• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2000.04a
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• pp.14-14
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• 2000

One of the most important aerodynamic performance characteristics for projectiles is the total drag which can be typically divided into three components, pressure drag (excluding the base), viscous skin friction drag, and base drag. In a range of supersonic flight speeds the base drag is a major contributor to the total drag and can be as much as 50%∼70% of the total drag, depending on the afterbody configuration of projectiles. It is of especial importance to minimize this part of. the drag.

• Transactions of the Korean Society of Pressure Vessels and Piping
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• v.16 no.2
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• pp.58-67
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• 2020

This study presents cyclic stress-strain and tensile test results at room temperature (RT) and 316℃ using cold-worked TP304 stainless steel base and weld metals. By comparing the cyclic hardening/softening behavior and failure cycle of cold-worked materials with those of irradiated austenitic stainless steels, the feasibility of simulating the irradiation effect on cyclic deformation and failure behaviors of TP304 stainless steel base and weld metals was investigated. It was found that, in the absence of strain-induced martensite trasformation, cold-working could properly simulate the change in cyclic hardening/softening behavior of TP304 stainless steel base and weld metals due to neutron irradiation. It was also recognized that cold-working could adequately simulate the reduction in failure cycles of TP304 stainless steel base and weld metals due to neutron irradition in the low-cycle fatigue region.

• Journal of the Korean Society of Propulsion Engineers
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• v.16 no.1
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• pp.72-78
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• 2012

The position effect of the solid propellant in the combustion chamber on the decrease of the differential pressure has been investigated using the IBcode. Generally the metallic cartridge or CCC (combustible cartridge case) are used to load the propellant of the gun propulsion system. The position of the cartridge(propellant) is, therefore, a major factor for the interior ballistics in case the combustion chamber is larger than the cartridge. In this study, three different positions in the empty space of the chamber have been considered. As results, the case of the propellant located in the region near the base and breech has shown that the negative differential pressure and the difference between the breech pressure and the base pressure are much higher than those of the case of the propellant located in the center of the chamber. The case of the propellant in the center of the chamber is, therefore, more profitable to improve the performance of the interior ballistics.

• PNF and Movement
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• v.15 no.3
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• pp.343-351
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• 2017

Purpose: This study aimed to suggest effective lunge exercise methods for various purposes by comparing differences in the muscle activity of thigh and plantar pressure according to changes in base of support during lunge exercises. Methods: The subjects were 20 college students who agreed to participate in the experiment. They performed three types of lunges-a basic lunge (BL), wide lunge (WL), and narrow lunge (NL). In a static position during each lunge, the muscle activity of the thigh and plantar pressure were measured. Each movement was maintained for 7 seconds, and the muscle activity for the 3 seconds in the middle was measured and analyzed. The plantar pressure was divided into six areas for analysis. The subjects randomly performed the lunges to prevent the influence of an experimental sequence. Each movement was performed three times, and the mean value of the three measurements was analyzed. Results: The analysis of muscle activities in the thigh during the three lunge movements showed statistically significantly higher muscle activity of biceps femoris in WL and NL than BL. Moreover, the analysis of plantar force showed statistically significant differences between BL and WL and WL and NL on the medial-forefoot and medial-midfoot, as well as between BL and WL and BL and NL on the lateral-midfoot. The analysis of plantar contact pressure exhibited statistically significant differences between BL and NL and WL and NL on the medial-forefoot, as well as a statistically significant difference between WL and NL on the medial-midfoot and lateral-hindfoot. Conclusion: This study suggests that changing the base of support during lunges can be useful to suit the purposes of various rehabilitation programs.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2011.04a
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• pp.236-241
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• 2011

The position effect of the solid propellant in the combustion chamber on the decrease of the differential pressure has been investigated using the IBcode. Generally the metallic cartridge or CCC (combustible cartridge case) as the propellant for the cannon has been loaded. The position of the propellant(cartridge) is, therefore, a major factor for the interior ballistics in case the combustion chamber is larger than the cartridge. In this study, three cases of the existence of empty space in the chamber has been considered. As results, the case of the propellant located in the region near the base and breech has shown that the negative differential pressure and the difference between the breech pressure and the base pressure are much higher than those of the case of the propellant located in the center of the chamber. The case of the propellant in the center of the chamber is, therefore, more profitable to improve the performance of the interior ballistics.

