• Journal of Korean Society of Water and Wastewater
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• v.13 no.3
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• pp.83-90
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• 1999

This study was carried out to investigate the characteristics of trihalomethane (THM) formation from chlorination of groundwater in the northeastern area of Cheju Island. Effects of total organic carbon (TOC) and bromide in groundwater on the THM formation were studied. Samples were taken from two regions withe altitude. The concentrations of TOC and bromide in groundwater were higher at the regions of lower altitude, especially at the altitude below 50m. Generally the THM formation in GA region containing a high TOC was higher than that in GB region containing a relatively high bromide. At the altitude below 100m, the formation of total and brominated THM was highest at GB region. The most part of THM formation was brominated THM at GB region. The formation ratio of chloroform and brominated THM was similar to the others. Among the brominated THM, dibromochloromethane and bromoform in GB region were containing high bromide. Bromodichloromethane and dibromochloromethane in GA region were containing low bromide. At the altitude above 200m, chloroform was formed mainly. Comparing the ratio of brominated THM of total THM in Cheju Island with that in other areas, Seoul and Pusan, it can be konwn that the former showing 51.3% was much higher than the latter showing 6.7% and 28.8%, respectively.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.5
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• pp.54-61
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• 2014

In this study, a plume exhausted from rocket nozzle is investigated by using an unstructured 2-dimensional axisymmetirc DSMC code at various altitude. The small back-pressure to total-pressure ratio($P_b/P_o$) and large $P_b/P_o$ represent low and high altitude condition, respectively. At low altitude, the plume shows a typical complicated structure (e.g. Mach disk) of underexpanded jet while the high altitude plume experiences plain expansion. The various features of exhaust plume is discussed including density, translational/rotational temperature, Mach number and Knudsen number. The results shows that even at 20 km altitude where the freestream Knudsen number is small as $1.5{\times}10^{-5}$, the transitional and rarefied flow regimes can occur locally within the plume. It confirms the necessity of DSMC computation at low altitude.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.10
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• pp.100-106
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• 2019

Ground and high altitude simulated combustion experiments were conducted using a liquid rocket engine with hydrogen peroxide and kerosene as the propellant. A ground and high altitude simulated combustion test facility was constructed by installing a high altitude model diffuser and TMS (Thrust Measuring System) on a vertical combustion test bench. The thrust characteristics according to altitude were investigated using the combustion test equipment. The diffuser was designed on a 1:4.8 scale to verify the characteristics of the high diffusing diffuser and starting pressure. The cold flow tests were conducted using nitrogen gas, and the performance characteristics and starting characteristics of the scale down diffuser were verified. A diffuser and TMS were installed on the vertical combustion test bench, and the thrust correction equations for the system resistance were derived. The thrust correction equations were derived from the step test and vacuum step test before the actual hot firing test. Nozzles with an operating altitude of 10km were designed. Hot firing tests were conducted to analyze the thrust characteristics according to the operating altitude changes. The actual thrust was calculated using each correction equation with the thrust value measured by the TMS.

• Asian-Australasian Journal of Animal Sciences
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• v.32 no.12
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• pp.1801-1808
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• 2019

Objective: As an iconic symbol of Qinghai-Tibetan Plateau and of high altitude, yak are subjected to hypoxic conditions that challenge aerobic metabolism. Matrix metalloproteinases-3 (MMP3) is assumed to be a key target gene of hypoxia-inducible factor-$1{\alpha}$ that function as a master regulator of the cellular response to hypoxia. Therefore, the aim of this investigation was to identify the DNA polymorphism of MMP3 gene in domestic yak and to explore its possible association with high-altitude adaptation. Methods: The single-nucleotide polymorphisms (SNPs) genotyping and mutations scanning at the MMP3 locus were conducted in total of 344 individuals from four domestic Chinese yak breeds resident at different altitudes on the Qinghai-Tibetan Plateau, using high-resolution melting analysis and DNA sequencing techniques. Results: The novel of SNPs rs2381 $A{\rightarrow}G$ and rs4331 $C{\rightarrow}G$ were identified in intron V and intron VII of MMP3, respectively. Frequencies of the GG genotype and the G allele of SNP rs2381 $A{\rightarrow}G$ observed in high-altitude Pali yak were significantly higher than that of the other yak breeds resident at middle or low altitude (p<0.01). No significant difference was mapped for SNP rs4331 $C{\rightarrow}G$ in the yak population (p>0.05). Haplotype GC was the dominant among the 4 yak breeds, and Pearson correlation analysis showed that the frequencies of GC was significantly lower in Ganan (GN), Datong (DT), and Tianzhu white yaks (TZ) compared with Pali (PL) yak. The two SNPs were in moderate linkage disequilibrium in high-altitude yaks (PL) but not in middle-altitude (GN, DT) and low-altitude (TZ) yaks. Conclusion: These results indicate that MMP3 may have been subjected to positive selection in yak, especially that the SNP rs2381 $A{\rightarrow}G$ mutation and GC haplotypes might contribute to adaptation for yak in high-altitude environments.

