Parametric studies for cometary nucleus sample return missions using electrically propelled spacecraft

Details Parametric studies for cometary nucleus sample return missions using electrically propelled spacecraft Parametric studies for cometary nucleus sample return missions using electrically propelled spacecraft

Dec 1986

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=1986esasp.249..207s&link_type=abstract

In ESA Proceedings of an ESA Workshop on the Comet Nucleus Sample Return Mission p 207-210 (SEE N87-25109 18-90)

Physics

Comet Nuclei, Core Sampling, Flyby Missions, Launch Vehicle Configurations, Mission Planning, Parameterization, Solar Electric Propulsion, Ariane Launch Vehicle, Low Thrust, Payload Mass Ratio, Round Trip Trajectories, Titan Launch Vehicles

Scientific paper

Comet nucleus sample return mission launcher configurations are discussed: Titan 34D7/G'; Ariane 5/H10; and Ariane 44L, represented by 3 injected mass/escape energy configurations. Additional missions must be investigated to obtain more insight on the influence of the parameters that describe the mission requirements. The values obtained indicate that the dry mass of the ion propulsion system must be well below 1.5 kg/mN thrust to obtain a reasonable payload back to Earth. The total mass ratio of this type of missions is below 2, i.e., more than half of the launch mass returns to Earth, including a 15% in situ mass at the comet.

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