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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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Analytical methods for determining signal errors due to geometric deviations and nonlinearities in coherent optical data processors
Space radiator steady state thermal design using approximate analytic method
Analytical method predicting heat generation in sealed batteries, noting overcharge ratio effects
This study program was conducted to obtain a sound theoretical understanding of and a valid analytical method for predicting the performance of porous plate water boilers.
Three-step thermal process quantitatively determines the hydroxyl content in samples of magnesium oxide. Analytical method can be adapted to large-scale production of hydroxyl-free magnesium oxide.
Analytical methods development for predicting radiant heat transfer and temperature of engineering surfaces in space environment
Wind tunnel tests, analytical methods and fixed base simulation for predicting fighter aircraft spin characteristics
Sonic boom waves diffraction and reflection, developing analytical method for pressure-time history in vicinity of walls and corners
Developing general analytical methods for predicting planar and three dimensional attitude motion of gravity gradient spacecraft in elliptical orbit
Shell impact response and wave propagation in cylindrical and conical shells by experimental and analytical methods
Wind tunnel evaluation of analytical method for predicting longitudinal stability and aerodynamic characteristics of large flexible aircraft applied to supersonic transport configuration
Failure Modes, Effects, and Criticality Analysis Model disregards failures of insignificant components. Assumptions used to establish baselines for reliability prediction and analytical method are listed. Techniques are applicable to any commercial design and can be extended into software or management systems.
Study resulting in a satisfactory stress corrosion cracking test with extremely consistent results produced six new analytical methods. Methods detect and determine differences in the minor constituent composition of different types of dinitrogen tetroxide.
Analytical methods and four computer programs have been developed for calculating wave motion in closed, baffled chambers with rigid and non-rigid boundaries. Application of these methods to design of injector-face baffles in liquid propellant engines will provide significant insight into effects of baffles on combustion stability.
Experimental and analytical investigations of the vibratory behavior of ring-stiffened truncated-cone shells are described. Vibration tests were conducted on 60 deg conical shells having up to four ring stiffeners and for free-free and clamped-free edge constraints and 9 deg conical shells, for two thicknesses, each with two angle rings and for free-free, free-clamped, and clamped-clamped edge constraints. The analytical method is based on linear thin shell theory, employing the Rayleigh-Ritz method. Discrete rings are represented as composed of one or more segments, each of which is a short truncated-cone shell of uniform thickness. Equations of constraint are used to join a ring and shell along a circumferential line connection. Excellent agreement was obtained for comparisons of experimental and calculated frequencies.
The general motion of a variable mass flexible missile with internal flow and aerodynamic forces is considered. The resulting formulation comprises six ordinary differential equations for rigid body motion and three partial differential equations for elastic motion. The simultaneous differential equations are nonlinear and possess time-dependent coefficients. The differential equations are solved by a semi-analytical method leading to a set of purely ordinary differential equations which are then solved numerically. A computer program was developed for the numerical solution and results are presented for a given set of initial conditions.
An analytical method is developed for determining the flow interaction when a two-dimensional jet is injected between two moving streams. The jet is flowing out of channel and is turned as it enters between the external streams. The local velocity variation resulting from the flow interaction provides a static pressure variation along the jet bounding streamlines that is a priori unknown. Hense, the flow must be obtained by coupling the three flow regions (the jet and the free stream on either side) along the jet boundaries. Both external streams have the same total pressure, which is different from that in the jet. The solution is for the condition that the total pressure in the jet does not differ from the free-stream value by a large amount compared with the free-stream dynamic head. Results are given for the shape of the jet boundaries for various injection configurations.
The guidance, navigation, and control displays associated with manned spaceflight are summarized. Major emphasis were placed on methodologies useful for determining necessary information and its uses, systems analysis techniques, and analytic methods for design and evaluation of such systems.