ALBERT

Description: A model of the complex between the acetylcholine receptor and the snake neurotoxin, cobratoxin, was built by molecular model building and energy optimization techniques. The experimentally identified functionally important residues of cobratoxin and the dodecapeptide corresponding to the residues 185-196 of acetylcholine receptor alpha subunit were used to build the model. Both cis and trans conformers of cyclic L-cystine portion of the dodecapeptide were examined. Binding residues independently identified on cobratoxin are shown to interact with the dodecapeptide AChR model.

Description: A 26-year-old man presented with ipsilateral femur and ankle fractures. The patient was treated with interlocking nail of his femur fracture, followed by open reduction and internal fixation of his ankle fracture under tourniquet control. Postoperatively, the patient developed compartment syndrome of his thigh with elevated pressures, requiring decompressive fasciotomies. This case illustrates the possible complication of treating a femur fracture with intramedullary nailing and then immediately applying a tourniquet to treat an ipsilateral extremity fracture. Because of the complication with this patient, we feel the procedure should be staged, or a tourniquet should be avoided if possible.

Description: No abstract available

Description: No abstract available

Description: Previous studies have shown that a decrease in red cell mass occurs in astronauts, and some studies indicate a leukocytosis occurs. A life science module housing young and mature rats was flown on shuttle mission Spacelab 3 (SL-3), and the results of hematology studies of flight and control rats are presented. Statistically significant increases in the hematocrit, red blood cell counts, and hemoglobin determinations, together with a mild neutrophilia and lymphopenia, were found in flight animals. No significant changes were found in bone marrow and spleen cell differentials or erythropoietin determinations. Clonal assays demonstrated an increased erythroid colony formation of flight animal bone marrow cells at erythropoietin doses of 0.02 and 1.0 U/ml but not 0.20 U/ml. These results agree with some but vary from other previously published studies. Erythropoietin assays and clonal studies were performed for the first time.

Description: To gain some insight into the early effects of spaceflight on skeletal metabolism, we quantified the major chemical constituents and a noncollagenous protein, osteocalcin, in the third-lumbar vertebrae and humeri from 8-wk-old rats that were part of the 7-day NASA Spacelab 3 flight experiments. The ratio of calcium to hydroxyproline in the humeral diaphysis increased from 8.5 in preflight to 9.8 in ground simulation control and only to 8.9 in flight bones. There was no demonstrable change in the fraction of nonmineralized collagen. Osteocalcin content was reduced in the humerus and vertebra. Reduced accumulation of mineral and osteocalcin with no associated decrease in collagen in flight animals suggests that both mineralization and collagen metabolism are impaired in growing animals during spaceflight within a few days after launch. Strength tests of the humeri of flight rats showed substantial deficits that appeared to be related, not only to the reduced bone mass, but also to the composition and quality of new bone formed.

Description: Five small (55 days old, 196 +/- 5 g) (mean +/- SE) and five large (83 days old, 382 +/- 4 g) Sprague-Dawley strain, specific pathogen-free rats were exposed to a 7-day spaceflight and 12-h postflight recovery period. As measured in 3-micron sections, periodontal ligament (PDL) fibroblastlike cells were classified according to nuclear size: A + A' (40-79), B (80-119), C (120-169), and D (greater than or equal to 170 microns 3). Since the histogenesis sequence is A----A'----C----D----osteoblast, the relative incidence of A + A' to C + D is an osteogenic index. No difference in A + A' or C + D cells in small rats may reflect partial recovery of preosteoblast formation (A----C) during the 12-h postflight period. Large flight rats demonstrated increased numbers of A + A', indicating an inhibition of preosteoblast formation (A----C). At least in the older group, a 7-day flight is adequate to reduce PDL osteogenic potential (inhibition in PDL osteoblast differentiation and/or specific attrition of C + D cells) that does not recover by 12-h postflight.

Description: Male Sprague-Dawley rats were placed in orbit for 7 days aboard the space shuttle. Bone histomorphometry was performed in the long bones and lumbar vertebrae of flight rats and compared with data derived from ground-based control rats. Trabecular bone mass was not altered during the 1st wk of weightlessness. Strong trends were observed in flight rats for decreased periosteal bone formation in the tibial diaphysis, reduced osteoblast size in the proximal tibia, and decreased osteoblast surface and number in the lumbar vertebra. For the most part, histological indexes of bone resorption were normal in flight rats. The results indicate that 7 days of weightlessness are not of sufficient duration to induce histologically detectable loss of trabecular bone in rats. However, cortical and trabecular bone formation appear to be diminished during the 1st wk of spaceflight.

Description: In the course of a 5-day space flight of two rhesus-monkeys the following parameters were recorded at an interval of 16 min: core body temperature (Tc), skin temperature (Ts), and motor activity (MA). The telemetric Tc sensor was implanted subcutaneously in the right axilla, Ts thermistor was attached to the right ankle, and the MA piezotape was fixed to the inner side of the vest. Circadian rhythms of Tc varied with a period of 24 hours in one monkey and 25 hours in the other. The daily Tc decreased on the average by 0.5 degrees C, Ts fell immediately after launch and remained close to the lower limit throughout the flight. The Ts amplitude decreased 5-fold. Phases of the circadian rhythms of Ts changed and circadian rhythms of MA remained unchanged and equal to 24 hours.

Description: The neural mismatch theory of space motion sickness asserts that the central and peripheral autonomic sequelae of discordant sensory input arise from central integrative processes falling to reconcile patterns of incoming sensory information with existing memory. Stated differently, perceived novelty reaches a stress level as integrative mechanisms fail to return a sense of control to the individual in the new environment. Based on evidence summarized here, the severity of the neural mismatch may be dependent upon the relative amount of attention selectively afforded to each sensory input competing for control of behavior. Components of the limbic system may play important roles in match-mismatch operations, be therapeutically modulated by antimotion sickness drugs, and be optimally positioned to control autonomic output.

Description: Prolonged exposure of humans to hypogravity causes weakening of their skeletal muscles. This problem was studied in rats exposed to hypogravity for 7 days aboard Spacelab 3. Hindlimb muscles were harvested 12-16 hours postflight for histochemical, biochemical, and ultrastructural analyses. The majority of the soleus and extensor digitorum longus fibers exhibited simple cell shrinkage. However, approximately 1% of the fibers in flight soleus muscles appeared necrotic. Flight muscle fibers showed increased glycogen, lower subsarcolemmal staining for mitochondrial enzymes, and fewer subsarcolemmal mitochondria. During atrophy, myofibrils were eroded by multiple focal losses of myofilaments; lysosomal autophagy was not evident. Tripeptidylaminopeptidase and calcium-activated protease activities of flight soleus fibers were significantly increased, implying a role in myofibril breakdown. Simple fiber atrophy appears to account for muscle weakening during spaceflight, but fiber necrosis is also a contributing factor.

Description: Further insight into the structure and dynamics of amorphous water ice, at low temperatures, was obtained by trapping in it Ar, Ne, H2, and D2. Ballistic water-vapor deposition results in the growth of smooth, approximately 1 x 0.2 micrometer2, ice needles. The amorphous ice seems to exist in at least two separate forms, at T 〈 85 K and at 85 〈 T 〈 136.8 K, and transform irreversibly from one form to the other through a series of temperature-dependent metastable states. The channels formed by the water hexagons in the ice are wide enough to allow the free penetration of H2 and D2 into the ice matrix even in the relatively compact cubic ice, resulting in H2-(D2-) to-ice ratios (by number) as high as 0.63. The larger Ar atoms can penetrate only into the wider channels of amorphous ice, and Ne is an intermediate case. Dynamic percolation behavior explains the emergence of Ar and Ne (but not H2 and D2) for the ice, upon warming, in small and big gas jets. The big jets, each containing approximately 5 x 10(10) atoms, break and propel the ice needles. Dynamic percolation also explains the collapse of the ice matrix under bombardment by Ar , at a pressure exceeding 2.6 dyn cm-2, and the burial of huge amounts of gas inside the collapsed matrix, up to an Ar-to-ice of 3.3 (by number). The experimental results could be relevant to comets, icy satellites, and icy grain mantles in dense interstellar clouds.

Description: No abstract available

Description: In an effort to determine which biological reactions can occur in relation to the water content of seeds, the regulation of lettuce seed dormancy by red and far red light was determined at various hydration levels. Far red light had an inhibiting effect on germination for seeds at all moisture contents from 4 to 32% water. Germination was progressively stimulated by red light as seed hydration increased from 8 to 15%, and reached a maximum at moisture contents above 18%. Red light was ineffective at moisture contents below 8%. Seeds that had been stimulated by red light and subsequently dried lost the enhanced germinability if stored at moisture contents above 8%. The contrast between the presumed photoconversion of phytochrome far red-absorbing (Pfr) to (Pr) occurring at any moisture content and the reverse reaction occurring only if the seed moisture content is greater than 8% may be explained on the basis of the existence of unstable intermediates in the Pr to Pfr conversion. Our results suggest that the initial photoreaction involved in phytochrome conversion is relatively independent of water content, while the subsequent partial reactions become increasingly facilitated as water content increases from 8 to 18%.

Description: Some characteristics of the gravity sensing mechanism in maize root caps were investigated using a bioelectric current as an indicator of gravity sensing. This technique involves the measurement of a change in the current density which arises at the columella region coincidently with the presentation time. Two inhibitors of auxin transport, triiodobenzoic acid and naphthylphthalamic acid, blocked gravitropic curvature but not the change in current density. Two inhibitors of calmodulin activity, compound 48/80 and calmidazolium, blocked both curvature and gravity-induced current. The results suggest that auxin transport is not a component of gravity sensing in the root cap. By contrast, the results suggest that calmodulin plays an intrinsic role in gravity sensing.

