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陈成 , 赵良玉 , 谢浩怡 , 等 . 单通道控制旋转弹角运动的复分析方法 [J ] . 兵工学报 , 2021 , 42 ( 2 ): 308 - 319 .

CHEN C , ZHAO L Y , XIE H Y , et al. Complex analysis for angular motion of a spinning projectile with one pair of canards [J ] . Acta Armamentarii , 2021 , 42 ( 2 ): 308 - 319 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2021.02.009 http://doi.org/10.3969/j.issn.1000-1093.2021.02.009 The stability of coning motion of spinning projectile with one pair of canards cannot be directly analyzed by the analytic method due to the aerodynamic asymmetry. The angular motion model and complex analysis method for the spinning projectile are studied. A complex angle-of-attack motion equation is established, and a scaling factor is introduced to the asymmetric aerodynamic term in the equation. On this basis, the analytical expressions of complex angle-of-attack motion equation under different actuator deflection angles are obtained. The convergence process, steady state and resonance of the model are analyzed. The validity of complex angle-of-attack motion equation is confirmed through numerical simulation, and the cause of resonance instability under sinusoidal actuator deflection is revealed.

宋韬 , 林德福 , 魏志军 , 等 . 滚转导弹过载驾驶仪控制耦合解耦算法研究 [J ] . 兵工学报 , 2014 , 35 ( 4 ): 454 - 460 . DOI: 10.3969/j.issn.1000-1093.2014.04.004 http://doi.org/10.3969/j.issn.1000-1093.2014.04.004 舵机动力学滞后引起的控制耦合严重限制了过载驾驶仪在滚转导弹上的应用。建立滚转导弹驾驶仪模型，推导了等效舵机动力学传递函数矩阵，对比研究了基于最优舵面超前角度补偿和输出反馈动态的解耦控制方法，进行了仿真验证。仿真结果表明：随着转速与舵控系统频带比值的提高，控制耦合增加；基于最优舵面超前角度补偿的解耦方法实现简单，适用于工程应用，然而当转速与舵机频带的比值、输入指令频率与舵机频带的比值增加时，解耦效果变差，舵机控制效率降低；基于输出反馈动态解耦方法能够实现完全解耦，且受转速测量精度的影响较小，但该方法要求对舵机的传递函数精确已知，且补偿器的复杂性与舵机阶数密切相关，工程应用存在一定的难度。

SONG T , LIN D F , WEI Z J , et al. Research on decoupling algorithm for control coupling of a spinning missile autopilot [J ] . Acta Armamentarii , 2014 , 35 ( 4 ): 454 - 460 . (in Chinese) DOI: 10.3969/j.issn.1000-1093.2014.04.004 http://doi.org/10.3969/j.issn.1000-1093.2014.04.004 The application of acceleration autopilot in spinning missile is restricted by the control coupling resulting from the actuator kinetics. A model of spinning missile autopilot is established, and the transfer function matrix of the equivalent actuator is derived. The methods of optimal actuator leading angle compensation and decoupling control based on dynamic output feedback are studied. Simulation results show that, with increase in the ratio of actuator band to rotating frequency, the control coupling becomes larger. The optimal actuator leading angle compensation is suitable for engineering application, but when the rotating frequency and the actuator frequency are increased, the decoupling effect deteriorates and the actuator control efficiency decreases. The complete decoupling can be achieved by using the method of decoupling control based on dynamic output feedback, and the measured errors have little effect on the application. However, this method needs a precise actuator kinetics model, and the complexity of compensator is closely related to the actuator order.

于剑桥 , 林凡 , 方正 . 自激振荡线性化舵机延迟补偿时间处理方法研究 [J ] . 兵工学报 , 2009 , 30 ( 5 ): 652 - 656 . 针对某单通道控制炮射导弹所采用的自激振荡线性化舵机，给出了一种有效的舵机延迟补偿时间处理方法。自激振荡线性化舵机的高频振荡特性使得对其延迟时间的测量和处理相当困难，为解决此问题提出采用弹体滤波去除舵机高频振荡所造成的不确定性，并由导弹法向加速度延迟确定舵机延迟补偿时间的方法。数据处理结果表明，采用所提出的方法能够有效地确定自激振荡线性化舵机的延迟补偿时间。还从舵机延迟补偿难易的角度对比了调幅方波和调幅正弦波两种舵机指令形式的优劣，得到了自激振荡线性化舵机对正弦波指令的响应特性优于方波指令的结论。

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YE S C . Fuzzy sliding mode observer with dual SOGI-FLL in sensorless control of PMSM drives [J ] . ISA Transactions , 2019 , 85 : 161 - 176 . DOI: S0019-0578(18)30383-5 http://doi.org/S0019-0578(18)30383-5 To improve the performance of permanent-magnet synchronous motor (PMSM) drives, a sensorless control scheme based on a sliding mode observer (SMO) with a fuzzy logic controller (FLC) and a dual second-order generalized integrator-frequency locked loop (DSOGI-FLL) is proposed in this paper. The major drawbacks of the conventional SMO, namely chattering phenomena, high-order harmonics and external noise, are discussed. These drawbacks affect the estimated accuracy of the SMO and reduce the control reliability of the system. To eliminate these drawbacks, an FLC is designed and integrated into the SMO to adjust the observer gain in a self-adaptive manner and to reduce the chattering; an existing dual synchronous frequency extract filter-phase locked loop (DSFF-PLL) is used to filter out the main components of high-order harmonics and to calculate the rotor position and speed precisely. Furthermore, to obtain an accurate fundamental frequency for the phase locked loop (PLL) and filter out the remaining harmonics and external noise signals, DSOGI-FLL processing is developed and incorporated into the DSFF-PLL. An overall PMSM sensorless control system based on the proposed SMO is designed, and an experimental platform using the TMS320F28335 DSP controller is built. Comparative experiments using the proposed SMO and the conventional SMO are performed to validate the effectiveness of the proposed FLC and the DSFF-DSOGI-FLL-PLL structures. Performance experiments of the overall proposed SMO-based sensorless control scheme are performed to verify the robustness and control reliability of the system. The results show that the proposed SMO has satisfactory performances and can be used in practical engineering.Copyright © 2018 ISA. Published by Elsevier Ltd. All rights reserved.

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