Advanced substructuring techniques Interim report
Digital computer programs for evaluating free undamped vibrational characteristics of structural systems
Jones, C. E.↗
SEARCH · Search NASA
Results for “Structural characteristics”
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.
Practical Analysis of Plate Vibrations Using NASTRAN
NASTRAN program for calculating structural vibration characteristics of plate configurations
Clary, R. R.↗
Satellite networks for education
Satellite based educational networking is discussed with particular attention given to the potential uses of communications satellites to help meet educational needs in the United states. Four major subject areas were covered; (1) characteristics and structure of networks, (2) definition of pressures within educational establishment that provide motivation for various types of networks, (3) examination of current educational networking status for educational radio and television, instructional television fixed services, inter- and intra-state educational communication networks, computer networks, and cable television for education, and (4) identification of possible satellite based educational telecommunication services and three alternatives for implementing educational satellite systems.
Singh, J. P.↗
Design of a space shuttle structural dynamics model
A 1/8 scale structural dynamics model of a parallel burn space shuttle has been designed. Basic objectives were to represent the significant low frequency structural dynamic characteristics while keeping the fabrication costs low. The model was derived from the proposed Grumman Design 619 space shuttle. The design includes an orbiter, two solid rocket motors (SRM) and an external tank (ET). The ET consists of a monocoque LO2 tank an interbank skirt with three frames to accept SRM attachment members, an LH2 tank with 10 frames of which 3 provide for orbiter attachment members, and an aft skirt with on frame to provide for aft SRM attachment members. The frames designed for the SRM attachments are fitted with transverse struts to take symmetric loads.
Source record↗
Design assurance test of the Thiokol Te-M-521-5 apogee kick motor tested in the spin mode at simulated altitude conditions
One Thiokol Chemical Corporation TE-M-521-5 solid-propellant apogee rocket motor was successfully fired at an average simulated altitude of about 108,000 ft while spinning at 46 rpm. The general program objectives were to verify compliance of motor performance with the manufacturer's specifications. Specific primary objectives were to determine vacuum ballistic performance of the motor after prefire vibration conditioning and temperature conditioning at 40F, altitude ignition characteristics, motor structural integrity, and motor temperature-time history during and after motor operation. Additional objectives were to measure the lateral (nonaxial) thrust component during motor operation and to measure radiation heat flux in the vicinity of the nozzle exit plane.
Cimino, A. A.↗
Satellite networks for education.
Consideration of satellite-based educational networking. The characteristics and structure of networks are reviewed, and pressures within the educational establishment that are providing motivation for various types of networks are discussed. A number of studies are cited in which networking needs for educational sectors and services are defined. The current status of educational networking for educational radio and television, instructional television fixed services, inter- and intrastate educational communication networks, computer networks, cable television for education, and continuing and proposed educational experiments using NASA's Applications Technology Satellites is reviewed. Possible satellite-based educational telecommunication services and three alternatives for implementing educational satellite systems are described. Some remarks are made concerning public policy aspects of future educational satellite system development.
Singh, J. P.↗
Material cutting, shaping, and forming: A compilation
Information is presented concerning cutting, shaping, and forming of materials, and the equipment and techniques required for utilizing these materials. The use of molds, electrical fields, and mechanical devices are related to forming materials. Material cutting methods by devices including borers and slicers are presented along with chemical techniques. Shaping and fabrication techniques are described for tubing, honeycomb panels, and ceramic structures. The characteristics of the materials are described. Patent information is included.
Source record↗
Contributions to the acoustic protection of civil buildings taking into account the use of light prefabs
Usually it is expensive to obtain suitable damping coefficients for exterior and interior walls made up of light materials. Hence, acoustic protection problems must be tackled in parallel with the design and introduction of new types of elements. A comparison of classical solutions shows that interior separating walls raise the most difficult problems. In order to reduce building costs it is necessary to make a careful study of architectural solutions and to provide for wall structures with characteristics that vary with the particular case.
Smigelschi, M.↗
Advanced fusion welding processes, solid state joining and a successful marriage
Joining processes for aerospace systems combine fusion welding and solid state joining during production of metal structures. Detailed characteristics of electron beam welding, plasma arc welding, diffusion welding, inertia welding and weldbond processes are discussed.
Miller, F. R.↗
SSME/side loads analysis for flight configuration, revision A
This document describes the dynamic loads analysis accomplished for the Space Shuttle Main Engine (SSME) considering the side load excitation associated with transient flow separation on the engine bell during ground ignition. The results contained herein pertain only to the flight configuration. A Monte Carlo procedure was employed to select the input variables describing the side load excitation and the loads were statistically combined. This revision includes an active thrust vector control system representation and updated orbiter thrust structure stiffness characteristics. No future revisions are planned but may be necessary as system definition and input parameters change.
