• Wind and Structures
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• v.26 no.4
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• pp.215-229
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• 2018

The appearance of a rivulet at the upper surface of a stay cable is responsible for rain-wind-induced vibration (RWIV) of cables of cable-stayed bridges. However, the formation mechanism of the upper rivulet and its aerodynamic effects on the stay cable has not been fully understood. Large eddy simulation (LES) method is used to investigate flow around and aerodynamics of a circular cylinder with an upper rivulet at a Reynolds number of 140,000. Results show that the mean lift coefficients of the circular cylinder experience three distinct stages, zero-lift stage, positive-lift stage and negative-lift stage as the rivulet located at various positions. Both pressure-induced and friction-induced aerodynamic forces on the upper rivulet are helpful for its appearance on the upside of the stay cable. The friction-induced aerodynamic forces, which have not been considered in the previous theoretical models, may not be neglected in modeling the RWIV. In positive-lift stage, the shear layer separated from the upper rivulet can reattach on the surface of the cylinder and form separation bubbles, which result in a high non-zero mean lift of the cylinder and potentially induces the occurrence of RWIV. The separation bubbles are intrinsically unsteady flow phenomena. A serial of small eddies first appears in the laminar shear layer separated from the upper rivulet, which then coalesces and reattaches on the side surface of the cylinder and eventually sheds into the wake.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.171-179
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• 2007

The Test Equipment for the upper stage of KSLV-I has following functions via umbilical cable interface; external power supply, command output such as discrete and analog, data acquisition, CS-I interface simulation for first stage of KSLV-I and RS-422 serial communication for PDU. The main purpose of UTE is the experiment or function verification of system-level upper stage. To realize this system, we used PXI control system. The UTE is consisted of the PXI control system, power supply, terminal block, internal harness, connector panel and so on. The software functions of UTE are classified by four blocks. These are Discrete/Analog I/O control, PDU RS-422 serial communication control, power supply GPIB control and UTE remote control. In this paper, we will describe the design on the hardware and software of UTE.

• Journal of Biomedical Engineering Research
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• v.36 no.5
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• pp.155-161
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• 2015

In the paper, we developed the mobile based rehabilitation system for patients with upper extremity hemiplegia after stroke and evaluated clinical usefulness and effectiveness of the system. The sensors built in the smartphone were used to track patients' upper limb motion and the movements was transferred to the tablet PC through bluetooth connection so that the game contents could be interact with the movements. The rehabilitation game contents was based on Brunnstrom stage(B-stage), and was designed to lead accurate movement of upper limb. For the clinical evaluation of the effectiveness, 11 patients were recruited and make them perform an exercise of their wrist, shoulder, and forearm using the system for two weeks. The change of upper limb motor function was measured using fugl-meyer assessment(FMA), Brunnstrom stage(B-stage). And the change of quality of life was measured using EuroQoL-5 Dimension(EQ-5D), Beck Depression Inventory(BDI). The results showed significant improvement in upper limb function but not in quality of life. We verified mobile based rehabilitation program could be useful and effective for the clinical use.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2010.11a
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• pp.807-808
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• 2010

To insert payload to the orbit over the 200km-altitude using launch vehicle which has 300sec the Isp, multi staging technique for launch is necessary. The range between the sea-level to the transfer orbit about 200~250km is for operation of 1st and 2nd rocket engines and the higher altitude is for propulsion system of the acceleration block and satellite. The upper stage rocket engine should have the high technology for entering the payload into the orbit precisely more than the performance for high thrust level. With this investigation of the upper stage rocket engines which have been used, we want to understand their development trend and prospect which is going to be references for the development of ours.

