Computer Science – Performance
Scientific paper
Sep 1982
adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1982pari.iafcu....j&link_type=abstract
International Astronautical Federation, International Astronautical Congress, 33rd, Paris, France, Sept. 27-Oct. 2, 1982, 18 p.
Computer Science
Performance
Ariane Launch Vehicle, European Space Programs, Interplanetary Flight, Launch Escape Systems, Mission Planning, Multistage Rocket Vehicles, Escape Velocity, Hyperbolic Trajectories, Launch Windows, Payload Mass Ratio
Scientific paper
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.
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