Automated Flight Control Design for Guided Munitions
Technical Report,01 Jun 2017,01 Sep 2019
CCDC Army Research Laboratory Aberdeen Proving Ground United States
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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.
- Guided Munitions