• International Journal of Aeronautical and Space Sciences
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• v.1 no.1
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• pp.48-61
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• 2000

Korea Aerospace Research Institute (KARI) have gained experience with Helicopter Vibration Health Monitoring (VHM) System technology with the help of UK GKN-WHL. GKN-WHL have had many years of experience with the research and development of vibration analysis techniques to improve the health monitoring of helicopter transmissions. This activity was targeted at transmission rig testing at first, but the techniques have been progressively developed where they are now used as a part of integrated Health and Usage Monitoring (HUM) systems on many types of in-service and new helicopters. The technique development process has been considerably aided by an ever expanding database of transmission monitoring experience from both the rig testing and aircraft operations. This experience covers a wide range of failure types from naturally occurring faults to crack propagation studies and covering a wide range of transmission configurations. Primarily based on accelerometer signals GKN-WHL's vibration analysis methods have also been applied to a variety of other sensor types. The transition from an experimental environment to operational VHM systems has been a lengthy process, there being a need to demonstrate technique reliability as well as effectiveness to both regulatory (Airworthiness Authority) and commercial organizations. Another important feature of this process has been the development of close relationships with a number of VHM system hardware and software suppliers. Such an experienced GKN-WHL provides various raw vibration data which was acquired from transmission ground test rig and allow KARI to develop it's own analysis program. KARI made a program and then analyzed the data to coma pre with the results of GKN-WHL. The KARI's results both time domain signals and statistical values show comparable to GKN's.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.8
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• pp.728-740
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• 2016

Korea developed several satellites through government-led satellite development projects, and now operates earth observation satellites of various sensors, science and technology satellites, and communication satellites. Satellites can be utilized in many fields, and Satellite Information, Global Navigation Satellite System, Satellite Communications and Broadcasting, Space Solar Power System are typical application fields. Now that we have developed and operated several satellites, we have to concentrate more efforts on satellite application. In this paper, we reviewed the current states of the technologies of four satellite application fields mentioned above and analyzed the future prospects of them.

• Proceedings of the Korea Institute of Fire Science and Engineering Conference
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• 2011.11a
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• pp.7-10
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• 2011

최근 국제우주정거장에서 화재안전에 관한 중요성의 인식으로 화재의 감지/소화의 메커니즘을 구체적으로 이해하기 위한 다양한 연구들이 시도되고 있다. 본 연구에서는 국제우주정거장에서 각종 실험과 연구를 진행하는 가압모듈을 대상으로 환기, 연기거동 및 감지에 관한 수치모델링을 수행하였다. 수치모델링은 NIST에서 개발된 FDS (Fire Dynamic Simulator)가 사용되었다. 국제우주정거장 내부는 마이크로중력환경으로 부력이 존재하지 않아 화재 발생 시 화염 및 연기거동은 지상에서의 현상들과 큰 차이를 보이게 된다. 따라서 현재 가압모듈에서 적용되고 있는 환기조건의 변화에 따른 연기거동 및 감지특성에 대한 연구는 향후 국내의 국제 우주정거장 실험 참여를 위한 기초적인 정보를 제공할 것으로 기대된다.

• Transactions of the Korean Society of Mechanical Engineers B
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• v.34 no.2
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• pp.213-218
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• 2010

A cooling system utilizing liquid helium to chill the cryopanel (800 mm $\times$ 700 mm dimensions) down to 4.2 K was designed, implemented, and tested to verify the role of the cryopanel as a heat sink for the payload of a spacecraft inside the large thermal vacuum chamber (effective dimensions : 8 m ($\Phi$) $\times$ 10 m (L)) of KARI (Korea Aerospace Research Institute). Two LHe (Liquid Helium) Dewars, one for the main supply and the other for refilling, were used to supply liquid helium or cold helium gas into this cryopanel, and flow control for the target temperature of the cryopanel within requirements was done through fine adjustment of the pressure inside the LHe Dewars. The return helium gas from the cryopanel was reused as a thermal barrier to minimize the heat influx on the core liquid helium supply pipe. The test verified a cooling time of around three hours from the ambient temperature to 40 K (combined standard uncertainty of 194 mK), the capacity for maintaining the cryopanel at intermediate temperatures, and a 1 K uniformity over the entire cryopanel surface at around 40 K with 20 W cooling power.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.2
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• pp.148-153
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• 2017

KARI LSWT(Korea Aerospace Research Institute Low Speed Wind Tunnel) has accumulated close to 20 years of know-how since its completion in 1998 and is trying to commercialize related technologies. As part of this research, KARI LSWT is studying design of vertical wind tunnel equipped with a skydiving simulator. KARI carries out concept design together with high performance/low noise design and is to transfer the related technology to a domestic producible company to increase commercialization possibility. In addition, KARI is seeking cooperation with related organizations in China to enter Chinese market.

