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Search indexed NASA NTRS and DOE OSTI research on propulsion, heat transfer, battery materials and energy systems. Follow report and document links to the original sources.
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Gravity gradient stabilization system for Applications Technology Satellites - boom subsystem and combination passive damper
Gravity gradient stabilization system for Applications Technology Satellites - TV camera, solar aspect and RF attitude sensors, and manufacturing and quality control processes
Systems analysis for ERTS ground data handling system and operations control center
Systems analysis for ERTS NASA Data Processing Facility system and subsystems
Systems analysis for ERTS NASA Data Processing Facility subsystems, installation, and support functions
Developing structure, payload, communication and data handling subsystems for ERTS
Developing attitude control, orbit adjust, thermal, power, electrical integration, integration test and launch support subsystems for ERTS
Bibliography of management sciences literature
Handling of waste products on spacecraft to include identification, potential for on-board utilization, pretreatment requirements for storage, and disposal concepts - Vol.1
Computer program for storage and processing of available data on spacecraft waste control and description of search and retrieval capabilities - Vol. 3
Definition of waste products resulting from manned spacecraft systems with various combinations of mission activities and subsystems - Vol. 2a
The detail engineering data sheets are presented for all concepts considered in the final phase of the study as well as those only carried through the interim phase due to non-applicability or deleted missions.
The formulae, assumptions, calculations, and supporting analyses for the element concept data sheets are given.
Results of a preliminary investigation of the effect on the candidate experiment program implementation of experiment module operations in the absence of an orbiting space station and with the availability of the space shuttle orbiter vehicle only are presented. The fundamental hardware elements for shuttle-only operation of the program are: (1) integrated common experiment modules CM-1, CM-3, and CM-4, together with the propulsion slice; (2) support modules capable of supplying on-orbit crew life support, power, data management, and other services normally provided by a space station; (3) dormancy kits to enable normally attached modules to remain in orbit while shuttle returns to earth; and (4) shuttle orbiter. Preliminary cost estimates for 30 day on-orbit and 5 day on-orbit capabilities for a four year implementation period are $4.2 billion and $2.1 billion, respectively.
An analysis of the factors which determined the selection of the solid rocket propellant engines for the space shuttle booster is presented. The 156 inch diameter, parallel burn engine was selected because of its transportability, cost effectiveness, and reliability. Other factors which caused favorable consideration are: (1) recovery and reuse are feasible and offer substantial cost savings, (2) abort can be easily accomplished. and (3) ecological effects are acceptable.
The baseline SRM design for the space shuttle employs proven technology based on actual motor firings. Supporting research and technology are therefore required only to address system technology that is specific to the shuttle requirements, and that is needed for optimization of design features. Eight programs are recommended to meet these requirements.
Cost estimating data for the 156 inch diameter, parallel burn solid rocket propellant engine selected for the space shuttle booster are presented. The costing aspects on the baseline motor are initially considered. From the baseline, sufficient data is obtained to provide cost estimates of alternate approaches.
A second iteration of the program baseline configuration and cost for the solid propellant rocket engines used with the space shuttle booster system is presented. The purpose of the study was to ensure that total program costs were complete and to review areas where costs might be overly conservative and could be reduced. Labor and material were analyzed in more depth, more definition was prepared to separate recurring from nonrecurring costs, and the operations portions of the engine and stage were separated into more identifiable activities.