Date of Award

3-1999

Document Type

Thesis

Degree Name

Master of Science

Department

Department of Aeronautics and Astronautics

First Advisor

William E. Wiesel, PhD

Abstract

This study investigates the ability of the proposed Liquid Fly Back Booster, a replacement for the Space Shuttle's Solid Rocket Boosters (SRBs), to eliminate the need for the Return to Launch Site (RTLS) abort mode. A Fortran model of a nominal launch trajectory was perturbed to simulate a single Space Shuttle Main Engine-out (SSME-out) abort scenario at different times in the launch with the goal being to abort to the southern most landing site possible. The model accounts for vehicle lift, drag, dynamic pressure, throttling times and includes atmospheric effects to enhance fidelity. Results show the RTLS abort mode can be eliminated and successful landings made as far south as Savannah, Georgia. This success is attributed to the throttling capability of the Liquid Fly Back Booster engines.

AFIT Designator

AFIT-GSO-ENY-99M-07

DTIC Accession Number

ADA361613

Comments

The author's Vita page is omitted.

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