Description: We placed agar blocks adjacent to tips of electrotropically stimulated primary roots of Zea mays. Blocks placed adjacent to the anode-side of the roots for 3 h induced significant curvature when subsequently placed asymmetrically on tips of vertically-oriented roots. Curvature was always toward the side of the root unto which the agar block was placed. Agar blocks not contacting roots and blocks placed adjacent to the cathode-side of electrotropically stimulated roots did not induce significant curvature when placed asymmetrically on tips of vertically-oriented roots. Atomic absorption spectrophotometry indicated that blocks adjacent to the anode-side of electrotropically-stimulated roots contained significantly more calcium than (1) blocks not contacting roots, and (2) blocks contacting the cathode-side of roots. These results demonstrate the presence of a gradient of endogenous Ca in mucilage of electrotropically-stimulated roots (i.e. roots undergoing gravitropic-like curvature).

Description: We launched imbibed seeds of Zea mays into outer space aboard the space shuttle Columbia to determine the influence of microgravity on cellular differentiation in root caps. The influence of microgravity varied with different stages of cellular differentiation. Overall, microgravity tended to 1) increase relative volumes of hyaloplasm and lipid bodies, 2) decrease the relative volumes of plastids, mitochondria, dictyosomes, and the vacuome, and 3) exert no influence on the relative volume of nuclei in cells comprising the root cap. The reduced allocation of dictyosomal volume in peripheral cells of flight-grown seedlings correlated positively with their secretion of significantly less mucilage than peripheral cells of Earth-grown seedlings. These results indicate that 1) microgravity alters the patterns of cellular differentiation and structures of all cell types comprising the root cap, and 2) the influence of microgravity on cellular differentiation in root caps of Zea mays is organelle specific.

Description: This time course and location of gravitropically induced curvatures in stems of goosegrass (Gallium aparine L.), a member of the Rubiaceae, have been investigated. In the early stages of the response (0-5 h), curvature develops throughout the growing region, and is followed by an autotropic straightening which affects the internodes only, leading to the production of essentially straight internodes some 15 h after the onset of gravistimulation. Curvatures developing in the nodal regions, however, continue to increase over this period, and are not subject to reversal by autotropism. The nodal curvatures are not entirely dependent on the presence of any other part of the plant, since marked curvatures can be induced in isolated nodal segments. This pattern of response leads ultimately to correction of the growth direction of the plant by means of curvature responses confined exclusively to the nodes, despite the initial participation of both nodes and internodes in the gravitropic reaction.

Description: A preservation technique for urine specimens before determination of stone risk factors was evaluated. The purpose of these experiments was to prove the effectiveness of the preservatives used to prevent changes in the concentrations of those constituents measured. Measured concentrations in fresh specimens were compared with those in the same specimens after storage with the preservatives. Refrigeration at 4 degrees C up to five days was appropriate in a laboratory setting, as no significant changes in urinary concentrations occurred. Refrigeration, however, did not offer a convenient method for shipping. Chemical preservation was found to be an effective alternative to refrigeration. Thymol prevented changes in concentration of pH, citrate, uric acid, sulfate, sodium, potassium, and cyclic AMP, while a mixture of hydrochloric (HCl) acid and boric acid prevented changes in calcium, magnesium, phosphorus, oxalate, ammonium, and creatinine. Thus, the addition of thymol or HCl/boric acid to urine specimens will prevent significant changes in the concentrations of stone risk factors.

Description: When water uptake by growing cells is prevented, the turgor pressure and the tensile stress in the cell wall are reduced by continued wall loosening. This process, termed in vivo stress relaxation, provides a new way to study the dynamics of wall loosening and to measure the wall yield threshold and the physiological wall extensibility. Stress relaxation experiments indicate that wall stress supplies the mechanical driving force for wall yielding. Cell expansion also requires water absorption. The driving force for water uptake during growth is created by wall relaxation, which lowers the water potential of the expanding cells. New techniques for measuring this driving force show that it is smaller than believed previously; in elongating stems it is only 0.3 to 0.5 bar. This means that the hydraulic resistance of the water transport pathway is small and that rate of cell expansion is controlled primarily by wall loosening and yielding.

Description: In an effort to define the nature of desiccation tolerance, a comparison of the water sorption characteristics was made between tissues that were resistant and tissues that were sensitive to desiccation. Water sorption isotherms were constructed for germinated and ungerminated soybean axes and also for fronds of several species of Polypodium with varying tolerance to dehydration. The strength of water binding was determined by van't Hoff as well as D'Arcy/Watt analyses of the isotherms at 5, 15, and/or 25 degrees C. Tissues which were sensitive to desiccation had a poor capacity to bind water tightly. Tightly bound water can be removed from soybean and pea seeds by equilibration at 35 degrees C over very low relative humidities; this results in a reduction in the viability of the seed. We suggest that region 1 water (i.e. water bound with very negative enthalpy values) is an important component of desiccation tolerance.

Description: The objective evidence of silent myocardial ischemia--ischemia in the absence of classical chest pain--includes ST-segment shifts (usually depression), momentary left ventricular failure, and perfusion defects on scintigraphic studies. Assessment of angina patients with 24-hour ambulatory monitoring may uncover episodes of silent ischemia, the existence of which may give important information regarding prognosis and may help structure a more effective therapeutic regimen. The emerging recognition of silent ischemia as a significant clinical entity may eventually result in an expansion of current therapy--not only to ameliorate chest pain, but to minimize or eliminate ischemia in the absence of chest pain.

Description: 1. Neural activity was recorded in an in vitro hamster hippocampal slice preparation while the temperature of the Ringer's solution bathing in the slice was controlled at selected levels. 2. The amplitude of the population spike (action potentials from a group of pyramidal cells) was measured as bath temperature was lowered from 35 degrees C to temperatures where a response could not be evoked. 3. Plots of population spike amplitude versus temperature have bell-shaped curves. The population spikes increased in amplitude as temperature was lowered from 35 degrees C, reached a peak amplitude between 25 and 20 degrees C, and then decreased until a response could not be evoked when temperature was further lowered. 4. These in vitro results obtained in the slice preparation are related to in vivo hippocampal studies. Results are interpreted as consistent with the proposal reviewed here that neural activity in the hippocampus plays a role at specific stages of entrance into and arousal from hibernation.

Description: We used quantitative electron-probe energy-dispersive x-ray microanalysis to localize endogenous Na, Cl, K, P, S, Mg and Ca in cryofixed and freeze-dried cryosections of the cap (i.e. the putative site of graviperception) and elongating zone (i.e. site of gravicurvature) of horizontally oriented roots of Zea mays. Ca, Na, Cl, K and Mg accumulate along the lower side of caps of horizontally oriented roots. The most dramatic asymmetries of these ions occur in the apoplast, especially the mucilage. We could not detect any significant differences in the concentrations of these ions in the central cytoplasm of columella cells along the upper and lower sides of caps of horizontally-oriented roots. However, the increased amounts of Na, Cl, K and Mg in the longitudinal walls of columella cells along the lower side of the cap suggest that these ions may move down through the columella tissue of horizontally-oriented roots. Ca also accumulates (largely in the mucilage) along the lower side of the elongating zone of horizontally-oriented roots, while Na, P, Cl and K tend to accumulate along the upper side of the elongating zone. Of these ions, only K increases in concentration in the cytoplasm and longitudinal walls of cortical cells in the upper vs lower sides of the elongating zone. These results indicate that (1) gravity-induced asymmetries of ions differ significantly in the cap and elongating zone of graviresponding roots, (2) Ca accumulates along the lower side of the cap and elongating zone of graviresponding roots, (3) increased growth of the upper side of the elongating zone of horizontally-oriented roots correlates positively with increased amounts of K in the cytoplasm and longitudinal walls of cortical cells, and (4) the apoplast (especially the mucilage) may be an important component of the pathway via which ions move in graviresponding rots of Zea mays. These results are discussed relative to mechanisms for graviperception and gravicurvature of roots.

Description: The effect of radiogenic heating on the thermal evolution of spherical icy bodies with radii 1 km 〈 R 〈 100 km was investigated. The radioisotopes considered were 26Al, 40K, 232Th, 235U, and 238U. Except for the 26Al abundance, which was varied, the other initial abundances were kept fixed, at values derived from those of chondritic meteorites and corresponding to a gas-to-dust ratio of 1. The initial models were homogeneous and isothermal (To = 10 K) amorphous ice spheres, in a circular orbit at 10(4) AU from the Sun. The main object of this study was to examine the conditions under which the transition temperature from amorphous into cubic ice (Ta = 137 K) would be reached. It was shown that the influence of the short-lived radionuclide 26Al dominates the effect of other radioactive species for bodies of radii up to approximately 50 km. Consequently, if we require comets to retain their ice in amorphous form, as suggested by observations, an upper limit of approximately 4 x 10(-9) is obtained for the initial 26Al abundance in comets, a factor of 100 lower than that of the inclusions in the Allende meteorite. A lower limit for the formation time of comets may thus be derived. The possibility of a coexistence of molten cometary cores and extended amorphous ice mantles is ruled out. Larger icy spheres (R 〉 100 km) reached Ta even in the absence of 26Al, due to the decay of the other radionuclides. As a result, a crystalline core formed whose relative size depended on the composition assumed. Thus the outermost icy satellites in the solar system, which might have been formed of ice in the amorphous state, have probably undergone crystallization and may have exhibited eruptive activity when the gas trapped in the amorphous ice was released (e.g., Miranda).

