In-e Ight Research Articles

A PAIR OF EQUATIONS IN EIGHT PRIME CUBES AND POWERS OF 2

AbstractIn this paper, we show that every pair of sufficiently large even integers can be represented as a pair of eight prime cubes and k powers of $2$ . In particular, we prove that $k=335$ is admissible, which improves the previous result.

TINGKAT SERANGAN HAMA PENGGEREK POLONG, Maruca testulalis Geyer (Lepidoptera: Pyralidae)) PADA DELAPAN VARIETAS KACANG HIJAU (Vigna radiata L.) DAN PENGARUHNYA TERHADAP HASIL

[THE INCIDENCE OF POD-BORER, Maruca testulalis Geyer (Lepidoptera: Pyralidae) IN EIGHT MUNG BEAN VARIETIES (Vigna radiata L.) AND ITS EFFECT ON YIELD]. Mung beans are an essential food crop in Indonesia, whose production is still increasing to meet domestic needs. However, the high attack of plant pests Maruca testulalis Geyer (Lepidoptera: Pyralidae) is one of the leading causes of the low production of green beans. The use of superior varieties is one solution to controlling these pests. This study was conducted to test seven superior varieties of green beans, namely Vima 1, Vima 2, Vima 3, Murai, Kenari, Kutilang and Seriti and one local variety against M. testulalis. The study used a completely randomized block design and was repeated three times. The results showed that the mungbean varieties Vima 1, Vima 2, and Vima 3 had M. testulalis attack with the lowest level of seed damage in sequence, namely 5.84%, 7.94%, and 6.39%. Even though the percentage of pod borers attack did not significantly affect the growth of all Balitkabi superior varieties and one local variety of mungbean planted, the Kutilang variety was the highest yield with seed yield rates that were as low as other low-attack varieties.

EVALUATION OF PHARMACOGNOSTICAL VARIATIONS IN EIGHT ACCESSION OF CURCUMA LONGA L.

Introduction: In recent days, usage of medicinal plants as an herbal drug to treat various kinds of ailments has got drastically increased. Conventionally, Curcuma longa (rhizome) is used in the treatment of inflammation, cancer, wound healing, diabetes, asthma, antioxidant, anti-aging, antimicrobial, etc. Materials and Methods: The present study deals with the pharmacognostic and preliminary phytochemical evaluation of different accessions of C. longa (rhizome). The pharmacognostical profiles include organoleptic study, microscopy evaluation of the rhizome, powder microscopy, physiochemical paramters and determination of total phenolic and flavonoid content were carried out. Results and Discussion: Results showed that there are significant pharmacognostical variations in different accessions of turmeric. Conclusions: The result of the present study is useful in establishing the standards for identification, authentication, and evaluation of the plant material and the variations as well.

Clinical classification of borderline cases in the family study of essential tremor: an analysis of phenotypic features.

BackgroundIn genetic research on essential tremor (ET), certain individuals may be particularly challenging to categorize diagnostically.MethodsIn the Family Study of Essential Tremor (>200 enrollees), 28 participants with borderline clinical findings who did not meet strict criteria for ET were assigned final diagnoses of ET. We scrutinized the clinical features of these cases and the sensitivity/specificity of certain features that best separated them from 19 unaffected individuals.ResultsBorderline ET cases differed from unaffected individuals in eight features: total tremor score, at least one kinetic tremor rating ≥1.5, at least one kinetic tremor rating ≥1.5 in the dominant arm, tremor rating during spiral drawing ≥1.5, higher spiral axis score, head tremor, complaint of tremor, and comment on tremor by others. The combination of at least one kinetic tremor rating ≥1.5 in the dominant arm and the presence of at least three of the remaining seven features predicted the clinician-assigned diagnosis in 88.6% of borderline ET vs. unaffected individuals (sensitivity 84.6%, specificity 94.4%).DiscussionIn a family study, a small number of clinical features characterized borderline ET, and a particular combination of these separated the majority of these borderline cases from normals. These analyses may help researchers minimize diagnostic misclassification.

A CORRELATION BETWEEN SURFACE DENSITIES OF YOUNG STELLAR OBJECTS AND GAS IN EIGHT NEARBY MOLECULAR CLOUDS

We report the discovery and characterization of a power law correlation between the local surface densities of Spitzer-identified, dusty young stellar objects and the column density of gas (as traced by near-IR extinction) in eight molecular clouds within 1 kpc and with 100 or more known YSOs. This correlation, which appears in data smoothed over size scales of ~1 pc, varies in quality from cloud to cloud; those clouds with tight correlations, MonR2 and Ophiuchus, are fit with power laws of slope 2.67 and 1.87, respectively. The spread in the correlation is attributed primarily to local gas disruption by stars that formed there or to the presence of very young sub-regions at the onset of star formation. We explore the ratio of the number of Class II to Class I sources, a proxy for the star formation age of a region, as a function of gas column density; this analysis reveals a declining Class II to Class I ratio with increasing column density. We show that the observed star-gas correlation is consistent with a star formation law where the star formation rate per area varies with the gas column density squared. We also propose a simple picture of thermal fragmentation of dense gas in an isothermal, self-gravitating layer as an explanation for the power law. Finally, we briefly compare the star gas correlation and its implied star formation law with other recent proposed of star formation laws at similar and larger size scales from nearby star forming regions.

