potential effects on different spacecraft structures are described. The status of experimental and theoretical work for the Columbus Space Station is reported in detail. A strategy for continued investigation of shielding performance is outlined. Ways in which the weight of shielding elements can be decreased are investigated. The use of composite materials for shielding is discussed. N91-11862# ESA Tohoku Univ., Sendai (Japan). Research Inst. for Fracture Technology. STANDARDIZATION PROGRAM FOR FRACTURE EVALUATION OF FUNCTIONALLY GRADIENT MATERIAL (FGM) OF VERY HIGH TEMPERATURE APPLICATION H. Takahashi, T. Hashida, and M. Niino (National Aerospace Lab., Kakuda, Japan) In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 331-337 Sponsored by Japanese Science and Technology Agency (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 Several Functionally Gradient Materials (FGM) 30 mm in diameter and 3 to 5 mm thick are described. Test results for fracture properties such as strength and thermal shock resistance are presented. Experimental investigation into miniaturized specimen test procedures are described. A modified small punch method developed to measure the elastic constant and fracture strength of each constitutional microstructure of FGM is outlined. Results of laser radiation thermal shock tests on both conventional ceramic materials and plasma-sprayed FGM are described. N91-11863# National Aerospace Lab., Kakuda (Japan). EVALUATION OF THERMOMECHANICAL PROPERTIES OF FUNCTIONALLY GRADIENT MATERIAL UNDER HIGH TEMPERATURE DIFFERENCE ESA A. Kumakawa, S. Maeda, M. Sasaki, M. Niino, A. Sakamoto, M. Sasaki, and T. Hirai (Tohoku Univ., Sendai, Japan) In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 339-344 (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 The thermal resistance and thermal fatigue properties of Functionally Gradient Materials (FGM) are measured. The effect of steep temperature gradients without any oxidation, corrosion or erosion effects is studied. A test apparatus developed for carrying out such tests is described. Tests results indicate that FGM would have the potential of relaxing the thermal stress caused by a mismatch of thermal expansion under a heavy heat load. Comparisons of FGM specimens with conventional materials are described. The FGM show higher thermal resistance and longer thermal fatigue life than conventional materials. ESA B. Goffaux and I. Verpoest In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 345-350 Sponsored by Belgian Inst. for Scientific Research in Industry and Agriculture (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 The various factors influencing the toughness of welded joints in thermoplastic composites are investigated. Three factors are identified as having a positive influence on weld quality. The use of an interlayer which creates fiber migration in the joint zone is described. The importance of the amorphous state of the surface of the composite before welding is stressed. The role played by the state of the joint after welding is outlined. It should be also amorphous for best results. The main advantage of the hybrid welding technique is that the welding temperature can be kept lower than the lamination temperature. ESA N91-11865# Aerospatiale Aquitaine, Saint-Medard en Jalles (France). Strategic and Space Div. HOW TO KNOW CMC... F. Albugues and P. Peres In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 351-362 (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 The factors involved in gaining a clear understanding of Ceramic Matrix Composite (CMC) are described. The various research partners within France working within this area are identified. Mechanical test validity on test samples are described. Fracture behavior modeling is discussed. Mechanical tests related to microstructure are outlined. Mathematical modeling of elementary structures is discussed. Precise characterization over a total temperature, environment and cycling range is investigated. Analysis and cartography of elementary defects and their evolution during nondestructive testing is outlined. ESA G. Romeo, C. Alonso, and A. Pennavaria In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 365-370 (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 An analytical solution for the buckling of anisotropic cylindrical plates under biaxial compression and shear loads is presented. Linear equations for laminated cylindrical shells, Donnell-type equations, are used in conjunction with Galerkin's method to determine critical buckling loads. Results obtained indicate that significant nonconservative errors can occur in buckling predictions in comparison with the orthotropic solution. Stacking sequence and curvature radius are shown to affect the buckling loads. Shear deformation effects on the buckling loads are seen to become more pronounced as the ratio of the principal moduli and the number of layers increase. ESA J. H. vanderSloot In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 371-379 (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 A simplified method for computing the estimated allowable compression load of stiffened composite panels is