Description: In higher plants, polyamines arise from arginine by one of two pathways: via ornithine and ornithine decarboxylase or via agmatine and arginine decarboxylase but in fungi, only the ornithine decarboxylase pathway is present. Since polyamines are required for normal growth of microorganisms and plants and since the ornithine pathway can be irreversibly blocked by alpha-difluoromethylornithine (DFMO) which has no effect on arginine decarboxylase, fungal infection of green plants might be controlled by the site-directed use of such a specific metabolic inhibitor. DFMO at relatively low concentrations provided effective control of the three biotrophic fungal pathogens studied, Puccinia recondita (leaf rust), P. graminis f. sp. tritici (stem rust), and Erysiphe graminis (powdery mildew) on wheat (Triticum aestivum L.) Effective control of infection by leaf or stem rust fungi was obtained with sprays of DFMO that ranged from about 0.01 to 0.20 mM in experiments where the inhibitor was applied after spore inoculation. The powdery mildew fungus was somewhat more tolerant of DFMO, but good control of the pathogen was obtained at less than 1.0 mM. In general, application of DFMO after spore inoculation was more effective than application before inoculation. Less control was obtained following treatment with alpha-difluoromethylarginine (DFMA) but the relatively high degree of control obtained raises the possibility of a DFMA to DFMO conversion by arginase.

Description: An improved synthesis of 7-hydroxy-2-oxoindolin-3-ylacetic acid via the base-induced condensation reaction between oxalate esters and 7-benzyloxyindolin-2-one is described. 7-Benzyloxyindolin-2-one was prepared in four steps and 50% overall yield from 3-hydroxy-2-nitrotoluene. The yield of the title compound from 7-benzyloxyindolin-2-one was 56%. This route was used to prepare 7-hydroxy-2-oxoindolin-3-yl[13C2]acetic acid in 30% yield from [13C2]oxalic acid dihydrate. The method could not be extended to the preparation of the corresponding [14C2]-compound. However, an enzyme preparation from Zea mays roots catalysed the conversion of carrier-free [5-n-3H]indol-3-ylacetic acid with a specific activity of 16.7 Ci mmol-1 to a mixture of 7-hydroxy-2-oxo[5-n-3H]indolin-3-ylacetic acid and its [5-n-3H]-7-O-glucoside in ca. 3 and 40% radiochemical yield respectively. The glucoside was converted into the 7-hydroxy compound in 80% yield by means of beta-glucosidase.

Description: 3'-Amino-3'-deoxyguanosine-5'-phosphorimidazolidate (ImpGNH2) oligomerizes more rapidly and regiospecifically than related nucleotide derivatives on a d(CpCpCpCpC) template. The greater nucleophilicity of the amino group leads to efficient oligomerization even when the structure of the double-helical complex formed by the template and the substrate is not optimal for reaction. The use of amine-containing analogues should permit us to develop models of potentially prebiotic polymerization reactions that cannot be studied easily using natural nucleotides.

Description: Samples of foraminiferal ooze from two North Atlantic cores were cleaned and progressively dissolved. Most of the P, Fe, and Mn was released during the first of two reductive cleaning steps. Most of the remainder of these elements and most of the Ca were released during the final acid dissolution step. The P in these samples is present largely in Fe- and Mn-rich coatings, not as a constituent of the foraminiferal shells themselves. Our results are consistent with those of earlier studies. The concentration of P in carbonate oozes in which it is clearly associated with coatings is similar to that of modern calcareous sediments in general, and with that of reasonably pure limestones of all ages. Phosphorus is apparently associated with (Fe, Mn)-oxide coatings in many carbonate sediments. The rate of removal of P from the oceans as a constituent of such sediments depends on the rate of formation of (Fe, Mn) coatings, not on the rate of incorporation of P into calcium carbonate.

Description: A patient with see-saw nystagmus had a lesion localized by Magnetic Resonance Imaging (MRI) to the paramedian ventral midbrain with involvement of the right interstitial nucleus of Cajal. This the first MRI study of see-saw nystagmus associated with a presumed brainstem vascular event. Our findings support animal and human studies suggesting that dysfunction of the interstitial nucleus of Cajal or its connections is central in this disorder.

Description: Viewgraphs from a presentation on multiple robot systems in space are included. Topics covered include categories of robots in space; scenarios of robot applications in space; some characteristics of robots in space; and some interesting problems and issues.

Description: The state of the art in the modeling of the dynamics of coordinated multiple robot manipulators is summarized and various problems related to this subject are discussed. It is recognized that dynamics modeling is a component used in the design of controllers for multiple cooperating robots. As such, the discussion addresses some problems related to the control of multiple robots. The techniques used to date in the modeling of closed kinematic chains are summarized. Various efforts made to date for the control of coordinated multiple manipulators is summarized.

Description: One of the most critical areas for inspection in the Space Shuttle Solid Rocket Motors is the bond between the steel case and rubber insulation in the region of the field joints. The tang-and-clevis geometry of the field joints is sufficiently complex to prohibit the use of resonance-based techniques. One approach we are investigating is to interrogate the steel-insulation bondline in the tang and clevis regions using surface-travelling waves. A low-frequency contact surface wave transmitting array transducer is under development at our laboratory for this purpose. The array is placed in acoustic contact with the steel and surface waves are launched on the inside surface or the clevis leg which propagate along the steel-insulation interface. As these surface waves propagate along the bonded surface, the magnitude of the ultrasonic energy leaking into the steel is monitored on the outer surface of the case. Our working hypothesis is that the magnitude of energy received at the outer surface of the case is dependent upon the integrity of the case-insulation bond, with less attenuation for propagation along a disbond due to imperfect acoustic coupling between the steel and rubber. Measurements on test specimens indicate a linear relationship between received signal amplitude and the length of good bend between the transmitter and receiver, suggesting the validity of this working hypothesis.

Description: The preparation of a variety of lanthanide-containing polyimide films is described, and results of their characterization are presented. The properties investigated include the glass transition temperature, thermooxidative stability, magnetic susceptibility, and electrical conductivity of the polymer. Films containing lanthanide chlorides, fluorides, and sulfides are flexible, but those containing lanthanide nitrates are extremely brittle. The addition of lanthanide acetates and acetylacetonates caused immediate gelation of two of the synthesis-mixture ingredients. It was found that, in general, the addition of lanthanide to the polyimide increases the density and glass transition temperature of the polymer but slightly decreases the thermooxidative stability.

Description: Present understanding of planetary atmospheres is surveyed. The formation of the planets and their atmospheres is briefly reviewed, and attention is given to the compositions of the atmospheres of earth, Venus, and Mars, the outer planets, and Titan. Lists of the individual atmospheric gases and their concentrations are included.

Description: No abstract available

Description: We studied adaptation to spectral light distribution in undisturbed benthic communities of cyanobacterial mats growing in hypersaline ponds at Guerrero Negro, Baja California, Mexico. Microscale measurements of oxygen photosynthesis and action spectra were performed with microelectrodes; spectral radiance was measured with fiber-optic microprobes. The spatial resolution of all measurements was 0.1 mm, and the spectral resolution was 10 to 15 nm. Light attenuation spectra showed absorption predominantly by chlorophyll a (Chl a) (430 and 670 nm), phycocyanin (620 nm), and carotenoids (440 to 500 nm). Blue light (450 nm) was attenuated 10-fold more strongly than red light (600 nm). The action spectra of the surface film of diatoms accordingly showed activity over the whole spectrum, with maxima for Chl a and carotenoids. The underlying dense Microcoleus population showed almost exclusively activity dependent upon light harvesting by phycobilins at 550 to 660 nm. Maximum activity was at 580 and 650 nm, indicating absorption by phycoerythrin and phycocyanin as well as by allophycocyanin. Very little Chl a-dependent activity could be detected in the cyanobacterial action spectrum, even with additional 600-nm light to excite photosystem II. The depth distribution of photosynthesis showed detectable activity down to a depth of 0.8 to 2.5 mm, where the downwelling radiant flux at 600 nm was reduced to 0.2 to 0.6% of the surface flux.

Description: Radiation from high-pressure sodium (HPS) lamps provided more than a 50% increased yield (fresh and dry weight of tops) of loose-leaf lettuce cultivars Grand Rapids Forcing and RubyConn, compared to that obtained by radiation from cool-white fluorescent (CWF) lamps at equal photosynthetic photon flux; yet, input wattage was approximately 36% less. It was postulated that the considerable output of 700 to 850 nm radiation from the HPS lamp was a significant factor of the increased yield. Under HPS lamps, the leaves of both cultivars were slightly less green with very little red pigmentation ('RubyConn') and slightly elongated, compared to CWF, but plant productivity per unit electrical energy input was vastly superior with HPS.

Description: A system was developed for subjecting plants to elevated air ion levels. This system consisted of a rectangular Plexiglas chamber lined with a Faraday cage. Air ions were generated by corona discharge from frayed stainless steel fibers placed at one end of the chamber. This source was capable of producing varying levels of either positive or negative air ions. During plant exposures, environmental conditions were controlled by operating the unit in a growth chamber.

Description: This paper describes a closed-loop control system for controlling the irradiance and spectral quality generated by fluorescent lamps in a controlled environment chamber. The 400 to 800 nm irradiance and the ratio of the red waveband (600 to 700 nm) to the far-red waveband (700 to 800 nm) were independently controlled and varied as functions of time. A suggested application is to investigate the possibility of synergistic effects of changing irradiance levels and changing spectral distributions on photoperiodism and photomorphogenesis.

Description: Treatment of greenhouse-grown eggplant (Solanum melongena L. var. esculentum Nees. 'Burpee's Black Beauty') seedlings with supplemental photosynthetically active radiation from cool-white fluorescent lamps increased growth of plants subsequently transferred outdoors relative to growth of plants that received no supplemental radiation or were shaded to 45% of solar irradiation in the greenhouse before transfer outdoors. Eggplant seedlings transferred outdoors were placed under plastic tarps either to provide relative protection from solar ultraviolet-B (UV-B) radiation (280-315 nm) using Mylar film or to allow exposure to UV-B using cellulose acetate. Protection of seedlings from UV-B radiation resulted in greater leaf expansion than for UV-B-exposed seedlings, but no change in leaf or shoot dry weight occurred after 9 days of treatment. Specific leaf weight increased in response to UV-B exposure outdoors. Exposure of eggplant to UV-B radiation from fluorescent sunlamps in the greenhouse also decreased leaf expansion and leaf and shoot dry weight gain after 5 days of treatment. However, there were no differences in leaf or shoot dry weight relative to control plants after 12 days of UV-B treatment, indicating that UV-B treated plants had acclimated to the treatment and actually had caught up with non-UV-B-irradiated plants in terms of growth.