Longitudinal Flying Qualities Prediction for Nonlinear Aircraft

An analysis tool is presented that predicts longitudinal e ying qualities of a piloted aircraft subject to elevator rate limiting and nonlinear stick gradient. The method produces an explicit mathematical pilot model for the pitch attitude tracking task. By performing pilot-in-the-loop simulation, e ying qualities metrics are computed for evaluationofthelevelof e ying qualities.Theproposedmethodisvalidated using thee ightexperimentcalledHAVE LIMITS e own at the U.S. Air Force Test Pilot School. Good agreement was obtained between our analytical e ying qualities prediction and Cooper ‐Harper pilot ratings obtained in-e ight for elevator rate limits of 10 ‐157 deg/s.

Optical Fouling of the RB199 Pyrometer

The Turbo-Union RB199 aeroengine, which powers the Panavia Tornado aircraft, has two pyrometers installed to measure and control turbine blade temperature. The utilization of pyrometry and its installation, together with system cone guration, for this in-e ight application are described. The most important issue with pyrometry for in-service use is the deposition of particulates, or optical fouling, of the system’ s lens. The e owe eld and particle trajectories in the RB199 pyrometer purge air design are investigated together with an analysis of the deposits that constitute the fouling of the pyrometer lens. It will be shown that the predominant e ow feature within the purging system is a swirl pattern that develops at the mouth of the still tube. This feature has the ability to draw contaminant particles into the still tube and, thus, signie cantly increase the likelihood of particle deposition onto the lens resulting in optical fouling of the instrument’ s optics.

Analysis of In-Flight Behavior of Truncated Plug Nozzles

Plug nozzles are usually designed to achieve altitude adaptation in a wide range of chamber/ambient pressure ratios.In actual in-e ight operationsofplug nozzles, this phenomenon musttakeplacein a e owing airstream,which can affect the performance. To understand the e ow behaviorin such conditionsand to evaluate the departure from the ideal nozzle performance, an investigation is carried out with a validated numerical tool based on the solution of turbulent Navier ‐Stokes equations and on shock e tting. A sample rocket plug nozzle is analyzed parametrically to evaluate the effect of varying Mach number at constant pressure and the effect of varying pressure ratio at constant Mach number. The results indicate that the interaction with a e owing airstream reduces the pressure of the external air, as seen from the nozzle exhaust jet, yielding a reduction of the performance. In particular, a dramaticdecrease of nozzleperformance may takeplacein the transonicregion iftheslipstream effect is neglected in thedesign. Theresults also provide useful indications on how the Mach numberand the shroud shapecan affect the value of ambient pressure where the transition from open to closed wake takes place.

Solid-Fuel Ramjet Regulation by Means of an Air-Division Valve

An in-e ight regulation technique, which can provide an optimal operation of a solid-fuel ramjet (SFRJ) motor over a wide e ight envelope, has been analyzed. Regulation capability is essential for an efe cient use of the SFRJ propulsionforapplicationsinvolvingvariablee ightandoperatingconditions.Themethodisbasedonacontrollable air-division valve, which drivespart of the inlet airinto thesolid-fuel port, whiletherest of the aire ow ischanneled through a bypass to the aft-mixing section of the combustor. The model takes into account parameters ine uencing the burning rate of the solid fuel (e.g., port-e ow rate, port diameter ) and formulates a general regulation law in terms of the instantaneous opening state of the division valve fora constant fuel-to-air ratio operation. The control lawwascheckedforcertaincases,considering typicaltrajectories.Ithasdemonstrated agoodregulationcapability over a broad operational range (between sea level and 15-km altitude ). Nomenclature A = area d = diameter f = fuel-to-air ratio f (h) = function of altitude in the regulation law, Eq. (22) G = air mass e ux g(M) = function of Mach number in the regulation law, Eq. (23) H = inlet step height h = heat-transfer coefe cient; altitude L = fuel grain length M = Mach number m = temperature exponent C m = mass-e ow rate n = mass-e ow rate or mass e ux exponent C

Simulator Platform Motion Effects on Pilot-Induced Oscillation Prediction

Simulator motion platform characteristics were examined to determine if the amount of motion affects pilotinduced oscillation prediction. Five test pilots evaluated how susceptible 18 different setsof pitch dynamics were to pilot-induced oscillations with three different levels of simulation motion platform displacement: large, small, and none. The pitch dynamics were those of a previous in-e ight experiment, some of which elicited oscillations. These in-e ight resultsserved as truth data for the simulation. As such, the in-e ight experiment wasreplicated asmuch as possible. Objective and subjective data were collected and analyzed. With large motion, pilot-induced oscillation and handling qualities ratings matched the e ight data more closely than with small motion or no motion. Also, regardlessof the aircraft dynamics, large motion increased pilot cone dencein assigning handling qualitiesratings, reduced safety pilot trips, and lowered touchdown velocities. Whereas both large and small motion provided a pitch rate cue of high e delity, only large motion presented the pilot with a high e delity vertical acceleration cue.

