• Journal of Yeungnam Medical Science
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• v.19 no.1
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• pp.11-27
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• 2002

Allogenic hematopoietic stem cell transplantation is one of the effective therapy for several hematologic malignancies. Transplantation preparative regimen is designed to eradicate the patient's underlying disease and immunosuppress the patient adequately to prevent rejection of donor's hematopoietic stem cells. So, conventional myeloablative preparative regimens with high-dose chemotherapy or radiotherapy are related to high rate of morbidity and mortality. However, It has become clear that the high-dose therapy dose not eradicate the malignancy in some patients, and that the therapeutic benefit of allogenic transplantation is largely related to graft-versus-leukemia/graft-versus-tumor (GVL/GVT) effect. An new approach is to utilize less toxic, nonmyeloablative preparative regimens to achieve engraftment and allow GVL/GVT effects to develop. This strategy reduces the risk of treatment-related mortality and allows transplantation for elderly and those with comorbidities that preclude high-dose chemoradiotherapy.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.5
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• pp.41-49
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• 2005

This paper discusses the test procedure, instrumentation, verification methodology and the results of the ground vibration test(GVT) performed on the KF-16D aircraft to estimate experimentally dynamic characteristics of the aircraft. The modal tests for 7 external store configurations were conducted to estimate effects of external stores on the aircraft vibration modes. To emulate free-free boundary conditions the test aircraft was mounted on its landing gear structure with deflated tires during the GVT. The airframe modal tests were done by burst random excitations with 6 to 8 shakers and about 200 accelerometers. Frequency response functions(FRFs) were measured for each test, and the FRFs were reduced and analyzed to identify the dynamic parameters interested. The analyses were carried out in two steps. To extract modal parameters such as, frequencies and damping ratios, the poly-reference least square complex exponential method was used in the time domain. The mode shape coefficients were estimated with the least squares frequency domain method to identify the vibration modes.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.6
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• pp.495-501
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• 2013

Korean Utility Helicopter (KUH) has been designed to avoid the blade passing frequency and any instability due to a coupling of dynamic characteristics between the main rotor and the airframe in ground operation. For these design objectives, the vibration analysis and the ground resonance analysis were performed to analyze the dynamic characteristics of the airframe and the main rotor. Then, the whirl-tower test was conducted to identify the dynamic characteristics of the main rotor and the ground vibration test (GVT) was conducted to identify the dynamic characteristics of the airframe. The GVT for KUH was conducted with the test conditions and test articles established in consideration of each flight and ground condition. This paper shows the method and technique for performing the GVT for KUH and presents the correlation technique and the results for the correlated analysis model.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.5
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• pp.482-489
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• 2010

This paper describes the test procedure, instrumentation, verification methodology and the results of the ground vibration test(GVT) and force vibration test(FVT) of the SmartUAV aircraft to estimate experimentally dynamic characteristics of the aircraft. Bungee cords are used to emulate free-free boundary conditions of the test aircraft. The SmartUAV is excited by three shakers and one-hundred frequency response functions(FRF's) is measured. The FRF's are reduced and analyzed to identify the dynamics parameters of the SmartUAV. To extract modal parameters of the SmartUAV such as, natural frequencies and damping ratios, the poly-reference least square complex exponential method is used in the time domain. The mode shape coefficients are estimated with the least squares frequency domain method to identify the vibration modes. The FVT was performed by fixed sine frequency with three shakers on the x, y and z direction and vibration characteristics of structures and detail equipments are measured.

• Advances in aircraft and spacecraft science
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• v.6 no.2
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• pp.117-144
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• 2019

High Altitude and Long Endurance (HALE) aircraft are capable of providing intelligence, surveillance and reconnaissance (ISR) capabilities over vast geographic areas when equipped with advanced sensor packages. As their use becomes more widespread, the demand for additional range, endurance and payload capability will increase and designers are exploring non-conventional configurations to meet the increasing demands. One such configuration is the joined-wing concept. A joined-wing aircraft is one that typically connects a front and aft wings in a diamond shaped planform. One such example is the Boeing SensorCraft configuration. While the joined-wing configuration offers potential benefits regarding aerodynamic efficiency, structural weight, and sensing capabilities, structural design requires careful consideration of elastic buckling resulting from the aft wing supporting, in compression, part of the forward wing structural loading. It has been shown already that this is a nonlinear phenomenon, involving geometric nonlinearities and follower forces that tend to flatten the entire configuration, leading to structural overload due to the loss of the aft wing's ability to support the forward wing load. Severe gusts are likely to be the critical design condition, with flight control system interaction in the form of Gust Load Alleviation (GLA) playing a key role in minimizing the structural loads. The University of Victoria Center for Aerospace Research (UVic-CfAR) has built a 3-meter span scaled and flexible wing UAV based on the Boeing SensorCraft design. The goal is to validate the nonlinear structural behavior in flight. The main objective of this research work is to perform Ground Vibration Tests (GVT) to characterize the dynamic properties of the scaled flight vehicle. Results from the experimental tests are used to characterize the modal dynamics of the aircraft, and to validate the numerical models. The GVT results are an important step towards a safe flight test program.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.10a
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• pp.72-77
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• 2011

