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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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Reference data for advanced microwave and laser communication and tracking systems - Vol. 3
Photometric flow meter with comparator reference means
Design and tests of single-axis reference strapdown inertial measuring unit
Method and means for recording and reconstructing holograms without use of reference beam
Reference atmosphere for Vandenburg AFB, California based on current annual tabulation of thermodynamic quantities
Significance of solar geomagnetic processes in determining distribution of ionospheric components and implications for reference models of ionosphere
Derivation and tables of spherical harmonic coefficients and isoporic charts for International Geomagnetic Reference Field for 1965
Computer program for generating cross reference index in operating system of IBM 360 computer
Surface flame spreading characteristics of ICRPG reference composite propellant composed of ammonium perchlorate with polyurethane binder
Derivation of International Geomagnetic Reference Field with tables of spherical harmonic coefficients and test results of various magnetic field models
Liapunov design technique for model reference adaptive control systems with feedback and prefilter adjustable gains
Harvard-Smithsonian reference atmosphere model of solar atmosphere, combining photosphere and quiet lower chromosphere
Blind goldfish gravity reference response under linear accelerations on motor car and parallel swing from movie camera recording
Computer program to collect key data from Stage Two input of OS/360 system and to prepare formatted listing of index entries collected is discussed. Program eliminates manual paging through system output by providing comprehensive cross reference.
Thermal conductivity data were obtained by the axial one-dimensional heat flow method for a cylindrical rod 3.6 mm in diameter and 23 cm long with an electric heater at one end and a temperature controlled sink at the other. Variability of this iron was studied by means of electrical residual resistivity ratio measurements on 63 specimens. This study showed that with a two-hour anneal at 1000 C one can obtain a thermal conductivity Standard Reference Material that has variability of less than 1% in thermal conductivity.
A hydrogen slush density reference system was designed for calibration of field-type instruments and/or transfer standards. The device is based on the buoyancy principle of Archimedes. The solids are weighed in a low-mass container so arranged that solids and container are buoyed by triple-point liquid hydrogen during the weighing process. Several types of hydrogen slush density transducers were developed and tested for possible use as transfer standards. The most successful transducers found were those which depend on change in dielectric constant, after which the Clausius-Mossotti function is used to relate dielectric constant and density.
Proposal of an algorithmic procedure, based on mathematical programming methods, to design compensators for hyperstable discrete model-reference adaptive systems (MRAS). The objective of the compensator is to render the MRAS insensitive to initial parameter estimates within a maximized hypercube in the model parameter space.
The Reference Design Document, of the Preliminary Safety Analysis Report (PSAR) - Reactor System provides the basic design and operations data used in the nuclear safety analysis of the Rector Power Module as applied to a Space Base program. A description of the power module systems, facilities, launch vehicle and mission operations, as defined in NASA Phase A Space Base studies is included. Each of two Zirconium Hydride Reactor Brayton power modules provides 50 kWe for the nominal 50 man Space Base. The INT-21 is the prime launch vehicle. Resupply to the 500 km orbit over the ten year mission is provided by the Space Shuttle. At the end of the power module lifetime (nominally five years), a reactor disposal system is deployed for boost into a 990 km high altitude (long decay time) earth orbit.