Options for a lunar base surface architecture

The Planet Surface Systems Office at the NASA Johnson Space Center has participated in an analysis of the Space Exploration Initiative architectures described in the Synthesis Group report. This effort involves a Systems Engineering and Integration effort to define point designs for evolving lunar and Mars bases that support substantial science, exploration, and resource production objectives. The analysis addresses systems-level designs; element requirements and conceptual designs; assessments of precursor and technology needs; and overall programmatics and schedules. This paper focuses on the results of the study of the Space Resource Utilization Architecture. This architecture develops the capability to extract useful materials from the indigenous resources of the Moon and Mars. On the Moon, a substantial infrastructure is emplaced which can support a crew of up to twelve. Two major process lines are developed: one produces oxygen, ceramics, and metals; the other produces hydrogen, helium, and other volatiles. The Moon is also used for a simulation of a Mars mission. Significant science capabilities are established in conjunction with resource development. Exploration includes remote global surveys and piloted sorties of local and regional areas. Science accommodations include planetary science, astronomy, and biomedical research. Greenhouses are established to provide a substantial amount of food needs

OTV impacts and interactions

The possible impacts and interactions of the agency's planning activities for the Orbit Transfer Vehicle (OTV) that is tentatively scheduled for initial operational capability in the late 1990's are identified. In general, the various Mars missions require vehicles of significant size and performance far greater than that provided by any OTV configuration currently being seriously considered. Therefore, interactions and impacts on these current concepts are minimal. These impacts and interactions fall into categories of technologies, systems, and operations. Each category is addressed

On Becoming a Strategic Partner: The Role of Human Resources in Gaining Competitive Advantage

Although managers cite human resources as a firm\u27s most important asset, many organizational decisions do not reflect this belief. This paper uses the VRIO (value, rareness, imitability, and organization) framework to examine the role that the Human Resource (HR) function plays in developing a sustainable competitive advantage. We discuss why some popularly cited sources of sustainable competitive advantage are not, and what aspects of a firm\u27s human resources can provide a source of sustainable competitive advantage. We also examine the role of the HR executive as a strategic partner in developing and maintaining competitive advantage within the firm

Pitfall Trap Collections of Ground Beetle Larvae (Coleoptera: Carabidae) in Kentucky Alfalfa Fields

Pitfall traps were installed in alfalfa fields to monitor the seasonality and abundance of immature ground beetles. Head capsule widths were determined by instar for Evarthrus sodalis, Harpalus pennsylvanicus, Chlaenius tricolor, Scarites subterraneus, Amara cupreolata, and A. impuncticollis. Seasonality of larval and adult catches indicated that E. sodalis, H. pennsylvanicus and A. impuncticollis overwinter in a larval diapause while A. cupreolata and S. subterraneus overwinter in the adult stage

Baseline program

This assumed program was developed from several sources of information and is extrapolated over future decades using a set of reasonable assumptions based on incremental growth. The assumptions for the NASA baseline program are as follows: balanced emphasis in four domains; a constant level of activity; low to moderate real budget growth; maximum use of commonality; and realistic and practical technology development. The first domain is low Earth Orbit (LEO). Activities there are concentrated on the space station but extend on one side to Earth-pointing sensors for unmanned platforms and on the other to the launch and staging of unmanned solar system exploration missions. The second domain is geosynchronous Earth orbit (GEO) and cislunar space. Activities here include all GEO missions and operations, both unmanned and manned, and all transport of materials and crews between LEO and the vicinity of the Moon. The third domain is the Moon itself. Lunar activities are to include both orbiting and landing missions; the landings may be either unmanned or manned. The last domain is Mars. Missions to Mars will initially be unmanned but they will eventually be manned. Program elements and descriptions are discussed as are critiques of the NASA baseline

Alternative scenarios utilizing nonterrestrial resources

A collection of alternative scenarios that are enabled or substantially enhanced by the utilization of nonterrestrial resources is provided. We take a generalized approach to scenario building so that our report will have value in the context of whatever goals are eventually chosen. Some of the topics covered include the following: lunar materials processing; asteroid mining; lunar resources; construction of a large solar power station; solar dynamic power for the space station; reduced gravity; mission characteristics and options; and tourism

Concept for a manned Mars flyby

A concept is presented for a three man crew to fly by the planet Mars. The ground rule for the study is to execute the mission as quickly as possible which dictates using late 1990's technologies and space infrastructure. The proposed mission described herein uses a preliminary concept for the agency's Manned Orbit Transfer Vehicle (MOTV) and proposed space station elements. The space vehicle will depart from the LEO space station and is delivered to Low Earth Orbit (LEO) by a future launch vehicle of a Shuttle Derived Launch Vehicle (SDV) class. The trajectory parameters are chosen such that the mission duration is on the order of one year, with a two and one-half hour period within ten planetary radii of Mars. If the issues of acceptable crew g loads and entry vehicle heat load can be resolved, then the returning vehicle can aerobrake at Earth into a space station compatible orbit. Otherwise, a propulsive maneuver will be required to reduce vehicle velocity prior to Earth entry interface. It is possible to execute a mission of reasonable capability at an initial LEO departure weight of 716,208 pounds for the aerobraked case of 1,350,000 pounds for the propulsive case