Abstract
Powered trajectory calculations have been carried out for missions from Earth to Venus, Mars, Jupiter and return. The procedure used was based upon an optimization that minimizes total energy requirements and maximizes payload. Data are presented which relate payload fraction, total mission time, and minimum specific power requirements. It is shown that propulsion plant weight-to-exhaust power ratios of 122 lb/kw and 22 lb/kw are adequate for missions ranging in difficulty from one-way trips to Mars with 10% payload fraction to round trips to Mars with 30% payload, respectively. In both cases the transfer is assumed to be between low altitade satellite orbits about the planets in question.
Sign-in/Register to access full text options 
Free) 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
