中国科学院机构知识库网格系统: 检索

UV-Epoxy-Enabled Simultaneous Intact Transfer and Highly Efficient Doping for Roll-to-Roll Production of High-Performance Graphene Films 期刊论文 OAI收割
ACS APPLIED MATERIALS & INTERFACES, 2018, 卷号: 10, 期号: 47, 页码: 40756-40763
作者: Ma, LP; Dong, SC; Chen, ML; Ma, W; Sun, DM

|

收藏 | 浏览/下载：48/0 | 提交时间：2018/12/25

flexible transparent electrode graphene adhesive doping roll-to-roll bubbling transfer

UV-Epoxy-Enabled Simultaneous Intact Transfer and Highly Efficient Doping for Roll-to-Roll Production of High-Performance Graphene Films 期刊论文 OAI收割
ACS APPLIED MATERIALS & INTERFACES, 2018, 卷号: 10, 期号: 47, 页码: 40756-40763
作者: Ma, Lai-Peng; Dong, Shichao; Chen, Maolin; Ma, Wei; Sun, Dongming

|

收藏 | 浏览/下载：23/0 | 提交时间：2021/02/02

flexible transparent electrode graphene adhesive doping roll-to-roll bubbling transfer

Solvent-resistant small molecule solar cells by roll-to-roll fabrication via introduction of azide cross-linkable group 期刊论文 OAI收割
SYNTHETIC METALS, 2014, 卷号: 195, 页码: 299-305
作者: Chen, Mei-Rong; Fan, Cong-Cheng; Andersen, Thomas R.; Dam, Henrik F.; Fu, Wei-Fei

|

收藏 | 浏览/下载：33/0 | 提交时间：2019/04/09

Solvent-resistant Roll-to-roll Fabrication Large Area Cross-linkable Small Molecule Solar Cells Diketopyrrolopyrrole

Improving the Morphology of PCDTBT:PC70BM Bulk Heterojunction by Mixed-Solvent Vapor-Assisted Imprinting: Inhibiting Intercalation, Optimizing Vertical Phase Separation, and Enhancing Photon Absorption 期刊论文 OAI收割
journal of physical chemistry c, 2014, 卷号: 118, 期号: 9, 页码: 4585-1595
Liu,Jianggang; Liang,Qiuju; Wang,Haiyang; Li,Mingguang; Han,Yanchun; Xie,Zhiyuan; Wang,Lixiang

收藏 | 浏览/下载：33/0 | 提交时间：2015/10/15

POLYMER SOLAR-CELLS ROLL-TO-ROLL NANOSCALE MORPHOLOGY AU NANOPARTICLES FULLERENE PERFORMANCE POLY(3-HEXYLTHIOPHENE) BLENDS FILMS LITHOGRAPHY

All polymer photovoltaics: From small inverted devices to large roll-to-roll coated and printed solar cells 期刊论文 OAI收割
SOLAR ENERGY MATERIALS AND SOLAR CELLS, 2013, 卷号: 112, 页码: 157-162
作者: Liu, Yao; Larsen-Olsen, Thue T.; Zhao, Xingang; Andreasen, Birgitta; Sondergaard, Roar R.

|

收藏 | 浏览/下载：27/0 | 提交时间：2019/04/09

All-polymer Solar Cells Inverted Geometry Roll-to-roll Process

Analysis of zenith pass problem and tracking strategy design for roll-pitch seeker (EI CONFERENCE) 会议论文 OAI收割
作者: Jiang H.

收藏 | 浏览/下载：18/0 | 提交时间：2013/03/25

Roll-pitch seeker is currently applied in particular missiles. There is a stubborn problem called zenith pass problem while roll-pitch seeker is used. Analysis of the zenith pass problem which always results in loss of target is presented in this paper. Based on the analysis result tracking strategy is carried out to deal with zenith pass problem. To prove the validity of tracking strategy a practical roll-pitch seeker was accomplished. Model identification and common PID controllers for the physical roll-pitch seeker are taken on after that both disadvantages derived from zenith pass problem in tracking process and meliorated phenomenons by the tracking strategy are shown. It is concluded that the tracking strategy designed for solving the zenith pass problem is efficient. 2011 Elsevier Masson SAS. All rights reserved.