presented. It is developed from one available for aluminum alloys panels and specifically tailored for the analysis of composite panels. Critical loads for panels with reduced stiffness can be calculated using this method. The reduced stiffnesses are derived from an analysis of postbuckling behavior of typical panel elements. Computational results for panels of practical configurations are reported and correlated with other solutions or test results. ESA c39 N91-11868# Fokker B.V., Amsterdam (Netherlands). Ways to optimize design validity are outlined. Uncoupling of research on materials technology and product design activities are called for. The advantages of having handbooks applicable to standardized materials made readily available to users is stressed. Applied safety factors for a project are based on experience and the ratio of ultimate versus yield stress of the material. The factors influencing the safety of ductile and brittle materials are discussed. The importance of improving the knowledge of such safety behavior ESA in nonhomogeneous polymer materials is stressed. COST OPTIMISATION OF LOAD CARRYING STRUCTURES C18 B. A. Reid and A. Pradier (European Space Agency. European Space Research and Technology Center, ESTEC, Noordwijk, Netherlands) In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 397-402 (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 Research on identifying cost drivers and establishing guidelines for optimizing the cost of satellite structures is described. Specifications envelope, qualification philosophy, and standardization and methodology are identified as critical cost drivers. To assess the impact of material selection on achievement of the mass budget, alternative minimum mass and minimum cost design philosophies are applied to a range of materials. It is found that applying minimum mass philosophy to each material, up its performance limit is the most cost effective. ESA TESTING AND INTEGRITY OF THERMOSTRUCTURAL D. P. Bashford and R. Raynal (European Space Agency. European Copyright Avail: NTIS HC/MF A19 The properties of continuous fiber ceramic matrix composites are investigated. Very high temperatures, around 1600 C, are needed to characterize these materials, in both neutral and oxidizing atmospheres. The key mechanical characteristics relating to tensile, compressive, shear and flexural loading modes are discussed. The factors to be considered before developing test methods are identified. These include representative test specimens, machining, load introduction, strain measurement and failure characteristics. The significance of fracture characteristics is assessed in relation to design allowables. N91-11872# ESA Avions Marcel Dassault-Breguet Aviation, Saint-Cloud (France). Gerard Bernhart In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 411-417 (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 The general logic of a material testing program designed to test the Hermes Thermal Protection System (TPS) is described. Mission specifications during launch, orbital mission and reentry are taken into consideration in the program. Two types of materials, carbon-carbon and carbon-silicon carbide composites are selected as candidates for the TPS system. The specifications of each of these materials are presented with respect to the nominal design. Definition of antioxidation processes is discussed. Optimal material development is outlined. ESA N91-11873# Aerospatiale Aquitaine, Saint-Medard en Jalles (France). Strategic and Space Div. SIMOUN: NEW TEST METHODS FOR DEVELOPMENT WORK c18 In P. Charpentier and R. Leroux In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 419-425 FRENCH (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 The SIMOUN test apparatus is described. It is designed for testing the thermal protection systems developed for the Hermes Manned Space Plane. It develops a flow of extremely hot air by means of a plasma generator. The potential uses and various configurations possible using the system are described. Diagrams and photographs of the test apparatus are presented. The various parameters that can be simulated using SIMOUN are described. The operational framework and organization of test apparatus operation are described. ESA N91-11874# United Kingdom Atomic Energy Authority, Harwell (England). Dept. of Advanced Engineering Materials. THE CURRENT STATUS AND FUTURE PROSPECTS OF R. Davidson In ESA, Space Applications of Advanced Structural Copyright Avail: NTIS HC/MF A19 Smart or intelligent materials, modeled on biological systems with sensors acting as a nervous system are discussed. Actuators act as muscles in these materials and real time computers act as a brain to interpret signals and control the system. Smart materials concepts are most easily applied in structural composite materials where appropriate sensors and actuators can be embedded into the structure during manufacture. The concepts involved in this area are reviewed. What is currently possible and will be possible in the future through emerging technology is discussed. ESA N91-11875# Dornier System G.m.b.H., Friedrichshafen (Germany, F.R.). MULTIFUNCTIONAL STRUCTURES FOR AEROSPACE