Automated Flight Control Design for Guided Munitions

Abstract

The objective of this effort is to efficiently design flight controllers for different vehicle configurations to satisfy performance requirements. Optimal control and linear system analysis techniques are applied to a demonstration vehicle consisting of onboard inertial sensors and four independently actuated canards. The controller gains are automatically computed using pole placement with the linearized system dynamics and desired rise time, settling time, and overshoot. Linear and nonlinear controlled flight simulations were performed with control gains determined using the automated routine. Results show the utility of this method and quantifies how well the linearization characterizes the nonlinear system dynamics.

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Document Details

Document Type
Technical Report
Publication Date
Sep 01, 2019
Accession Number
AD1081091

Entities

People

  • Luisa Fairfax

Organizations

  • United States Army Research Laboratory

Tags

DTIC Thesaurus Topics

  • Actuators
  • Algorithms
  • Closed Loop Systems
  • Control Systems
  • Dynamics
  • Eigenvalues
  • Feedback
  • Linear Systems
  • Mach Number
  • Monte Carlo Method
  • Munitions
  • Nonlinear Systems
  • Projectiles
  • Simulations
  • Steady State
  • Transfer Functions
  • Trim Angle

Readers

  • Computational Modeling and Simulation
  • Control Systems Engineering.
  • Robotics and Automation.