Aiming at a series of problems caused by the position sensor required by the salient pole permanent magnet synchronous motor (IPMSM) control system, a high-frequency square wave injection sensorless control algorithm suitable for IPMSM low-speed control system is realized in this paper. Compared with other sensorless control algorithms, its advantages are that it avoids the system delay caused by the filter by injecting high-frequency square wave signal, and has good stability and robustness at low speed. The feasibility and effectiveness of this method are verified by simulation. At the same time, it shows that the high-frequency square wave injection method has good accuracy of rotor position estimation, and can ensure the good stability and dynamic performance of the whole drive system. Through the simulation results, better injection voltage amplitude is selected to reduce the electromagnetic interference and electromagnetic noise caused by high-frequency square wave injection signal.
KEYWORDS: Space operations, Digital signal processing, Control systems, Vibration control, Signal processing, Field programmable gate arrays, Solar energy, Feedback signals, Control systems design, Bridges
"Tianzhou-1" cargo spacecraft is an important part of China's manned stations. Its main task is to add propellant and transport goods for the manned stations, and bring the station waste back to the atmosphere for burning. The "Tianzhou1" series cargo spacecraft is the backbone of the material supply of China's manned stations. The energy of cargo spacecraft in space comes from the flexible solar wing, but the solar wing is easy to vibrate by the unstable excitation from the platform. To solve this problem, the vibration response of the flexible solar wing system is analyzed, and the dynamic model of the flexible solar wing is established. On this basis, the control system is designed by using negative velocity feedback and linear quadratic optimal regulator, and then the vibration is suppressed. Finally, the experimental verification of vibration control of flexible solar wing of cargo spacecraft is realized by designing the experimental system of peripheral circuit, driving circuit and position detection circuit of processor based on DSP + FPGA. Through experimental verification, the system can realize the vibration suppression function of the extension mechanism with high disturbance, and realize the engineering application that the large flexible solar wing can expand and close repeatedly and smoothly. It has certain application value and provides reference for subsequent engineering applications.
KEYWORDS: Control systems, Field programmable gate arrays, Solar energy, Control systems design, Vibration control, Bridges, Transformers, Switching, Sun, Analog electronics
The space flexible solar wing is easy to be affected by the vibration from the satellite platform, which has characteristics of low frequency, dense frequencies and large static deformation. In order to ensure that the extension mechanism of the large flexible solar wing can realize the reliable, repetitive and stable deployment and retraction of the sun tracking, adynamic model of the flexible solar wing is established. On this basis, a double closed-loop control strategy of improved sliding mode and variable integral PID regulator is proposed to realize the double closed-loop control system of speed and current. Finally, the experimental system of peripheral circuit, driving circuit and position detection circuit based on single chip anti fuse FPGA is designed, and the experimental verification of large flexible solar wing deployment control based on FPGA is realized. Through the experimental verification, the system can achieve the vibration suppression function of the extension mechanism with high disturbance, and realize the engineering application that the large flexible solar wing can be repeatedly and smoothly unfolded and folded which has a certain application value and provides a reference for the subsequent engineering application.
During the on-orbit operation of space spacecraft, it is easy to be affected by the small vibration from the satellite platform, especially the key sensitive loads carried by the spacecraft. The traditional method is to install a passive damping vibration isolation system between the platform and the sensitive loads. However, the passive vibration isolation system only has a good suppression effect on the high-frequency and large amplitude vibration, and can suppress the low-frequency and large amplitude vibration below 10Hz,the vibration isolation effect in the resonance section is poor. Therefore, in order to solve this problem, an active vibration isolation system of 6-DOF Stewart platform driven by piezoelectric actuator is proposed in this paper. Firstly, the characteristics of Stewart platform are analyzed and modeled, and on this basis, the deformation and displacement of each leg are obtained through decoupling calculation, and each leg is servo controlled with high precision; Secondly, the inherent hysteresis nonlinearity of piezoelectric ceramics has a serious impact on the positioning accuracy. By analyzing the hysteresis mechanism of piezoelectric actuator, a phenomenal hysteresis mathematical model based on Maxwell-Slip operator is established. Finally, the feedforward inverse compensation and feedback linearization methods are proposed, and the system verification test is established. The test results show that, the active and passive vibration isolation system designed in this paper greatly improves the positioning accuracy of piezoelectric actuator and the active vibration isolation performance of the platform.
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