Kay W. Dittrich In ESA, Space Applications of Advanced Structural Copyright Avail: NTIS HC/MF A19 Multifunction or smart structures are discussed. Such structures are defined as structures incorporating additional functions besides the function of load carrying. The additional functions may be sensing, communication data processing or shape changing. To achieve this multifunctionality, additional elements must be embedded into the structure. Ways in which smart structures may enhance the performance and reduce the weight of space structures are discussed. Incorporation of antennas, sensors, electronics, processors, etc., into spacecraft construction materials is discussed. ESA DEVELOPMENT OF INTELLIGENT STRUCTURES Copyright Avail: NTIS HC/MF A19 The development of structures within composite materials used to provide a quiet vibration free mounting for sensitive equipment is described. Fiber optic sensors embedded in composite thermoset materials can measure vibration. Advanced thermoplastic composites offer better environmental characteristics. Ways to incorporate vibration free structures into a carbon fiber reinforced thermoplastic matrix are discussed. Development of an actuation system to counteract vibration is described. Difficulties involved in M. P. Hentschel, A. Lange, and W. Harbich In ESA, Space Applications of Advanced Structural Materials Jun. 1990 p 447-450 (For primary document see N91-11812 03-24) Copyright Avail: NTIS HC/MF A19 The uses of x ray diffraction scanning microscopy in gaining greater insight into the microstructure of opaque materials are described. Computer section images of the layered structures of thick carbon fiber reinforced plastic and carbon fiber reinforced ceramic samples are shown. The method can be applied to condensed matter of any kind. The technique can be considered as an expansion of classical x ray tomography. Use of the method is recommended for new material development rather than large structure inspection. ESA N91-11878# Ballistic Research Labs., Aberdeen Proving Ground, CURE SIMULATION OF THICK THERMOSETTING Travis A. Bogetti and John W. Gillespie, Jr. (Delaware Univ., (DA Proj. 1L1-662618-AH-80) (AD-A224885; BRL-TR-3121) Avail: NTIS HC/MF A04 CSCL 13/8 The potential for enhanced performance characteristics of composite materials over conventional metals, such as high strength-to-weight ratio, high stiffness, corrosion resistance and low radar signature, makes them extremely attractive for a wide range of military applications. The curing process of thick-section thermosetting composites is critical to the quality and in-service performance of the finished component. An investigation into the 2-D cure simulation of thick thermosetting composites is presented. Temperature and degree of cure distributions within typical glass/polyester and graphite/epoxy structural elements of arbitrary cross-section (ply-drop and angle bend) are analyzed to provide insight into the non-uniform curing process unique to thick-sections. An incremental, transient finite difference solution scheme is implemented to solve the pertinent governing equations and boundary conditions. Correlation between experimentally measured and predicted through-the-thickness temperature profiles in glass/polyester laminates are presented for various arbitrary temperature cure cycle histories. Spatial gradients in degree of cure are shown to be strongly dependent on part geometry, thermal anisotropy, cure kinetics and the temperature cure cycle. These spatial gradients directly influence the quality and in-service performance of the finished component by inducing warpage and residual stress during the curing process. GRA N91-11879# Colorado School of Mines, Golden. Center for FUNDAMENTAL CONCEPTS OF WETTABILITY AND Glen R. Edwards and David L. Olson Jul. 1990 52 p (AD-A225158; CSM-MT-CWR-090-012) Avail: NTIS HC/MF A04 CSCL 07/4 Research accomplishments include: Surface Energy Measurement - Differential optical reflectance was used to measure the optical transitions in aluminum and its alloys. The semi-empirical correlation developed earlier was used to calculate the surface energy from the measured transition energies. Predicted surface energies, using the model, were in close agreement with experimentally determined surface energies found in the literature. Wettability Predictions - Wettability studies are based on surface DESIGNING COMPOSITE STRUCTURES FOR LOW-VELOCITY IMPACT M.S. Thesis Timothy Clark Lindsay Aug. 1990 353 p (AD-A225217) Avail: NTIS HC/MF A16 CSCL 11/4 This thesis presents a methodology and set of tools which the designer can use to improve the resistance of composite structures to low-velocity impacts typical of those experienced in the maintenance, handling, service, and manufacturing of composites, typically termed tool drops. The author has investigated the role of simple analysis and experimental techniques which may be used in the early stages of concept evaluation to provide design-decision support for impact resistant concepts. Identifying the most important customer needs and related design criteria through the application of a coherent, cohesive, and comprehensive design methodology