Multi-objective control of aerodynamically unstable launcher

被引：0
|
作者：
Khalate, Amol A. [1 ]
Naseer, Abdul [2 ]
Jose, Sheelu [1 ]
Dhekane, M. V. [1 ]
机构：
[1] ISRO, Vikram Sarabhai Space Ctr, Control Design Div, Thiruvananthapuram, Kerala, India
[2] Engn Coll, Dept Elect Engn, Thiruvananthapuram, Kerala, India
来源：
2007 MEDITERRANEAN CONFERENCE ON CONTROL & AUTOMATION, VOLS 1-4 | 2007年
关键词：
D O I：
暂无
中图分类号：
TP [自动化技术、计算机技术];
学科分类号：
0812 ;
摘要：
This paper deals with the attitude stabilization problem of highly aerodynamically unstable launch vehicle during atmospheric phase. The autopilot design is characterized by classical requirements such as Aero Margin (AM), Gain Margin GM), and Phase Margin (PM) as well as time-domain constraints on the response of angle of attack to a worst-case wind profile. These robustness requirements are difficult to meet during atmospheric phase when launcher is highly aerodynamically unstable. An autopilot has been designed by multi-objective control technique based on H. control theory for rigid body dynamics of launcher during high dynamic pressure region. To show the efficacy of the multi-objective controller, the design has been compared with an H. and classical controller.
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页码：134 / +
页数：2
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