Model Helicopter Rotor Aerodynamics and Acoustics As Measured in Two Anechoic Wind Tunnels

The qualities that are important for helicopter impulsive noise wind-tunnel testing are evaluated by comparing aerodynamic and acoustic data gathered on a single-scaled model main rotor that was tested in two open-jet wind anechoicwindtunnelsofmarkedlydifferentsize:theCEPRA19tunnelinFranceandtheDNWinTheNetherlands. The rotor was instrumented with miniature blade-mounted pressuretransducers and was tested on thesamerotor test stand located within the e ow of both open-jet wind tunnels. In-the-e ow rotor acoustic signatures and selected on-blade dynamic pressure signatures are presented for each facility and discussed in relation to the differences in tunnel geometry, tunnel e ow quality, and the aeroacoustic characteristics of each facility. This comparison shows that lowbackground noiselevels,a large in-the-e ow anechoicmeasurement space, and lowine ow turbulenceto the rotorarenecessarytoyieldhighqualityaerodynamicandacousticdata.Thebestmatchofacousticdatabetweenthe two facilitiesoccurswhen thetip-path planeoftherotorischosen tomatch closely dynamicblade-surface-mounted pressures. Achieving a good match between scaled wind-tunnel acoustics and in-e ight measurements are shown to be more dife cult: Agreement is reasonably good at low advance ratios but marginal at higher advance ratios.

Flight-Test Techniques Employed to Successfully Verify F/A-18E In-Flight Lift and Drag

F/A-18E e ight results successfully cone rmed pree ight aerodynamic and performance predictions. Because this was achieved very early in the e ight-test program, the need to rely heavily on e ight data to characterize aircraft performance capabilities was signie cantly reduced. The original aircraft performance e ight evaluation plan was reduced by 60 e ights with obvious cost benee ts. This was a direct result of early e ight test planning by a working group composed of representatives carefully selected from the involved organizations. Flight-test techniques were developed to determine high-quality, in-e ight lift and drag data and to directly demonstrate aircraft performance capability. These techniques are disscussed and a successful correlation of pree ight predictions and early e ight results is presented.

Certification and Operation of Helicopters in Icing Environments

This paper presents the issues gathered from a survey carried out on helicopter airframe and engine manufacturers, and helicopter operators and aircrews, throughout Europe and Canada. The work focused on in-e ight icing and the problems of manufacturing, testing, and subsequently, operating helicopters in such conditions. Most commercially operated helicopters are not permitted to e y in known icing conditions, because they are not certie ed to do so by the aviation authority. However, during the survey it was established that owing to commercial pressures, aircrews do e y in icing conditions, using helicopters that do not have an icing clearance. In addition, there is a disparity between what the airframe manufacturers and icing specialist know are the most dangerous icing conditions, and the knowledge held by helicopter aircrews. Aircrews would like a better method of ice detection and would prefer an ice predictor, which indicates that an icing environment is approaching, rather than a detector, which tells them that they are already in icing. Furthermore, operators would like all helicopters to have a full icing clearance if there were no operational penalties. In conclusion, the industry as a whole would like to verify that the icing envelope described in the certie cation regulations is applicable for helicopters. The current parameters have been modie ed from e xed-wing aircraft, which tend to cruise at much higher altitudes and in colder, drier conditions.

Time-Frequency Analysis for Transfer Function Estimation and Application to Flutter Clearance

Atransferfunction estimationprocedurethatrelies on thetime-frequency analysis of input and output signalsis described. This method was developed in an attempt to better identify the aeroelastic behavior of NASA Dryden’ s F-18 systems research aircraft and to predict its e utter boundaries using in-e ight experimental data. Numerical experimentson e eld data show thatexploiting thetime-frequency characteristics of the excitation inputscan bring enhanced accuracy and cone dence when identifying multi-input/multi-output transfer functions. In particular, the proposed approach complements many well-established black-box identie cation procedures by providing an independent way to obtain transfer function estimates. A computational tool implementing this approach is now being evaluated for practical use at NASA Dryden Flight Research Center.

