Onboard Stability Control System for a Flapping Wing Nano Air Vehicle

Abstract

This paper describes the design and development of a feedback system for controlling the dynamics of a flapping wing nano air vehcile (NAV). A model of the vehicle dynamics and models of sensors and unique actuator mechanisms are built. An extended Kalman filter is designed to eliminate the effects of sensor bias on state estimation. Results of this study demonstrate stability and yield responses that are approaching desired performance capabilities.

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Document Details

Document Type
Technical Report
Publication Date
Apr 24, 2009
Accession Number
ADA499960

Entities

People

  • Jason Geder

Organizations

  • United States Naval Research Laboratory

Tags

Communities of Interest

  • Materials and Manufacturing Processes
  • Sensors
  • Space

DTIC Thesaurus Topics

  • Aerodynamic Forces
  • Aircrafts
  • Algorithms
  • Automatic Pilots
  • Closed Loop Systems
  • Command And Control
  • Control Systems
  • Coordinate Systems
  • Diagrams
  • Equations
  • Filters
  • Filtration
  • Fluid Dynamics
  • Kalman Filters
  • Measurement
  • Simulations
  • Vehicles

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