• Journal of the Korean Society of Propulsion Engineers
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• v.12 no.5
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• pp.60-66
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• 2008

Each weapon system's muzzle velocity can be used as basic data for operating accurate automatic firing control system. Even among the same kind of ammunition, despite taking into consideration various battlefield parameters, irregular performance causes difficulties in obtaining accurate muzzle velocity data. In this study, pressure in the gun barrel was measured, the experimental relationship between chamber pressure and the projectile's base pressure was found, and a method of obtaining muzzle velocity was researched. Through this method, data regarding muzzle velocity is offered that corrects irregular performance.

• Journal of the Korean Society of Visualization
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• v.10 no.1
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• pp.47-54
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• 2012

Single Stage To Orbit (SSTO) missions which require its engines to be operated at varying back pressure conditions, use engines operate at high combustion chamber pressures (more than 100bar) with moderate area ratios (AR 70~80). This ensures that the exhaust jet flows full during most part of the operational regimes by optimal expansion at each altitude. Aero-spike nozzle is a kind of altitude adaptation nozzle where requirement of high combustion chamber pressures can be avoided as the flow is adapted to the outside conditions by the virtue of the nozzle configuration. However, the thrust prediction using the conventional thrust equations remains to be a challenge as the nozzle plume shapes vary with the back pressure conditions. In the present work, the performance evaluation of a new aero-spike nozzle is being carried out. Computational studies are carried out to predict the thrust generated by the aero-spike nozzle in varying back pressure conditions which requires the unsteady pressure boundary conditions in the computational domain. Schlieren pictures are taken to validate the computational results. It is found that the flow in the aero-spike nozzle is mainly affected by the base wall pressure variation. The aerospike nozzle exhibits maximum performance in the properly expanded flow regime due to the open wake formation.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2012.10a
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• pp.546-552
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• 2012

This paper is a study on squeal noise simulation under the consideration of temperature and pressure dependent material properties of friction material. For this, data of pressure and temperature dependent material properties of lining is achieved by using lining data base and exponential curve fit. Complex eigenvalue analysis is performed for predicting squeal noise frequency and instability and chassis dynamo test is performed for achieving squeal noise frequency, sound pressure level, occurrence temperature & pressure. Initial multi models are composed for considering complex interface conditions such as pad ear-clip, piston-housing and guide pin-torque member. The simulation result of base models is compared with the test result. Squeal noise simulation under the consideration of temperature and pressure dependent material properties of friction material is performed and analyzed using multi models. And additional condition is disc material property variation. Entire simulation conditions are combined and analyzed. Finally, this paper proposes direction of the warm squeal noise model.

• Proceedings of the Earthquake Engineering Society of Korea Conference
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• 2002.09a
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• pp.98-105
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• 2002

The effects of the base-isolation system and elastic soil foundation on the behavior of a liquid storage tank are studied. To evaluate the seismic response of liquid storage tank accurately, the coupled dynamic system considering base isolation and soil interaction problem is formulated in time domain. Results show that the base isolation system reduces effectively the radial displacements, base shears, overturning moments, axial resultant stresses and the hydrodynamic pressure by providing flexibility and energy dissipation capability. Base Isolation may, however, increase the relative liquid sloshing amplitude due to the effect of liquid-structure interaction and cause excessive large relative displacements between structure and foundation. In addition to base-isolator, the dynamic behavior of liquid storage tank is related to the flexibility of base foundation, so the analysis of soil-structure interaction s achieved.

• Proceedings of the KSME Conference
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• 2004.04a
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• pp.1589-1594
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• 2004

A numerical analysis has been performed to give an understanding of the physics of a compressible base flow with mass bleed in a Mach 2.47 freestream. Axisymmetric, compressible mass-averaged Navier-Stokes equations are computed using a two-equation turbulence model, standard ${\kappa}-{\omega}$, and a fully implicit finite volume scheme. The mass bleed is characterized by the change in the mass flow rate of the bleed jet non-dimensionalized by the product of the base area and freestream mass flux. The result showing that there is an optimum bleed condition with maximum base pressure, leading to a minimum base drag, is clearly predicted and the validation with experimental data shows reasonable agreement.