This report describes the design of an attitude controller for an unpowered, winged re-entry vehicle. The decoupling of the symmetric and asymmetric motion makes it possible to design two separate controllers, one for the pitch motion and one for the lateral motion. The design of the controller, a Linear Quadratic Regulator, is based on linearization of the equations of motion and feedback of the attitude and angular rates. The gains appearing in the control laws are computed by defining a quadratic cost criterion and then solving the matrix Riccati equation. Results of the study include the step and ramp response of the two separate controllers and the flight along the nominal trajectory with the integrated controller. The deviations from the nominal trajectory are acceptable, so this controller can be used for a detailed sensitivity analysis.
Linear Quadratic Regulator Design for an Unpowered, Winged Re-Entry Vehicle
1997
162 pages
Report
No indication
English
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