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571.
WU Yunjie LIU Xiaodong TIAN Dapeng Science Technology on Aircraft Control Laboratory School of Automation Science Electrical Engineering Beihang University Beijing China 《中国航空学报》2011,24(5):613-621
A compound controller is proposed to alleviate the considerable chattering in output of zero phase error tracking controller (ZPETC), when the flight simulator losses command data of simulation signal. Besides, the shortcomings, caused by conventional differential methods in retrieving velocity and acceleration signals, are avoided to a certain extent. The compound controller based on disturbance observer (DOB) is composed of a feed-forward controller and a feedback controller. It estimates velocity and acceleration of unknown tracking signal, and also velocity response with an approximate method for differential. The experiments on a single-axis flight simulator show that the proposed method has strong robustness against parameter perturbations and external disturbances, owing to the introduced DOB. Compared with the scheme with ZPETC, the proposed scheme possesses more simple design and better tracking performance. Moreover, it is less sensitive to position command distortion of flight simulator. 相似文献
572.
地线设计在PCB电磁兼容性中的作用 总被引:1,自引:0,他引:1
简介了电磁兼容性(EMC)的基本概念,并结合某项目实际应用,说明地线设计的一点改变即可在PCB电磁兼容方面起到重要作用. 相似文献
573.
USB系统是目前中国载人航天和月球探测任务的主要测控网.由于USB测量设备本身以及无线电信号传播媒介以及其他误差因素的影响,USB测量数据中包含了各种误差,需要在定轨时对观测数据进行误差修正.通常,例行的USB测量误差修正包括对流层折射修正、电离层延迟修正和通道延迟修正,但对定轨过程中可能影响观测数据计算精度的时标偏差并未作修正.针对USB测距测速观测数据,详细研究了观测数据时标偏差对观测值计算精度的影响,分析了误差影响特性,建立了相应的误差修正模型,并通过与卫星星历偏差对USB测距测速观测值计算精度影响特征的比较,发现时标偏差对测量的影响与轨道沿迹误差对观测计算值的影响等效,这使得在定轨过程中分离时标偏差的难度较大.提出了基于星载GPS定位数据分离时标偏差的方法,并利用某次任务的实测数据,分离出了该次任务中USB测量的时标偏差.最后针对目前USB数据时标偏差影响和观测误差量级相当的情况,建议将目前的观测时标精度提高到优于0.1ms的水平,使得时标偏差的影响降低到比观测误差小一个量级的水平. 相似文献
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A轴单元作为五轴数控机床的关键功能部件,其控制精度直接影响整体叶盘的加工精度和表面质量.针对摩擦、齿隙、参数摄动和测量噪声等非线性干扰对A轴伺服系统控制精度的影响,提出了基于线性二次型最优控制(LQC)和滑模控制(SMC)相结合的鲁棒控制算法(LQSMC).该方法以系统状态空间表达式及LQC为基础,通过引入基于卡尔曼滤波器和控制输入的状态估计,对系统状态空间模型进行改进并定义新的滑模面方程,使得改进后的控制算法在性能上接近LQC并能有效抑制SMC的抖振.仿真分析和实验结果表明,LQSMC算法具有控制精度高、鲁棒性强和抑制干扰能力强等优点,其能有效提高A轴伺服系统的定位精度和跟踪精度,使整体叶盘型面加工精度和表面一致性得到保证,并显著降低了表面粗糙度. 相似文献
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579.
《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2023,71(1):420-438
Space-based gravitational wave (GW) detector such as the LISA (Laser Interferometer Space Antenna) mission requires high-precision and stability of the triangular formation. The dynamic environment of the detectors is complex, the science requirements for the formation are tight, and consequently, design and optimization of this high-standard formation with essentially many decision variables are very challenging. This paper studies the design and optimization of the stable initial formation of the heliocentric GW detector by taking the LISA as an example. The linearization method based on relative orbital elements is used for formation design in the two-body system. Three constraints are presented to reduce the number of decision variables to fourteen. The geometric features of the arm length and breathing angle of the triangular formation and the relative position of LISA to the Earth are analyzed and numerically verified in a high-fidelity dynamic model, from which the relationships of multiple requirements of LISA are studied, and a single index is summarized to simplify the optimization. Sobol sensitivity analysis is used to quantitatively evaluate the sensitivities of the decision variables to the cost function, with which a self-adaptive adjustment algorithm of the region of the variables is presented to improve the computational efficiency. The availability of the method to quickly and precisely find a stable initial formation in an extensive neighborhood of the nominal formation is verified by numerical simulation, where the best solution decreases about 47.54% of the arm length change from the requirement. This study shows that the initial formation should be deployed appropriately away from the Earth, and the gravitations of Venus and Jupiter should be utilized to maintain the formation stability. 相似文献
580.
Takaya Inamori Jihe Wang Phongsatorn Saisutjarit Shinichi Nakasuka 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2013
Nowadays, nano- and micro-satellites, which are smaller than conventional large satellites, provide access to space to many satellite developers, and they are attracting interest as an application of space development because development is possible over shorter time period at a lower cost. In most of these nano- and micro-satellite missions, the satellites generally must meet strict attitude requirements for obtaining scientific data under strict constraints of power consumption, space, and weight. In many satellite missions, the jitter of a reaction wheel degrades the performance of the mission detectors and attitude sensors; therefore, jitter should be controlled or isolated to reduce its effect on sensor devices. In conventional standard-sized satellites, tip-tilt mirrors (TTMs) and isolators are used for controlling or isolating the vibrations from reaction wheels; however, it is difficult to use these devices for nano- and micro-satellite missions under the strict power, space, and mass constraints. In this research, the jitter of reaction wheels is reduced by using accurate sensors, small reaction wheels, and slow rotation frequency reaction wheel instead of TTMs and isolators. The objective of a reaction wheel in many satellite missions is the management of the satellite’s angular momentum, which increases because of attitude disturbances. If the magnitude of the disturbance is reduced in orbit or on the ground, the magnitude of the angular momentum that the reaction wheels gain from attitude disturbances in orbit becomes smaller; therefore, satellites can stabilize their attitude using only smaller reaction wheels or slow rotation speed, which cause relatively smaller vibration. In nano- and micro-satellite missions, the dominant attitude disturbance is a magnetic torque, which can be cancelled by using magnetic actuators. With the magnetic compensation, the satellite reduces the angular momentum that the reaction wheels gain, and therefore, satellites do not require large reaction wheels and higher rotation speed, which cause jitter. As a result, the satellite can reduce the effect of jitter without using conventional isolators and TTMs. Hence, the satellites can achieve precise attitude control under low power, space, and mass constraints using this proposed method. Through the example of an astronomical observation mission using nano- and micro-satellites, it is demonstrated that the jitter reduction using small reaction wheels is feasible in nano- and micro-satellites. 相似文献