Holland, W.↗
Numerical analysis of a two-dimensional nonsteady detonations
In the present work a system of two-dimensional nonsteady hydrodynamic and chemical kinetic equations was numerically integrated for an exothermic system. Assumed two-step reaction model simulates practically an oxyhydrogen mixture. The calculation starts from a plane Chapman-Jouguet detonation as an initial condition. Two-dimensional disturbances are generated by artificially placing nonuniformities ahead of the detonation front. Regardless of the difference of the given initial disturbances, a fixed number of triple shock waves were produced for a fixed combination of mixture model and geometry when the transition period was over. This shows that for a given detonation tube geometry any exothermic system has its own characteristic multidimensional structure. The obtained number of triple shock waves contained in the detonation front was in agreement with existing experimental observations under the same condition.
Taki, S.↗
Data management in engineering
An introduction to computer based data management is presented with an orientation toward the needs of engineering application. The characteristics and structure of data management systems are discussed. A link to familiar engineering applications of computing is established through a discussion of data structure and data access procedures. An example data management system for a hypothetical engineering application is presented.
Browne, J. C.↗
Aeroelastic analysis for helicopter rotor blades with time-variable, non-linear structural twist and multiple structural redundancy: Mathematical derivation and program user's manual
The differential equations of motion for the lateral and torsional deformations of a nonlinearly twisted rotor blade in steady flight conditions together with those additional aeroelastic features germane to composite bearingless rotors are derived. The differential equations are formulated in terms of uncoupled (zero pitch and twist) vibratory modes with exact coupling effects due to finite, time variable blade pitch and, to second order, twist. Also presented are derivations of the fully coupled inertia and aerodynamic load distributions, automatic pitch change coupling effects, structural redundancy characteristics of the composite bearingless rotor flexbeam - torque tube system in bending and torsion, and a description of the linearized equations appropriate for eigensolution analyses. Three appendixes are included presenting material appropriate to the digital computer program implementation of the analysis, program G400.
Bielawa, R. L.↗
Large area silicon sheet by EFG
Progress in a program to produce high speed, thin, wide silicon sheets for fabricating 10% efficient solar cells is reported. An EFG ribbon growth system was used to perform growth rate and ribbon thickness experiments. A new, wide ribbon growth system was developed. A theoretical study of stresses in ribbons was also conducted. The EFG ribbons were observed to exhibit a characteristic defect structure which is orientation dependent in the early stages of growth.
Morrison, A. D.↗
Efficient reanalysis of structures by a direct modification method
A procedure for the local stiffness modifications of large structures is described. It enables structural modifications without an a priori definition of the changes in the original structure and without loss of efficiency due to multiple loading conditions. The solution procedure, implemented in NASTRAN, involved the decomposed stiffness matrix and the displacement vectors of the original structure. It solves the modified structure exactly, irrespective of the magnitude of the stiffness changes. In order to investigate the efficiency of the present procedure and to test its applicability within a design environment, several real and large structures were solved. The results of the efficiency studies indicate that the break-even point of the procedure varies between 8% and 60% stiffness modifications, depending upon the structure's characteristics and the options employed.
Raibstein, A. I.↗
Shuttle Experiment Pointing Mount /EPM/ Systems
Shuttle Experiment Pointing Mount System concepts and technology have been investigated and assessed with regard to payload requirements having a wide range of stability, accuracy, and control functions. Pointing systems were analyzed with end-mounted and center of gravity-mounted payloads viewing stellar and solar targets. Major error sources are identified with dynamical, stochastic, and nonlinear characteristics of structures, isolators, sensors, bearings, actuators, and controller. Results are presented which place a perspective on the potential of advanced technology to satisfy the most stringent sub-arc second pointing requirements.
Mettler, E.↗
Soft X-ray spectrum and structure of the supernova remnant G65.2+5.7
The HEAO 1 low energy detectors have observed the supernova remnant G65.2+5.7 in the energy range 0.2-2.5 keV. A strong, extended source of X-ray emission is observed coincident with the eastern side of the optical filamentary structure. The characteristic temperature of the emission is in the range 2-3.8 x 10 to the 6th K, and evidence is found for line emission at about 0.8 keV in the X-ray spectrum. These observations imply a shock velocity (425 km/s) and age (about 20,000 yr) that markedly disagree with the estimates from optical and radio observations.
Mason, K. O.↗
Thrust oscillations of the Space Shuttle solid rocket Booster motor during static tests
Thrust oscillations have occurred during static tests of Space Shuttle Booster solid rocket motors. These oscillations in measured axial thrust occurred primarily near 15 Hz; these oscillations late in the motor burn reach magnitudes up to approximately + or - 3% of motor thrust. The phenomenon has consistently occurred on the four demonstration motors which have been static tested and appears to be associated with small amplitude, 15 Hz pressure oscillations inside the motor. The source of the pressure oscillations is thought to be associated with the fundamental longitudinal acoustic resonance of the motor at 15 Hz. These thrust oscillations potentially can impact the design of the Space Shuttle vehicle structure. The demonstration motors have been instrumented with an array of transducers to aid in understanding the phenomenon. In addition to measuring axial and lateral thrust of the motor, pressure transducers were located to measure chamber pressure oscillations at the forward dome. Accelerometers and extensometers have measured motions of the structure. A modal survey was conducted on a fired motor to identify its structural dynamic characteristics, and these data were used to validate mathematical models of the motor in the static test facility.
Mason, D. R.↗