Description: The patterns and rates of organelle redistribution in columella (i.e., putative statocyte) cells of agravitropic agt mutants of Zea mays are not significantly different from those of columella cells in graviresponsive roots. Graviresponsive roots of Z. mays are characterized by a strongly polar movement of 45Ca2+ across the root tip from the upper to the lower side. Horizontally-oriented roots of agt mutants exhibit only a minimal polar transport of 45Ca2+. Exogenously-induced asymmetries of Ca result in curvature of agt roots toward the Ca source. A similar curvature can be induced by a Ca asymmetry in normally nongraviresponsive (i.e., lateral) roots of Phaseolus vulgaris. Similarly, root curvature can be induced by placing the roots perpendicular to an electric field. This electrotropism increased with 1) currents between 8-35 mA, and 2) time between 1-9 hr when the current is constant. Electrotropism is reduced significantly by treating roots with triiodobenzoic acid (TIBA), an inhibitor of auxin transport. These results suggest that 1) if graviperception occurs via the sedimentation of amyloplasts in columella cells, then nongraviresponsive roots apparently sense gravity as do graviresponsive roots, 2) exogenously-induced asymmetries of a gravitropic effector (i.e., Ca) can induce curvature of normally nongraviresponsive roots, 3) the gravity-induced downward movement of exogenously-applied 45Ca2+ across tips of graviresponsive roots does not occur in nongraviresponsive roots, 4) placing roots in an electrical field (i.e., one favoring the movement of ions such as Ca2+) induces root curvature, and 5) electrically-induced curvature is apparently dependent on auxin transport. These results are discussed relative to a model to account for the lack of graviresponsiveness by these roots.

Description: The microgravity environment of spaceflight produces rapid cardiovascular changes which are adaptive and appropriate in that setting, but are associated with significant deconditioning and orthostatic hypotension on return to Earth's gravity. The rapidity with which these space flight induced changes appear and disappear provides an ideal model for studying the underlying pathophysiological mechanisms of deconditioning and orthostatic hypotension, regardless of etiology. Since significant deconditioning is seen after flights of very short duration, muscle atrophy due to inactivity plays, at most, a small role. These changes in circulatory control associated with cephalad fluid shifts, rather than inactivity per se, are probably more important factors. In order to test this hypothesis in a systematic way, a multidisciplinary approach which defines and integrates inputs and responses from a wide variety of circulatory sub-systems is required. The cardiovascular experiments selected for Spacelab Life Sciences flights 1 and 2 provide such an approach. Both human and animal models will be utilized. Pre- and post-flight characterization of the payload crew includes determination of maximal exercise capacity (bicycle ergometry), orthostatic tolerance (lower body negative pressure), alpha and beta adrenergic sensitivity (isoproterenol and phenylephrine infusions), baroreflex sensitivity (ECG-gated, stepwise changes in carotid artery transmural pressure with a pneumatic neck collar), and responses to a 24 h period of 5 deg head-down tilt. Measurements of cardiac output (CO2 and C2H2 rebreathing), cardiac chamber dimensions (phased-array 2-dimensional echocardiography), direct central venous pressure, leg volume (Thornton sock), limb blood flow and venous compliance (occlusion plethysmography), blood and plasma volumes, renal plasma flow and glomerular filtration rates, and various hormonal levels including catecholamines and atrial natriuretic factor will also be obtained. The central venous catheter will be inserted immediately pre-launch and monitored with heart rate and blood pressure in-flight until cardiac output, respiratory gas exchange and quantitative 2D echocardiography measurements can be performed. In-flight hemodynamic measurements will be repeated at rest and during submaximal exercise daily and also during maximal exercise midway through the flight to document the timecourse and extent of cardiovascular changes in the payload crew. Parallel studies are planned for the animals. In addition to measurements of right atrial and aortic pressures and cardiac output, a dorsal micro-circulatory chamber will allow determinations of changes in capillary and venular architecture and function in six of the rats. The techniques and findings from many of the SLS-1 and 2 supporting studies have already yielded significant information about circulatory regulation in patients with both hypo- and hypertension. The flight experiments themselves will provide new data to test the validity of both animal and human models currently used for simulating the fluid shifts of a micro-gravity environment. The development of effective countermeasures, not only for short and long duration space travellers, but also for Earth-bound medical patients can then be physiologically based on experimental data rather than anecdote.

Description: Oxidative processes are probable determinants of longevity of seeds in storage. Measurements of actual oxygen uptake rates were made for soybean and pea seeds as a comparison of short and long lived seeds when light, temperature, and moisture contents were varied. In both peas and soybeans, the oxygen uptake was depressed at low temperatures (〈16 degrees C) and low water contents (〈 0.25 gram H2O per gram dry weight). Apparent activation energies under these conditions are very high, while apparent activation energies of seeds at higher water contents and at temperatures greater than 22 degrees C are much less. Light enhances the level of oxygen uptake in pea, but reduces the level of oxygen uptake in soybean. The complexities of the interactions of oxygen uptake with environmental conditions in soybean compared to pea suggest that oxidative processes occur in soybean at low water contents, but are essentially absent in pea. It is suggested that the additional oxidative processes in soybean with moisture contents between 0.10 and 0.24 gram per gram may contribute to the poorer longevity of soybean seed compared to pea seed.

Description: The physical status of water in seeds has a pivotal role in determining the physiological reactions that can take place in the dry state. Using water sorption isotherms from cotyledon and axis tissue of five leguminous seeds, the strength of water binding and the numbers of binding sites have been estimated using van't Hoff analyses and the D'Arcy/Watt equation. These parameters of water sorption are calculated for each of the three regions of water binding and for a range of temperatures. Water sorption characteristics are reflective of the chemical composition of the biological materials as well as the temperature at which hydration takes place. Changes in the sorption characteristics with temperature and hydration level may suggest hydration-induced structural changes in cellular components.

Description: Circumnutations of hypocotyls of sunflower (Helianthus annuus L. cv. Californicus) were studied under 1 g and 3 g conditions. Root mean square values of the hypocotyl deviation from the plumbline and period of the movements were determined from calculations of the autocorrelation functions of the movements. The amplitude and the period of the circumnutations increased under 3 g as compared to 1 g. A transition from 3 to 1 g or vice versa also caused changes in period and amplitude of the movements. The results are interpreted as a support for the idea that gravity influences the circumnutation parameters in this sunflower variety. A comparison is made with published results on the dwarf sunflower cv. Teddy Bear where the force influence is very small or negligible. Simulations of a model for circumnutations show movements which are in qualitative agreement with the experimental results, provided adaptation to g-levels is included in the model. Finally, the results are discussed with the recent Spacelab-experiment (SL1) as a background.

Description: From elements formed in interstellar furnaces to humans peering back at the stars, the evolution of life has been a long, intricate and perhaps inevitable process. Life as we know it requires a planet orbiting a star at just the right distance so that water can exist in liquid form. It needs a rich supply of chemicals and energy sources. On Earth, the combination of chemistry and energy generated molecules that evolved ways of replicating themselves and of passing information from one generation to the next. Thus, the thread of life began. This chart traces the thread, maintained by DNA molecules for much of its history, as it weaves its way through the primitive oceans, gaining strength and diversity along the way. Organisms eventually moved onto the land, where advanced forms, including humans, ultimately arose. Finally, assisted by a technology of its own making, life has reached back out into space to understand its own origins, to expand into new realms, and to seek other living threads in the cosmos.

Description: This semester, efforts were concentrated on the design of the Lunox transfer line from the storage area to the launch site. Emphasis was placed on flow and heat transfer problems and their remedies by reducing the effect of radiation by selecting materials for storage tanks, transfer lines and insulation. The design for the storage tank was based on a medium sized Lunox production facility of 6,000 metric tons per year and the frequency of transportation of Lunox from lunar launch site to lower lunar orbit of four launches per month. The design included the selection of materials for cryogenic storage, insulation and radiation shielding. Lunox was pumped to the storage area near the launch site through a piping network designed for maximum mass flow rate with a minimum boil off. The entire network incorporated specially designed radiation shields made of material which was lightweight and low in secondary radiation.

Description: The topics addressed are: (1) phobos power plant; (2) fusion power/propulsion system; (3) surface power from an orbiting spacecraft; (4) RTG replacement; (5) MHD-thermoelectric burst reactor; (6) TAU Voyage power/propulsion device; (7) ESCAPE to ODYSSEY.

Description: A pair of compatible transfer stations or Space Ports and associated transfer vehicles was designed in order to support permanent manned lunar facilities. One of the Space Ports was placed in earth orbit (not necessarily Low Earth Orbit - LEO), and the other in lunar orbit. The primary purposes of the Space Ports was to support the lunar surface facility, the return of lunar manufactured items to the earth, and the transfer of lunar manufactured items to space vehicles and earth orbital space stations. The design was constrained by the following: (1) The orbital altitudes and inclinations of the Earth Port and Moon Port were chosen to minimize the overall cost of transporting materials to and from the moon. The ETO (Earth-to-Orbit) costs were considered separately to allow consideration of initiating planetary missions, etc., from the Earth Port. (2) A new earth launch point was chosen to facilitate the support of the lunar facility. This launch point was chosen to minimize overall costs, maximize overall safety, and to avoid political problems. To this end, it was mandatory the launch site be owned by the United States or one of its close allies. In addition, the launch would take place over water and expendable stages would drop into the ocean. Space shuttle type vehicles could be used if appropriate provisions were made for aborts, SRB and ET impact, etc. The ground track and impact point studies included space shuttle type vehicles, current ELV's (expendable launch vehicles, and HLLV's (heavy lift launch vehicles). (3) The Earth Port and Moon Port orbits were selected so that transfer trajectories between the two facilities could be initiated often without major plane change penalties. The amount of these penalties was calculated. Families of Earth Port to Moon Port and Moon Port to Earth Port trajectories were calculated to document the energy requirements and penalties. (4) Space Port module designs included module systems definitions, module masses, system masses, module and system volumes, module and system power requirements, etc. (5) The Space Port designs included specifications and justification for: Permanent crew size; Warehousing capacity; Assembly, assembly support, and repair; Unsupported operational capability; Nominal resupply intervals; Contingency resupply options; Transient personnel support capability; Costing, based on the Space Station Cost Model.

