance are extracted through a non-orthogonal phase-locked loop, and then sensorless control over the motor is achieved. According to the control method, sensorless control during normal and fault operation of thepermanent magnet fault-tolerant motor can be realized, and the precision and reliability of motor position / speed detection are improved; and the reliability and the fault-tolerant operation performance of the permanent magnet fault-tolerant motor system are remarkably improved. And the controller is small in size, high in precision and high in reliability, and can effectively meet the performancerequirements of the airborne electric actuator.
Description
technical field [0001] The invention belongs to the technical field of permanent magnet fault-tolerant motor drive control, and in particular relates to a low-speed position sensorless control method based on envelope detection and non-orthogonal phase-locked loop for a permanent magnet fault-tolerant motor system for a highly reliable airborne electric actuator. Background technique [0002] As the electrification of airborne equipment continues to increase, multi-electric / all-electric aircraft will gradually become the main development direction of future aircraft due to their significant technical advantages. The typical feature of multi-electric / all-electric aircraft is to replace the hydraulic and pneumatic transmission mechanisms of traditional aircraft with electric actuators, reduce or completely eliminate the centralized hydraulic oil source and pipelines all over the fuselage, reduce the weight of the aircraft, and simplify the aircraft. The secondary energy system...
Claims
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Patent Timeline
Login to View More IPC IPC(8): H02P6/18H02P6/06H02P21/22H02P21/18H02P21/00
CPCH02P6/183H02P6/06H02P21/22H02P21/18H02P21/0003H02K11/33H02K21/14H02P27/08H02P6/186H02P6/34H02P23/03H02K21/12H02P6/085H02P23/009H02P2207/055
Inventor 徐金全方豪郭宏
Owner BEIHANG UNIV