The goal of this research is to formulate flight controllers for highly maneuverable munitions. Complex aerodynamic phenomena such as vortex interactions and flow separation exist on munitions flying at certain maneuvering conditions. Aerodynamic models are proposed to capture these mechanisms within an adaptive control framework. The adaptive control algorithm is derived and wrapped around a nominal optimal controller using inertial sensor feedback. The vehicle dynamics and flight control algorithms are implemented in simulation. Results indicate that only the adaptive algorithm recovers satisfactory control when encountering these complex aerodynamic phenomena.
Adaptive Missile Flight Control for Complex Aerodynamic Phenomena
2017
40 pages
Report
Keine Angabe
Englisch
ADAPTIVE MISSILE FLIGHT CONTROL FOR COMPLEX AERODYNAMIC PHENOMENA (AIAA 2017-4207)
British Library Conference Proceedings | 2017
|Comparison of Missile Flight-Test Drag with Aerodynamic Predictions
Online Contents | 1993
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