FEASIBILITY STUDY OF AN ION-PROPELLED MARS ORBITER/LANDER SPACECRAFT WITH SOLAR PHOTOVOLTAIC POWER. VOLUME I. SUMMARY.
Final technical rept., Mar-Sep 65,
XEROX ELECTRO-OPTICAL SYSTEMS PASADENA CA
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Volume I describes a solar-electric propelled spacecraft using ion engines and photovoltaic power to effect the heliocentric transfer from Earth to Mars, carrying a lander and orbiter to perform a Voyager-type mission. The mission feasibility is described in terms of trajectory analysis, launch requirements and parametric trade-offs, resulting in substantial gains for electric propulsion compared with conventional chemical propulsion. Feasibility of the ion propulsion system is described with summaries of supporting programs on feed systems, neutralizers, power conditioning, and thrustor system life tests. Spacecraft feasibility is described in terms of subsystem integration, launch vehicle compatibility, deployment, and system operation. Volume II describes mission analysis and propulsion system design, together with its development to a fixed thrust line, boost-coast trajectory employing a near-rendezvous approach. Volume III describes the craft design and its interfaces with the launch vehicle and lander. Selection and analysis of subsystems includes the structure, power, attitude control, telecommunications, and scientific payload. System integration discussion includes mass distribution, thermal analysis, mechanisms, deployment, mission profile and system operation. The conceptual design and weight summary for a baseline craft are given, together with comparison with the basic Voyager design. Author
- Electric and Ion Propulsion
- Unmanned Spacecraft