中国科学院机构知识库网格系统: 检索

Incorporating environmental impacts into zero-point shifting diagnosis of wind turbines yaw angle 期刊论文 OAI收割
ENERGY, 2022, 卷号: 238
作者: Yang, Jian; Wang, Li; Song, Dongran; Huang, Chaoneng; Huang, Liansheng

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收藏 | 浏览/下载：79/0 | 提交时间：2021/11/01

Wind turbines Yaw angle Zero-point shifting Air temperature Turbulence intensity

LOS rate reconstruction and application of roll-pitch seeker (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
Yang C.; Zhang N.; Jia H.

收藏 | 浏览/下载：22/0 | 提交时间：2013/03/25

Frame motion form of roll-pitch seeker is introduced in this paper. There is corresponding relationship between the frame angle of the roll-pitch seeker and the traditional yaw-pitch seeker. The discrepancy of line-of-sight (LOS) rate of the two seekers is caused by the different frame motion forms. LOS rate reconstruction method of roll-pitch seeker is deduced. Compared to the pure proportional navigation guidance law the true proportional navigation guidance law is more suitable for the roll-pitch seeker missile guidance. 2011 IEEE.

Gimbal displacement error analysis on an electro-optical seeker (EI CONFERENCE) 会议论文 OAI收割
Optical Design and Testing IV, October 18, 2010 - October 20, 2010, Beijing, China
作者: Zhang X.; Zhang X.; Zhang X.

收藏 | 浏览/下载：35/0 | 提交时间：2013/03/25

It is essential to analyze the gimbal displacement errors for a seeker due to the importance for cueing of targets and tracking for the final approach. Otherwise for a seeker electro-driven with a concentric glass dome the large errors will decrease the picking pointing and tracking precision rooted from the displacement errors existing between the rotation center of the optical system and the gimbal. And the gimbaled camera system displacement errors are never eliminated but reduced due to the geometric errors consists of geometric tolerances of gimbal structure manufacture installation and vibration coming from working environment. In this paper the gimbal displacement errors in an electro-optically stabilized platform resulting from geometric errors and environment errors were analyzed and shown in detail. The mathematical modal of the gimbal displacement errors created based on multi-body dynamics demonstrated the connection between the gimbal displacement errors and the stabilized platform. Taking a visible light image seeker as a case the diameter is 120mm and the geometric tolerances came from the values of primary design and the vibration data came from the environmental vibration test on the pitch-yaw seeker and at the same time the errors resulting from installation were considered too. Based on calculating the maximum gimbal displacement error will reach to 0.2mm for pitching angle smaller than 40 and yawing angle smaller than 60. However the critical parts have been found out according to the probability theory and the reliability analysis successfully used in the paper and finally the maximum gimbal displacement error reduced to 0.1mm which is acceptable corresponding to the picking pointing and tracking precision for an optical imaging seeker. 2010 Copyright SPIE - The International Society for Optical Engineering.

Research of programming about the level flight of aircraft (EI CONFERENCE) 会议论文 OAI收割
2010 3rd International Conference on Advanced Computer Theory and Engineering, ICACTE 2010, August 20, 2010 - August 22, 2010, Chengdu, China
作者: Lijiang

收藏 | 浏览/下载：25/0 | 提交时间：2013/03/25

In order to carries on the plan and the control to aircraft level flight then obtain that the factors control the level route are the route position and the radius of turn finally carries on the software simulation using this algorithm the attitude and the route has been analyzed. First obtain that the factors control the level attitude are the roll angle and the yaw angle and infers the algorithm of flight route according to the attitude and the route restraint and infers the computation algorithm of attitude produce shortest aircraft level flight road map which through the giving route position on the software surface. According to this algorithm it may control and plan the aircraft level flight through to limit of the aircraft security attitude and the route position. 2010 IEEE.

The method on the measurement of the aircraft attitude by the spatial cosines relationship of the single station and planes to the intersection the multi-station of electro-optical theodolite (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
Zhao L.-R.; Cao Y.-G.

收藏 | 浏览/下载：17/0 | 提交时间：2013/03/25

In order to realize the aircraft attitude measurement The paper advances electro-optical theodolite methods of measuring the aircraft attitude by using the spatial cosines relationship the single station theodolite and how to use intersection of the multi-station theodolite. The single station theodolite was introduced in a measured distance from the aircraft posture information. An exhaustive approach was used to access to the aircraft axis of the feature points and the location in the space was used to obtain space posture parameters. The multi-station theodolite was introduced to get the information of the aircraft flight attitude by method of using planes to the intersection. Two-dimensional image to obtain objective axis by fitting algorithm using Hough transform. And then Calculate the vertical distance of the origin to the target of the central axis and the origin to the target of the central axis of the angle between the normal and the X-axis obtaining the linear equation in the two-dimensional plane. Two-dimensional axis of the target image and the camera system's optical center only identified a space plane. The aircraft yaw axis angle and pitch angle can be obtained by getting the space axis using plains to the intersection method. Experimental results show that attitude angle error of the single station theodolite is less than 1 when its distance is less than 6000m and attitude angle error of the multi-station theodolite is less than 0.6 when its intersection angle is between 30 and 150. In this paper according to test result of precision comparing the mathematical model is correct and the algorithm is reasonable in extracting effective parameters of the aircraft's attitude. 2010 IEEE.

