机构

• 长春光学精密机械与物... [1]
• 数学与系统科学研究院 [1]
• 过程工程研究所 [1]

采集方式

• OAI收割 [3]

内容类型

• 会议论文 [2]
• 期刊论文 [1]

发表日期

• 2021 [1]
• 2013 [1]
• 2011 [1]

学科主题

• Graphics P... [1]

筛选

浏览/检索结果: 共3条，第1-3条 帮助 条数/页： 5101520253035404550556065707580859095100 排序方式： 请选择题名升序题名降序提交时间升序提交时间降序作者升序作者降序发表日期升序发表日期降序 Rational dynamical systems, S-units, and D-finite power series 期刊论文  OAI收割 ALGEBRA & NUMBER THEORY, 2021, 卷号: 15, 期号: 7, 页码: 1699-1728 作者:  Bell, Jason P.;  Chen, Shaoshi;  Hossain, Ehsaan   |  收藏  |  浏览/下载：9/0  |  提交时间：2022/04/02 S-units  D-finite series  arithmetic dynamics  algebraic groups  orbits   Petascale molecular dynamics simulation of crystalline silicon on Tianhe-1A 会议论文  OAI收割 作者:  Hou, Chaofeng;  Xu, Ji;  Wang, Peng;  Huang, Wenlai;  Wang, Xiaowei   |  收藏  |  浏览/下载：0/0  |  提交时间：2023/06/16 Computer graphics equipment - Surface reactions - Program processors - Molecular dynamics - Reaction kinetics - Digital arithmetic - Silicon - Crystalline materials - Image coding - Computer graphics - Surface defects - Grain boundaries   Research on model reference sliding mode control in roll stabilization of aerocraft (EI CONFERENCE) 会议论文  OAI收割 2011 International Conference on Electric Information and Control Engineering, ICEICE 2011, April 15, 2011 - April 17, 2011, Wuhan, China Chu H.-R. 收藏  |  浏览/下载：37/0  |  提交时间：2013/03/25 Aimed at aerospace roll stabilization  control arithmetic based on model reference sliding mode variable structure theory and chattering reduction arithmetic are formulated. Correctness and validity of arithmetic are analyzed. With flight dynamics  the roll-loop mathematic model and reference model are established. Sliding hyperplane is deduced based on model reference sliding mode variable structure theory. Combing with reaching law  control law is derived  and stability of roll-loop is analyzed. Chattering of aileron instructions is alleviate by using boundary layer approach. Digital flying simulation result shows that variable structure control arithmetic realized roll stabilization control  the roll angle is less than 5.3 under powered flight  and that of unpowered flight is less than 0.5  respectively. The command fin angle is less than 1.5. High frequency chattering of fin command nearby the minimum velocity was trailed off by chattering reduction arithmetic. The sliding mode control arithmetic show good performance when aerodynamic coefficients varies 20%. The control arithmetic is easy to be implemented for its simplicity. 2011 IEEE.