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This thesis introduces a method of three-axis spacecraft attitude
control using only aerodynamic torques. Attitude actuation is
achieved using four control panels mounted on the rear of a cubical
spacecraft bus. The controller consists of an outer loop using
linear state feedback to determine desired control torque and an
inner loop to choose appropriate control panel angles. The inner
loop uses a Jacobian-based approachto invert the nonlinear
relationship between panel angles and generated torque. Controller
performance is evaluated via simulations, which show that
three-axis control is possible over a range of initial angles and
angular rates. The analysis used partial accommodation theory as
the basis for aerodynamic torque calculations and assumed a
rotating atmosphere with an exponential density profile.
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