Description: The objective of the 1986-87 space system design project was to design and procure the hardware necessary to demonstrate continuous production of oxygen from simulated Mars atmosphere. The work was an extension of a design project that was started during the previous academic year. A yttria stabilized, zirconium oxide electrochemical cell was operated in a controlled temperature environment to separate oxygen, which has been dissociated thermally from the primary constituent of the Martian atmosphere-carbon dioxide. This system was perhaps the most primitive chemical processor that could be developed as part of an extraterrestrial chemicals production demonstration project. The course began in January, 1987. Speakers were brought in to discuss the Martian environment, concepts for resource extraction and system requirements for an autonomous chemical processor. The class simultaneously refined its work plans, which were developed as part of the fall semester senior seminar course. Hardware was purchased using funds provided by the Planetary Society. However, the key hardware element was the zirconia cell. Development of that type of cell is beyond the capabilities of undergraduate engineering students. Consequently, the cell was borrowed. The design elements emphasized in this project were as follows: (1) System reliability analysis; (2) Autonomous operation and control; (3) High temperature seal design; (4) Design for minimum thermal stress; (5) Passive shut down environmental control; (6) Integrated instrumentation concepts; (7) Identification of extraterrestrial resources; (8) Evaluation of chemical processor concepts; (9) Integrated hardware design; and (10) Finite element analysis.

Description: Eight fourth-year engineering design students formed two teams to study methods of varying the perceived gravity level in a variable gravity research facility. A tether system and an arm system were the chosen topics. Both teams have produced and built scale models of their design. In addition, a three-credit Special Topics Course (Aviation 370) was formed, as the project offers an excellent opportunity to build a multi-disciplinary program around the initial conceptualization process. Fifty students were registered in the Special Topics course. Each week during a three hour class, a guest lecturer covered one or more of the many areas associated with the concept of a variable-gravity facility. The students formed small groups organized on a multi-disciplinary basis (there were twelve separate disciplines represented by one or more students) where they discussed among themselves the various issues involved. These groups also met outside class for three or more hours each week. During class each group presented oral reports on their findings during a one-hour general question and answer period.

Description: Based on previous design studies the 1986-87 design team developed a personnel transportation system between Earth and Mars in support of an established manned Mars base. The vehicle designed, an interplanetary space station, will make use of specialized trajectories known as 'circulating orbits'. These trajectories have the property of periodically repeating encounters with Earth and Mars. They have been studied in the past, but have attracted renewed interest since the National Commission on Space has proposed the idea of placing large interplanetary space stations in such orbits. During planetary flybys, small, austere, taxi vehicles from the planet surface will rendezvous with the station and transfer the personnel to it. Here the space travelers will have roomier, more elaborate living quarters for the long journey. This method of manned travel is visualized to be more economical for supporting a manned Mars surface operation than others thus far conceived. The Aerospace System Design class produced a conceptual design of a circulating orbit transportation system. The design included the station configuration, other usual subsystems treated to the necessary degree e.g., propulsion, power, attitude and thermal control, and communications. Special attention was given the gravity environment and the human needs for the long trip. An operational scenario was developed which included the initial construction and establishment in orbit as well as provisions for maintenance of replenishment of consumables.

Description: A group of fifteen students in the Electrical Engineering Department at the University of Maryland, College Park, has been involved in a design project under the sponsorship of NASA Headquarters, NASA Goddard Space Flight Center and the Systems Research Center (SRC) at UMCP. The goal of the NASA/USRA project was to first obtain a refinement of the design work done in Spring 1986 on the proposed Mobile Remote Manipulator System (MRMS) for the Space Station. This was followed by design exercises involving the OMV and two armed service vehicle. Three students worked on projects suggested by NASA Goddard scientists for ten weeks this past summer. The knowledge gained from the summer design exercise has been used to improve our current design of the MRMS. To this end, the following program was undertaken for the Fall semester 1986: (1) refinement of the MRMS design; and (2) addition of vision capability to our design.

Description: The University of Kansas NASA/USRA Design Team worked on the design/evaluation of using 'family' concept in the case of a series of regional transport airplanes. Mission specifications for the four designs in the series are shown. Further design characteristics were specified as follows: (1) common cockpit instrumentation; (2) common structural and systems design (to as high a degree as possible); (3) jet-like ride quality and cabin environment; (4) identical handling qualities to allow for cross rating of pilots; and (5) low acquisition cost and low life-cycle costs

Description: The presence of a manned space colony on Mars may be expected to involve three phases in the utilization of planetary resources: (1) survival phase in which air, water, and food are produced, (2) self sufficiency phase in which chemicals, fuels, pharmaceuticals, polymers, and metals are produced, and (3) export to earth of materials and technology 1 phase in which the unique advantage of the extraterrestrial environment is fully exploited. The Advanced Design Project is administered as an interdisciplinary effort involving students and faculty throughout the College of Engineering. Senior students from Chemical, Civil, Electrical, and Mechanical Engineering are participating as a team. Multi discipline interfacing and coordination are stressed throughout the project. An interdisciplinary senior design course was developed and offered in the Spring of 1987. The first task of the survival phase is that of providing a supply of water and air adequate to support a ten person colony. The project has been divided into three subgroups: (1) design of a manufacturing and storage facility for air, (2) search and drill for water or water-bearing materials, and (3) retrieve, purify, and store potable water. The conceptual design phase has been completed and the project is being documented. The second task of the survival phase is that of providing a replenish able food supply. This task has two requirements: producing a supply of protein and providing an environment for growing plants for food. For the first requirement, we considered the design of a bioreactor system capable of growing beef cells for protein production. For the second, a design must be developed for a manufacturing system to produce materials needed to build a greenhouse farm.

Description: Approximately one-half of the 73 students in the design course elected to relate to the NASA/USRA Advanced Aeronautics Design Program. Five teams of 5-6 students each worked on the following projects: (1) 200 passenger, 3000 mile range prop fan transport; (2) 115/120 passenger, 1800 mile range prop fan transport; (3) flying wing military transport; and (4) assault transports (A & B). Within the teams, individuals were assigned responsibility for major portions of the design; e.g., structures, aerodynamics, and propulsion. The early part of the term was devoted to the study of factors such as market analysis/mission definitions, trade off studies of materials/structural configuration, and consideration of various alternative designs. The most promising design candidates were then the subject of more detailed studies later in the term. The final detailed designs were documented in a report at the end of the study. As a part of the study, recommendations were made for areas of future investigation.

Description: The Advanced Aeronautics Design Program at The Ohio State University was to design a vehicle for hypersonic passenger flight across the Pacific Ocean. The specifications were as follows: (1) hypersonic flight; (2) range of 8000 nm; (3) passenger seating greater than 250; (4) operation from 15000 ft runways Mach number and altitude of operation were at the discretion of the design teams as were the propulsion system and type of fuel. The advanced aeronautics design sequence established specifically for this program consisted of a three quarter sequence as follows: Fall: ME 694 Senior Design Seminar - one quarter hour. Designers and specialists met one hour each week for ten weeks on relevant flight vehicle design topics. Winter: ME 515H Flight Vehicle Design - four quarter hours. Three design teams of six students each performed preliminary design studies of hypersonic configurations and potential propulsion systems. Each team's results were summarized in a final presentation to NASA Lewis Research Center personnel. The presentations resulted in the selection of the most promising design for additional development. Spring: AAE 516H Advanced Flight Vehicle Design - four quarter hrs. The class was reorganized to focus upon the specific design selected from the Winter configuration studies. Detailed analyses of thermal protection systems, costs, mission refinements, etc., completed the design task and final presentations were made to NASA Lewis Research Center staff.

Description: Based on a provided mission model, this project considered three different classes of launch vehicles for possible use: (1) modifications to the current Space Transportation System, or replacement by a second-generation vehicle using current technology; (2) a heavy-lift cargo vehicle, designed to minimize the cost of bulk cargo to low earth orbit; and (3) an advanced man-rated system incorporating technology anticipated for the year 1995. The mission model provided included commercial, scientific, and military payloads for the years 1990 through 2010. Use of the current Space Transportation System was also permitted in the final fleet sizing analysis. The near-term shuttle group performed trade studies on a number of modifications and variations before selecting a new vehicle design, incorporating a fly-back reusable first stage and reduced-size orbiter. Orbiter payload was limited to 5000 kg (priority items), with up to 25,000 kg of payload carried in a forward payload bay within the nose shroud of the orbiter external tank. This allowed reduction of orbiter size, without significant loss of reusability.

