Missile autopilot design using optimal control and frequency constraint

Author

Fan Jun-fang ; Lin De-fu ; Qi Zai-kang ; Wang Jiang

Author_Institution

Dept. of Flying Vehicle Eng., Beijing Inst. of Technol., Beijing

fYear

2008

fDate

10-12 Dec. 2008

Firstpage

1

Lastpage

6

Abstract

The benefits of relaxed static stability on missile were examined. Based on optimal control and open-loop crossover frequency constraint, an acceleration autopilot design methodology was developed and applied to a highly unstable airframe. Performance and robustness comparisons for three autopilot topologies were made. The analysis reveals the topology origin of classic three-loop autopilot, and simulation results show that the four-loop topology looks very promising.

Keywords

control system synthesis; missile guidance; open loop systems; optimal control; robust control; acceleration autopilot design methodology; autopilot topologies; four-loop topology; missile autopilot design; open-loop crossover frequency constraint; optimal control; relaxed static stability; robustness; three-loop autopilot; unstable airframe; Acceleration; Aerodynamics; Equations; Frequency; Missiles; Optimal control; Robust stability; Robustness; Topology; Vehicles; autopilot; frequency constraint; optimal control; optimization; static unstable missile;

fLanguage

English

Publisher

ieee

Conference_Titel

Systems and Control in Aerospace and Astronautics, 2008. ISSCAA 2008. 2nd International Symposium on

Conference_Location

Shenzhen

Print_ISBN

978-1-4244-3908-9

Electronic_ISBN

978-1-4244-2386-6

Type

conf

DOI

10.1109/ISSCAA.2008.4776240

Filename

4776240