A Comparison of Nuclear and Chemical Propulsion Upper-Stage and Launch Systems for LEO to GEO Orbital Transfers Lockheed Missiles and Space Company

Format:

Conference/Event

Author/Creator:

Bailey, Patrick G., author.

Conference Name:

27th Intersociety Energy Conversion Engineering Conference (1992) (1992-08-03 : San Diego, California, United States)

Language:

English

Physical Description:

1 online resource

Place of Publication:

Warrendale, PA SAE International 1992

Summary:

Comparisons are given between various launch vehicles, transfer vehicles, and propulsion methods to launch satellites into low Earth orbital parking orbits and then into a final geosynchronous orbit. The studies indicate that a Thermionic Space Nuclear Power System (TI-SNPS) can have significant advantages over solar array power systems for both orbital transfer capabilities and mission applications. Also, by utilizing a relatively inexpensive Atlas IIAS launch vehicle, a particular TI-SNPS hybrid design with a specific impulse of 950 sec can place a satellite weighing 3,511 kg into GEO orbit, as compared to only a corresponding 1,104 kg satellite capability when using conventional chemical propulsion techniques

Notes:

Vendor supplied data

Publisher Number:

929505

Access Restriction:

Restricted for use by site license