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Space Settlements - A Design Study 1977
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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).
Figure 5-24 — Structural frame assembly.
Figure 4-15 — SSME powered modular tug.
Figure 5-18 — Energy flow in the colony.
Figure 4-2 — Basic and composite shapes.
Figure 4-12 — Processes by which aluminum can be extracted from anorthosite. Heavy line indicates the preferred process.
Figure 4-23 — Photovoltaic SSPS.
Figure 6-6 — Cash flow Benefits - Costs).
Figure 5-16 — Life support mass balance, g/person/day.
Figure 6-2 — Cost summary. Transportation costs are reduced at year 12 due to oxygen available in space. Total costs are in 1975 dollars.
Figure 5-11 — View of the agricultural areas. (See also frontispiece to ch. 3.)
Figure 4-29 — Altitude distribution of HCI deposition rate from a Space Shuttle launch vehicle (A-JPL, 1975, B-Oliver, 1973).
Figure 5-14 — Continuous wet oxidation process.
Chapter 6 — Building The Colony And Making It Prosper
Figure 3-2 — Alternative transportation modes in the colony.
Chapter 6 — Building The Colony And Making It Prosper
Figure 4-4 — Properties of rotating habitat systems.
Figure 5-32 — Estimating factors for RPL design.
Figure 5-20 — The mass catcher.
Figure 5-21 — The rotary pellet launcher
Figure 4-27 — Lunar gas gun.
Figure 6-3 — The production schedule for terrestrial satellite solar power stations.
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…
Figure 5-10 — Section showing distribution of residential and agricultural areas.
Figure 5-13 — Water removal.
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).
Comparison of street dimensions for collector and local streets.
Figure 1-1 — The colony at Lagrangian point L5.
Figure 4-17 — Projected areas of basic shapes.
NASA insignia with space theme.
Figure 5-36 — Cross section of the radiation chevron shield configuration.
Figure 4-28 — Passive bag-catcher concept.
Figure 4-24 — Titanium processing.
Figure 4-20 — Solenoid core plasma shield.
Figure 5-17 — Heat balance of water supply, per person.
Figure 4-5 — Magnetic shield around a torus.
Flyback F-1 schematic diagram of spacecraft components.
Ionization and energy loss versus spacecraft thickness.
Figure 5-30 — Integrated trajectories between the Moon and L2 (after Edelbaum and D;4mario, AIAA Journal, April 1974).
Figure 4-13 — Baseline transportation system.
Figure 6-7 — Parametric variations of system costs.
Figure 5-5 — Terrace housing application exterior views.
Figure 4-7 — Schematic of a Bernal sphere configuration.
Figure 2-1 — Earth-Moon libration points.
Energy removal in spacecraft with increasing thickness.
Figure 4-26 — Glass processing.
Figure 5-6 — A possible apartment plan.
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