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.
Out-of-Ecliptic Using Ariane Launch Vehicle. Volume 1: Executive Summary
1977
59 pages
Report
No indication
English
Space Launch Vehicles & Support Equipment , Astronautics , 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 , Great Britain