is the first step in a successful design, and insuring that these customer needs are translated through the design, engineering, and manufacture of the product is the essence of design. The author has developed a comprehensive impact design methodology which is contextual, i.e., it is presented in the context of all other design criteria. Instrumented impact testing has been used to identify the incipient damage load in typical unidirectional carbon fiber thermoset and thermoplastic matrix composite coupons subjected to low-velocity impacts. Results have been correlated with static load-deflection response of equivalent coupons in a unique test setup using the same apparatus and then correlated with a finite element analysis of the test specimens. GRA N91-11881# Dayton Univ., OH. COMPOSITES SUPPORTABILITY RAPID TEST AND (Contract F33615-86-C-5031) (AD-A225243; UDR-TR-90-24; WRDC-TR-90-4035) Avail: NTIS HC/MF A08 CSCL 11/1 Materials investigations were conducted in the general areas of adhesive bonding, composite materials, aircraft transparencies, and elastomeric seals. These studies were oriented towards characterization of new materials and processes, development of repair techniques, development of new processing techniques, and solution of current operational problems involving materials and processing. Some qualification testing was carried out on new materials. Studies involved the characterization of inorganic and water-based primers for adhesive bonding, adhesive and resins for aircraft repair, novel surface preparation procedures for aluminum and composite adherends, high temperature adhesives, bonding of aluminum castings, composite paint removal techniques, techniques to prepare thermoplastic prepreg, use of induction heating to cure composites, honeycomb repair procedures, evaluation of heat lamps for curing of composite repair patches, assessment of resin transfer molding for filament wound structure, studies of battle-damage-repair techniques for aircraft transparencies, and determination of aircraft fuel and lubricating oil compatibility with elastometic seal materials. GRA 80 P Arthur C. Lind and Charles G. Fry 9 Apr. 1990 Nuclear magnetic resonance (NMR) was studied for use in the nondestructive evaluation of composite materials, with particular emphasis on NMR imaging. NMR parameters of potential use for generating images showing high contrast between acceptable and unacceptable regions of composites were measured for typical organic matrix materials. The attenuating effects of carbon fibers were measured and relationships were developed to compute the conditions necessary to obtain images of carbon fiber composites. NMR images of aerospace composites containing poly(aryl-ether-ether-ketone) (PEEK) and epoxy resins were obtained using solid state C-13 techniques. The contrast mechanism used for these images was the composites. NMR images of hydrogen in PEEK were also obtained using multiple pulse techniques to reduce dipolar broadening. Selective pulses were used to obtain images of the spatial variations in the crystalline content of PEEK. The results of these experiments were used to assess the feasibility of using NMR for nondestructive evaluation of composite materials. GRA N91-11908# Office National d'Etudes et de Recherches METAL MATRIX COMPOSITE WITH LONG FIBERS (LES J. F. Stohr In AGARD, New Light Alloys Sep. 1990 39 P In FRENCH, ENGLISH summary (For primary document see N91-11905 03-26) Copyright Avail: NTIS HC/MF A11; Non-NATO Nationals requests available only from AGARD/Scientific Publications Executive N91-11909# Nottingham Univ. (England). Dept. of Materials DEVELOPMENTS IN PARTICULATE AND SHORT FIBER S. J. Harris In AGARD, New Light Alloys Sep. 1990 21 p (For primary document see N91-11905 03-26) Copyright Avail: NTIS HC/MF A11; Non-NATO Nationals requests available only from AGARD/Scientific Publications Executive 25 INORGANIC AND PHYSICAL CHEMISTRY Includes chemical analysis, e.g., chromatography; combustion theory; electrochemistry; and photochemistry. For related information see also 77 Thermodynamics and Statistical Physics.. N91-11883 Michigan Univ., Ann Arbor. Avail: Univ. Microfilms Order No. DA9023587 drop An experimental and theoretical study of combusting monopropellant (hydroxylammonium-nitrate-based liquid gun propellants) sprays at pressures of 3 to 9 MPa was considered. Measurements of spray combustion properties included liquid volume fraction profiles, drop size distributions, and liquid mass flux profiles. Locally-homogeneous and separated flow analyses were developed to estimate the structure of the combusting monopropellant sprays. In addition, monopropellant combustion properties were observed and drop burning rates were measured (for use in the separated flow analysis) using drops supported in a combustion gas environment at pressures of 0.2 to 7.0 MPa. Observations of monopropellant drop combustion properties showed that subsurface liquid reactions leading to bubble growth and microexplosions dominated the process at low pressures while conventional surface gasification dominated the process at high pressures. The drop burning rates of 10 to 20 mm/s, with weak