Random phase approximation for a plasma in an external electric field.
Random phase approximation for plasma, establishing perturbed electron distribution in oscillating electric field
SEARCH · Search NASA
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.
Quote a phrase for an exact phrase match. Source license links do not imply unrestricted reuse.
Random phase approximation for plasma, establishing perturbed electron distribution in oscillating electric field
Solar corona observations of Surveyor I, discussing extent of measurable radiance and occurrence of streamer
Solar corona temperature from intensity gradients measured during total eclipse of May 30, 1965
Corona temperature and logarithmic intensity gradients determined by pointwise three-color photoelectric photometry during solar eclipse
Explore the source record for details and available documents.
Computational and display requirements for man-computer guidance and control techniques for reusable manned spacecraft
Metallic film used as bandpass filter to isolate night helium glow from Lyman alpha night glow
Load reducing flight control system for Saturn 5 with various payloads
Lunar data and results of Surveyor 1 lunar probe
Convective plus radiative shock tube model stagnation point heating rate measurements for planetary entry heating rate in air and Venus gas
Convective plus radiative shock tube model stagnation point heating rate measurements for planetary entry heating rate in air and Venus gas
An optimization technique has been developed which combines the practical features of hybrid simulation of the dynamic system under study with the systematic approach of modern control theory where a mathematically formulated design criterion is optimized by functional minimization. Standard hybrid computer optimization methods using high-speed repetitive simulations and gradient minimization schemes have been extended to obtain time-varying optimal gain schedules and reduce the sensitivity of the optimized system to parameter and disturbance uncertainties. In this approach the performance index is expressed in meaningful engineering terms that reflect the interactions among all major disciplines, structures, control/actuation system design, aerodynamics and performance. The basic optimization technique is developed and its application to current aerospace control problems including the space shuttle is presented in detail. In the discussion of the application, the controllers resulting from the technique are compared with controllers developed by conventional methods. The paper concludes with a review of the advantages and disadvantages of the technique and plans for future applications.
Shuttle mission objectives are examined. The outstanding characteristic of the payload handling system will be its versatility. A practical system is needed that combines man's adaptability, skill, and reflexes with the strength, endurance, and relative indestructibility of a machine. Systems that meet these standards, called teleoperators, have been in use for many years. The other half of the problem, the retention of man's natural manipulative skills, is solved by use of a 'master-slave' control system. Two independent, parallel preliminary design studies based on the requirements considered were conducted.
Review of sunspot umbral velocity measurements obtained free from any cross talk introduced by photospheric and penumbral scattered light by using lines formed only in the sunspot umbrae and showing no Zeeman effect. The maximum peak-to-peak amplitude of the umbral oscillatory velocity component is found to be of the order of 0.5 km per sec.
The mechanical and electrical characteristics of the conical arc-chamber driver and the 1450-microfarad capacitor bank are described. The system dynamic performance can be approximated by a second-order nonlinear equation. The discharge of the capacitor bank into the conical arc-chamber was investigated at a variety of initial conditions. Details of the discharge are explained and compared for typical performance with both hydrogen and helium arc-chamber gases. At peak current the hydrogen plasma resistivity is significantly higher than that of the helium plasma and this, in part, accounts for the better shock speed performance with hydrogen. The lower melting and boiling point exploding wires of aluminum, copper, and stainless steel produced higher shock speed performance than the apparently nonexploding tungsten wire.
On 11 September 1973 a peculiar prominence was observed. The prominence displayed strong (approximately 50 km per sec) systematic motions toward and away from the observer. The unusual spectrographic appearance of the prominence might have been due to downflowing material lifted into the corona during an earlier coronal transient.