Date of Award

3-7-2007

Document Type

Thesis

Degree Name

Master of Science in Astronautical Engineering

Department

Department of Aeronautics and Astronautics

First Advisor

Nathan A. Titus, PhD

Abstract

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 approach to 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.

AFIT Designator

AFIT-GA-ENY-07-M08

DTIC Accession Number

ADA469919

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