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	Theoretical Analysis Method for Roll Motion of Popup Data Communication Beacons 期刊论文 OAI收割 Journal of Marine Science and Engineering, Journal of Marine Science and Engineering, 2023, 2023, 卷号: 2023, 2023, 期号: 11（6）, 页码: 1193, 1193 作者: Tian Chuan; Song YJ(宋元杰) \| 收藏 \| 浏览/下载：10/0 \| 提交时间：2023/08/29 PDCB PDCB roll angle Morrison theoretical formula additional inertia moment computational fluid dynamics roll angle Morrison theoretical formula additional inertia moment computational fluid dynamics
	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：43/0 \| 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：30/0 \| 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%
	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：24/0 \| 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.
	Analysis of zenith pass problem in a roll-pitch optics seeker (EI CONFERENCE) 会议论文 OAI收割 2011 International Conference on Electronics and Optoelectronics, ICEOE 2011, July 29, 2011 - July 31, 2011, Dalian, China 作者: Jiang H. 收藏 \| 浏览/下载：36/0 \| 提交时间：2013/03/25 There are mainly two kind of structures for a missile two-axes seeker which is always mentioned as elevate-azimuth and roll-pitch. The elevate-azimuth structured seeker has been studied for a long time and it is applied in all sort of missiles. Not only structure design but also control algorithm of the elevate-azimuth seeker are deeply developed. But for elevate-azimuth seeker there are several disadvantages such as big size and large abaxial angle blind. So the elevate-azimuth seeker gimbal angle is designed up to 65 according to relative references. In modern air war it is important for a missile to have the ability of "first recognize" and "first attack". That means the air to air missile seeker is required to be a system with large gimbal angle and large abaxial launch angle. With the mentioned requirement roll-pitch seeker with its advantages smart size and large gimbal angle is studied widely and deeply. The pitch angle of roll-pitch is up to 90 while its roll angle up to n 360. But there are also some disadvantages for the roll-pitch seeker the most troublesome one is the zenith pass problem. The zenith pass problem is brought about from the gimbal kinematics it is said that when target moves in the center of image plane roll servo command gotten from the kinematics algorithm will go to infinite. Math model of zenith pass problem is proposed in this paper and two ways to solve the problem are brought forward. 2011 IEEE.
	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：27/0 \| 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.
	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：37/0 \| 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.
	Small roll angle measurement based on auto-collimation and moire fringe (EI CONFERENCE) 会议论文 OAI收割 2009 International Conference on Optical Instruments and Technology - Optoelectronic Measurement Technology and Systems, October 19, 2009 - October 22, 2009, Shanghai, China Bai X.-G.; Cai S.; Qiao Y.-F.; Dai M. 收藏 \| 浏览/下载：35/0 \| 提交时间：2013/03/25 A novel method for small roll angle measurement based on auto-collimation and moire fringe is presented. A right-angle prism is used as an indicator of small roll angle around the optical axis and a CCD is used to collect moire fringes that are generated by scale grating image which is reflected by prism and index grating. Any small roll angle of the prism will change the include angle of the grating pair and meanwhile induce a change in the moire fringe period. The relationship between roll angle and period of moire fringes is established. The period data is obtained by image processing. The experimental result certifies that the principle of small angle measurement method based on auto-collimation and moire fringe is correct and feasible. The measuring error is smaller than 0.2 within 7 range compared with 0.2 autocollimator. 2009 SPIE.
	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：37/0 \| 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.