Accession Number : ADA336420
Title : Optimal Orbit Insertion Strategies Using Combined High and Low Thrust Propulsion Systems
Descriptive Note : Master's thesis
Corporate Author : AIR FORCE INST OF TECH WRIGHT-PATTERSONAFB OH SCHOOL OF ENGINEERING
Personal Author(s) : Johnson, Darren W.
PDF Url : ADA336420
Report Date : DEC 1997
Pagination or Media Count : 101
Abstract : Low thrust electric propulsion systems are becoming sufficiently mature to consider their use as primary propulsion for orbital transfer in place of high thrust chemical systems. Instead of facing an either/or situation, it may be advantageous to use both types. This effort demonstrates a technique for finding orbital transfer strategies that use both high and low thrust propulsion systems and which result in optimal tradeoffs of the performance parameters cost of orbit insertion, total orbit transfer time, and available spacecraft mass at final orbit. These performance parameters are calculated as a function of the fraction of orbit transfer from Low Earth Orbit (LEO) to Geosynchronous Earth Orbit (GEO) provided by electric propulsion. Utility analysis is used to analyze each performance parameter and compute a total utility score for each orbit insertion strategy examined. Results from a variety of example space mission profiles yielded optimal orbit insertion strategies requiring both chemical and electric propulsion to provide a fraction of the LEO to GEO orbit transfer.
Descriptors : *EARTH ORBITS, *ELECTRIC PROPULSION, *TRANSFER TRAJECTORIES, OPTIMIZATION, LOW ORBIT TRAJECTORIES, THESES, THRUST CONTROL, SPACE MISSIONS, LAUNCH VEHICLES, SPECIFIC IMPULSE.
Subject Categories : Electric and Ion Propulsion
Spacecraft Trajectories and Reentry
Distribution Statement : APPROVED FOR PUBLIC RELEASE