Solar flat plate Final report
Computer program and mathematical model for calculating performance characteristics of solar thermoelectric energy conversion plate
Source record↗
SEARCH · Engineering Papers
Results for “programming model”
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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A mathematical model for simulation of the Apollo telescope mount pointing control system
Mathematical model and computer program for simulation of Apollo telescope mount pointing control system
Smith, P. G.↗
Analysis and mechanization of three and four gimbal systems
Mathematical model and computer program for analysis of three and four gimbal systems
Wilson, J. W.↗
A theory and model of human learning behavior in a manual control task
Human learning behavior theory in manual control task modeled as computer program
Preyss, A. E.↗
Nonlinear combustion instability in liquid propellant rocket motors
Mathematical models and computer program on nonlinear combustion instability in liquid propellant rocket engines
Burstein, S. Z.↗
Analytical study of catalytic reactors for hydrazine decomposition Annual progress report, 15 Apr. 1967 - 14 Apr. 1968
Mathematical model and computer program of catalyzed hydrazine decomposition reaction chamber
Kesten, A. S.↗
ECSS - An extendable computer system simulator
Extendable computer simulation model /ECSS/ overcoming programming and debugging problems, discussing language selection, design, specification, work load, etc
Nielsen, N. R.↗
Prediction of radiation from rocket exhaust gases
Rocket exhaust gases radiant heat transfer prediction, using band models with computer program
Reardon, J. E.↗
A study of high frequency nonlinear combustion instability in baffled annular liquid propellant rocket motors
Computer program contains mathematical model which provides relationship between engine gas dynamics and combustion processes. Mathematically simulated explosions initiate gas disturbances. Design methods for damping disturbances can be studied to prevent future engine shutdown or destruction.
Abreu, A.↗
Static and Dynamic Analysis, F-14A Boron Horizontal Stabilizer
A static stress analysis and a dynamic modal analysis of the horizontal stabilizer of the F-14A aircraft has been conducted at the Naval Air Development Center employing the NASTRAN program. The structural model contains 1518 elements including bars, rods, shear panels and orthotropic and isotropic membrane elements with 1357 degrees of freedom. Static deflection and stresses, including thermal stresses, under maximum load at room and at elevated temperatures are calculated and results are in good agreement with experimental data. Through application of "Guyan Reduction" the number of degrees of freedom used in the dynamic analysis is reduced to 137 . The frequencies and mode shapes for the first two modes are obtained .
S. L. Huang↗
A method for predicting helicopter wake geometry, wake-induced flow and wake effects on blade airloads
Wake model and computer program to compute geometries, flows and velocity influence coefficients for helicopter blade load calculations
Sadler, S. G.↗
Shuttle cryogenic supply system optimization study
Technical information on different cryogenic supply systems is presented for selecting representative designs. Parametric data and sensitivity studies, and an evaluation of related technology status are included. An integrated mathematical model for hardware program support was developed. The life support system, power generation, and propellant supply are considered. The major study conclusions are the following: Optimum integrated systems tend towards maximizing liquid storage. Vacuum jacketing of tanks is a major effect on integrated systems. Subcritical storage advantages over supercritical storage decrease as the quantity of propellant or reactant decreases. Shuttle duty cycles are not severe. The operational mode has a significant effect on reliability. Components are available for most subsystem applications. Subsystems and components require a minimum amount of technology development.
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Users guide for guidance and control Launch and Abort Simulation for Spacecraft (LASS), volume 1
The mathematical models and computer program which are used to implement LASS are described. The computer program provides for a simulation of boost to orbit and abort capability from boost trajectories to a prescribed target. The abort target provides a decision point for engine shutdown from which the vehicle coasts to the vicinity of the selected abort recovery site. The simulation is a six degree of freedom simulation describing a rigid body. The vehicle is influenced by forces and moments from nondistributed aerodynamics. An adaptive autopilot is provided to control vehicle attitudes during powered and unpowered flight. A conventional autopilot is provided for study of vehicle during powered flight.
Havig, T. F.↗
Main rotor free wake geometry effects on blade air loads and response for helicopters in steady maneuvers. Volume 1: Theoretical formulation and analysis of results
A mathematical model and computer program were implemented to study the main rotor free wake geometry effects on helicopter rotor blade air loads and response in steady maneuvers. The theoretical formulation and analysis of results are presented.
Sadler, S. G.↗
A modification of the Avrett-Krook temperature-correction procedure.
In the course of developing a computer program for blanketed model stellar atmospheres, it was found that near the surface the Avrett-Krook temperature correction procedure (1963) has poor convergence properties. The problem is most apparent when frequencies shortward of the Lyman discontinuity are included. Slightly different assumptions have been made to improve the convergence.
Karp, A. H.↗
Techniques for generating highly reliable redundant systems.
A simple heuristic algorithm for designing highly reliable modularly redundant computer systems under complexity constraints is presented. The technique, which produces near optimal solutions, is intuitively appealing and easy to apply. The algorithms performance is shown to compare very well with the optimal solution obtained via a computerized model for dynamic programming.
White, J. B.↗
Analysis of propellant feedline dynamics
An analytical model and computer program were developed for studying the disturbances of liquid propellants in engine feedline systems. It was found that the predominant effect of turbulence is to increase the spatial attenuation at low frequencies; at high frequencies the laminar and turbulent frequencies coincide. Recommendations for future work are included.
Astleford, W. J.↗
Development and in-flight performance of the Mariner 9 spacecraft propulsion system
On November 14, 1971, Mariner 9 was decelerated into orbit about Mars by a 1334-newton (300-lbf) liquid bipropellant propulsion system. The development and in-flight performance are described and summarized of this pressure-fed, nitrogen tetroxide/monomethyl hydrazine bipropellant system. The design of all Mariner propulsion subsystems has been predicated upon the premise that simplicity of approach, coupled with thorough qualification and margin-limits testing, is the key to cost-effective reliability. The qualification test program and analytical modeling of the Mariner 9 subsystem are discussed. Since the propulsion subsystem is modular in nature, it was completely checked, serviced, and tested independent of the spacecraft. Proper prediction of in-flight performance required the development of three significant modeling tools to predict and account for nitrogen saturation of the propellant during the six-month coast period and to predict and statistically analyze in-flight data. The flight performance of the subsystem was excellent, as were the performance prediction correlations. These correlations are presented.
Evans, D. D.↗