中国科学院机构知识库网格系统: 检索

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	Measurement of leakage neutron spectra for aluminium with D-T fusion neutrons and validation of evaluated nuclear data 期刊论文 OAI收割 FUSION ENGINEERING AND DESIGN, 2021, 卷号: 171, 页码: 6 作者: Zhang, S.; Niu, D.; Wang, D. X.; Nie, Y.; Song, N. \| 收藏 \| 浏览/下载：39/0 \| 提交时间：2021/12/08 Aluminium Integral benchmark experiment Time-of-flight method Evaluated nuclear data
	Design of back-streaming white neutron beam line at csns 期刊论文 iSwitch采集 Applied radiation and isotopes, 2018, 卷号: 132, 页码: 212-221 作者: Zhang, L. Y.; Jing, H. T.; Tang, J. Y.; Li, Q.; Ruan, X. C. 收藏 \| 浏览/下载：68/0 \| 提交时间：2019/04/23 Back-streaming white neutrons Time-of-flight (top) method Neutron characteristics Neutron beam collimation Neutron and gamma background
	Design of back-streaming white neutron beam line at CSNS 期刊论文 OAI收割 APPLIED RADIATION AND ISOTOPES, 2018, 卷号: 132, 页码: 212-221 作者: Ning CJ(宁常军); Ruan, XC; Li Q(李强); Tang JY(唐靖宇); Jing HT(敬罕涛) \| 收藏 \| 浏览/下载：50/0 \| 提交时间：2019/09/24 Back-streaming white neutrons Time-of-flight (TOP) method Neutron characteristics Neutron beam collimation Neutron and gamma background
	The benchmark experiment on slab beryllium with D-T neutrons for validation of evaluated nuclear data 期刊论文 OAI收割 FUSION ENGINEERING AND DESIGN, 2016, 卷号: 105, 页码: 8-14 作者: Ding, Y.; Nie, Y.; Liu, P.; Zhou, Z.; Ruan, X. \| 收藏 \| 浏览/下载：21/0 \| 提交时间：2018/05/31 Beryllium Evaluated nuclear data Benchmark experiment Neutron leakage spectrum Time-of-flight method MCNP-4B
	Self-adaptive echo signal processing method for pulse radar ranging system 会议论文 OAI收割 2016 IEEE Information Technology, Networking, Electronic and Automation Control Conference, ITNEC 2016, Chongqing, China, May 20-22, 2016 作者: Gao J(高洁); Du JS(杜劲松); Bi X(毕欣) 收藏 \| 浏览/下载：44/0 \| 提交时间：2016/11/01 time-of-flight Pulse radar characteristic values Parabola fitting the least-squares method
	复合金属/金属氧化物纳米材料在污染物可视化及质谱分析中的应用学位论文 OAI收割博士, 北京: 中国科学院研究生院, 2013 马玉荣收藏 \| 浏览/下载：105/0 \| 提交时间：2014/08/22 磁性纳米材料多巴胺纳米银可视化方法基质辅助激光解析电离-飞行时间质谱 magnetic nanoparticles dopamine silver nanoparticles colorimetric method matrix-assisted laser desorption/ionization time-of-flight mass spectrometry
	Precision analysis of simulation systems with hardware-in-loop caused by performance of three-Axis virtual flight motion simulator (EI CONFERENCE) 会议论文 OAI收割 2011 International Conference on Manufacturing Science and Technology, ICMST 2011, September 16, 2011 - September 18, 2011, Singapore, Singapore Wang T.; Zhu M.-C.; Yin S.-L.; Jia H.-G. 收藏 \| 浏览/下载：45/0 \| 提交时间：2013/03/25 Simulation systems with hardware-in-loop are composed by three-Axis virtual flight motion simulator simulation computer load torque simulator and visual simulation systems. Three-Axis Virtual Flight Motion Simulator are used to simulate the attitude of missile in simulation system with hardware-in-loop so its performance influenced the result of simulation directly. This paper mainly analyzed the factors which influenced the performance of a three-Axis virtual flight motion simulator which we are used now in the lab then analyzed the entire simulation system's error caused by these factors through numerical simulation method. By analysis we can see that bandwidth is the main factor influenced the precision of simulation systems with hardware-in-loop mechanical device installation error and measurement error may also cause some errors of the systems at the same time.
	Three-loop autopilot design and simulation (EI CONFERENCE) 会议论文 OAI收割 2012 9th IEEE International Conference on Mechatronics and Automation, ICMA 2012, August 5, 2012 - August 8, 2012, Chengdu, China 作者: Zhang Y. 收藏 \| 浏览/下载：42/0 \| 提交时间：2013/03/25 In order to realize missile real-time change flight trajectory three-loop autopilot is setting up. The structure characteristics autopilot model and control parameters design method were researched. Firstly this paper introduced the 11th order three-loop autopilot model. With the principle of systems reduce model order the 5th order model was deduced. On that basis open-loop frequency characteristic and closed-loop frequency characteristic were analyzed. The variables of velocity ratio dynamic pressure ratio and elevator efficiency ratio were leading to correct system nonlinear. And then autopilot gains design method were induced. System flight simulations were done and result shows that autopilot gains played a good job in the flight trajectory autopilot satisfied the flight index. 2012 IEEE.
	A strong coupled CFD-CSD method on computational aeroelastity (EI CONFERENCE) 会议论文 OAI收割 2011 2nd International Conference on Mechanic Automation and Control Engineering, MACE 2011, July 15, 2011 - July 17, 2011, Inner Mongolia, China Xi R.; Jia H. 收藏 \| 浏览/下载：67/0 \| 提交时间：2013/03/25 In this paper a strong coupled CFD-CSD method is developed to simulate the aeroelastic phenomena. The CFD solver is based on the finite-volume algorithm for the Navier-Stokes equations on unstructured grid. The CSD solver solves the aeroelastic governing equations in the modal space. Their coupling is realized by a dual-time method. The spring-based smoothing method is adopted to deform and regenerate the aerodynamic grid. Two test cases are selected to validate the authors' method for static and dynamic aeroelastity .The results of the simulation for the static aeroelastic problems of a missile wing show that the Lift Coefficient and Drag Coefficient are severally 7% and 5% lower than those don't consider the elasticity of the wing. The results for the flutter boundary prediction of the AGARD 445.6 wing have been proved much closer to the experiment than using the DLM. This method can describe the effects of fluid viscosity more exactly for highly nonlinear transonic flight conditions. The calculation has proved reliable in the subsonic regime but not accurate enough in the supersonic regime. 2011 IEEE.