Nuclear electric propulsion mission to NeptuneA nuclear electric propulsion (NEP) mission to Neptune is studied. Results of trajectory and propulsion parameter optimization are presented which lead to a selection of key electric propulsion system parameters. Spiral earth escape and spiral capture modes are assumed in the optimization studies. Flight time vs payload for Space Transportation System (STS)/Centaur injection and Triton-aided orbit capture at Neptune are also briefly investigated as methods of improving mission performance. Radiation effects of the earth spiral phase are discussed. The effects of NEP technology on science payloads and mission and system designs are evaluated. NEP is shown to be a very flexible and high performing propulsion technology.
Document ID
19830031241
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Nock, K. T. (Jet Propulsion Lab., California Inst. of Tech. Pasadena, CA, United States)
Garrison, P. W. (California Institute of Technology, Jet Propulsion Laboratory, Pasadena CA, United States)
Date Acquired
August 11, 2013
Publication Date
November 1, 1982
Subject Category
Astronautics (General)
Report/Patent Number
AIAA PAPER 82-1870
Meeting Information
Meeting: Japan Society for Aeronautical and Space Sciences, and DGLR, International Electric Propulsion Conference