Engineering Papers⌕ Search

SEARCH · Engineering Papers

Results for “Step”

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.

At least 397 records · Page 22
All sourcesNASA NTRSDOE OSTI
NASA NTRS1974

Evaluation of chromium oxide and molybdenum disulfide coatings in self-acting stops of an air-lubricated Rayleigh step thrust bearing

Two coatings for a Rayleigh step thrust bearing were tested when coasting down and stopping under self-acting operation in air. The thrust bearing had an outside diameter of 8.9 cm (3.5 in.), an inside diameter of 5.4 cm (2.1 in.), and nine sectors. The load was 73 N (16.4 lbf). The load pressure was 19.1 kN/per square meter (2.77 lbf/per square inch) on the total thrust bearing area. The chromium oxide coating was good to 150 stops without bearing deterioration, and the molybdenum disulfide coating was good for only four stops before bearing deterioration. The molybdenum disulfide coated bearing failed after nine stops.

Nemeth, Z. N.↗
NASA NTRS1973

Algorithms for changing the step size

Approximately ten different ways for changing the step size used by multistep methods are enumerated, and their good and bad features are compared. More efficient algorithms are given for the difference formulations of a frequently used halving and doubling process, and a cure for the instability inherent in this halving process is proposed.

Krogh, F. T.↗
NASA NTRS1974

Turbulent boundary-layer separation due to a forward-facing step

Pressure distribution tests were made at Mach numbers of 1.61 and 2.20, over a step-height range from 0 to 2.54 centimeters, and an effective Reynolds number range from about 8 to 150 million. The results were compared with some obtained at higher Mach numbers at approximately comparable boundary-layer conditions. The comparison showed several unexplainable anomalies, and pointed up the lack of boundary-layer information necessary for a proper analysis. An analysis of the data indicates the existence of a transverse vortex in the separated-flow region which weakens with increases in Reynolds and Mach number and significantly affects the pressure distributions.

Czarnecki, K. R.↗
NASA NTRS1975

Evaluation by step response tests of prototype relief valves designed for YF-12 inlet stability bleed system

Two stability bleed system relief valves were tested in a special dynamic test facility. These poppet valves are prototypes for a stability bleed system designed for use in a YF-12 flight inlet. One valve is unshielded, while the other has a special shield to eliminate the flow effect pressures on the piston. The tests determined the size of a damping orifice to be used during wind tunnel tests of the bleed system and verified an analog simulation of the valves. The effects of initial pressure level, pressure step size, and spring rate were investigated.

Dustin, M. O.↗
NASA NTRS1976

Stepping optical path difference in an interferometer

Stepping method permits higher amplitude modulation of secondary mirror of Fourier interferometer. Amplitude of mirror motion is limited only by available voltage drive on error-correcting actuator. Closed-loop controller provides servo error voltage linearly proportional to offset from proper null position. Bidirectional counter serves to count number of reference laser fringes offset from null position.

Schindler, R. A.↗
NASA NTRS1977

Strain partitioning of three alloys in ultrahigh vacuum using the step stress method

The ultrahigh vacuum strain controlled thermal-mechanical strain cycling fatigue behavior of ASTAR 811C, 304 stainless steel and A-286 was studied. The step stress procedure of experimental strainrange partitioning was utilized to partition the inelastic strainranges for tests duplicating conditionings previously reported by TRW. An analytical method is described in which these partitioned inelastic strainrange data can be used to develop the four basic life relationships for these materials.

Kortovich, C. S.↗
NASA NTRS1976

Ion drive - A step toward 'Star Trek'

The design of a solar-powered electric propulsion system is seen as the first step in the ultimate development of an ion drive system which might incorporate many features of a spacecraft propulsion system described in a science fiction novel written by Anderson (1970). The considered ion propulsion systems would make it possible to augment significantly the operational capabilities of space transportation systems utilizing the Shuttle orbiter in combination with a solid-propellant interim upper stage. The use of the ion drive in a number of applications is discussed, giving attention to the resulting enhancement of national space capabilities, the role of the ion drive in the space transportation system, the development and the operation of a manned space station, satellite positioning and service, the elimination of space debris objects, the study of Halley's comet, interplanetary or lunar shuttle services, and space missions involving the outer planets.

Atkins, K. L.↗
NASA NTRS1978

Gaussian step-pressure loading of rigid viscoplastic plates

The response of a thin, rigid viscoplastic plate subjected to a spatially axisymmetric Gaussian step pressure impulse loading was studied analytically. A Gaussian pressure distribution in excess of the collapse load was applied to the plate, held constant for a length of time, and then suddenly removed. The plate deforms with monotonically increasing deflections until the dynamic energy is completely dissipated in plastic work. The simply supported plate of uniform thickness obeys the von Mises yield criterion and a generalized constitutive equation for rigid viscoplastic materials. For the small deflection bending response of the plate, the governing system of equations is essentially nonlinear. Transverse shear stress is neglected in the yield condition and rotary inertia in the equations of dynamic equilibrium. A proportional loading technique, known to give excellent approximations of the exact solution for the uniform load case, was used to linearize the problem and to obtain the analytical solutions in the form of eigenvalue expansions. The effects of load concentration, of an order of magnitude change in the viscosity of the plate material, and of load duration were examined while holding the total impulse constant.

