• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2012.05a
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• pp.24-27
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• 2012

In this study, the full scale flight type Dual-Pulse Rocket Motor(DPRM) with the bulkhead type Pulse Separation Device(PSD) was designed, manufactured, and fire-tested. The bursting time and pressure of PSD were analyzed by the pressure, thrust and vibration results of static fire tests and ablation of PSD was measured with 3-D coordinate measuring machine. As a result, PSD requirements, bursting conditions and thermal safety, were satisfied.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.42 no.11
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• pp.988-995
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• 2014

Two axis gimbal type X-band antenna system has been widely used to effectively transmit the real time image data from the observation satellite to the ground station. The micro-vibration generated by stepping motor actuation and imperfect intermeshed gear configuration of the antenna is one of the sources to degrade the image quality. To guarantee a high quality image of high resolution observation satellite, micro-vibration isolation of X-band antenna is required. In this paper, the X-band antenna vibration isolation system using pseudoelastic SMA(Shape Memory Alloy) mesh washer has been newly suggested. The basic characteristics of the SMA mesh washer isolator proposed in this study has been measured through static load tests and its effectiveness has been demonstrated by the micro-vibration isolation test of the X-band antenna.

• Explosives and Blasting
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• v.28 no.2
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• pp.37-49
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• 2010

Ground vibration caused by blasting in the urban area close to structures can give some indirect damage to human body and may lead to structural damage to buildings. At the stage of design or when complaints were filed by residents, the test blasting in borehole, which is most practical for expressing simple vibration wave form quantitatively, is usually chosen for assessing the degree of damage to structures. In this paper, some lessons gained from the application of electronic detonator triggering system in borehole test blasting are presented. The difference in delay time of detonator when borehole is blasted by electronic detonator and electric detonator are discussed. The peak particle velocities measured at the structure embedded in the similar rock layer to main line of tunnel at test site and measured at the road surface just above the tunnel having different overburden layers were analysed to draw their relationship. By comparing the results with those appearing in some published literatures, the usefulness of the borehole test blasting and the importance of delay time of detonator are addressed.

• Aerospace Engineering and Technology
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• v.9 no.2
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• pp.143-152
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• 2010

Development and verification of whole vibration test system was requested for developing a geostationary satellite. This satellite is enlarged significantly compared with fore-satellite in KARI. For vertical vibration test, new vertical vibration system was developed. For lateral vibration test, thermal equilibrium test was performed because of difference of thermal characteristics between test adapter and slip table. And lateral vibration system performance for overturning moment was verified by analysis and test. As the number of acquisition channels was increased, new shaker control and data acquisition system was installed. In this paper, verification process and techniques to improve test stability are introduced for the whole vibration test system.

• Journal of the Korea Institute of Military Science and Technology
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• v.10 no.4
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• pp.176-184
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• 2007

The missile for this study has shown different natural frequency characteristics depending on the test conditions; natural frequencies obtained from its flight test are higher than those in its ground test. It was found that the hinged joints connecting front airframe to rear one had the nonlinear stiffness and caused the missile to show very complex dynamic characteristics. The angular stiffness at hinged joints was calculated using 3D finite element analysis, and it was verified that there was a highly nonlinear relationship between angular stiffness and external load. Natural frequencies calculated considering the nonlinearity of angular stiffness were nearly the same as test results. Through this study, the dynamic characteristics of a missile having split airframes with hinged joints could be clearly identified and a way of maintaining its natural frequencies consistent was generated.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2005.11b
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• pp.45-48
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• 2005

Tile gust generator was designed for generating the gust field in the wind tunnel test of the scaled flexible wing model for validating gust response alleviation system. The ground operation test was performed for estimating the dynamic performance of tile gust generator before installing it in the wind tunnel for gust field measurement. The ground test results showed that the gust generator has sufficient dynamic capability to simulate the sinusoidal and random motion of the gust generator wing and thus can be used in the wind tunnel test related to gust.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.5
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• pp.439-446
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• 2016

The characteristics of bearingless main rotor of helicopter are investigated through non-rotating tests and rotating tests. The stiffness and natural frequencies of rotor blades, flexbeam, and torque tube which are core components of baearingless rotor are measured to obtain input material properties for rotor analysis. The functional test on ground for assembly of one hub with damper, snubber, and no blade is carried out to check interfaces between components, kinematics of components, and pitch motion ranges under applied loads including centrifugal load. The 4-bladed bearingless rotor with 5.82m of rotor radius is tested on the whirl tower with rotation plane of 9.65m height. The thrust and power are measured to obtain hover performance and the frequencies and dampings of the rotor are obtained by excitation of cyclic pitch by hydraulic actuators.

• The Bulletin of The Korean Astronomical Society
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• v.37 no.2
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• pp.133.2-133.2
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• 2012

위성체는 발사체에 탑재되어 임무수행을 위한 우주설정궤도로 이동하게 된다. 이 과정중 발사체에서 분사되는 방대한 양의 추진제, 고속 추진에 따른 페어링 외기의 동압 변화등은 위성체가 안치되어 있는 페어링 내부에 수천 Hz의 주파수 대역에 걸쳐 130 ~ 150 dB에 이르는 음장을 형성한다. 이러한 페어링 내부의 고에너지 음장은 위성체 구조물 및 탑재물의 기계적인 진동을 유발하여, 물리적인 파손을 일으키거나 주요 기능에 중대한 결합을 유발 시킬 수 있다. 이에 따라 위성체는 개발단계에서부터 소음환경에 대한 검증시험을 수행하게 된다. 지상에서의 검증시험은 잔향실과 음향 모듈레이터로 구성되어 있는 음향챔버 시스템을 이용하여 수행된다. 음향 모듈레이터는 기화된 고압의 대용량 질소가를 이용하여 발사체에서 생성되는 고 에너지의 소리를 발생하게 된다. 본 논문에서는 음향환경 시험용 음향 모듈레이터에 대한 분석, 시험을 바탕으로 작동 원리 및 음향특성 분석을 수행하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.22 no.1
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• pp.80-88
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• 2018

The function of a vehicle holding device (VHD) is to securely hold a launch vehicle on the launch pad and release the launch vehicle at maximum thrust after engine ignition to allow lift-off of the launch vehicle. During the release of the launch vehicle, to prevent the Ka doing a doing a doing mode, which is the vertical oscillation of the entire liquid propellant, the release of the launch vehicle should be gradual. In this study, for the gradual release of a launch vehicle, a hydraulic system comprising an accumulator and pyro valve to operate a hydraulic cylinder and control the speed of the cylinder with an orifice is introduced. Through a test, the influence of design variables on the cylinder speed is analyzed. Based on this, the design values of the hydraulic cylinder are determined. Through this study, the engineering basis for developing a VHD releasing a launch vehicle at maximum thrust is provided.

• 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.