QQ客服 官方微博 反馈留言

浏览/检索结果: 共5条，第1-5条 帮助 限定条件 内容类型：会议论文    专题：长春光学精密机械与物理研究所    第一署名单位    第一作者单位    通讯作者单位     已选(0)清除 条数/页：5101520253035404550556065707580859095100   排序方式：请选择作者升序作者降序题名升序题名降序发表日期升序发表日期降序提交时间升序提交时间降序 The hinge moment optimization of rudder base on CFD numerical simulation 会议论文 3rd International Conference on Advanced Design and Manufacturing Engineering, ADME 2013, July 13, 2013 - July 14, 2013, Anshan, China Zhang N.; Zhang Y. 收藏  |  浏览/下载：9/0  |  提交时间：2014/05/15 Numerical simulation on flight dynamic characteristics of elastic wing based on gust response 会议论文 3rd International Conference on Advanced Design and Manufacturing Engineering, ADME 2013, July 13, 2013 - July 14, 2013, Anshan, China Dong W. H.; Yang C. L.; Li Y. H.; Jia H. G. 收藏  |  浏览/下载：13/0  |  提交时间：2014/05/15 The aircraft autopilot design of parameters changing in a wide range (EI CONFERENCE) 会议论文 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：19/0  |  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 2011 International Conference on Electronics and Optoelectronics, ICEOE 2011, July 29, 2011 - July 31, 2011, Dalian, China Jiang H.; Jia H.; Wei Q. 收藏  |  浏览/下载：21/0  |  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 30th Chinese Control Conference, CCC 2011, July 22, 2011 - July 24, 2011, Yantai, China Qin S.; Gong Y.; Liu Y.; Wang Z.; Peng S. 收藏  |  浏览/下载：17/0  |  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.