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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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Advanced space system concepts and their orbital support needs (1980 - 2000). Volume 4: Detailed data. Part 2: Program plans and common support needs (a study of the commonality of space vehicle applications to future national needs
The methodology of alternate world future scenarios is utilized for selecting a plausible, though not advocated, set of future scenarios each of which results in a program plan appropriate for the respective environment. Each such program plan gives rise to different building block and technology requirements, which are analyzed for common need between the NASA and the DoD for each of the alternate world scenarios. An essentially invariant set of system, building block, and technology development plans is presented at the conclusion, intended to allow protection of most of the options for system concepts regardless of what the actual future world environment turns out to be. Thus, building block and technology needs are derived which support: (1) each specific world scenario; (2) all the world scenarios identified in this study; or (3) generalized scenarios applicable to almost any future environment. The output included in this volume consists of the building blocks, i.e.: transportation vehicles, orbital support vehicles, and orbital support facilities; the technology required to support the program plans; identification of their features which could support the DoD and NASA in common; and a complete discussion of the planning methodology.
Analysis of structural dynamic data from Skylab. Volume 2: Skylab analytical and test modal data
A compendium is presented of orbital configuration test modal data, analytical test modal data, analytical test correlation modal data and analytical flight configuration 1.2 modal data. Section A presents tables showing the generalized mass contributions for each of the thirty test modes. Section B presents the two dimensional mode shape plots for the thirty test modes. Tables of GMC's for the test correlated analytical modes are presented in Section C. These analytical modes were generated from a model that was adjusted to match test results by use of the methodology discussed in Sections 2.3 and 5.4 of Volume I of this report. Section D presents the two dimensional mode shape plots for the analytical modes. Sections E and F contain the uncoupled and coupled modes of the orbital flight configuration 1.2 at three development phases of the model.
Entry into outer planet environments. II - Performance of volume reflecting hyperpure silica heat shields
The performance of hyperpure silica heat shields that backscatter incident radiation in the depths of the material, i.e., a volume reflecting heat shield, is mapped for probes entering the atmospheres of Saturn and Uranus. Three models of each atmosphere are considered; the warm, nominal, and cool models. The most recent thermophysical and optical properties of hyperpure silica are employed. Detailed incident radiative spectra and the effects of ablation on radiative and convective heating obtained from benchmark flowfield solutions are used. In-depth material response is examined and results are presented in terms of the peak rear-face temperature as a function of initial thickness for each atmosphere. Results are compared with carbon phenolic heat-shield requirements.
Determining critical temperatures and volumes
Technique estimates critical temperature and volume of fluid from chemical composition and structure without additional empirical data. Method can help designers interested in materials for which critical constants are unavailable.
Estimating molar volume and expansion
Molar volumes and expansion coefficients of polymers are estimated quickly from minimal experimental data.
Effect of air temperature and relative humidity at various fuel-air ratios on exhaust emissions on a per-mode basis of an Avco Lycoming 0-320 DIAD light aircraft engine. Volume 2: Individual data points
A carbureted four cylinder air cooled 0-320 DIAD Lycoming aircraft engine was tested to establish the effects of air temperature and humidity at various fuel-air ratios on the exhaust emissions on a per-mode basis. The test conditions included carburetor lean-out at air temperatures of 50, 59, 80, and 100 F at relative humidities of 0, 30, 60, and 80 percent. Temperature-humidity effects at the higher values of air temperature and relative humidity tested indicated that the HC and CO emissions increased significantly, while the NOx emissions decreased. Even at a fixed fuel-air ratio, the HC emissions increase and the NOx emissions decrease at the higher values of air temperature and humidity. Volume II contains the data taken at each of the individual test points.
Small axial compressor technology, volume 2
Complete computer printout data are presented and supporting tests discussed in Volume I.
A plan for application system verification tests. The value of improved meteorological information, volume 2
For abstract, see volume 1 N77-12634.
Spacelab experiment computer study. Volume 2: Study elements and approach
For abstract, see volume 1 N77-13097.
Spacelab experiment computer study. Volume 3: Spacelab cost data
For abstract, see volume 1 N77-13097.
Spacelab experiment computer study. Volume 4: Spacelab user cost data (central experiment computer)
For abstract, see volume 1 N77-13097.
Spacelab experiment computer study. Volume 5: Spacelab user cost data (distributed computer)
For abstract, see volume 1 N77-13097.
Results of a landing gear loads test using a 0.0405-scale model (16-0) of the space shuttle orbiter in the Rockwell International NAAL wind tunnel (OA163), volume 2
For abstract, see volume 1 N77-13130.
Results of a landing gear loads test using a 0.0405-scale model (16-0) of the space shuttle orbiter in the Rockwell International NAAL wind tunnel (OA163), volume 3
For abstract, see volume 1 N77-13130.
Results of a landing gear loads test using a 0.0405-scale model (16-0) of the space shuttle orbiter in the Rockwell International NAAL wind tunnel (OA163), volume 4
For abstract, see volume 1 N77-13130.
Floated pallet definition study. Volume 3: Retention/suspension systems, pallet common module configuration study
For abstract, see volume 1 N77-13130.
Determination of burning area and port volume in complex burning regions of a solid rocket motor
An analysis of the geometry of the burning in both star-cylindrical port interface regions and regions of partially inhibited slots is presented. Some characteristics parameters are defined and illustrated. Methods are proposed for calculating burning areas which functionally depend only on the total distance burned. According to this method, several points are defined where abrupt changes in geometry occur, and these are tracked throughout the burn. Equations are developed for computing port perimeter and port area at pre-established longitudinal positions. Some common formulas and some newly developed formulas are then used to compute burning surface area and port volume. Some specific results are presented for the solid rocket motor committed to the space shuttle project.