• Korean Journal of Clinical Oncology
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• v.14 no.2
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• pp.120-127
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• 2018

Purpose: The purpose of this study was to determine the immunologic role of lymph node (LN) and stage migration by assessing LN count and metastatic LN count. Methods: A total of 2,117 patients with gastric adenocarcinoma located in the body and antrum who underwent distal/subtotal gastrectomy with D2 LN dissection between January 1, 1998 and December 31, 2008 were enrolled. LN count and number of metastases were determined in the N1 tier (area of D1 dissection) and N2 tier (area of D2 dissection). The lower and upper quartiles of LN counts in the same pN stage were grouped to compare the prognosis and LN positivity according to the LN tier. Results: Stage migration from N1 tier to N2 tier occurred in 3.2% of cases. The 5-year disease-specific survival rates of the upper and lower LN count groups within the N1 tier were 91.0% and 86.7% (P=0.01), respectively. LN positivity in the N2 tier of the lower LN count group was higher than that of the upper LN count group (14.1% vs. 8.2%, P<0.01). Stage migration in the N2 tier of the lower LN count group was also higher than that of the upper LN count group (4.6% vs. 1.8%, P<0.01). Conclusion: The lower LN count group had a decreased survival rate compared to that of the upper LN count group, suggesting that perigastric LN has an immunological defense role in weakening the disseminating power of metastatic tumor cells, as indicated by the LN count.

• Journal of the Korean Society of Propulsion Engineers
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• v.26 no.2
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• pp.79-95
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• 2022

Since space exploration began in the 1950s, numerous upper stage engines have been developed and used based on various design concepts. In this paper, information of upper stage engines which developed or developing is analysed and their characteristics and performance are summarized. These days, there are many cases of commercial heavy launch vehicles applying upper stage engines using liquid hydrogen with expander cycle which launched recently. Engines operating by Kerosene seem to be close to its theoretical maximum performance based on past experiences. Meanwhile, engines using methane propellant, which has recently become an issue, are also undergoing many developments because of various advantages. Recently, private companies are actively participating in launch vehicle market, and there are many cases in which the government and companies jointly research of next-generation engine.

• Aerospace Engineering and Technology
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• v.7 no.1
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• pp.194-201
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• 2008

The launch vehicle upper stage generally executes collision and contamination avoidance maneuver after the satellite separation. Through this maneuver the satellite safely settles in its orbit and the launch vehicle moves away from the satellite with minimum contamination. In this paper collision and contamination avoidance maneuvers by foreign launch vehicles are analyzed. Criteria for satellite contamination during the avoidance maneuver is given for KSLV-I upperstage.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.10
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• pp.709-716
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• 2022

In this paper the Gamma guidance law, which was used for IUS (Inertial Upper Stage), is applied for solid-motor guidance of a upper stage of a satellite launch vehicle. The RCS (Reaction Control System), which activates after burnout of the upper stage, is employed for the convergence of the guidance algorithm and compensation of velocity errors induced by the solid motor. The algorithm is also simplified by replacing the time-consuming numerical integration process to predict final vehicle states with Keplerian trajectories. The performance of the algorithm is evaluated by conducting 3-DOF computer simulations for off-nominal flight conditions. The numerical results show that Gamma guidance can reduce the orbit injection accuracy in comparison with that obtained by applying open-loop commands.

• Proceedings of the Korean Society of Precision Engineering Conference
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• 1991.04a
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• pp.46-58
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• 1991

An upper-bound method is applied to determine the final-stage extrsuion load and the deformed configuration of extruded billet. A simple kinematically admissible velocity field for trhee-dimensional deformation at final-stage is proposed. From the proposed velocity field the upper-bound extrusion load, the velocity distribution and the configuration of extruded billet are determined byminimizing the otoal power consumption. Experiments are carried out with full-annealed commercial aluminum billets at room temperature by using different sizes of elliptic punches. The theroretical predictions both in extrusion load and deformed configuration of extruded billet are ingood agreements with the experimentalresults.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.543-545
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• 2008

The Inner Arch developed several softwares: $\circ$ One dedicated to solid propulsion project : APSOL $\circ$ One dedicated to liquid propulsion projects ELIS A third one, PERFOL, is used to optimize the trajectory and the propulsion parameters The paper will describe the main software used for this study and illustrate the interest of these tools to make the first design of a new version of a launch vehicle with optimisation both of intrinsic propulsion parameters and of the trajectory.