Effects of thrust vector control on the performance of the aerobang orbital plane change maneuver
Authors
Johnson, Richard E.
Subjects
Aerobang
Synergetic
Aero-assist
MRRV
Synergetic
Aero-assist
MRRV
Advisors
Ross, I. Michael
Date of Issue
1993-06
Date
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
The aerobang maneuver, one of three types of aero-assisted orbital change methods, holds the possibility of reducing fuel consumption for orbital craft capable of atmospheric entry. It has been previously shown that different types of vehicles provide varying results over a constant heating rate trajectory. Further investigation into the optimization of the aerobang maneuver in this thesis includes the effects of using thrust vector control, the examination of the effects of increasing fuel mass fraction to increase orbital inclination changes, and the effects of that increase on both angle of attack and heating rate. The aerobang maneuver is shown to be capable of significant changes in orbital inclination in either a fixed heating rate or a fixed angle of attack mode for the Maneuverable Reentry Research Vehicle
Type
Thesis
Description
Series/Report No
Department
Astronautical Engineering
Organization
Naval Postgraduate School
Identifiers
NPS Report Number
Sponsors
Funding
Format
63 p.
Citation
Distribution Statement
Approved for public release; distribution is unlimited.