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Optimal Spacecraft Attitude Controlusing Aerodynamic Torques

Optimal Spacecraft Attitude Controlusing Aerodynamic Torques

Hardcover

Technology & EngineeringAstronomy & Space

ISBN10: 1025121023
ISBN13: 9781025121024
Publisher: Hutson Street Press
Published: May 22 2025
Pages: 92
Weight: 0.68
Height: 0.25 Width: 6.14 Depth: 9.21
Language: English

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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