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Results of lap shear tests of various silane primers are presented in graphs and tables. The OH-absorption of these primers (FTIR area values) are correlated with the lap shear tests of coated panels.
There are many factors affecting the spaced antenna drift results, only one of which is antenna spacing. Generally, good results are obtained at MF for receiver antenna spacings of 1-1.5 lambda, and at VHF (e.g., SOUSY) for spacings approx. 6 lambda. Since one of the factors, local atmospheric/ionospheric conditions, are difficult to predict, this paper will be restricted to a short discussion of relevant factors, and methods for comparing various antenna/analysis configurations.
Technical aspects of mesosphere-stratosphere-troposphere (MST) Radar on site and frequency selection were discussed. Recommendations on site selections are presented. Tests of interference will be conducted before selecting a site. A small directional antenna may be suitable to simulate sidelobe sensitivity of radars however, sophisticated data-processing methods make system sensitivity extremely good. The use of the complete data system to look for interference is recommended. There is the difficulty of allocation of frequencies -- almost continuous use by these radars will be made when the band 40 to 60 MHz is allocated to other services.
The majority of mesosphere-stratosphere-troposphere (MST) and ST radars are located in or near mountainous terrain. When measuring horizontal velocities, the terrain is a small factor, but when measuring vertical velocities, the meteorological noise induced by rough terrain can severely limit the usefulness of the observations. When the variance of the vertical velocity is too large, it is not possible to suitably filter the data to detect the small synoptic-scale signal with reasonable statistical confidence. The variance of vertical velocity at all tropospheric levels is directly related to the low level wind speed during flow over rough terrain. It is suggested that the synoptic-scale vertical velocity can be measured by ST radars where the terrain is smooth. The large-scale vertical velocity cannot always be reliably determined from MST radar data when the underlying terrain is rough. The vertical velocity is potentially on of future radar site selections, taking into account the desired meteorological applications of the data and engineering design factors. If the synoptic-scale vertical velocity is a desired variable, the radar should not be located near mountains.
The power spectra S(f) of MST radar signals contain useful information about the variance of refractivity fluctuations, the mean radial velocity, and the radial velocity variance in the atmosphere. When noise and other contaminating signals are absent, these quantities can be obtained directly from the zeroth, first and second order moments of the spectra. A step-by-step procedure is outlined that can be used effectively to reduce large amounts of MST radar data-averaged periodograms measured in range and time to a parameterized form. The parameters to which a periodogram can be reduced are outlined and the steps in the procedure, that may be followed selectively, to arrive at the final set of reduced parameters are given. Examples of the performance of the procedure are given and its use with other radars are commented on.
The theory of gamma ray amplification through stimulated annihilation radiation (grasar) was developed by Ramaty, McKinley and Jones. For gamma ray bursts similar to the March 5, 1979 burst, an observed annihilation line of width 0.03 MeV would imply a grasar source. The minimum pair density needed for the onset of grasar action is approx. 10 to the 30th power/cu cm and the peak of the grasar line, without a gravitational redshift, is at 0.5 MeV.
Sufficient excitation conditions are derived for three adaptive observation schemes for the case in which the order of the observer is less than that of the plant being observed. The reduced-order excitation requirement, found to be identical for all three observers, is that the input contain more than (n+N-1)/2 frequencies, where n is the observer order, and N is the dimension of the portion of the plant which is both controllable and observable.
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Assuming that a parabolic insolation-collection mirror-based solar pumped laser has a collector and heat emitter whose weights are proportional to their areas, and that the weight of the laser is negligible by comparison, the output power/unit weight can be expressed in terms of the efficiencies and working temperatures of the system. This ratio appears to be several times higher for an IBr laser than for one operating on C3F7I, because the solar utilization efficiency is greater for the former despite its lower working temperature.
The purpose of this work is to highlight the particular aspects of miniature heat exchangers performance and to determine an appropriate design approach. A thermodynamic analysis is performed to express the generated entropy as a function of material and geometric characteristics of the heat exchangers. This expression is then used to size miniature heat exchangers.
An investigation to determine the sensitivity of the space shuttle base and forebody aerodynamics to the size and shape of various solid plume simulators was conducted. Families of cones of varying angle and base diameter, at various axial positions behind a Space Shuttle launch vehicle model, were wind tunnel tested. This parametric evaluation yielded base pressure and force coefficient data which indicated that solid plume simulators are an inexpensive, quick method of approximating the effect of engine exhaust plumes on the base and forebody aerodynamics of future, complex multibody launch vehicles.
The development of flying qualities experiments (OFQ) as a part of the Orbiter Experiments Program (OEX) was continued. The data base was extended to use the ground based cinetheodolite measurements of orbiter approach and landing. Onboard the cinetheodolite data were analyzed from flights STS 2 through 7 to identify the effective augmented vehicle dynamics, the control strategy employed by the pilot during preflare, shallow glide, and final flare segments of the landing, and the key approach and touchdown performance measures. A plan for an OFQ flying qualities data archive and processing is presented.
Notched members were tested at temperatures far above those recorded till now. Simulation of the notch root stress response was accomplished to establish notch stress-strain behavior. Cyclic stress-strain profiles across the net-section were recorded and on-line direct notch strain control was accomplished. Data are compared to three analysis techniques with good results. The objective of the study is to generate experimental data that can be used to evaluate the accuracy of constitutive models of time dependent cyclic plasticity.
Knowledge based expert systems are applicable to a wide range of engineering problems ranging from formation to derivation. At the formation end of the spectrum, design, planning and prediction have been identified as generic tasks with similar issues that are dealt with by experts, and need to be formalized for successful expert system implementation. At the derivation end, diagnosis, interpretation and monitoring have been identified as generic tasks with similar subproblems with which experts must cope. At theimplementation level, four levels of programming have been identified: logic programming, production system programming, object oriented programming and hybrid programming.
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The examination of glasses from all of the Apollo landing sites has led to the identification of 25 groups of pristine glass. The nickel found in these glasses is shown to be indigenous, not meteoritic contamination, and to be correlated with Mg. Chemical data indicate that these glasses are more suitable for primary magma than most crystalline mare basalts. In addition, these pristine glasses support the view that assimilative processes involving two cumulative systems in the differentiated mantle operated during mare petrogenesis. Two linear arrays found among the chemistries of the glasses attest to the existence of these interactions. Data suggest that these cumulate components in the mantle continue for 1000 km (laterally) and therefore are likely to be products of a magma ocean that existed early in lunar history.
Based on the RECERT Program findings, NASA-Langley funded a fatigue study of code-unacceptable welds. Usage curves were developed which were based on the structural integrity of the welds. The details of this study are presented in NASA CR-178114. The information presented is a condensation and reinterpretation of the information in NASA CR-178114. This condensation and reinterpretation generated usage curves for welds having: (1) indications 0.20 -inch deep by 0.40-inch long, and (2) indications 0.195-inch deep by 8.4-inches long. These curves were developed using the procedures used in formulating the design curves in Section VIII, Division 2 of the American Society of Mechanical Engineers Boiler and Pressure Vessel Code.
The objective was to verify the design thermal environments for the Space Shuttle External Tank. These environments encompassed a myraid of potential flight cases which included nominal and dispersed trajectories launched from Kennedy Space Center (KSC) and Vandenberg and abort cases. Many iterations of environments have been produced during the evolution of the Space Shuttle system which required an analysis and assessment of each environment. A significant effort was expended in the analysis and application of wind tunnel and heat transfer data to develop math/computer models. Various versions of the aeroheating computer code MINIVER were tailored to calculate ascent aeroheating environments for the External Tank. The significant environment assessment results are summarized.