Out-of-ecliptic using Ariane launch vehicle. Volume 1: Executive summary

Details Out-of-ecliptic using Ariane launch vehicle. Volume 1: Executive summary Out-of-ecliptic using Ariane launch vehicle. Volume 1: Executive summary

Nov 1977

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1977bac..reptq....s&link_type=abstract

Final Report, Phase A Study British Aircraft Corp. (Operating) Ltd., Bristol (England). Electronic and Space Systems Group.

Computer Science

Ariane Launch Vehicle, Interplanetary Spacecraft, Payloads, Space Missions, Cost Estimates, Ecliptic, Liquid Propellant Rocket Engines, Mission Planning, Spacecraft Configurations, Spacecraft Design, Spacecraft Orbits, Swingby Technique

Scientific paper

The work carried out on a phase A study of an out-of-ecliptic mission using the Ariane launch vehicle is reported. It comprises a single spacecraft with a model experiment payload similar to payload A of the earlier phase A studies, and uses a Delta Vega orbit to provide an adequate spacecraft mass for injection into the transfer orbit to Jupiter. This feature increases the complexity of the spacecraft by the addition of a 400 N bi-propellant rocket motor and increases the overall mission duration from launch to recrossing the ecliptic plane after solar passage to nearly 6 years. Using May 1983 launch opportunity, it is concluded that a useful payload could be carried which achieves a maximum heliographic latitude of about 70 deg, for a phase C/D industrial development program cost of about 38 MAU at mid 1975 rates.

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