Interplanetary mission possibilities with Ariane

Performance parameters of the Ariane 3 launcher which affect its capability as a vehicle for satellites intended for escape trajectories are discussed. The AR 3 is not currently configured to have a restartable third stage, and attention is given to mass penalties incurred in attempting a direct launch to escape without a coast phase. Considering the location of the Kourou launch site, it is shown that a minimum inclination of 5.23 deg is required for a hyperbolic departure orbit if payload mass penalties are to be avoided. A limiting factor is also derived for the orbit perigee. Addition of a fourth stage to increase the payload mass and launch window opportunities is mentioned, and an analysis of a Mars orbiter for the Kepler-Mars project is presented. Finally, consideration is given to the feasibility of dedicated Ariane launches for placing two spacecraft in geosynchronous transfer orbit, where they would rendezvous.