In the flight process of aircrafts, their electromechanical actuators（EMA） must have the ability of enduring uncertainties caused by factors such as load disturbance, the variation of work temperature and the EMA＇s...In the flight process of aircrafts, their electromechanical actuators（EMA） must have the ability of enduring uncertainties caused by factors such as load disturbance, the variation of work temperature and the EMA＇s nonlinearity. At present, in order to increase the EMA＇s robustness on the uncertainties, the H, control method has been applied in aircrafts. The major problems with standard H∞ control lie in the large overshoot of step response and the high orders of the controller. For the purpose of addressing the two problems, this paper investigates several kinds of robust control strategies of the EMA. A mathematical model of the EMA is first built, and then with MATLAB software a H∞ controller and an improved hybrid robust controller composed of a reduced order H∞controller and a lead compensator are designed. In order to make a scientific comparison of the control effects of H∞ controller, hybrid controller and classic proportion-integral-differential（PID） controller, a simulation research is made in respect of the open loop frequency response and the closed loop step response of the three controllers. For comparing the robustness of the three controllers, the load torque is entered as a disturbance and the disturbance response of error and control input are thus obtained. The experiments with the three controllers are also conducted. Through giving the EMA a command and a disturbance torque successively, the transient response and disturbing process of EMA are recorded. The simulation and experiment results show that with the help of the hybrid controller, the EMA not only guarantees good dynamic characteristics, but also has strong robustness of disturbance rejection. Therefore, the excogitated H∞ hybrid control method effectively solves the problem of large overshoot in dynamic response, and moderately meets the requirement of overcoming the uncertainties in the EMA of aircrafts.展开更多
连续体建模是一种研究大规模电力系统机电动态的新方法,面向复杂的大型电力系统,关注机电扰动在整个电力系统中的传播过程。基于描述机电波传播的非线性偏微分方程,在空间上进行差分处理,通过微分方程组体现了电力网络的拓扑连接关系,...连续体建模是一种研究大规模电力系统机电动态的新方法,面向复杂的大型电力系统,关注机电扰动在整个电力系统中的传播过程。基于描述机电波传播的非线性偏微分方程,在空间上进行差分处理,通过微分方程组体现了电力网络的拓扑连接关系,合理地处理了线路分支问题。同时,采用一种新的方法,将发电机转子的惯性按照Gauss函数连续地分布于与其相连接的线路上,体现了发电机在电力系统中的地理位置。最后,通过用连续体模型和传统模型的PSS/E动态仿真对改进的New England 10机39节点系统进行了扰动传播实验,研究了机电扰动在电力系统中的传播特性。2种方法在扰动传播时间上获得基本一致的结果。展开更多
The Electromechanical Oxygen Regulator(EMOR)is a new type of aviator oxygen equipment.Positive pressure refers to the pressure difference between the breath pressure and the ambient pressure during pressurized oxygen ...The Electromechanical Oxygen Regulator(EMOR)is a new type of aviator oxygen equipment.Positive pressure refers to the pressure difference between the breath pressure and the ambient pressure during pressurized oxygen supply.The phenomenon of positive pressure fluctuation was believed to reduce the system performance.The current open-loop control method cannot solve this problem.In this paper,the mathematical model was established and main factors were analyzed.By combining experimental research and simulation calculation,it was determined that pressure fluctuation was caused by inlet pressure and diaphragm deformation together.With the increase of pulmonary ventilation volume,the influence of inlet pressure on fluctuation decreases gradually,while the proportion of diaphragm deformation increases rapidly.A closed-loop control strategy of Proportional Resonant with Feedforward Compensation(PRFC)was proposed to solve the problem and control parameters were obtained through co-simulation.The effectiveness of the control strategy was verified by experiments.The results show that the control strategy can enhance the anti-disturbance ability of the system and significantly reduce the pressure fluctuation range,which is beneficial to improving the overall system performance.展开更多
Compared with traditional hydraulic actuators, an Electro-Mechanical Actuator(EMA)is small in size and light in weight, so it has become more widely used. Aerodynamic load on aircraft control surface varies dramatical...Compared with traditional hydraulic actuators, an Electro-Mechanical Actuator(EMA)is small in size and light in weight, so it has become more widely used. Aerodynamic load on aircraft control surface varies dramatically, and a change of flight environment leads to uncertainties of motor parameters. Therefore, high-dynamic response and strong anti-disturbance capability of an EMA are of great significance for aircraft rudder control and flight attitude adjustment. In order to improve dynamic response and disturbance rejection of an EMA and simplify control parameters tuning, a robust high-dynamic servo system based on Linear Active Disturbance Rejection Control(LADRC) is proposed for an EMA employing a Permanent Magnet Synchronous Motor(PMSM).Firstly, total disturbances of the EMA are analyzed, including parameter uncertainties, load variation, and static friction. A disturbance observer based on a reduced-order Extended State Observer(ESO) is designed to improve the anti-interference ability and dynamic performance. Secondly, the servo control architecture is simplified to a double-loop system, and a composite control of position and speed with acceleration feed-forward is presented to improve the EMA frequency bandwidth.Thirdly, the ideal model of the EMA is transformed into a simple cascade integral form with a disturbance observer, which makes it convenient to analyze and design the controller. Robustness performance comparisons are realized in frequency domain. Finally, simulation and experimental results have verified the effectiveness of the proposed strategy for EMAs.展开更多