Hayduk, R. J.↗
NASA NTRS1978

Combustion of hydrogen in a two-dimensional duct with step fuel injectors

An investigation of the combustion of hydrogen perpendicularly injected from step fuel injectors into a Mach 2.72, 2100 K vitiated test gas was conducted. The model simulated the flow between the center and side struts of an integrated scramjet module at Mach 7 flight and an altitude of 29 km. Parametric variation included equivalence ratio, fuel dynamic pressure ratio, and area distribution of the model. The overall area ratio of the model was held constant at 2.87. The data analysis indicated that no measurable improvement in mixing or combustion efficiency was obtained by varying the fuel dynamic pressure ratio from 0.79 to 2.45. Computations indicated approximately 80 percent of the fuel was mixed so that it could react; however, only approximately 50 percent of the mixed fuel actually reacted in two test configurations, and 74 percent in later tests where less area expansion of the flow occurred.

Eggers, J. M.↗
NASA NTRS1978

Interaction between step fuel injectors on opposite walls in a supersonic combustor model

Results are presented from an experimental investigation of perpendicular, hydrogen fuel injection and combustion from opposing walls in a scramjet combustor model using a longitudinally staged laterally inline step-injection configuration. The model represents a portion of the flow in the Langley integrated modular scramjet engine combustor operating at a flight Mach number of 7. When operating at a ratio of jet pressure to free-stream dynamic pressure of 3, the injectors produce a bulk equivalence ratio of unity. This investigation represents part of a continuing study of the modular engine fuel injectors and is specifically designed to eliminate the adverse lateral pressure gradient observed at the injector location in a previous test. Flow survey contours at three axial locations, ranging from one-third of the engine combustor length to the total engine combustor length, are used to determine mixing efficiency and fuel distribution. Wall static pressures are analyzed by using one-dimensional theory to determine the combustion efficiency. Results show a significant improvement over previous injector designs tested in this duct geometry.

Mcclinton, C. R.↗
NASA NTRS1978

G-seat system step input and sinusoidal response characteristics

The step input and sinusoidal response characteristics of a pneumatically driven computer controlled G set are examined in this study. The response data show that this system can be modeled as a first order system with an 0.08 sec time lag and a 0.53 sec time constant.

Showalter, T. W.↗
NASA NTRS1978

Accelerated step-temperature aging of Al/x/Ga/1-x/As heterojunction laser diodes

Double-heterojunction A2(0.3)Ga(0.7)As/Al(0.08)Ga(0.92)As lasers (oxide-striped and Al2O3 facet coated) were subjected to step-temperature aging from 60 to 100 C. The change in threshold current and spontaneous output was monitored at 22 C. The average time required for a 20% pulsed threshold current increase ranges from about 500 h, when operating at 100 C, to about 5000 h at a 70 C ambience. At 22 C, the extrapolated time is about 1 million h. The time needed for a 50% spontaneous emission reduction is of the same order of magnitude. The resulting activation energies are approximately 0.95 eV for laser degradation and approximately 1.1 eV for the spontaneous output decrease

Kressel, H.↗
NASA NTRS1980

Four-step reaction for polytriazine elastomers

Four step imidoylamidine reaction sequence is used to make crosslinked polyperfluoralkyltriazines with superior elastomeric properties, greater molecular weight, and crosslinking control. Polymers can find useful application in fuel tank sealants, o-ring, wire enamels, pneumatic ducts, and many other applications.

Rosser, R. W.↗
NASA NTRS1978

Effect of step and/or gap tile misalignment on shuttle transition

The effect of tile misalignment, simulating both step type and gap type misalignment was determined on transition locations in the plane of symmetry of the shuttle orbiter. Data were obtained in a closed circuit hypersonic tunnel with a 50-in. diameter test section providing a Mach number of 8 over a range of pressure levels from 345,000 N/sq m (50 psi) to 620 million N/sq m (900 psi). The stagnation temperature is sufficient to avoid air liquefaction in the test section.

Bertin, J. J.↗
NASA NTRS1978

On a new algorithm for time step integration of nonlinear systems

A new implicit algorithm for time step integration of finite element structural dynamic equations is presented. Convergence, stability and numerical damping properties are discussed. Due to the way nonlinear structural behavior is taken into account, the algorithm is expected to compare favorably with existing ones. Some simple numerical results are presented. A related explicit algorithm is also derived and shortly discussed.

Anderheggen, E.↗
NASA NTRS1978

Diode step stress program, JANTX1N5614

The reliability of switching diode JANTX1N5614 was tested. The effect of power/temperature step stress on the diode was determined. Control sample units were maintained for verification of the electrical parametric testing. Results are reported.

Source record↗
NASA NTRS1978

Diode step stress program, JANTX1N981B

Power/temperature step stress was applied to the Zener diode JANTX1N981B. Reliability of the device was determined. Control units were maintained for verification of the electrical parametric testing. Results are reported.

Source record↗