Control Limitations on Static Unstable Airframe Using Two-Loop Acceleration Autopilot

Jiang Wang; De Fu Lin; Jun Fang Fan

doi:10.4028/www.scientific.net/AMR.383-390.4385

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HomeAdvanced Materials ResearchAdvanced Materials Research Vols. 383-390Control Limitations on Static Unstable Airframe...

Control Limitations on Static Unstable Airframe Using Two-Loop Acceleration Autopilot

Abstract:

An analysis for controlling a static-unstable tactical missile using two-loop acceleration autopilot was detailed. The rate feedback loop was firstly presented. The equivalent actuator dynamics was introduced and examined. Thus an overall stabilization condition combined with both low and high frequency cases was proposed. The lever effect led by inertial measurement unit was of benefit to a great controllable range. The results show that the autopilot control capacity is dominated by actuator bandwidth, and a compromise should be determined between the flight performance and the actuator requirement for a static unstable tactical missile.

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Periodical:

Advanced Materials Research (Volumes 383-390)

Pages:

4385-4390

DOI:

https://doi.org/10.4028/www.scientific.net/AMR.383-390.4385

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Online since:

November 2011

Authors:

Jiang Wang, De Fu Lin, Jun Fang Fan

Keywords:

Actuator, Autopilot, Control Limitation, Lever Effect

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References

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