A stability condition for linear comparison systems
Linear comparison systems stability condition proved with Kotelianskii and Bailey theorems
Gunderson, R. W.↗
SEARCH · Engineering Papers
Results for “Comparison”
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.
Comparison of several demand assignment multiple access/modulation techniques for satellite communications
Comparison of demand assignment multiple access/ modulation techniques for satellite communication using high quality telephone channels
Jones, M. E.↗
An empirical comparison of two sequential decoding algorithms
Fano and stack algorithms comparison by computer simulation of two sequential decoding algorithms
Geist, J. M.↗
An analysis and comparison of several trajectory optimization methods
The sensitivities of the convergence characteristics of the methods to initially assumed parameters and trial solution, convergence times, computer logic, and storage requirements are discussed. Numerical comparison of the convergence characteristics is made by considering a minimum time, low thrust, Earth-Mars transfer trajectory. A modified quasi-linearization method reduces convergence time by approximately 70% when compared with the generalized Newton-Raphson method and allows the terminal boundary to be specified by a general function of the problem variables. A uniquely specified and easily determined, time dependent weighting matrix for the gradient techniques accelerates the shaping of the optimal control program and improves the convergence characteristics during the terminal iterations. Convergence envelopes, indicating how sensitive the convergence characteristics are to initially assumed parameters, are plotted for the perturbation and quasi-linearization methods. Several iteration schemes are proposed which increase the size of the convergence envelopes and decrease the sensitivity of the method to initially assumed parameters.
Lewallen, J. M.↗
Comparison of hinge moments for a simple delta wing and a delta-wing orbiter concept at Mach 6
Comparisons of hinge moments for simple delta wing and delta wing orbiter concept at Mach 6
Ashby, G. C., Jr.↗
Comparison of the solar sail with electric propulsion systems
The propulsive efficiencies of the solar sail and of electric propulsion systems are compared on the basis of specific impulse. It is shown that the solar sail is more efficient at one a.u. for mission durations greater than about two months, that the advantage is increased for missions toward the inner planets, and that the same conclusions are reached when the comparison is based on maximizing the momentum transferred to the payload. Other factors that will influence the choice of a propulsion system for a specific mission are mentioned.
Macneal, R. H.↗
Demonstration of the range over which the Langley Research Center digital computer charring ablation program (CHAP) can be used with confidence: Comparisons of CHAP predictions and test data for three ablation materials
Comparisons of ablation calculations with the charring ablation computer code and ablation test data are presented over a wide range of environmental conditions in air for three materials: low-density nylon phenolic, Avcoat 5026-39HC/G, and a filled silicon elastomer. Heat fluxes considered range from over 500 Btu/sq ft-sec to less than 50 Btu/sq ft-sec. Pressures range from 0.5 atm to .004 atm. Enthalpies range from about 2000 Btu/lb to 18000 Btu/lb. Predictions of recession, pyrolysis penetration, and thermocouple responses are considered. Recession predictions for nylon phenolic are good as steady state is approached, but strongly transient cases are underpredicted. Pyrolysis penetrations and thermocouple responses are very well predicted. Recession amounts for Avcoat and silicone elastomer are less well predicted, although high heat flux cases near steady state are fairly satisfactory. Pyrolysis penetrations and thermocouple responses are very well predicted.
Moyer, C. B.↗
Rocket/Nimbus Sounder Comparison (RNSC)
The experimental results for radiance and temperature differences in the Wallops Island comparisons indicate that the differences between satellite and rocket systems are of the same order of magnitude as the differences among the various satellite and rocket sounders. The Arcasondes produced usable data to about 50 km, while the Datasondes require design modification. The SIRS and IRIS soundings provided usable data to 30 mb; extension of these soundings was also investigated.
Source record↗
A comparison of simulated reduced gravity flight with actual orbital flight conditions
Five basic techniques used to simulate reduced gravity are compared. Some representative Apollo 7 experiences are cited for comparison.
Eisele, D. F.↗
Comparison of the effect of two damper sizes on the performance of a low-solidity axial-flow transonic compressor rotor
The experimental performance of a 20-inch-diameter axial-flow transonic compressor rotor with small dampers is presented. The compressor rotor was tested earlier with large dampers which were twice in size, and comparisons of overall performance and radial distributions of selected flow and performance parameters are made. The rotor with small dampers experienced lower losses in the damper region which resulted in locally higher values of temperature rise efficiency and total pressure ratio. However, there was no appreciable effect on overall efficiency and pressure ratio. A greater stall margin was measured for the rotor with small dampers at design speed, but at 70 and 90 percent of design speed the rotor with large dampers had somewhat greater flow range.