Description: The design topic selected was an outgrowth of the experimental design work done in the Fluid Behavior in Space experiment, which relies on the measurement of minute changes of the pressure and temperature to obtain reasonably accurate volume determinations. An alternative method of volume determination is the use of ultrasonic imaging. An ultrasonic wave system is generated by wall mounted transducer arrays. The interior liquid configuration causes reflection and refraction of the pattern so that analysis of the received wave system provides a description of the configuration and hence volume. Both continuous and chirp probe beams were used in a laboratory experiment simulating a surface wetting propellant. The hardware included a simulated tank with gaseous voids, transmitting and receiving transducers, transmitters, receivers, computer interface, and computer. Analysis software was developed for image generation and interpretation of results. Space instrumentation was pursued in support of a number of experiments under development for GAS flights. The program included thirty undergraduate students pursuing major qualifying project work under the guidance of eight faculty supported by a teaching assistant. Both mechanical and electrical engineering students designed and built several microprocessor systems to measure parameters such as temperature, acceleration, pressure, velocity, and circulation in order to determine combustion products, vortex formation, gas entrainment, EMR emissions from thunderstorms, and milli-g-accelerations due to crew motions.

Description: The design group focused on three topics: (1) Extravehicular Activities, (2) Sample Return Missions, and (3) Structural and Construction Considerations of a Manned Mars Habitat. Extravehicular Activities permit a Mars based astronaut to exit the habitat and perform mission activities in the harsh Mars environment. Today's spacesuit gloves are bulky, hard to manipulate and fatiguing. A mechanical assistance mechanism has been developed for the glove that will reduce user fatigue and increase the duration of EVA's. Oxygen supply systems are also being developed for the EVA astronaut. A scuba type system of tanked breathing air proves to be the most efficient system for short duration EVA's. A system that extracts the oxygen from atmospheric carbon dioxide can provide oxygen for long duration FVA's. Sample Return Missions require that samples be taken from several sites. Transportation considerations are addressed and two transportation schemes are proposed. The first scheme involves a lighter than air balloon. This system provides excellent range. The second design is a rover that uses tracks rather than wheels. Track rovers perform well in soft, sandy conditions. Engineering aspects of a habitat and domed greenhouse were investigated and plans for the habitat have been made. A configuration has been established and construction details have been made.

Description: This report shall cover all major aspects of the design of an Aeroassisted Manned Transfer Vehicle (or TAXI) for use as part of advanced manned Mars missions based on a cycling ship concept. Along with the heliocentric orbiting Cycling Spacecraft, such a TAXI would be a primary component of a long-term transportation system for Mars exploration. The Aeroassisted Manned Transfer Vehicle (AMTV) design developed shall operate along transfer trajectories between Earth and a Cycling Spacecraft (designed by the University of Michigan) and Mars. All operations of the AMTV shall be done primarily within the sphere of influence of the two planets. Maximum delta-V's for the vehicle have been established near 9 km/sec, with transfer durations of about 3 days. Acceleration deltaV's will be accomplished using 3 SSME-based hydrogen-oxygen chemical rockets (l(sub sp) = 485 sec & Thrust greater than = 300,00 Ib(sub f)/engine) with a thrust vector directly opposite the aerobraking deceleration vector. The aerobraking deceleration portion of an AMTV mission would be accomplished in this design by a moderate L/D aeroshield of an ellipsoidally-blunt, raked-off, elliptic cone (EBROEC) shape. The reusable thermal protection material comprising the shield will consist of a flexible, multi-layer, ceramic fabric stretched over a lightweight, rigid, shape - defining truss structure. Behind this truss, other components, including the engine supports, would be attached and protected from heating during aerobraking passes. Among these other components would be 2 LOX tanks and 4 LH2 tanks (and their support frames) holding over 670,000 lbm of propellant necessary to impart the required delta-V to the 98,000 lbm burnout mass vehicle. A 20,000 lbm crew module with docking port (oriented parallel to the accel./decel. axis) will provide accommodations for 9 crew members (11 under extreme conditions) for durations up to seven days, thus allowing extra time for emergency situations. This AMTV will be equipped with complete guidance, navigation, control and communications systems modules attached near the crew module. Control of vehicle attitude will be provided by a set of small reaction control thrusters quite similar to those on the current Space Shuttle. All crew module and vehicle electrical functions will be powered via a set of H2/O2 fuel cells with radio-isotopic generators as backup supplies. Also included in the burnout mass of 98,000 lb is allowance for 10,000 lbm of miscellaneous payload (scientific equipment or other supplies).

Description: The project selected by the U.S. Naval Academy and NASA Goddard Space Flight Center for the 1986-87 NASA/USRA University Advanced Design Program was a variable artificial gravity facility, an adjunct to the Space Station. Recently, Goddard Space Flight Center had proposed that a formal study be conducted by NASA to investigate the question of whether an artificial gravity capability should be added to the Space Station. Therefore, not only does this project fit the goals of the Design Program, but it was a timely and interesting project. The variable artificial gravity was generated by a spinning module, and became an adjunct to the Space Station. It was planned that as much of the Space Station technology as possible be incorporated into the design. The components of the system were inserted into orbit. The specific design parameters were essentially open. The primary design objectives were: (1) The highest gravity level sufficient to prevent bone calcium loss in astronauts. (2) The cost of the Space Station should not be increased by more than 20 percent. (3) The number of launches to orbit the Space Station should not be increased by more than 30 percent. A secondary design objective was to investigate whether this design was suitable for a long duration space flight, such as a mission to Mars, or if the design is easily and inexpensively modified for such a mission.

Description: University of Houston's The Sasakawa International Center for Space Architecture is pursuing research and design studies for permanent lunar settlements. One such study, Project LEAP, has produced staged growth concepts for a habitat to support lunar mining operations. The principal purpose assumed for the development is to produce liquid oxygen and hydrogen propellant for Advanced Space Transportation System and future orbital infrastructure consumption use. The base has been designed to grow over a ten year period from an initial six-person crew occupancy to an advanced facility capable of accommodating as many as one hundred and fifty people. Evolutionary growth stages would rely increasingly upon acquisition, processing and utilization of lunar materials to optimize self-sufficiency. Project LEAP's study objectives have sought to identify incremental site development and facility requirements; to identify candidate site development and construction options; to propose site layout and habitat design/growth concepts; and to survey requirements to achieve a high level of self-sufficiency. As an ongoing research and development program, the project has evolved from research and data collection for concept and design through three dimensional solids computer modeling. The University of Houston project is funded through the advanced Missions Office of the Johnson Space Center. Project representatives are guests of the Johnson Space Center at this conference.

Description: The small, chemically primitive objects of the solar system, comets and asteroids, are one of the most important frontiers remaining for future planetary exploration. So stated the Solar System Exploration Committee of the NASA Advisory Council in its 1986 report 'Planetary Exploration Through the Year 2000.' The Halley's comet flyby missions completed last spring raised more questions than were answered about the nature of comets. The next mission to a comet must be able to explore some of these questions. In the late 1990's, a spacecraft might be built to explore the hazardous area surrounding a comet nucleus. Rigorous pointing requirements for remote sensing instruments will place a considerable burden on their attendant control systems. To meet these requirements we have pursued the initial design and analysis of a multi-bodied comet explorer spacecraft. Sized so as to be built on-orbit after the space station is operational, the spacecraft is comprised of Orbit Replaceable Unit (ORU) subsystems, packaged into two major components: a three-axis controlled instrument platform and a spinning, detached comet dust shield. Such a configuration decouples the dynamics of dust impaction from the stringent pointing out requirements of the imaging experiments. At the same time, it offers an abundance of simple analysis problems that may be carried out by undergraduates. These problems include the following: Selection of subsystem components, sizing trade studies, investigation of three-axis and simple spin dynamics, design of simple control systems, orbit determination, and intercept trajectory generation. Additionally, such topics as proposal writing project management, human interfacing, and costing have been covered. A new approach to design teaching has been taken, whereby students will 'learn by teaching.' They are asked to decompose trade options into a set of 'if-then' rules, which then 'instruct' the Mechanically Intelligent Designer (MIND) expert design system in how to carry out a design.

Description: Georgia Tech's student design projects for the 1986-1989 academic years relate to the proximate era of lunar exploration and habitation. This era might be described as beginning with robotic prospecting for hydrogen at the lunar poles and ending when a continuously inhabited lunar base is established. The focus was on the design of equipment and systems needed to support the activities contemplated for this portion of the space program. Some specific interests which were identified are listed: Geological exploration; Soils testing; Site preparation; Landing and launch operations; Cargo handling; Base construction; Terrain reconfiguration; Mining, beneficiation and haulage; Pilot - plant manufacturing processes. These design efforts were closely coordinated with those by others as they developed habitat modules, flight vehicles, etc. An example is the development of a standardized inter modal cargo interface. Projects for fall quarter 1986 were: A three-legged walker which serves as a chassis for various interchangeable implements; A digging implement for the walker; A lifting implement for the walker; A cargo interface standard. Some projects were limited to one academic quarter, but most have been pursued for several quarters. A few are expected to evolve over the three-year period.

Description: The design course is an eight semester credit multi-disciplinary engineering design course taught primarily to Engineering Science, Aerospace, Electrical and Mechanical Engineering seniors. This year the course project involved the design of the three interrelated loops: atmospheric, liquid nutrient and solid waste management, associated with growing higher plants to support man during long-term space missions. The project is complementary to the NASA Kennedy Space Center Controlled Environmental Life Support System (CELSS) project. The first semester the class worked on a preliminary design for a complete system. This effort included means for monitoring and control of composition, temperature, flow rate, etc., for the atmosphere and liquid nutrient solution; disease and contaminant monitoring and control; plant mechanical support, propagation and harvesting; solid and liquid waste recycling; and system maintenance and refurbishing. The project has significant biological, mechanical, electrical and Al/Robotics aspects. The second semester a small number of subsystems or components, identified as important and interesting during the first semester, were selected for detail design, fabrication, and testing. The class was supported by close cooperation with The Kennedy Space Center and by two teaching assistants. The availability of a dedicated, well equipped project room greatly enhanced the communication and team spirit of the class.

