Date of Award

3-2025

Document Type

Dissertation

Degree Name

Doctor of Philosophy (PhD)

Department

Department of Aeronautics and Astronautics

First Advisor

Robert A. Bettinger, PhD

Abstract

A modeling simulation tool for exo-to-endo atmospheric flight is developed to characterize errors associated with varying simulation fidelities from 3 to 6 degrees-of-freedom (DOF). Engineering approximation errors are quantified and compared with flight data from Apollo 10 and the first Space Shuttle Orbiter reentry (STS-1). The reentry reachability optimal control problem (OCP) is formulated in 6DOF and compared with point-mass solutions, revealing that point-mass solutions oversimplify the problem. A cylindrical reentry vehicle (CRV-1), similar to the SpaceX Starship, is introduced with necessary details for 6DOF analysis. The performance and reentry control capabilities of CRV-1 are captured through 6DOF solutions of the reentry reachability OCP, demonstrating cross-range maneuvers exceeding 2,200 km. Finally, the controllability of the CRV design is showcased in a simulation where a heavy mass payload of 65,000 kg is shifted mid-flight. The simulation results indicate that 1 m lateral offsets are permissible, and control solutions can be found with minimal impact on guidance tracking errors.

AFIT Designator

AFIT-ENY-DS-25-M-162

DTIC Accession Number

AD1356396

Comments

An embargo was observed for posting this dissertation on AFIT Scholar.

Distribution A: Approved for Public Release, Distribution Unlimited.

PA clearance case 88ABW-2025-0470

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