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The influence on living organisms of radiant energy, the psychophysical problems of space flight, methods of physiological investigations in flight, and the transmission of information are considered.
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Available analyses and material property information are summarized relevant to the design of four rocket motor nozzles currently incorporated in the four solid propellant rocket stages of the NASA SCOUT launch vehicle. The nozzles discussed include those for the following motors: (1) first stage - Algol IIIA; (2) second stage - Castor IIA; (3) third stage - Antares IIA; and (4) fourth stage - Altair IIIA. Separate sections for each nozzle provide complete data packages. Information on the Antares IIB motor which had limited usage as an alternate motor for the third stage is included.
The objective elements representative of the kinds of space activities that will be supported by the space construction base (SCB) are discussed in (1) a brief mission overview including the primary purpose and general objectives; (2) descriptions of the processes involved (where applicable), the mission hardware, the principal activities to be undertaken, the test requirements, and the principal tests; and (3) the SCB requirements including such items as special devices (e.g., fabrication modules, assembly or construction fixtures, cranes, and airlocks), power, data management and communications, waste management, environmental control, safety, and logistics. Each program option is then described in terms of the objective elements it supports, its orbit, the general makeup of the SCB, the transportation approach, and the program schedule goals. The specific requirements that are imposed on the SCB in order to support program option L are given.
Options and designs are analyzed for the space construction base, environmental control and life support systems, high voltage array, cranes, low cost modules, and vehicle mass properties.
Topics discussed include: (1) design considerations for a MARS sample return laboratory module for space station investigations; (2) crew productivity as a function of work shift arrangement; (3) preliminary analysis of the local logistics problem on the space construction base; (4) mission hardware construction operational flows and timelines; (5) orbit transfer vehicle concept definition; (6) summary of results and findings of space processing working review; (7) crew and habitability subsystem (option L); (8) habitability subsystem considerations for shuttle tended option L; (9) orbiter utilization in manned sortie missions; (10) considerations in definition of space construction base standard module configuration (option L); (11) guidance, control, and navigation subsystems; and (12) system and design tradeoffs.
A Heavy Lift Airship combining buoyant lift derived from a conventional helium-filled non-rigid airship hull with propulsive lift derived from conventional helicopter rotors was investigated. The buoyant lift essentially offsets the empty weight of the vehicle; thus the rotor thrust is available for useful load and to maneuver and control the vehicle. Such a vehicle is capable of providing a quantum increase in current vertical lifting capability. Certain critical deficiencies of past airships are significantly minimized or eliminated.
A separation method to provide reasonable yields of high specificity isoenzymes for the purpose of large scale, early clinical diagnosis of diseases and organic damage such as, myocardial infarction, hepatoma, muscular dystrophy, and infectous disorders is presented. Preliminary development plans are summarized. An analysis of required research and development and production resources is included. The costs of such resources and the potential profitability of a commercial space processing opportunity for electrophoretic separation of high specificity isoenzymes are reviewed.
The potential profitability of a commercial space processing opportunity for the production of transparent forms of certain metallic oxides was studied.
The development plans, analysis of required R and D and production resources, the costs of such resources, and finally, the potential profitability of a commercial space processing opportunity for containerless melting and resolidification of tungsten are discussed. The aim is to obtain a form of tungsten which, when fabricated into targets for X-ray tubes, provides at least, a 50 percent increase in service life.
Preliminary development plans, analysis of required R and D and production resources, the costs of such resources, and, finally, the potential profitability of a commercial space processing opportunity for the production of very high frequency surface acoustic wave devices are presented.
A glossary of terms, a work breakdown structure, and work element descriptions, resource needs, and costs are introduced. The generic work breakdown structure was utilized to organize specific structures for each product under study; each structure containing both space and ground elements arrived at via mutual interaction. Concept definition and assessment, provided the study team and the participants visibility of the limits, and the organization of the efforts provided by both groups spelling out where such efforts fit into the generation of processing concepts.
The physical, thermal, and electrical interfaces that exist between Spacelab-AMPS Payload No.(TBD) and the orbiter are described.
The interfaces between AMPS Payload No.(TBD) and Spacelab are described. The interfaces specified cover the AMPS physical, electrical, and thermal interfaces that are established to prescribe the standard Spacelab configuration required to perform the mission. If the configuration definition changes due to change of Spacelab equipment model, or serial numbers, then reidentification of the Labcraft payload may be required.
The electrical, mechanical, and environmental interfaces between the boom-mounted flux gate magnetometer and the AMPS/Spacelab are described.
The performance, design, verification and operational requirements for Labcraft equipment and Labcraft integrated payloads are described. The requirements are based on the current definition of Spacelab and Space Transportation System equipment and the constraints associated with their use.
The interfaces between the scientific instruments and the Spacelab/Labcraft equipment are described. The characteristics of the Spacelab/Labcraft equipment pertinent to the scientific instruments and the requirements placed on the scientific instruments by the Spacelab/Labcraft equipment are described.