Counterexample of theorems on star versions of Hurewicz property

[EN] In this paper, an example contradicting Theorem 4.5 and Theorem 5.3 is provided and these theorems are proved under some extra  hypothesis.The author acknowledges the fellowship grant of University Grants Commission, India.Bhardwaj, M. (2020). Counterexample of theorems on star versions of Hurewicz property. Applied General Topology. 21(1):53-56. https://doi.org/10.4995/agt.2020.11976OJS5356211M. Bonanzinga, F. Cammaroto and Lj. D. R. Kocinac, Star-Hurewicz and related properties, Appl. Gen. Topol. 5, no. 1 (2004), 79-89. https://doi.org/10.4995/agt.2004.1996R. Engelking, General Topology, Revised and completed edition, Heldermann Verlag Berlin (1989).J. Gerlits and Zs. Nagy, Some properties of $C(X), I$, Topology Appl. 14 (1982), 151-161. https://doi.org/10.1016/0166-8641(82)90065-7W. Hurewicz, Über eine verallgemeinerung des Borelschen Theorems, Math. Z. 24 (1925), 401-421. https://doi.org/10.1007/BF01216792W. Hurewicz, Über Folgen stetiger Funktionen, Fund. Math. 9 (1927), 193-204. https://doi.org/10.4064/fm-9-1-193-210Lj. D. Kocinac, Star-Menger and related spaces, Publ. Math. Debrecen 55 (1999), 421-431.Lj. D. Kocinac and M. Scheepers, Combinatorics of open covers (VII): Groupability, Fund. Math. 179 (2003), 131-155. https://doi.org/10.4064/fm179-2-2M. Scheepers, Combinatorics of open covers (I) : Ramsey theory, Topology Appl. 69 (1996), 31-62. https://doi.org/10.1016/0166-8641(95)00067-

A CFD/CSD Interaction Methodology for Aircraft Wings

With advanced subsonic transports and military aircraft operating in the transonic regime, it is becoming important to determine the effects of the coupling between aerodynamic loads and elastic forces. Since aeroelastic effects can contribute significantly to the design of these aircraft, there is a strong need in the aerospace industry to predict these aero-structure interactions computationally. To perform static aeroelastic analysis in the transonic regime, high fidelity computational fluid dynamics (CFD) analysis tools must be used in conjunction with high fidelity computational structural fluid dynamics (CSD) analysis tools due to the nonlinear behavior of the aerodynamics in the transonic regime. There is also a need to be able to use a wide variety of CFD and CSD tools to predict these aeroelastic effects in the transonic regime. Because source codes are not always available, it is necessary to couple the CFD and CSD codes without alteration of the source codes. In this study, an aeroelastic coupling procedure is developed which will perform static aeroelastic analysis using any CFD and CSD code with little code integration. The aeroelastic coupling procedure is demonstrated on an F/A-18 Stabilator using NASTD (an in-house McDonnell Douglas CFD code) and NASTRAN. In addition, the Aeroelastic Research Wing (ARW-2) is used for demonstration of the aeroelastic coupling procedure by using ENSAERO (NASA Ames Research Center CFD code) and a finite element wing-box code (developed as part of this research)

PHARMACEUTICAL PREPARATION OF TAMRA BHASMA

Bhasma occupy the highest attention and have got a very unique place because of their small doses, tastelessness, quick action, easy absorption and also their prolonged shelf life, wide range of therapeutic efficacy and better rejuvenating (Rasayana) effects. Metals and minerals are integral part of therapeutics in Ayurveda and Tamra is one of such metals which if properly processed and detoxified is useful in many diseases. But if not processed properly it shows many ill effects called Ashtmaha Dosha. In the present study Tamra Bhasma was prepared by using Tamra Patra. This study included procedures like Shodhana, Marana, Amrutikarana as per classical texts. 380gm of raw Tamra Patra were taken. Samanya and Vishesha Shodhana were done as per reference of Rasa Ratna Samuchya. After complete Shodhana, total 350gm Shudha Tamra was obtained. Loss in weight after Shodhana may be due to loss in impurities present in raw Tamra. Total 21 Puta were given in the electrical muffle furnace to prepare Tamra Bhasma. Specific temperature pattern was adopted for Puta in the electrical muffle furnace. Total 300gm of Tamra Bhasma was obtained. After each Puta there was significant loss in weight of Tamra may be due to loss in hardness and impurities. Marana was followed by Amrutikarana and net weight of Tamra Bhasma obtained was 330gm. 30gm weight gain may be due to the organic material used for the Amrutikarana process. Color of Bhasma became black after Amrutikarana

Comparison of SIA defect morphologies from different interatomic potentials for collision cascades in W

The morphology of defects formed in collision cascades is an essential aspect of the subsequent evolution of the microstructure. The morphological composition of a defect decides its stability, interaction, and migration properties. We compare the defect morphologies in the primary radiation damage caused by high energy collision cascades simulated using three different interatomic potentials in W. An automated method to identify morphologies of defects is used. While most defects form 1/2⟨111⟩ dislocation loops, other specific morphologies include ⟨100⟩ dislocation loops, multiple loops clustered together, rings corresponding to C15 configuration and its constituent structures, and a combination of rings and dislocations. The analysis quantifies the distribution of defects among different morphologies and the size distribution of each morphology. We show that the disagreement between predictions of the different potentials regarding defect morphology is much stronger than the differences in predicted defect numbers.Peer reviewe