pressure dependence, were observed. Present findings were consistent with measurements for gelled propellants at pressures greater than 10 mPa. Present measurements of monopropellant spray combustion properties yielded a much larger liquid-containing region than earlier measurements. Furthermore, locally-homogeneous flow predictions generally overestimated rates of spray development for present test conditions, since separated-flow effects due to non-negligible relative phase velocities, finite interphase transport rates, and finite rates of drop combustion were important. In contrast, the present separated-flow analysis yielded the correct trends of variations of Sauter mean diameters, drop size distributions, and liquid mass flow rates of the sprays. Dissert. Abstr. N91-11884 Georgia Inst. of Tech., Atlanta. Avail: Univ. Microfilms Order No. DA9023833 Progress in the measurement of correlations involving pressure in a turbulent premixed flame is presented. The goal is to measure all of the terms necessary to calculate the pressure-strain and pressure-scalar gradient correlations as are found in stress and scalar transport equations. A stoichiometric, turbulent premixed methane-air flame open to the surroundings is used as the test medium. The experimental techniques used are molecular Rayleigh scattering for density measurement, laser Doppler velocimetry for velocity measurement, and dynamic Pitot barometry for pressure measurement. The terms in the pressure-scalar gradient correlation which have been measured are presented and the pressure-density correlation is shown to be important in scalar transport equations. Current numerical approximation of the derivatives involved is shown to lack the accuracy needed to determine the pressure-scalar gradient correlation because of the errors involved. A new technique to accomplish these measurements was developed which involves the spatial separation of the two components of the laser Doppler velocimeter. The concept of the spatial separation was verified for a constant density air flow and then pressure-velocity correlations using both Pitot barometry and the spatial separation technique were compared, and the results show that both the spatial separation and the Pitot barometry are reliable methods to measure correlations involving pressure. Dissert. Abstr. N91-11885 Council for National Academic Awards (England). F. L. J. deCastro 1989 390 p Avail: Univ. Microfilms Order No. BRDX89764 A zero-dimensional model of turbulent combustion was developed for the spark ignition engine. In addition to the prediction of thermodynamic state properties, the model includes the following elements: heat transfer from the combustion chamber, a geometrical model of turbulent spherical flame propagation, and detailed post flame chemical equilibria. The model is responsive to such engine operating parameters as spark timing, equivalence ratio, engine speed, and also to such design parameters as compression ratio, spark plug position, and combustion chamber geometry. Two different geometries were studied extensively with the program, namely the disc chamber and the bowl-in-piston chamber. Ethanol and isooctane were investigated as fuels during the numerical simulations at variable conditions of spark advance, equivalence ratio, engine speed, and compression ratio. The model was employed in a partly diagnostic role to predict the engine performance using different correlations for a critical model parameter, the flame speed ratio. Comparison between prediction and experiment was made possible by a diagnostic investigation of the expanding flame front into the combustion chamber of a homogeneous charge spark ignition engine. The turbulent flame speed was determined experimentally by a dual-beam laser deflection technique. The measurement of flame transit times was performed using a specially designed and built system incorporating equipment for data acquisition based on a microcomputer. The results obtained experimentally and those obtained by the numerical simulation in general show good agreement. In the absence of detailed in-cylinder turbulence information the more fundamentally-based turbulent flame propagation models often do not perform as satisfactorily as those developed specifically for zero-dimensional engine simulation. Dissert. Abstr. N91-11886# Army Cold Regions Research and Engineering Lab., PURITY DETERMINATION OF STANDARD ANALYTICAL Patrick B. Black and Dean Pidgeon May 1990 11 p Sponsored by Army Toxic and Hazardous Materials Agency, Aberdeen Proving Ground, MD (AD-A224669; CRREL-SR-90-16; CETHA-TE-CR-89044) Avail: NTIS HC/MF A03 CSCL 14/2 Standard Analytical Reference Materials (SARMs) are a high-purity representative set of compounds used in the production of explosives. Because the National Bureau of Standards has only a limited amount of these reference materials available for trace organic analysis, the United States Army Toxic and Hazardous Materials Agency (USATHAMA) has initiated a program for developing SARMs for use in its laboratories (USATHAMA 1987). This two-part program consists of procuring and producing the high-purity reference materials and then monitoring their