• Bulletin of the Korean Space Science Society
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• 2009.10a
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• pp.46.3-46.3
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• 2009

The SAR (Synthetic Aperture Radar) satellite has the advantage of implementing the imaging mission even though it is night time, cloudy weather, and all weather conditions, which is different from the satellite with the optical payload. This is the reason why the SAR satellite comes into the spotlight in the observation satellite field. The Korea Aerospace Research Institute (KARI) has been developing the first Korean SAR satellite and is currently integrating and testing the Flight Model. For the launch vehicle service, KARI finalized the selection of the launch vehicle service provider and finished Critical Design Review (CDR) of the interface between the bus and the launch vehicle. KARI and launch vehicle service provider also finished the test of the telemetry interface between the bus and the launch vehicle. The test of the telemetry interface has the purpose of checking the interface of the telemetry which is the SOH(State-of-Health) of the satellite in an early launch stage. For this test, KARI has finished the development of the spacecraft simulator which is composed of the bus simulator to generate the analog telemetry and the launch vehicle simulator to gather the telemetry. In this research, the result of the hardware implementation and the software implementation for the spacecraft simulator were described. Finally the results of the launch vehicle telemetry MUX test which were performed at the launch vehicle provider's design office by using the spacecraft simulator were summarized. It is expected that this simulator will be used in the next test after the manufacture of the launch vehicle.

• International Journal of Aeronautical and Space Sciences
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• v.1 no.1
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• pp.13-20
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• 2000

The applications of CFD in the design process of a transonic civil transport at Korea Aerospace Research Institute (KARI) are outlined. Three Navier-Stokes solvers, developed at KARI with different grid approaches, are used to predict the aerodynamic coefficients and solve the flowfield of various configurations. Multi-block, Chimera, and unstructured grids are the approaches implemented. The accuracy of the codes is verified for the transonic flow about RAE wing/fuselage configuration. The multi-block code is used to provide the detailed data on the flowfield around a wall interference model with different test section sizes which will be used in establishing the wall interference correction method. The subsonic and transonic flowfields about K100-04A, one of the configurations of a 100-seater transport developed by KARI and Korea Commercial Aircraft Development Consortium (KCDC), are computed to predict the aerodynamic coefficients. The results for the subsonic flow are compared with those of wind tunnel test, and the agreement is found to be excellent. The interference effect of nacelle installation on the wing of K100-04A is also investigated using the unstructured grid method, and about 10% reduction in wing lift is observed. The accuracy of the three developed codes is verified, and they are used as an efficient tool in the design process of a transonic transport.

• Proceedings of the KSRS Conference
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• 2003.11a
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• pp.31-33
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• 2003

Recently, KARI developed in-house meteorological sensor processing system named MESIS for GOES GVAR 5-CH Imager for better KOMPSAT EOC mission operation. MESIS consists of antenna system, receiver, serial telemetry card, processing and mapping software, and 2 NT PC systems. This paper shows system requirement, system design, characteristic and test results of processing system. System operation concept and sample image are also provided. Implemented system was proven to be fully operational through lots of operations covering from RF signal reception to web publishing.

• Korean Journal of Remote Sensing
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• v.19 no.1
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• pp.37-42
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• 2003

Recently, KARI implemented the receiving and processing system for MODIS sensor data from NASA EOS satellites (TERRA and AQUA). This paper shows the development strategy considered, system requirement derived, system design, characteristic and test results of processing system. System operation concept and sample image are also provided. Implemented system was proven to be fully operational through lots of pass operations activities from RF signal reception to level-1 processing.

• Proceedings of the KSRS Conference
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• v.1
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• pp.60-63
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• 2006

Geostationary Ocean Color Imager (GOCI) is under development to provide a monitoring of oceancolor around the Korean Peninsula from geostationary platforms. It is planned to be loaded on Communication, Ocean, and Meteorological Satellite (COMS) of Korea. In this paper radiometric calibration concept of the GOCI is introduced. The GOCI radiometric response is modeled as a nonlinear system in order to reflect a nonlinear characteristic of detector. In this paper estimation approaches for radiometric parameters of GOCI model are discussed. For the GOCI, the offset signal depends on each spectral channel because dark current offset signal is a function of integration time which is different from channel to channel. The offset parameter can be estimated by using offset signal measurements for two integration time setting is described.