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	Supercritical and subcritical aeroelastic behaviors of a three-dimensional wing coupled with a nonlinear energy sink 期刊论文 OAI收割 INTERNATIONAL JOURNAL OF NON-LINEAR MECHANICS, 2024, 卷号: 161, 页码: 17 作者: Huang CD(黄程德); Zheng GN(郑冠男); Nie XY(聂雪媛); Yang GW(杨国伟) \| 收藏 \| 浏览/下载：9/0 \| 提交时间：2024/05/27 Flutter Nonlinear energy sink Equivalent linearization method Reduced order model
	New incremental secant linearization method for mean-field homogenization approach of elasto-viscoplastic microscopic heterogeneous materials 期刊论文 OAI收割 COMPOSITE STRUCTURES, 2021, 卷号: 271, 页码: 114125 作者: Rao W(饶威); Yu, Chao; Zhang, Juan; Kang, Guozheng \| 收藏 \| 浏览/下载：23/0 \| 提交时间：2022/10/25 Incremental secant linearization method Micro-mechanics Elasto-viscoplastic microscopic heterogeneous materials
	Reentry guidance based on feedback linearization (EI CONFERENCE) 会议论文 OAI收割 2011 International Conference on Electronics, Communications and Control, ICECC 2011, September 9, 2011 - September 11, 2011, Ningbo, China Li D.-W. 收藏 \| 浏览/下载：30/0 \| 提交时间：2013/03/25 This paper presents a new reentry guidance algorithm for RLV (Reusable Launching Vehicle). The algorithm consists of two integrated components: trajectory planning algorithm and tracking algorithm. The most striking feature of algorithm here lies in that both planning and tracking are executed directly in height-velocity space which is different from the methodology of configuration of drag in traditional shuttle guidance. In the session of trajectory planning all trajectory constraints can be expressed with upper bound and lower bound in height-velocity space then a linear interpolation is carried to search the nominal trajectory satisfying the requirement of downrange and target constraints. Then the tracking algorithm uses feedback linearization method to track this nominal profile and meet all constraints. Another typical feature of this algorithm is the strategy of downrange extension using FPA (flight path angle) controller to fulfill the requirement of large downrange. Proper combination of planning-tracking algorithm and FPA controller can bring great flexibility and adaptability to reentry guidance. The algorithm is proved to be robust enough to accommodate the model error and noises in the dynamics. 2011 IEEE.
	Stability control of quad-rotor based on explicit model following with inverse model feedforward method (EI CONFERENCE) 会议论文 OAI收割 2011 IEEE International Conference on Mechatronics and Automation, ICMA 2011, August 7, 2011 - August 10, 2011, Beijing, China Bai Y.; Gong X.; Hou Z.; Tian Y. 收藏 \| 浏览/下载：21/0 \| 提交时间：2013/03/25 The quad-rotor is expected to carry out many different tasks. It is hoped that the quad-rotor can have different characteristics according to the different mission requirements. For this reason a flight stability augmentation control system based on explicit model following with inverse model feedforward control method is proposed in this paper. This control system is composed of an explicit model an inverse model and a feedback controller module. In order to calculate an inverse model of the coupled multivariable aircraft system a feedback linearization loop is also applied to this control system. At last simulations are performed to show the effectiveness of the designed stability augmentation control system in the presence of external disturbance and model uncertainty. The influence of explicit model to the characteristics of quad-rotor is also indicated in a contrast simulation result. 2011 IEEE.
	The analysis for the reason of limit cycle generated by friction in servo system (EI CONFERENCE) 会议论文 OAI收割 2010 International Conference on Computer, Mechatronics, Control and Electronic Engineering, CMCE 2010, August 24, 2010 - August 26, 2010, Changchun, China 作者: Li M. 收藏 \| 浏览/下载：20/0 \| 提交时间：2013/03/25 In this paper limit cycle which results from friction during low-velocity servo system has been discussed. First the piecewise linearization method has been applied to change nonlinear stribeck model to linear model. Second with analysis of equilibrium property it is proved the existence of limit cycle and its certain region. The analysis reveals that it is because of stability of equilibrium repeatedly changing results in the limit cycle during low-velocity state. In addition it also points that the key point to avoid this phenomenon is to keep robust stability of the close-loop system. 2010 IEEE.
	Linearization Method and Linear Complexity 期刊论文 OAI收割 IEICE Transactions on Fundamentals of Electronics, Communications and Computer Sciences, 2008, 卷号: E91-A, 期号: 1, 页码: 22-29 Hidema Tanaka \| 收藏 \| 浏览/下载：20/0 \| 提交时间：2010/05/14 algebraic cryptanalysis linear complexity linearization method pseudo-random number generator stream cipher
	Comparison of two linearization methods for optimal attitude maneuver of a non-linear flexible spacecraft 期刊论文 OAI收割 Ima Journal of Mathematical Control and Information, 2006, 卷号: 23, 期号: 2, 页码: 127-136 Zheng, J. H. 收藏 \| 浏览/下载：25/0 \| 提交时间：2014/04/30 non-linear flexible spacecraft optimal attitude maneuver vibration suppression control recursive approximating sequence approach linearization method small sphere approximating approach linearization method stabilization systems