Engineering topics
Publications and source records attributed to Morrison, R..
A review of the status of InP cell efficiency and of approaches to the reduction of cell cost is presented. The use of heteroepitaxial techniques such as InP-on-GaAs and InP-on-Si is discussed along with the use of chemical and mechanical techniques for removal and recovery of the substrate. The efficiency ultimately obtainable with designs made possible by such an approach is calculated.
The need to provide the necessary funding to research, design and contract the building of an advanced technology rotorcraft that will meet the mission demands of public service (fire, police, paramedics and rescue) operators is discussed. Noise and cost factors, the greatest objections on the part of many police and public adminstrators are addressed. The growth of helicopter utilization in public service is documented.
An effective absorption cross section per hydrogen atom has been calculated as a function of energy in the 0.03-10 keV range using the most recent atomic cross section and cosmic abundance data. Coefficients of a piecewise polynomial fit to the numerical results are given to allow convenient application in automated calculations.
Cosmic ray exposure data for Apollo 17 samples and quantitative photogeologic data are presented which support the hypothesis that the Central Cluster unit and the Bright Mantle at the Apollo 17 landing site are related to impact of ejecta from the crater Tycho, lying about 2000 km to the southwest. The exposure ages point to a site-wide event 96 m.y ago, which included emplacement of the Bright Mantle and Central Cluster units.
A redundant inertial measuring unit (IMU) incorporating six strapdown laser gyros and six accelerometers, arranged so that sensitive axes are normal to the faces of a dodecahedron, provides enhanced reliability with reduced hardware weight. Software monitoring of sensor outputs senses failure of sensors and the system is designed for triple redundancy, with built-in test equipment. Attention is centered on redundancy and fail-safe features, and on the closed-path ring laser gyro arrangement.
A broad spectrum of commercial and military vehicles employ some form of inertial measurement equipment. In general this equipment has a special purpose in that it was tailored for each specific application thereby resulting in high installation and maintenance costs. Recently the emphasis has been directed toward developing low cost building blocks from which the desired inertial functions can be derived. This paper describes a National Aeronautics and Space Administration (NASA) program that combines inertial system sensor and computational advances into a flight demonstration configuration. Specifically, an inertial navigation system employing strapdown laser gyro angular rate sensors and a miniature, modular digital flight computer is described. The objective of this program is to demonstrate, via flight test evaluation, the capabilities of the advanced sensor and computer as they apply to future low cost, high reliability inertial system applications.
Synoptic observations of reddish soil areas by Gemini 4 color photography
Two-level voltage regulator for silver cadmium battery charge control
To prevent fluid leakage around piston seals separating two fluids under differential pressure, a venting system has been devised. Two methods may be used for venting seals through internal passages to an external low-pressure area, O-ring or split-ring seals.
Cost effectiveness improvement in launch vehicle programs
Simulation of stabilization and control for spinning, manned space station to provide artificial gravity station environment
Atmospheric density calculated from the drag of a satellite in a circular orbit