purity level while in storage. This paper, which is concerned with the second part of the program, reports on the method of determining the purity of the seven SARMs noted in Table 1 that are suited to differential scanning calorimetry (DSC). The purity of the remaining SARMS are determined by other methods and will not be discussed further. The USATHAMA Quality Assurance program manual (USATHAMA 1987) recommends a surveillance program that tests the purity of the SARMS at six-month intervals. For this project the criterion that is used for accepting the standard is that it does not have a purity level below 98 mol percent. If the SARM fails to meet this criterion, the central repository is to be contacted and appropriate decisions made on its status. GRA N91-11887# State Univ. of New York, Buffalo. Dept. of CLUSTER PRODUCTION IN FREE-JET EXPANSIONS: Jul. J. R. Grover (Brookhaven National Lab., Upton, NY.), W. J. Herron, M. T. Coolbaugh, William R. Peifer, and James F. Garvey 1990 14 p Submitted for publication (Contracts N00014-88-K-0493; DE-AC02-76CH-00016) (AD-A224692; TR-15) Avail: NTIS HC/MF A03 CSCL 20/5 Molecular beams collimated from the free jet expansion of a 200:1 ammonia-chlorobenzene mixture were analyzed to obtain the relative intensities of the neutral clusters produced, and their dependence on nozzle pressure up to 1200 torr. A single photon photoionization method was used. All species observed, (NH3)2, (NH3)4, C6H5CI NH3, and C6H5CI(NH3)2, rise rapidly from low pressure but decrease slowly to higher pressures, contrary to present understanding. Possible reasons for this behavior are discussed. Jet expansions of ammonia readily induce condensation, so this phenomenon has long been used to make ammonia clusters for spectroscopic, thermochemical, and reactivity studies. N91-11888# Engineering. GRA Wisconsin Univ., Milwaukee. Dept. of Mechanical used in a stored chemical energy propulsion system. The reactants considered are molten lithium fuel and gaseous sulfur hexafluoride oxidant. Extensive equilibrium state relationships as a function of mixture fraction were presented over a temperature range of possible operating conditions. They were subsequently employed to predict the complex flow structure of a choked, turbulent, reacting SF6 gas jet submerged in a molten lithium bath. Detailed profiles of velocity, temperature, void fraction and mass fraction of all phases in the jet were presented. GRA N91-11889# Ballistic Research Labs., Aberdeen Proving Ground, A METHODOLOGY FOR QUANTITATIVE COMPARISON OF Tracy P. Hindman and Bambi S. Steelman Jul. 1990 89 p Evaluation techniques were developed to assess computer simulation of single chemical munition field trials. These techniques were used to quantitatively compare the predicted to experimental deposition data. The methods employed for evaluating single munitions are not appropriate for the multiple munition field trials that are currently being conducted. Hence, the data fitting techniques were re-examined and new methodology developed that could be applied regardless of the number of munitions tested. The statistical tests chosen were the Sign, Mann-Whitney U, and Chi-Square tests. An additional metric was a modified version of the Chi-Square, referred to as the Point-by-Point. Each test was exercised using data from eleven field trials to test its appropriateness for this application. A bet-fit criterion was established based on the evaluation of the test results. GRA Polarimetry and spectropolarimetry are optical measurement techniques which use polarized light to obtain electrooptical material property information. These techniques are being used to make measurements on infrared electrooptical materials. Infrared materials of interest are those which find use in two dimensional modulators, i.e., optical processing applications and infrared scene projectors. Polarimetry measurements are made at one infrared wavelength at a time using laser sources. Spectropolarimetry measurements are made over an entire infrared spectral region, e.g., 2 to 14 um. A Fourier transform infrared spectrometer is the source of radiation in this case. The Mueller matrix formulation can be used to describe the polarized light and its interaction with the sample and measurement system optics. A Mueller matrix of the sample can then be obtained from a series of measurements with different input polarization states. The sample Mueller matrix contains information on the polarization properties. Electric fields are imposed on the sample as optical measurements are made. Fundamental constants associated with the sample material can be derived from the measured Mueller matrix elements. GRA N91-11891# Rice Univ., Houston, TX. Dept. of Chemistry. SEMICONDUCTOR CLUSTER SURFACE CHEMISTRY Interim Technical Report Richard E. Smalley 2 Aug. 1990 21 p Presented at the ONR Cluster Science Workshop, Lake Arrowhead, CA, Jan. 1990 (Contract N00014-88-K-0553) (AD-A224947; TR-7) Avail: NTIS HC/MF A03 CSCL 07/4 The combination of laser-vaporization supersonic cluster beam techniques with the technology of Fourier transform ion cyclotron resonance, FT-ICR, has opened a new approach to the detailed |