Ionization and energy loss versus spacecraft thickness.
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Figure 5-30 — Integrated trajectories between the Moon and L2 (after Edelbaum and D;4mario, AIAA Journal, April 1974).
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Energy removal in spacecraft with increasing thickness.
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Flyback F-1 schematic diagram of spacecraft components.
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Figure 4-6 — Magnetic shielding parameters — torus: R = 900 m; r = 60 m. This figure plots the structural mass of a magnetic cosmic ray shield as well as the annual radiation dose versus the shield’s cutoff energy. The dose is derived from a rough calculation which includes spectrum cutoff, nuclear attenuation, secondary particle production, and self-shielding (50 g/cm2 from body tissue and local mass concentrations). The dose calculated is probably uncertain by a factor of two. The essential reason why the dose declines so slowly with cutoff energy above 3 GeV is that the spectrum cutoff factor is cancelled, largely by secondary production in the shield’s structural mass.
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Figure 4-4 — Properties of rotating habitat systems.
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Figure 4-20 — Solenoid core plasma shield.
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Figure 4-5 — Magnetic shield around a torus.
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Figure 5-24 — Structural frame assembly.
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Figure 5-14 — Continuous wet oxidation process.
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Figure 5-6 — A possible apartment plan.
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Figure 5-16 — Life support mass balance, g/person/day.
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Figure 4-17 — Projected areas of basic shapes.
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Figure 2-1 — Earth-Moon libration points.
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Figure 6-6 — Cash flow Benefits - Costs).
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Comparison of street dimensions for collector and local streets.
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Chapter 6 — Building The Colony And Making It Prosper
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Figure 5-13 — Water removal.
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Figure 4-7 — Schematic of a Bernal sphere configuration.
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Figure 4-24 — Titanium processing.
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Figure 5-11 — View of the agricultural areas. (See also frontispiece to ch. 3.)
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Figure 6-2 — Cost summary. Transportation costs are reduced at year 12 due to oxygen available in space. Total costs are in 1975 dollars.
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Figure 5-35 — Growth of the lunar atmosphere for various constant gas addition rates. Comparable densities in the terrestrial atmosphere are indicated. Dashed lines indicate decay in the total mass if the gas source is shut off (after Vondrak, 1974).
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Figure 6-5 — Total costs and electricity benefits.
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Figure 5-17 — Heat balance of water supply, per person.
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Figure 6-3 — The production schedule for terrestrial satellite solar power stations.
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NASA insignia with space theme.
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Figure 4-23 — Photovoltaic SSPS.
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Figure 6-7 — Parametric variations of system costs.
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Figure 4-13 — Baseline transportation system.
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Figure 4-28 — Passive bag-catcher concept.
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Figure 4-29 — Altitude distribution of HCI deposition rate from a Space Shuttle launch vehicle (A-JPL, 1975, B-Oliver, 1973).
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Figure 5-32 — Estimating factors for RPL design.
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Figure 4-12 — Processes by which aluminum can be extracted from anorthosite. Heavy line indicates the preferred process.
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Figure 4-26 — Glass processing.
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Figure 5-36 — Cross section of the radiation chevron shield configuration.
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Figure 5-20 — The mass catcher.
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Chapter 6 — Building The Colony And Making It Prosper
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Figure 5-21 — The rotary pellet launcher
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Figure 4-15 — SSME powered modular tug.
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Figure 2-4 — Average compositions of rocks and soil returned by Apollo missions, excluding oxygen (-45%) and elements present in amounts less than 1000 ppm.
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Figure 5-5 — Terrace housing application exterior views.
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Figure 1-1 — The colony at Lagrangian point L5.
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Figure 5-18 — Energy flow in the colony.
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Figure 5-34 — Loss rates for an oxygen atmosphere (mass = 16 amu). At a total mass of 108 kg, the lunar atmosphere approaches a constant rate of mass loss (after Vondrak, 1974).
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Figure 4-27 — Lunar gas gun.
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Figure 3-2 — Alternative transportation modes in the colony.
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Figure 5-10 — Section showing distribution of residential and agricultural areas.
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Figure 4-2 — Basic and composite shapes.
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Spacecraft radiation shield figures gallery

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