Description: The Florida Institute of Technology established an Interdisciplinary Design Team to design a lunar based facility whose primary function involves launch and landing operations for future moon missions. Both manned and unmanned flight operations were considered in the study with particular design emphasis on the utilization (or reutilization) of all materials available on the moon. This resource availability includes man-made materials which might arrive in the form of expendable landing vehicles as well as in situ lunar minerals. From an engineering standpoint, all such materials are considered as to their suitability for constructing new lunar facilities and/or repairing or expanding existing structures. Also considered in this design study was a determination of the feasibility of using naturally occurring lunar materials to provide fuel components to support lunar launch operations. Conventional launch and landing operations similar to those used during the Apollo Program were investigated as well as less conventional techniques such as rail guns and electromagnetic mass drivers. The Advanced Space Design team consisted of students majoring in Physics and Space Science as well as Electrical, Mechanical, Chemical and Ocean Engineering.

Description: Redundant search often makes Prolog programs inefficient. Prolog execution corresponds to a depth-first traversal of an AND/OR graph; often a large subgraph will be searched successfully, with failure resulting from a subsequent small one. It is shown how reordering of Prolog clauses and especially goals can prevent unnecessary search. The restrictions on reordering are characterized and how they may be detected is shown. A new system of calling modes for Prolog, geared to reordering, and a system for inferring them automatically are designed. An improved method for determining a good goal order for Prolog clauses is presented, and it is used as the basis for a reordering system, showing how it can be guided by information about modes and restrictions to generate reordered Prolog that behaves correctly.

Description: An overview of Illinois Computer Laboratory for Aerospace Systems and Software (ICLASS) Research: Reliable and Parallel Computing is presented. Topics covered include: reliable and fault tolerant computing; fault tolerant multiprocessor architectures; fault tolerant matrix computation; and parallel processing.

Description: A parallel simulated annealing algorithm for standard cell placement that is targeted to run on the Intel Hypercube is presented. A tree broadcasting strategy that is used extensively in our algorithm for updating cell locations in the parallel environment is presented. Studies on the performance of our algorithm on example industrial circuits show that it is faster and gives better final placement results than the uniprocessor simulated annealing algorithms.

Description: A new method of efficiently accelerating relatively large masses (up to several metric tons) to velocities of 0.6 km/sec up to 12 km/sec using chemical energy has been developed. The vehicle travels through a tube filled with a premixed gaseous fuel and oxidizer mixture. There is no propellant on-board the vehicle. The tube acts as the outer cowling of a ram jet and the energy release process travels with the vehicle. The ballistic efficiency remains high up to extremely high velocities and the acceleration can be maintained at a nearly constant level. Five modes of ram accelerator operation have been investigated; these modes differ primarily in the method of chemical heat release and the operational velocity range, and include two subsonic combustion modes (one of which involves thermally choke a combustion behind the vehicle) and three detonation drive modes. These modes of propulsion are capable of efficient acceleration in the range of 0.6-12 km/sec, although aerodynamic heating becomes severe above about 8 km/sec. Experiments carried out to date at the University of Washington up to 2 km/sec have established proof of principle of the ram accelerator concept and have shown close agreement between predicted and measured performance. A launch system capable of delivering two metric tons into low earth orbit was selected for the purposes of the present study. The preliminary analysis indicates that the overall dimensions of a restricted acceleration (less than approx. 1000 g) launch facility would require a tube 1 m in diameter, with an overall length of approximately 4 km. As in any direct launch scheme, a small on-board rocket is required to circularize the otherwise highly elliptical orbit which intersects the Earth. Various orbital insertion scenarios have been explored for the case of a 9 km/sec ram accelerator launch. These include direct insertion through a single circularization maneuver (i.e., on rocket burn), insertion involving two burns, and a maneuver involving two burns and aerobraking. In each case an initial launch angle of 20-25 deg. appears to minimize the delta V for orbital insertion. The maneuver which includes aerobraking results in the lowest overall delta V requirement. The survivability of such a vehicle through the atmosphere and the attendant loss in kinetic energy has been examined and it appears that despite the very high velocities, it is within the state of the art of modern reentry protection to design a vehicle that can survive a passage into space even from a sea level launch.

Description: Growing interest in a future manned mission to Mars illuminated a critical need for more information on the Martian environment, surface conditions, weather patterns, topography, etc. While the Viking landers provided valuable information of this type, the information came from fixed locations. There is a real need for Viking type of information from a number of locations on the Martian surface in order to adequately survey the planet for future landing and exploration sites. Current site survey mission discussions range from Mars orbiters to sample return missions. The limited data return from the former and the extreme expense of the latter suggest consideration of a 'middle ground' mission which provides needed survey information for an acceptable investment. Utah State University (USU) designed a Mars Lander/Rover (MLR) for use in gathering needed environmental and surface information from Mars. Philosophically, the MLR resembles a mobile Viking; that is, it moves from location to location on the Martian surface, measuring environmental conditions, analyzing soil samples, charting topographical features etc. Measured data is then telemetered to earth for further analysis. Conceptually, it was envisioned that MLR survey locations would be rather widely separated. In that sense the MLR was not a terrestrial vehicle limited to local movement about a fixed location. Rather, it would have the capability for movement over long distances to reach widely separated locations. The design focus, then, was upon a Mars Lander/Rover that leaves an orbit around Mars, reenters and soft lands on the Martian surface and moves sequentially to widely scattered locations to sample, measure, and analyze Martian environmental and surface conditions. Primary goals were payload mass and size definition, characterization of the Martian atmosphere, selection of sampling locations, identification of alternative design concepts, selection of a preferred concept, team organization, and preparation for the detailed design phase.

Description: The detailed design of a small beam-powered trans-atmospheric vehicle, 'The Apollo Lightcraft,' was selected as the project for the design course. The vehicle has a lift-off gross weight of about six (6) metric tons and the capability to transport 500 kg of payload (five people plus spacesuits) to low Earth orbit. Beam power was limited to 10 gigawatts. The principal goal of this project is to reduce the low-Earth-orbit payload delivery cost by at least three orders of magnitude below the space shuttle orbiter--in the post 2020 era. The completely reusable, single-stage-to-orbit, shuttle craft will take off and land vertically, and have a reentry heat shield integrated with its lower surface--much like the Apollo command module. At the appropriate points along the launch trajectory, the combined cycle propulsion system will transition through three or four air breathing modes, and finally a pure rocket mode for orbital insertion. As with any revolutionary flight vehicle, engine development must proceed first. Hence, the objective for the spring semester propulsion course was to design and perform a detailed theoretical analysis on an advanced combined-cycle engine suitable for the Apollo Light craft. The analysis indicated that three air breathing cycles will be adequate for the mission, and that the ram jet cycle is unnecessary.

Description: This Facilities Utilization Program Implementation Handbook (FUPIH) prescribes procedures for the review and the reporting on the utilization of NASA facilities. The Directors of NASA Field Installations should designate an Installation Official responsible for coordinating the assignment of buildings space and implementing the facilities utilization reviews and annual report preparation. The individual designated shall be known as the 'Facilities Utilization Officer (FUO).' Functional responsibilities of the FUO are detailed in NASA Management Instruction (NMI) 7234.1. It is recognized that titles used in the implementation of the Facilities Utilization Program may vary between field installations. The Facilities Utilization Program (FUP) is designed to provide a uniform and orderly process for meeting or addressing the following objectives: the establishment of sound facilities requirements to meet NASA's programmatic and institutional needs; the optimum allocation of available facilities and related resources to meet these requirements; and the early identification and request for required additional facilities resources. The detailed review and reporting system enacted by NMI 7234.1 should encourage more comprehensive utilization planning for all NASA facilities and ensure, to the maximum extent practicable, that all such facilities are put to their highest and best use consistent with NASA programmatic and institutional priorities. A principal purpose of the FUP is the early identification of NASA facilities which may be or may become underutilized or excess to NASA needs and to provide a timely reference point from which corrective actions (i.e., consolidation, elimination of duplication, improved utilization of disposal) may be taken. Because the supply of this handbook is limited, distribution should be controlled at the field installation level.

Description: The Department of Aerospace Engineering Sciences in conjunction with the NASA Ames Research Center has embarked upon an advanced space mission design that involves the provision for a long term space habitat. The program, by intent, is a cumulative effort of successive approximations that builds from one semester to the next. Ideas founded in the initial design exercise are carried through to the present effort. These ideas are constantly questioned and refined. This effort has been scrutinized by active professionals involved in critical design reviews and by each new group of students in the subsequent classes. Each effort consists of a balance between hardware design, concept/mission design and economic/political tradeoffs. The student activities in the course are CAD intensive, communications intensive, and research intensive. Every effort is made to produce numerous design review opportunities for each of the involved students. As part of this year's effort, the students have done a number of follow-on design projects for individuals at NASA-Ames. Finally, the course has been refined to include documentation on the design process itself. At the end of the design effort the University of Colorado should have produced rather complete documentation for a long-term space habitat and should have produced rather effective guidelines for design efforts of this type.

Description: The production of a fiberglass/metal composite material suitable for building habitats and manufacturing facilities was the project for Clemson. The concept and development of the knowledge necessary to produce glass fibers originated in the spring semester. During the summer, while at Johnson Space Center, fiberglass from a rock composition similar to ones found at the Apollo 16 site on the moon was successfully produced. The project this year was a continuation of last year's studies. We addressed the following problems which emerged as the work progressed: (1) Methods for coating the fibers with a metal were explored. We manufactured composites in two stages: Glass fibers without any coating on them; and fibers coated with metals as they were made. This proved to be a difficult process. Future activities include using a chemical vapor deposition process on fibers which have been made. (2) A glass furnace was developed which relies primarily on solar energy for melting the glass. The temperature of the melted glass is maintained by electrical means. The design is for 250 kg of glass per day. An electrical engineering student developed a scheme for controlling the melting and manufacturing process from the earth. This was done to minimize the human risk. Graphite refractories are relied on to contain the melt. (3) The glass composition chosen for the project is a relatively pure anorthite which is available in the highland regions of the lunar surface. A major problems with this material is that it melts at a comparatively high temperature. This problem will be solved by using graphite refractory materials for the furnace. The advantage of this glass composition is that it is very stable and does not tend to crystallize. (4) We have also refined the experimental furnace and fiber making machinery which we will be using at Johnson Space Center this summer. We believe that we will be able to draw and coat glass fibers in a vacuum for use in composites. We intend to make and test the mechanical properties of these composites.

