BILEVEL OPTIMIZATION FOR FAST CONTROL MOMENT GYRO MANEUVERS

Agility is at the forefront of considerations on control moment gyro-equipped spacecraft. Common approaches to allocating control moment gyro gimbal rates for commanded body torques often sacrifice torque authority for straightforward, analytical methods that can be readily implemented in flight software. Full torque authority can be recovered by describing torque allocation as a constrained static optimization problem; previous efforts solved this problem by developing a set of algebraic differential equations that converge upon a solution. This thesis proposes a bilevel optimization problem, in which a higher-level minimum-time spacecraft reorientation problem encompasses the improved static optimization-driven steering logic at every point in a solution. Solutions to this problem are compared with the Moore-Penrose pseudoinverse in optimization and closed-loop guidance environments. It was observed that bilevel optimization solutions result in maneuver time decreases of up to 74% from closed-loop control. Maneuver optimization using pseudoinverse logic performed similarly well. This suggests that optimized maneuver planning is agnostic to the specific steering law used. Optimized solutions will plan a route to a target orientation that best accommodates the particular limitations and capabilities of a given steering law.

Department dc:contributor.department

Mechanical and Aerospace Engineering (MAE)

Grantor dc:publisher

Monterey, CA; Naval Postgraduate School

Year dc:date.issued

2024

Author dc:creator

• Zembruski, Miles S.

Advisor dc:contributor.advisor

• Karpenko, Mark

Statement dc:rights

• This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.

Handle dc:identifier.uri

https://hdl.handle.net/10945/73266

OAI identifier oai:identifier

oai:calhoun.nps.edu:10945/73266