• Journal of the Korea Institute of Military Science and Technology
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• v.16 no.2
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• pp.101-110
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• 2013

This paper considers the many kinds of attitude control systems including launcher. JVC(Jet vane control), Jet tap, Jetvator and Movable nozzles are used to control the initial attitude of a missile only. Recently side jet thruster and it's applications to control initial turn and to maneuver at high altitude have been increased. How to design and develop the missile for an initial turn and a high maneuver at high altitude using side jet thrust were described in this paper.

• Journal of Astronomy and Space Sciences
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• v.39 no.3
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• pp.79-86
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• 2022

Thermospheric wind observations from high to mid latitudes are compared with the newly developed Multiscale Atmosphere Geospace Environment (MAGE) model for the Nov 3-4 geomagnetic storm. The observation and simulation comparison shows a very good agreement and is better at high latitudes in general. We were able to identify a thermospheric poleward wind reduction possibly linked to a northward turning of the Interplanetary Magnetic Field (IMF) at ~22 UT on Nov 3 and an enhancement of the poleward wind to a southward turning near 10 UT on Nov 4 at high latitudes. An IMF southward turning may have led to an enhancement of equatorward winds at Boulder, Colorado near midnight. Simultaneous occurrence of aurora may be associated with an IMF By turning negative. The MAGE model wind simulations are consistent with observations in these cases. The results show the model can be a very useful tool to further study the magnetosphere and ionosphere coupling on short time scales.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.12
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• pp.1195-1201
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• 2010

Performance tests of a supersonic exhaust diffuser were conducted by using a liquid rocket engine for simulating high-altitude environment. The experimental setup consisted of a combustion chamber, a vacuum chamber and a diffuser. The combustion tests for simulating high-altitude environment were carried out at three cases by chamber pressure variation(26, 29, 32barg). The test results showed that the diffuser was started at all case and vacuum chamber pressures were approximately 140torr. The starting pressure using combustion gas was similar with that of cold gas, but the vacuum chamber pressure was relatively high because of high temperature in the vacuum chamber. The results of this test can be used as an essential database for the design of real-scale high-altitude simulation test facility in the future.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.11a
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• pp.75-81
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• 2006

The propulsion system of KSLV-I second stage is engine with high expansion ratio and its starting altitude is high. To verify the performance of engine before the launch in the ground, high altitude test facility to simulate its operating condition is necessary. This material is about the concept design of high altitude simulation test facility for second stage engine. And it will be the basis for the construction of test facility and the test of engine.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.180-187
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• 2007

Korea Aerospace Research Institute(KARI) is developing Korea Space Launch Vehicle(KSLV). KSLV-I is composed of liquid propulsion system for the first stage and apogee kick motor as the second stage. Kick motor has a high expansion ratio nozzle and its starting altitude is 300km high. To verify the performance of kick motor, high altitude test facility (HATF) to simulate its operating condition is necessary. This paper contains preliminary design for construction of HATF.

• Journal of IKEEE
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• v.22 no.3
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• pp.747-753
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• 2018

Currently, many companies have succeeded in logistics delivery experiments utilizing drone and report it. When a drone is used commercially, long-term flight is an important performance that a drone should have. However, unlike vehicles operated on the ground, drone is a vehicle that continues to consume energy when maintaining the current altitude or moving to the destination. Therefore, the drones can fly for a long time as the capacity of the battery is large, but the batteries with large capacity are restricted by heavy weight and it acts as a limiting factor in a commercial use. To address this issue, we attempt to compare how far we can fly than forward flight based on the flight pattern with the same energy consumption condition. In this paper, the comparison of energy consumption was performed in three flight pattern, forward flight without altitude change and forward flight with altitude change, by computer simulation and it shows the increasing of flight distances when the quadrotor fly with altitude change from high altitude to low altitude.