机构

• 长春光学精密机械与物... [2]

采集方式

• OAI收割 [2]

内容类型

• 会议论文 [2]

发表日期

• 2011 [2]

学科主题

筛选

浏览/检索结果: 共2条，第1-2条 帮助 条数/页： 5101520253035404550556065707580859095100 排序方式： 请选择题名升序题名降序提交时间升序提交时间降序作者升序作者降序发表日期升序发表日期降序 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%   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：27/0  |  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.