Computer Graphics. Volume 2 - an Annotated Bibliography to the NASA-MSFC Digital Computer Graphics Program
Annotated bibliography on digital computer graphics
Abbott, H. M.↗
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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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Optimal control for satellite attitude maneuvers. Volume 2 - Computer programs. Part 7 - Digital and hybrid simulator computer programs Research report
Digital and hybrid simulator computer programs for optimal control of satellite attitude maneuvers
Jones, G. S.↗
Trajectory computation by a hybrid computer for the Apollo midcourse abort simulation.
Hybrid computer simulation for Apollo midcourse guidance from elliptical preabort orbit to another ellipse, using coplanar/noncoplanar orbit change guidance scheme
Smith, C. L.↗
Computer systems for Saturn ground computer complex Final technical summary report, Aug. 1964 - Aug. 1967
Final technical summary report on fabrication, delivery, and installation of Saturn S-5 ground computer system
Kempf, B. E.↗
Computer recommendations for an automatic approach and landing system for V/STOL aircraft. Volume 1 - Computer recommendations
Evaluation of digital computer for V/STOL aircraft automatic approach and landing system
Gaines, H. T.↗
Computer data processing to compute NERVA transfer functions.
NERVA transfer functions evaluation by computer data processing, using Fourier algorithm
Benenson, H.↗
The STAR computer - A self-testing-and- repairing computer for spacecraft guidance, control, and automatic maintenance
Successful planetary exploration missions have been completed by unmanned Mariner spacecraft, which were designed at the Jet Propulsion Laboratory. Mariner II completed a 109-day flyby mission to Venus on December 14, 1962. This mission was followed by the flyby of Mars and return of 21 historic photographs of its surface by Mariner IV in July 1965. Further successful missions followed: Mariner V to Venus in 1967, Mariners VI and VII to Mars in 1969. In all of these missions, a Central Computer and Sequencer onboard the spacecraft was used to provide on-board control functions, although complete ground backup was also available.
Algirdas Avizienist↗
Designing a computer - The eclectic information processing system. The Computer Evolution Project /CEP/ report, volume 4, no. 1
Development of eclectic information processing system for computer design
Haynes, J. H.↗
Operations and functions of the MINKEY rendezvous computer program in the Apollo command module computer
Minkey rendezvous computer program in Apollo 15 CSM aiding guidance, navigation and control system functions
Copps, S. L.↗
Spaceborne computer executive routine functional design specification. Volume 1: Functional design of a flight computer executive program for the reusable shuttle
A flight computer functional executive design for the reusable shuttle is presented. The design is given in the form of functional flowcharts and prose description. Techniques utilized in the regulation of process flow to accomplish activation, resource allocation, suspension, termination, and error masking based on process primitives are considered. Preliminary estimates of main storage utilization by the Executive are furnished. Conclusions and recommendations for timely, effective software-hardware integration in the reusable shuttle avionics system are proposed.
Curran, R. T.↗
Analysis of the computed torque drive method and comparison with conventional position servo for a computer-controlled manipulator
A manipulator and its control system (modeled after a Stanford design) is being developed as part of an artificial intelligence project. This development includes an analytical study of the control system software. A comparison is presented of the computed torque method and the conventional position servo. No conclusion is made as to the perference of one system over the other, as it is dependent upon the application and the results of a sampled data analysis.
Markiewicz, B. R.↗
Liquid rocket combustion computer model with distributed energy release. DER computer program documentation and user's guide, volume 1
A computer program for analyzing rocket engine performance was developed. The program is concerned with the formation, distribution, flow, and combustion of liquid sprays and combustion product gases in conventional rocket combustion chambers. The capabilities of the program to determine the combustion characteristics of the rocket engine are described. Sample data code sheets show the correct sequence and formats for variable values and include notes concerning options to bypass the input of certain data. A seperate list defines the variables and indicates their required dimensions.
Combs, L. P.↗
Architecture and data processing alternatives for the TSE computer. Volume 2: Extraction of topological information from an image by the Tse computer
A simple programmable Tse processor organization and arithmetic operations necessary for extraction of the desired topological information are described. Hardware additions to this organization are discussed along with trade-offs peculiar to the tse computing concept. An improved organization is presented along with the complementary software for the various arithmetic operations. The performance of the two organizations is compared in terms of speed, power, and cost. Software routines developed to extract the desired information from an image are included.
Jones, J. R.↗
Computer prediction of three-dimensional potential flow fields in which aircraft propellers operate: Computer program description and users manual
A method was developed for predicting the potential flow velocity field at the plane of a propeller operating under the influence of a wing-fuselage-cowl or nacelle combination. A computer program was written which predicts the three dimensional potential flow field. The contents of the program, its input data, and its output results are described.
Jumper, S. J.↗
Accuracies of three computationally efficient algorithms for computing atmospheric transmittances
Three algorithms for calculating polychromatic atmospheric transmittance functions have been tested using a set of eleven distinct temperature profiles in order to compare transmittance accuracies achievable by the three methods. The comparison of rms errors demonstrates that the iterative method of McMillin and Fleming (1976) is the most accurate of the efficient algorithms currently available for gases with constant mixing ratios; its accuracy approaches that of the spectroscopic parameters and the computational approximations used in the ground-truth line-by-line calculations. The method of Arking et al. (1974), while less accurate, has the advantage of being perfectly general and easily adapted to cases where spectral bandwidths are varied
Mcmillin, L. M.↗
GRID3O: Computer program for fast generation of multilevel, three-dimensional boundary-conforming O-type computational grids
A fast algorithm was developed for accurately generating boundary-conforming, three-dimensional, consecutively refined computational grids applicable to arbitrary wing-body and axial turbomachinery geometries. The method is based on using an analytic function to generate two-dimensional grids on a number of coaxial axisymmetric surfaces positioned between the centerbody and the outer radial boundary. These grids are of the O-type and are characterized by quasi-orthogonality, geometric periodicity, and an adequate resolution throughout the flow field. Because the built-in nonorthogonal coordinate stretching and shearing cause the grid lines leaving the blade or wing trailing edge to end at downstream infinity, the numerical treatment of the three-dimensional trailing vortex sheets is simplified.
Dulikravich, D. S.↗
Reduction of computer usage costs in predicting unsteady aerodynamic loadings caused by control surface motion. Addendum to computer program description
Changes to be made that provide increased accuracy and increased user flexibility in prediction of unsteady loadings caused by control surface motions are described. Analysis flexibility is increased by reducing the restrictions on the location of the downwash stations relative to the leading edge and the edges of the control surface boundaries. Analysis accuracy is increased in predicting unsteady loading for high Mach number analysis conditions through use of additional chordwise downwash stations. User guideline are presented to enlarge analysis capabilities of unusual wing control surface configurations. Comparative results indicate that the revised procedures provide accurate predictions of unsteady loadings as well as providing reductions of 40 to 75 percent in computer usage cost required by previous versions of this program.
Rowe, W. S.↗
Reduction of computer usage costs in predicting unsteady aerodynamic loadings caused by control surface motions: Computer program description
A digital computer program was developed to calculate unsteady loadings caused by motions of lifting surfaces with leading edge and trailing edge controls based on the subsonic kernel function approach. The pressure singularities at hinge line and side edges were extracted analytically as a preliminary step to solving the integral equation of collocation. The program calculates generalized aerodynamic forces for user supplied deflection modes. Optional intermediate output includes pressure at an array of points, and sectional generalized forces. From one to six controls on the half span can be accomodated.
Petrarca, J. R.↗