Description: The Potential for V/STOL Aircraft Concepts for Air Transportation in the CALIFORNIA CORRIDOR in the 2010 time period is projected. The project description is to study the potential for V/STOL aircraft concepts in air transportation within the California Corridor, and emphasize V/STOL configurations that are innovative and unconventional in design for use in the 2010 time period. The project is consistent with the mission of the NASA/Ames Research Center and succeeding classes at Cal Poly can iterate and refine for meaningful results for NASA.

Description: A hypersonic transport aircraft design project was selected as a result of interactions with NASA Lewis Research Center personnel and fits the Presidential concept of the Orient Express. The Graduate Teaching Assistant (GTA) and an undergraduate student worked at the NASA Lewis Research Center during the 1986 summer conducting a literature survey, and relevant literature and useful software were collected. The computer software was implemented in the Computer Aided Design Laboratory of the Mechanical and Aerospace Engineering Department. In addition to the lectures by the three instructors, a series of guest lectures was conducted. The first of these lectures 'Anywhere in the World in Two Hours' was delivered by R. Luidens of NASA Lewis Center. In addition, videotaped copies of relevant seminars obtained from NASA Lewis were also featured. The first assignment was to individually research and develop the mission requirements and to discuss the findings with the class. The class in consultation with the instructors then developed a set of unified mission requirements. Then the class was divided into three design groups (1) Aerodynamics Group, (2) Propulsion Group, and (3) Structures and Thermal Analyses Group. The groups worked on their respective design areas and interacted with each other to finally come up with an integrated conceptual design. The three faculty members and the GTA acted as the resource persons for the three groups and aided in the integration of the individual group designs into the final design of a hypersonic aircraft.

Description: The purpose of this University of Central Florida (UCF) student design was to modify the existing Integrated Partial Payload Lifting Assembly (IPPLA) to increase its lifting capacity so it could lift the passenger tunnel. The IPPLA is used in the Orbiter Processing Facility to prepare and load the cargo bay of the Space Shuttle prior to flight. The report evaluated twelve design modifications assigning relative weights to safety, cost, strength, weight, reliability, size, installation and portability. Each potential modification was rated from 1 (poor) to 5 (excellent) in each of the weighted categories and the results were multiplied, summed, and displayed in a solution matrix. As a result of scoring highest in the solution matrix, the two most probable designs were further analyzed and evaluated to determine the recommended solution to the modification of the IPPLA. The modification of the IPPLA was one of six Aerospace and Mechanical Engineering designs in progress in the Engineering Design class at UCF during Fall Semester. The UCF student design team received counsel and guidance from NASA Kennedy Space Center.

Description: This design course is directed to studying problems related to mobile exploration of the surface of Mars. Constraints on the vehicles considered are set by the payload and performance currently envisioned by mission analysis carried out previously at the Jet Propulsion Laboratory. The students are given full flexibility to examine those aspects which suit their interests and background. There are no regularly scheduled class lectures. Weekly review meetings are held with personnel from the Jet Propulsion Laboratory, and students use JPL resources as required.

Description: The Advanced Space Design project for 1986-87 was the design of a two stage launch vehicle, representing a second generation space transportation system (STS) which will be needed to support the space station. The first stage is an unmanned winged booster which is fully reusable with a fly back capability. It has jet engines so that it can fly back to the landing site. This adds safety as well as the flexibility to choose alternate landing sites. There are two different second stages. One of the second stages is a manned advanced space shuttle called Space Shuttle II. Space Shuttle II has a payload capability of delivering 40,000 pounds to the space station in low Earth orbit (LEO), and returning 40,000 pounds to Earth. Servicing the space station makes the ability to return a heavy payload to Earth as important as being able to launch a heavy payload. The other second stage is an unmanned heavy lift cargo vehicle with ability to deliver 150,000 pounds of payload to LEO. This vehicle will not return to Earth; however, the engines and electronics can be removed and returned to Earth in the Space Shuttle II. The rest of the vehicle can then be used on orbit for storage or raw materials, supplies, and space manufactured items awaiting transport back to Earth.

Description: The design task for the Advanced Aeronautics Design Project at UCLA is to provide a design for a hypersonic trans-atmospheric vehicle capable of horizontal take-off and landing from conventional runways. To accomplish this task, students are developing unclassified, unrestricted generic hypersonic vehicle models. These models include aerodynamic, propulsive, and thermal effects. The models will be used in the 1987-1988 academic year for vehicle design emphasizing the use of trajectory studies to optimize the vehicle design. The design problem is being considered both in terms of conventional issues such as aerodynamics, propulsion, and thermal systems and also in terms of flight systems, flight controls, and flight testing. The goal of this program is to consider testing as an integral part of design.

Description: A list of requirements for computational fluid dynamics verification is analyzed and evaluated. Requirements include: clearly defined physics and modeling, sensitivity studies, range, validation to real conditions, duplication of key experiments and computations, and combining experiments and computations. All results are presented in viewgraph format.

Description: Information is given in viewgraph form on computational fluid dynamics (CFD) validation experiments at the Lockheed-Georgia Company. Topics covered include validation experiments on a generic fighter configuration, a transport configuration, and a generic hypersonic vehicle configuration; computational procedures; surface and pressure measurements on wings; laser velocimeter measurements of a multi-element airfoil system; the flowfield around a stiffened airfoil; laser velocimeter surveys of a circulation control wing; circulation control for high lift; and high angle of attack aerodynamic evaluations.

Description: Computational fluid dynamics objectives are presented for Marshall Space Flight Center. Topics covered include: codes in use, applications to hardware development, and the Center's benchmark plan for the future. All results are presented in viewgraph format.

Description: Requirements and meaning of validation of computational fluid dynamics codes are discussed. Topics covered include: validating a code, validating a user, and calibrating a code. All results are presented in viewgraph format.

Description: Development of a pressure-strain model, an algebraic stress model, and wall functions appropriate for flows with spanwise variations in the local wall shear stress are accomplished. Furthermore, a hot-wire measurement technique was also developed for determining the local mean velocity and Reynolds stresses in a complex flow. Experiments were performed on supersonic and subsonic turbulent flow in a square duct, flow about a strut-endwall, flow within a transition duct, and on co-flowing annular jets with swirl. All results are presented in a viewgraph format.

Description: Information is given in viewgraph form on computational fluid dynamics (CFD) for aircraft design. Topics covered include CFD validation for advanced systems, cavity flow, transonic flow, separated flow, boundary layer interaction, hypersonic flow, heat transfer, zonal modeling, the mathematical foundation for Navier-Stokes simulation, hypersonic inlets, and the role of wind tunnel tests.

Description: The objective is to establish a detailed experimental data base for evaluation of Navier-Stokes codes for confined separated flows in diffusing s-ducts. The computational thrusts include the following: (1) extension and validation of the LeRC parabolized Navier-Stokes solver, PEPSIG, into the separated flow regime using 'flare' type approximations; (2) evaluation and extensions of state-of-the-art turbulence models for confined separated flow with and without swirl; and (3) evaluation and validation of LeRC time marching 3-D Navier-Stokes code, PROTEUS, into confined separate flow regime. Various aspects of the study are presented in viewgraph form.

Description: The topics are presented in viewgraph form and include the following: codes for computational aeroelasticity validation; the benchmark transonic flutter (BTF) model; BTF testing; the BTF model program; features of transonic flutter; characteristics of attached and separated flow for complete aircraft; and the benchmark aeroelastic model program.

Description: Current multi-stage turbomachinery design/analysis methods are based on a time-averaged, axisymmetric representation of the flow field. The actual flow field is asymmetric and unsteady due to blade row interactions. The Reynolds averaged Navier-Stokes solvers are limited to single-stage machines for existing computers. Therefore, advanced multi-stage compressors will operate far off-design for portions of the flight regime. The objectives are to provide an experimentally validated average-passage calculation of multistage compressor blade row interactions and an experimentally validated time-accurate calculation of multi-stage compressor blade row interactions. Various aspects of this investigation are presented in viewgraph form.

Description: The objective of the research project is to develop and validate analytical methods for low-speed aerodynamics. The experimental needs for computational methods are presented. All data and results are presented in viewgraph format.

Description: A discussion is presented on the coupling of computational analysis and experiment. It is believed that this coupling is critical in developing new aerodynamic insights. Additionally, new methods for analyzing and interpreting data are discussed. These methods need to be developed in small-scale research studies and then applied to large-scale technology programs. The specific objectives of this program are threefold: (1) provide definitive data sets for the assessment of numerical simulations to the Navier-Stokes equations; (2) incorporate advanced instrumentation to measure the spatial and temporal structure of fluid flows; and (3) develop true parallelism between computational and experimental research using the 'scientific workstation' concept. The discussion is presented in viewgraph form.

Description: A computational fluid dynamics code is validated using data obtained through a nonintrusive laser Doppler velocimeter. A space marching technique and a parabolic marching technique are use to calculate the flow in a compressor using compressible and incompressible flow assumptions. In a viewgraph format, both computational fluid dynamics techniques and experimental data are compared to each other.

Description: Wind tunnel tests are performed in order to validate a computational fluid dynamics code. A large scale, two dimensional separation bubble is created on a flat plate, and low speed, turbulent flow is used. Extensive data sets are obtained with a nonintrusive laser velocimeter in addition to wall static pressure, total pressure, and hot-film measurements. All data and results are presented in a viewgraph format.