Adaptive Missile Flight Control for Complex Aerodynamic Phenomena

Abstract

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.

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Document Details

Document Type
Technical Report
Publication Date
Aug 09, 2017
Accession Number
AD1038103

Entities

People

  • Ben Gruenwald
  • Frank E. Fresconi
  • Jubaraj Sahu
  • Tansel Yucelen

Organizations

  • United States Army Research Laboratory

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Aerodynamic Loading
  • Aerodynamics
  • Algorithms
  • Angular Motion
  • Control Surfaces
  • Control Systems
  • Control Theory
  • Dynamics
  • Flow
  • Flow Separation
  • Fluid Dynamics
  • High Angles
  • Military Research
  • Munitions
  • Pressure Distribution
  • Simulations
  • Vehicles

Fields of Study

  • Engineering

Readers

  • Aerodynamics/Aeronautics.
  • Computer Networking
  • Team-Based Human-Centered Cognitive Task Decision Making and Information Performance.