Attitude determination of small, dim and high-speed targets based on multi-CMOS intersecting system (EI CONFERENCE) 会议论文 OAI收割
2nd International Conference on Information Science and Engineering, ICISE2010, December 4, 2010 - December 6, 2010, Hangzhou, China
作者: Li M.; Zhao L.; Wang J.

收藏 | 浏览/下载：34/0 | 提交时间：2013/03/25

In order to measure attitude of small dim and high-speed targets in shooting range intersecting system based on multiple high-speed CMOS cameras was introduced in this paper. CMOS cameras were laid near from objects for small size using multiple CMOS cameras to compose intersecting system for big number of targets tested and selecting CMOS camera between CMOS and CCD for low cost and considering damage to measurement equipment of objects tested. Pitch angle and yaw angle were measured by extracting axle wire through image processing image sequences were obtained from cameras laying on two sides. Velocity of objects was calculated by least square curve-fitting acquiring coordinate of centroid on image received by CMOS camera laying below effective viewing field. One CMOS camera was laid on right ahead for measuring roll angle. Station mode introduced in this paper has virtue of low cost and free extending. 2010 IEEE.

Real-time adjusting of yaw angle of space camera based on General Image-Quality Equation (EI CONFERENCE) 会议论文 OAI收割
2009 2nd International Conference on Intelligent Computing Technology and Automation, ICICTA 2009, October 10, 2009 - October 11, 2009, Changsha, Hunan, China
作者: Wang J.; He X.; Xu S.

收藏 | 浏览/下载：23/0 | 提交时间：2013/03/25

A Strategy of Real-Time Adjusting of Yaw Angle (SRTAYA) of space camera was proposed base on General Image-Quality Equation (GIQE). During space camera imaging yaw angle which is caused by rotation of the earth and the gesture changing of satellite impacts integral aspect of TDI (Time Delay and Integration) CCD (Charge Couple Device) so that the image quality degrades. For extending imaging time of space camera and enhancing image quality yaw angle must be adjusted. The descending value of GIQE reflects the degrading quantity of image quality. The SRTAYA calculated an acceptable augmenting value of yaw angle according with a specific value of GIQE which the degrading of image quality can't be neglected no longer. The example which actualized a practical orbit of satellite illuminated that the SRTAYA could limit the value of yaw angle less than 318.45". 2009 IEEE.

Three-dimensional angle measurement based on auto-collimation and moire fringe (EI CONFERENCE) 会议论文 OAI收割
2008 International Conference on Optical Instruments and Technology: Optoelectronic Measurement Technology and Applications, November 16, 2008 - November 19, 2008, Beijing, China
Cai S.; Liang S.; Qiao Y.-F.

收藏 | 浏览/下载：30/0 | 提交时间：2013/03/25

A method for small three-dimensional (3D) angle measurement based on auto-collimation and moire fringe is proposed and analyzed. A right-angle prism is used as the indicator of angle change. The inclined plane indicates the pitch and yaw angles and roll angle in indicated by the rib which is the intersection of two right-angle sides. Pitch and yaw angles measurement are implemented by auto-collimation based on reticule and roll angle measurement is measured based on moire fringe. Roll angle measurement is separated from pitch and yaw by using two light sources with different frequencies. Any small change of pitch and roll angles will induce the shift of the reticule image after reflecting by inclined plane. And any small roll angle will induce a change in moire fringe width that is generated by scale grating image which is reflected by the prism and index grating. The math model of this method is built up and error analysis is presented. The theoretical calculation results show that the proposed method is feasible and can achieve high accuracy. 2009 SPIE.

Feedback control for yaw angle with input nonlinearity via input-state linearization 会议论文 OAI收割
IEEE International Conference on Robotics and Biomimetics (ROBIO 2006), Kunming, China, December 17-20, 2006
作者: Jiang Z(姜哲); Qi JT(齐俊桐); Zhao XG(赵新刚); Wang H(王贺); Han JD(韩建达)

收藏 | 浏览/下载：20/0 | 提交时间：2012/06/06

dynamics feedback linearization input nonlinearity helicopter yaw angle

Robust adaptive single neural control for yaw angle with input nonlinearity on helicopter testbed 会议论文 OAI收割
9th International Conference on Control, Automation, Robotics and Vision, Singapore, SINGAPORE, December 5-8, 2006
作者: Jiang Z(姜哲); Zhao XG(赵新刚); Han JD(韩建达); Wang YC(王越超)

收藏 | 浏览/下载：18/0 | 提交时间：2012/06/06

adaptive neural control yaw angle input nonlinearity helicopter testbed