中国科学院机构知识库网格系统: 检索

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	A Torque Control Strategy for a Robotic Dolphin Platform Based on Angle of Attack Feedback 期刊论文 OAI收割 Biomimetics, 2023, 卷号: 8, 页码: 291 作者: Tianzhu Wang; Junzhi Yu; Di Chen; Yan Meng \| 收藏 \| 浏览/下载：11/0 \| 提交时间：2023/09/21 robotic dolphin torque control angle of attack motion improvement
	Infrared radiation characteristics of a hypersonic vehicle under time-varying angles of attack 期刊论文 OAI收割 CHINESE JOURNAL OF AERONAUTICS, 2019, 卷号: 32, 期号: 4, 页码: 861-874 作者: Chen, Biao; Niu, Qinglin; Yuan, Zhichao; Dong, Shikui \| 收藏 \| 浏览/下载：70/0 \| 提交时间：2019/06/20 Angle of attack Fluid-thermal interaction HTV-2 Hypersonic vehicle IR radiation Surface temperature
	Effects of Shock Impingement on Aerothermal and Aerodynamic Performance for High-pressure Capturing Wings 会议论文 OAI收割 Xiamen, China, 6-9 March 2017 作者: Li GL(李广利); Cui K(崔凯); Xiao Y(肖尧); Xu YZ(徐应洲) 收藏 \| 浏览/下载：42/0 \| 提交时间：2018/01/16 Aerodynamics Angle Of Attack Angle Of Attack Indicators Boundary Layers Drag Drag Coefficient High Pressure Effects Hypersonic Aerodynamics Hypersonic Flow Spacecraft
	Normal acceleration reduce guidanceand control for sub-orbit vehicle re-entry 会议论文 OAI收割 Xiamen, China, 6-9 March 2017 作者: Li WH(李文皓); Xiao XX(肖歆昕); Zhang H(张珩); Xiao XX(肖歆昕) 收藏 \| 浏览/下载：27/0 \| 提交时间：2018/01/16 Aerodynamics Air Navigation Angle Of Attack Control Surfaces Control Theory Degrees Of Freedom (Mechanics) Dynamic Models Flight Control Systems Flight Simulators Monte Carlo Methods Reentry Spacecraft Surface Reactions Uncertainty Analysis Vehicles
	The research of attack angle measurment of projectile with CCD vertical target system 会议论文 OAI收割 2011 international conference on advanced in control engineering and information science, dali, china, august 18-19, 2011 Wang M(王苗); Xu Wei 收藏 \| 浏览/下载：15/0 \| 提交时间：2011/12/26 CCD vertical target attack angle measurement analysis of accuracy
	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%
	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：29/0 \| 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.
	On optimal guidance arithmetic of Super-maneuverable aircraft (EI CONFERENCE) 会议论文 OAI收割 30th Chinese Control Conference, CCC 2011, July 22, 2011 - July 24, 2011, Yantai, China 作者: Liu Y.; Gong Y.; Wang Z.; Wang Z.; Liu Y. 收藏 \| 浏览/下载：24/0 \| 提交时间：2013/03/25 Due to the complexity of maneuverability Super-maneuver attack guidance of modern aircraft has become the most important function to be immediately solved and perfectly completed. Proceed from the maneuvering optimization position and based on the optimal control theory the optimal angle maneuver guidance arithmatic is proposed. On the basis of aircraft maneuver guidance algorithm we come up with a variety of constraint condition optimized index and optimization rule and present a set of steepest optimal angle maneuver guidance algorithm and the validity and feasibility of the steepest optimal angle maneuver guidance algorithm has been comfirmed by the super-maneuver guidance simulation. 2011 Chinese Assoc of Automati.