Comparison of SIA defect morphologies from different interatomic potentials for collision cascades in W

The morphology of defects formed in collision cascades is an essential aspect of the subsequent evolution of the microstructure. The morphological composition of a defect decides its stability, interaction, and migration properties. We compare the defect morphologies in the primary radiation damage caused by high energy collision cascades simulated using three different interatomic potentials in W. An automated method to identify morphologies of defects is used. While most defects form 1/2⟨111⟩ dislocation loops, other specific morphologies include ⟨100⟩ dislocation loops, multiple loops clustered together, rings corresponding to C15 configuration and its constituent structures, and a combination of rings and dislocations. The analysis quantifies the distribution of defects among different morphologies and the size distribution of each morphology. We show that the disagreement between predictions of the different potentials regarding defect morphology is much stronger than the differences in predicted defect numbers.Peer reviewe

Design of a pressurized lunar rover

A pressurized lunar rover is necessary for future long-term habitation of the moon. The rover must be able to safely perform many tasks, ranging from transportation and reconnaissance to exploration and rescue missions. Numerous designs were considered in an effort to maintain a low overall mass and good mobility characteristics. The configuration adopted consists of two cylindrical pressure hulls passively connected by a pressurized flexible passageway. The vehicle has an overall length of 11 meters and a total mass of seven metric tons. The rover is driven by eight independently powered two meter diameter wheels. The dual-cylinder concept allows a combination of articulated frame and double Ackermann steering for executing turns. In an emergency, the individual drive motors allow the option of skid steering as well. Two wheels are connected to either side of each cylinder through a pinned bar which allows constant ground contact. Together, these systems allow the rover to easily meet its mobility requirements. A dynamic isotope power system (DIPS), in conjunction with a closed Brayton cycle, supplied the rover with a continuous supply of 8.5 kW. The occupants are all protected from the DIPS system's radiation by a shield of tantalum. The large amount of heat produced by the DIPS and other rover systems is rejected by thermal radiators. The thermal radiators and solar collectors are located on the top of the rear cylinder. The solar collectors are used to recharge batteries for peak power periods. The rover's shell is made of graphite-epoxy coated with multi-layer insulation (MLI). The graphite-epoxy provides strength while the thermally resistant MLI gives protection from the lunar environment. An elastomer separates the two materials to compensate for the thermal mismatch. The communications system allows for communication with the lunar base with an option for direct communication with earth via a lunar satellite link. The various links are combined into one signal broadcast in the S-band at 2.3 GHz. The rover is fitted with a parabolic reflector disk for S-band transmission, and an omnidirectional antenna for local extravehicular activity (EVA) communication. The rover's guidance, navigation, and control subsystem consists of an inertial guidance system, an orbiting lunar satellite, and an obstacle avoidance system. In addition, the rover is equipped with a number of external fixtures including two telerobotic arms, lights, cameras, EVA storage, manlocks, a docking fixture, solar panels, thermal radiators, and a scientific airlock. In conclusion, this rover meets all of the design requirements and clearly surpasses them in the areas of mobility and maneuverability

CLINICAL COMPARISON OF TYMPANIC MEMBRANE PERFORATION CLOSURE WITH TRICHLOROACETIC ACID AND APAMARGA KSHARA (ACHYRANTHES ASPERA LINN. ALKALINE EXTRACT)

Tympanic membrane perforations are broadly pathological and traumatic in origin. The fibrosed rim of perforation and medially migrated epithelial layer of the perforated membrane offers a cauterization opportunity which conspicuously breaks the epithelial barrier, dissolves necrosed tissue over growth and enhances neo membrane formation. Trichloroacetic acid chemical cautery and patching is used from decades in order to reconstitute the tympanic membrane integrity with a successful rate hovering around 85-92% in various clinical studies. Nowhere in the classical Ayurveda texts or in the modern literature Apamarga Kshara (Achyranthes aspera Linn. alkaline extract) paste cauterization is used for re-epithelialization of the tympanic membrane although its tissue generative properties and antimicrobial traits are quite well documented. 34 tympanic membrane perforation patients after ramifying them into two groups were selected for the present clinical study which intends to compare the effectiveness of tympanic membrane perforation closure by application of trichloroacetic acid vis-a-vis application of Achyranthes aspera alkaline extract on the margins of the perforation. Achyranthes aspera alkaline extract for the current clinical trial as a trial drug has its proven tissue regeneration and vasoproliferative properties which is an indispensible prerequisite in any attempt to restore the integrity of a perforated tympanic membrane, also its antimicrobial and vasoproliferative capacity also compliments the selection of Achyranthes aspera alkaline extract. This cauterization with Apamarga Kshara was found to be quite effective as the results were encouraging and can successfully be advocated as an Ayurvedic cauterization substitute for the resurfacing of the ruptured tympanic membrane.

FIXED POINT THEOREM IN DISLOCATED QUASI METRIC SPACES

In the present paper we established some fixed point results in dislocated quasi metric spaces for random operator. Our results are generalized forms of various known results. Key words: Fixed point, common fixed point, Dislocated Metric spaces AMS classicification: 47 H1