Lewis, G. W., Jr.↗
Analysis of an electrohydraulic aircraft control surface servo and comparison with test results
An analysis of an electrohydraulic aircraft control-surface system is made in which the system is modeled as a lumped, two-mass, spring-coupled system controlled by a servo valve. Both linear and nonlinear models are developed, and the effects of hinge-moment loading are included. Transfer functions of the system and approximate literal factors of the transfer functions for several cases are presented. The damping action of dynamic pressure feedback is analyzed. Comparisons of the model responses with results from tests made on a highly resonant rudder control-surface servo indicate the adequacy of the model. The effects of variations in hinge-moment loading are illustrated.
Edwards, J. W.↗
Comparison of two gas chromatograph models and analysis of binary data
The overall objective of the gas chromatograph system studies is to generate fundamental design criteria and techniques to be used in the optimum design of the system. The particular tasks currently being undertaken are the comparison of two mathematical models of the chromatograph and the analysis of binary system data. The predictions of two mathematical models, an equilibrium absorption model and a non-equilibrium absorption model exhibit the same weaknesses in their inability to predict chromatogram spreading for certain systems. The analysis of binary data using the equilibrium absorption model confirms that, for the systems considered, superposition of predicted single component behaviors is a first order representation of actual binary data. Composition effects produce non-idealities which limit the rigorous validity of superposition.
Keba, P. S.↗
Comparison of genetic algorithms with conjugate gradient methods
Genetic algorithms for mathematical function optimization are modeled on search strategies employed in natural adaptation. Comparisons of genetic algorithms with conjugate gradient methods, which were made on an IBM 1800 digital computer, show that genetic algorithms display superior performance over gradient methods for functions which are poorly behaved mathematically, for multimodal functions, and for functions obscured by additive random noise. Genetic methods offer performance comparable to gradient methods for many of the standard functions.
Bosworth, J. L.↗
A comparison of surface brightness measurements from OAO-2 and OSO-6
A comparison of surface brightness measurements of the night sky from the OAO-2 and OSO-6 satellites with ground observations shows good agreement between the space experiments but a systematic error in the zero point of the ground observations, indicating an additional atmospheric source of radiation.
Roach, F. E.↗
Comparison of celescope magnitudes with model atmosphere fluxes for A, F and G supergiants
Comparison between theoretical colors calculated from model atmospheres and ultraviolet celescope observations of supergiant star atmospheres show that most stars are deficient in ultraviolet flux relative to theoretical models. It is concluded that not enough line blocking has been included in model atmospheres.
Parsons, S. B.↗
Transport of solar flare protons: Comparison of a new analytic model with spacecraft measurements
An analytic solution was obtained to the complete Fokker-Planck equation including the effects of convection, interplanetary deceleration and acceleration, corotation, and anisotropic diffusion. The solution yields a time to maximum for the particle flux of about 10 h and an exponential decay time of about 5 h. Several solar flare particle events were observed with the solar and galactic cosmic ray experiment on OGO-6. Comparisons of the calculated time dependence of the fluxes with these observations of 1 to 70 MeV protons show that the model adequately describes both the rise and decay times.
Lupton, J. E.↗
Comparison of NASTRAN and STARDYNE static analysis of a graphite fiber reinforced plastic truss structure
A static and buckling analysis of the ATS-F&G spacecraft reflector support truss (RST) and bridge truss assembly using NASTRAN was conducted. The RST is fabricated from a new material, graphite fiber reinforced plastic. A comparison is made with the NASTRAN results and the results of a similar analysis conducted using the stardyne program. The results of an actual static load test are also compared.
Honeycutt, G. H.↗
Comparison of heat transfer characteristics of three cooling configurations for air-cooled turbine vanes tested in a turbojet engine
A comparison was made of the heat transfer characteristics of three air cooled vanes. The vanes incorporated cooling schemes such as impingement cooling, film cooling, and convection cooling with and without extended surfaces. A redesign study was made for two vanes to improve the cooling effectiveness. An average impingement heat transfer coefficient was calculated on the bases of experimentally determined temperatures at the leading edge and a one dimensional heat transfer calculation. This heat transfer coefficient was compared with existing impingement heat transfer correlations.
Yeh, F. C.↗