Linear stability of USUSat using yaw-axis aerodynamic force maneuvering

This thesis explored the use of aerodynamic force maneuvering to control a small satellite relative to another while flying in formation. Relative acceleration was achievable by means of rotating the satellite about its yaw axis, thereby increasing or decreasing the spacecraft's relative ballistic coefficient. Use of a Linear Quadratic Regulator based on Hill's equations for orbital and relative motion control was investigated.; This controller was found to be nonrobust when applied to a variable density model simulation. This was due to the comparable values of neglected terms during the linearization of the relative equations of motion and available control acceleration, interconnectivity between the control forces on the y and z axes, and a mismatch between the controller constant density model and the variable density model used by the propagator. The simulation was stable for all nonlinear propagators and model components when a constant aerodynamic density model was used.