System level aspects of an out-of-ecliptic mission using the Ariane launch vehicle are discussed. They include: mission analysis and overall mission performance; configuration selection and description of the preferred solution; overall mass and power budgets; reliability analysis; radiation levels and protection; development plan; and cost estimates. It is concluded that a spacecraft using predominantly European hardware, but excluding the RTG, could be developed for a cost of some 38 MAU at mid 1975 rates (Phase C/D) to achieve a maximum heliographic latitude of just under 70 deg, using a Delta Vega type orbit, giving a total mission lifetime of about 6 years.
Out-of-Ecliptic Using Ariane Launch Vehicle. Volume 2: Systems Studies
1977
203 pages
Report
Keine Angabe
Englisch
Space Launch Vehicles & Support Equipment , Astronautics , Ariane launch vehicle , Interplanetary flight , Payloads , Space missions , Systems analysis , Cost estimates , Ecliptic , Mission planning , Radiation effects , Reliability analysis , Spacecraft configurations , Spacecraft design , Swingby technique , Great Britain