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：40/0 | 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.

The aircraft autopilot design of parameters changing in a wide range (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
Zhen D.; Yue Z.

收藏 | 浏览/下载：28/0 | 提交时间：2013/03/25

Autopilot is an important part of aircraft Under the action of the disturbance torque for the flight parameters of aircraft Changing in a wide range the range was about 16km on the basic of analyzing the typical trajectory the max height was about 5100m the trajectory of feature points were selected the deviation of lateral was about 12m taking pitch control loop for example the maximum angle of attack was about 3.6 a sub- PID autopilot was designed using classical control theory the maximum elevator deflection was less than 5 using single-mode Transient suppression method the maximum aileron deflection was less than 2 the overload due to control surface transition deflection was avoided when control parameters changing the maximum roll was less than 5 the verification was done by non-linear simulation. The result showed that: the phase margin of autopilot was greater than 30 the response of overload can accurately track the given overload instruction. An autopilot design method of aircraft of parameter changes in a wide range was provided. 2011 IEEE. the bandwidth was more than 14rad / s the settling time was less than 0.7s the maximum overshoot was 23.3%

The ship-borne infrared searching and tracking system based on the inertial platform (EI CONFERENCE) 会议论文 OAI收割
International Symposium on Photoelectronic Detection and Imaging 2011: Advances in Infrared Imaging and Applications, May 24, 2011 - May 24, 2011, Beijing, China
作者: Li Y.; Zhang H.; Zhang H.; Li Y.; Li Y.

收藏 | 浏览/下载：38/0 | 提交时间：2013/03/25

As a result of the radar system got interferenced or in the state of half silent it can cause the guided precision drop badly In the modern electronic warfare therefore it can lead to the equipment depended on electronic guidance cannot strike the incoming goals exactly. It will need to rely on optoelectronic devices to make up for its shortcomings but when interference is in the process of radar leading especially the electro-optical equipment is influenced by the roll pitch and yaw rotation it can affect the target appear outside of the field of optoelectronic devices for a long time so the infrared optoelectronic equipment can not exert the superiority and also it cannot get across weapon-control system "reverse bring" missile against incoming goals. So the conventional ship-borne infrared system unable to track the target of incoming quickly the ability of optoelectronic rivalry declines heavily.Here we provide a brand new controlling algorithm for the semi-automatic searching and infrared tracking based on inertial navigation platform. Now it is applying well in our XX infrared optoelectronic searching and tracking system. The algorithm is mainly divided into two steps: The artificial mode turns into auto-searching when the deviation of guide exceeds the current scene under the course of leading for radar.When the threshold value of the image picked-up is satisfied by the contrast of the target in the searching scene the speed computed by using the CA model Least Square Method feeds back to the speed loop. And then combine the infrared information to accomplish the closed-loop control of the infrared optoelectronic system tracking. The algorithm is verified via experiment. Target capturing distance is 22.3 kilometers on the great lead deviation by using the algorithm. But without using the algorithm the capturing distance declines 12 kilometers. The algorithm advances the ability of infrared optoelectronic rivalry and declines the target capturing time by using semi-automatic searching and reliable capturing-tracking when the lead deviation of the radar is great. 2011 Copyright Society of Photo-Optical Instrumentation Engineers (SPIE).

Control method research on wide flight envelope aerocraft (EI CONFERENCE) 会议论文 OAI收割
2nd Annual Conference on Electrical and Control Engineering, ICECE 2011, September 16, 2011 - September 18, 2011, Yichang, China
作者: Duan Z.

收藏 | 浏览/下载：28/0 | 提交时间：2013/03/25

The flying qualities of aerocraft was directly effected by the autopilot for the wide flight envelope aerocraft on the basic of analyzing the typical trajectory the three loop autopilots of roll stability pitch and yaw were designed using single-mode Transient suppression method the overload due to control surface transition deflection was avoided when control parameters changing the verification was done by non-linear simulation. The result showed that: Under the action of the disturbance torque the maximum roll was less than 5 the range of the aerocraft was from 13.5km to 22.4km the max height was about 5100m the max deviation of lateral was about 42m the maximum elevator deflection was less than 6.5 the control law was applicable within the effective range. An autopilot design method of wide flight envelope aerocraft was provided. 2011 IEEE.