In this study, the natural frequencies and mode shape of an external mounting pod were verified using the modal analysis and modal testing technique for a pod mounted on an aircraft. The procedure associated with the FEM building of an external mounted pod to predict the dynamic behavior of aircraft structures is described. The simplified FEM reflecting the results of the modal testing of a pod is built through the optimization, applied to the structural dynamic model of an Aircraft, used to verified the stability of vibration and flutter of an aircraft.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.10a
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• pp.191-195
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• 2011

The airframe ground vibration tests were conducted on the KC-100 aircraft according to the regulation requirement, KAS 23.629(a)(2) and the modal characteristics for the target modes were measured. To make FE model tuning, a design sensitivity approach with engineering judgment was implemented using MSC/Nastran and Attune, a genetic algorithm based parameter optimization software. Based on the comparison between initial prediction and test results, design variables such as beam cross-sectional properties and spring stiffnesses were devised. As the results, the correlation of the FE model to the GVT results was made appropriately, meeting the goal of matching the target frequencies within 5%.

• Proceedings of the Korean Vacuum Society Conference
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• 2012.02a
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• pp.225-225
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• 2012

국내에서 크라이오펌프를 생산한 지 여러해가 지나 냉동기 및 활성탄 어레이를 비롯한 대부분의 핵심 부품들을 가공하고 펌프를 조립하는 것을 자체적으로 해결하고 있지만 지금까지 펌프의 구조설계는 외국 제휴 회사에서 전수받은 것을 큰 수정없이 고수해 온 것이 현실이다. 따라서 펌프의 성능에 관한 별도의 시험과정 없이도 제공받은 성능값을 그대로 제시하는 것으로 충분했다. GVT(주)는 국내의 선도적인 크라이오펌프 전문생산 업체로서 독자적인 냉동기와 어레이 및 배플 설계에 기초한 신규 모델들을 정립하고 펌프를 생산하기 시작하였으며 다양한 크기의 표준용기를 마련하여 전 모델에 대해서 엄격한 시험검사를 시행하고 있다. 본 발표에서는 특별히 구경 200 mm UHV형 크라이오 펌프의 배기속도, 배기용량, cross-over 등 주요 배기성능 지표들을 측정한 결과 및 몬테카를로 계산을 통한 예측치와 비교한 결과를 소개한다.

• Journal of the Korea Society for Simulation
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• v.7 no.1
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• pp.69-83
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• 1998

In this paper, we present the results of simulation by running parallel VHDL simulation on typical MPP(Massively Parallel Processor) systems such as IBM SP2 and SGI Origin 2000. Parallel simulation uses the synchronous protocol and parallel program is implemented using MPI(Message Passing Interface) based on message passing model, so that it can urn on any parallel programming environment which supports MPI, a standard communication library. And then GVT(Global Virtual Time) computation for parallel simulation is based on the global broadcasting with MPI＿Bcast(), which is a standard function in MPI and piggybacking. Our benchmark exhibits that as size of VHDL grows, the parallel simulation has a better performance compared with the sequential simulation. In addition, we also show the results of comparison between IBM SP2 and SGI Origin 2000 by applying the same application to those indirectly.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.4
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• pp.91-99
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• 2005

Flight compatibility certification is performed to substantiate the compatibility between ALQ-X ECM pod and KF-16D/RF-4C aircraft. A certification plan for the ALQ-X flight compatibility is established. Similarity analysis, mass/inertia analysis, structural analysis/test, and ground vibration test/flutter analysis are made to support the safety of MIL-HDBK-1763 Test 250 (Captive compatibility flight profile). Aircraft flew along flight envelope boundary with representative ALQ-X configurations. Handling qualities are evaluated by comparing flight characteristics of the aircraft with and without ALQ-X. Structural integrity and endurance is evaluated using measured flight test data. Results of these flight tests showed that ALQ-X is compatible with KF-16D/RF-4C without altering the flight envelope which has originally been certified for ALQ-88 and ALQ-119 ECM pods. ALQ-X certification program made following technical achievements: Type III certification for foreign designed fighter, flutter analysis program development using GVT results, and utilization of MIL-STD-1553B data bus in flight test.