Similarity Criteria for Manipulator Loading and Control Sensitivity Characteristics

On thebasisofsimilarity-theorymethodsandtheauthors’ previouslydeveloped theoreticalapproach, similarity criteria are developed for the handling qualities of aircraft with different manipulators and control sensitivity characteristics. The basicconceptsarepresented forthetheoretical approach to estimating the ine uenceof various manipulator and control sensitivity characteristics on handling qualities. The method being substantiated allows estimationofthehandlingqualitiesofanaircraftwithcertainmanipulatorandcontrolsensitivitycharacteristicsby comparing them with the respective data obtained for the aircraft with other characteristics. Recommendations are given for modeling, on ground-based and in-e ight simulators, the controllability of an aircraft with certain manipulatorsandcontrolsensitivitythatmaydifferfromthoseofsimulators.Thedynamiccharacteristicsrequired of the manipulator feel systems used in ground-based and in-e ight simulators are considered.

Prediction of Pilot-in-the-Loop Oscillations Due to Rate Saturation

Rate saturation in modern e ight control systems has been shown as a main contributor to triggering of pilot-in-the-loop oscillations (PIOs). Oscillations with signie cant rate saturation effects are classie ed as category II PIO. A new method was developed to predict stability problems of rate-saturated closed-loop systems based on the rate-limiting element describing function. Jump phenomena are observed in the closed-loop system describing function after rate-limiting onset, which have been shown as highly correlated with location of the open-loop onset point (OLOP) of the rate limiter in the Nichols chart. The OLOP criterion and its background, physical signie cance, and determination are presented. Its relation to the negative inverse describing function technique is discussed. Application of the OLOP criterion to closed-loop aircraft-pilot systems in the roll axis was investigated by using aircraft models from in-e ight simulations e own on the NT-33 and the YF-16 e rst e ight cone guration. A high correlation was found between the OLOP criterion and the PIO susceptibility based on numerical investigations in the time domain with simple pilot models. Rate limiters in theforward path and feedback loop of the e ight control system were investigated.

Experimental Investigation of Spacecraft In-Flight Disturbances and Dynamic Response

In September 1991, NASA launched the Upper Atmosphere Research Satellite. In addition to its atmospheric sciences mission, analysis of data from the e rst 370 days after launch was used to investigate in-e ight spacecraft disturbances and responses. The investigation included a three-orbit in-e ight experiment to determine how each onboard instrument and subsystem disturbance contributed to the overall spacecraft dynamic response. The investigation quantie ed the spacecraft dynamic response produced by the solar array and high-gain antenna harmonic drive disturbances. The solar array’ s harmonic drive output resonated two solar array modes. Friction in the solar array gear drive provided sufe cient energy dissipation, which prevented the solar panels from resonating catastrophically; however, the solar array vibration amplitude was excessively large. The resulting vibration had a latitude-specie c pattern. Thermal elastic bending of the spacecraft’ s two e exible appendages as the spacecraft crosses the Earth’ s terminator and solar array modal contribution to the spacecraft response were also examined.

Diaphragm activity in obesity.

DIAPHRAGM ACTIVITY DURING CARBON DIOXIDE BREATHING AND TOTAL CHEST COMPLIANCE DURING DIAPHRAGM RELAXATION WERE MEASURED IN EIGHT OBESE SUBJECTS: four with normal blood gases and four with hypercapnia and hypoxemia. Whereas there were no significant differences in the values of total chest compliance between the two groups, there were marked differences in diaphragm activity. The increase in integrated electrical activity in the diaphragm, per millimeter increment in carbon dioxide tension in the arterial blood, averaged 66 units (range: 48-90) in the obese-normal subjects and 17 units (range: 12-22) in the obese-hypoventilation subjects. These results suggest that an incapacity to increase the activity in the respiratory muscles, to levels necessary to overcome the load caused by obesity, plays a major role in the genesis of respiratory failure in obese subjects.

SPECTRAL TYPES AND HΓ OBSERVATIONS FOR STARS IN EIGHT ASSOCIATIONS

SPECTRAL TYPES AND HΓ OBSERVATIONS FOR STARS IN EIGHT ASSOCIATIONS

Language disturbance and nonverbal cognitive performance in eight patients following injury to the right hemisphere.

Journal Article LANGUAGE DISTURBANCE AND NONVERBAL COGNITIVE PERFORMANCE IN EIGHT PATIENTS FOLLOWING INJURY TO THE RIGHT HEMISPHERE Get access Y. M. ARCHIBALD, Y. M. ARCHIBALD Search for other works by this author on: Oxford Academic PubMed Google Scholar J. M. WEPMAN J. M. WEPMAN Search for other works by this author on: Oxford Academic PubMed Google Scholar Brain, Volume 91, Issue 1, March 1968, Pages 117–130, https://doi.org/10.1093/brain/91.1.117 Published: 01 March 1968