Comparison of Orbit Transfer Vehicle Concepts Utilizing Mid-Term Power and Propulsion Options
Abstract
The recent announcement of a national nuclear space flight initiative1 has rekindled interest in nuclear propulsion options within the spacecraft propulsion community. Therefore, the Air Force Research Laboratory Propulsion Directorate (AFRL/PRSS) has decided to reexamine the value of utilizing nuclear propulsion for orbit transit and the repositioning of luture Air Force space assets. A trade study was conducted with the assumption that technologies had matured to the 2010 level. A comparison was made between advanced chemical, solar thermal, solar electric, and nuclear electric for both expendable and reusable mission concepts, with a particular interest in options that resulted in trip times of 30 days or less. Results show that for expendable stages both solar thermal and, to a greater degree, solar electric propulsion systems can provide a significant increase in payload delivered from LEO to GEO within the required trip times. The solar electric concepts utilize clustered Hall thrusters, thin film photovoltaic solar arrays for power generation, and advanced power processing topologies for power conversion. The nuclear electric option became advantageous for trip times greater than 30 days. For reusable vehicles, where payload and fuel are supplied to a reusable propulsion tug module, similar results were calculated based on trip time.
Document Details
- Document Type
- Technical Report
- Publication Date
- May 14, 2002
- Accession Number
- ADA406811
Entities
People
- Frank S. Gulczinski Iii
- John H. Schilling
Organizations
- Air Force Research Laboratory