基金supported by National Astronautic Foundation of China
文摘In the flight process of aircrafts, their electromechanical actuators（EMA） must have the ability of enduring uncertainties caused by factors such as load disturbance, the variation of work temperature and the EMA＇s nonlinearity. At present, in order to increase the EMA＇s robustness on the uncertainties, the H, control method has been applied in aircrafts. The major problems with standard H∞ control lie in the large overshoot of step response and the high orders of the controller. For the purpose of addressing the two problems, this paper investigates several kinds of robust control strategies of the EMA. A mathematical model of the EMA is first built, and then with MATLAB software a H∞ controller and an improved hybrid robust controller composed of a reduced order H∞controller and a lead compensator are designed. In order to make a scientific comparison of the control effects of H∞ controller, hybrid controller and classic proportion-integral-differential（PID） controller, a simulation research is made in respect of the open loop frequency response and the closed loop step response of the three controllers. For comparing the robustness of the three controllers, the load torque is entered as a disturbance and the disturbance response of error and control input are thus obtained. The experiments with the three controllers are also conducted. Through giving the EMA a command and a disturbance torque successively, the transient response and disturbing process of EMA are recorded. The simulation and experiment results show that with the help of the hybrid controller, the EMA not only guarantees good dynamic characteristics, but also has strong robustness of disturbance rejection. Therefore, the excogitated H∞ hybrid control method effectively solves the problem of large overshoot in dynamic response, and moderately meets the requirement of overcoming the uncertainties in the EMA of aircrafts.
文摘连续体建模是一种研究大规模电力系统机电动态的新方法,面向复杂的大型电力系统,关注机电扰动在整个电力系统中的传播过程。基于描述机电波传播的非线性偏微分方程,在空间上进行差分处理,通过微分方程组体现了电力网络的拓扑连接关系,合理地处理了线路分支问题。同时,采用一种新的方法,将发电机转子的惯性按照Gauss函数连续地分布于与其相连接的线路上,体现了发电机在电力系统中的地理位置。最后,通过用连续体模型和传统模型的PSS/E动态仿真对改进的New England 10机39节点系统进行了扰动传播实验,研究了机电扰动在电力系统中的传播特性。2种方法在扰动传播时间上获得基本一致的结果。
文摘The Electromechanical Oxygen Regulator(EMOR)is a new type of aviator oxygen equipment.Positive pressure refers to the pressure difference between the breath pressure and the ambient pressure during pressurized oxygen supply.The phenomenon of positive pressure fluctuation was believed to reduce the system performance.The current open-loop control method cannot solve this problem.In this paper,the mathematical model was established and main factors were analyzed.By combining experimental research and simulation calculation,it was determined that pressure fluctuation was caused by inlet pressure and diaphragm deformation together.With the increase of pulmonary ventilation volume,the influence of inlet pressure on fluctuation decreases gradually,while the proportion of diaphragm deformation increases rapidly.A closed-loop control strategy of Proportional Resonant with Feedforward Compensation(PRFC)was proposed to solve the problem and control parameters were obtained through co-simulation.The effectiveness of the control strategy was verified by experiments.The results show that the control strategy can enhance the anti-disturbance ability of the system and significantly reduce the pressure fluctuation range,which is beneficial to improving the overall system performance.
基金supported by the Shaanxi Provincial Key R&D Program, China (No. 2017KW-ZD-05)the Natural Science Basic Research Plan in Shaanxi Province of China (No. 2018JQ5187)the Fundamental Research Funds for the Central Universities,China(Nos.3102017JC06004, 3102017OQD029)
文摘Compared with traditional hydraulic actuators, an Electro-Mechanical Actuator(EMA)is small in size and light in weight, so it has become more widely used. Aerodynamic load on aircraft control surface varies dramatically, and a change of flight environment leads to uncertainties of motor parameters. Therefore, high-dynamic response and strong anti-disturbance capability of an EMA are of great significance for aircraft rudder control and flight attitude adjustment. In order to improve dynamic response and disturbance rejection of an EMA and simplify control parameters tuning, a robust high-dynamic servo system based on Linear Active Disturbance Rejection Control(LADRC) is proposed for an EMA employing a Permanent Magnet Synchronous Motor(PMSM).Firstly, total disturbances of the EMA are analyzed, including parameter uncertainties, load variation, and static friction. A disturbance observer based on a reduced-order Extended State Observer(ESO) is designed to improve the anti-interference ability and dynamic performance. Secondly, the servo control architecture is simplified to a double-loop system, and a composite control of position and speed with acceleration feed-forward is presented to improve the EMA frequency bandwidth.Thirdly, the ideal model of the EMA is transformed into a simple cascade integral form with a disturbance observer, which makes it convenient to analyze and design the controller. Robustness performance comparisons are realized in frequency domain. Finally, simulation and experimental results have verified the effectiveness of the proposed strategy for EMAs.
