• Title/Summary/Keyword: Kick Motor(KM)

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Modal Test of the 2nd stage structure of KSLV-I (KSLV-I 2단부 구조체 모드 시험)

  • Seo, Sang-Hyeon;Jeong, Ho-Kyeong;Youn, Se-Hyun;Park, Soon-Hong;Jang, Young-Soon
    • Aerospace Engineering and Technology
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    • v.6 no.1
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    • pp.114-119
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    • 2007
  • This paper introduces modal test of the 2nd stage structure of KSLV-I which is composed to satellite, PLA(Payload Adapter), EB(Equipment Bay), KMS(Kick Motor Support) and KM(Kick Motor) without PLF(Payload Fairing). In this test, to simulate free-free boundary condition, test object was hung by 4 bungee cords and excited by using impact hammer. From this test, dynamic properties of the 2nd stage structure of KSLV-I can be obtained. Modal test data are analyzed by using TDAS(Test Data Analysis Software). As the result, modal parameters and mode shapes below 100Hz of the 2nd stage of KSLV-I were identified.

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Velocity Loss Due to Atmospheric Drag and Orbit Lifetime Estimation (항력에 의한 속도 손실 및 궤도 수명 예측)

  • Park, Chang-Su;Jo, Sang-Beom;No, Ung-Rae
    • Aerospace Engineering and Technology
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    • v.5 no.2
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    • pp.205-212
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    • 2006
  • Atmospheric drag is the most significant factor effecting the low Earth satellites under the altitude of 800 km Although the atmospheric density of the low Earth orbit is very low compared to that of the sea level, the accumulated effect of the atmospheric drag slowly lowers the satellite velocity at the perigee. Decrease in velocity at perigee directly causes decrease in altitude at apogee which changes the eccentricity of the orbit. The orbit finally reaches a circular orbit before reentering the Earth. This paper states the methods of calculating the atmospheric drag and the lifetime of the satellite. The lifetime of the kick motor and the satellites which will be used on KSLV-L are calculated by Satellite Tool Kit.

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Plume Density Simulation of KM Residual Thrust Using DSMC Method (DSMC 방법을 이용한 킥모터 잔류추력 Plume Density 시뮬레이션)

  • Choi, Young-In;Kim, Keun-Taek
    • Journal of the Korean Society of Propulsion Engineers
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    • v.18 no.6
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    • pp.27-33
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    • 2014
  • 2nd stage of KSLV-I, NaRo-Ho, performs CCAM not to collide with Naro Science Satellite. At that moment, the satellite should pass through the Plume Density area which was generated by KSLV-I KM residual thrust. Therefore, it is necessary to predict Plume Density field of KM residual thrust and guarantee the safety of the trajectory of payload. In this paper, DSMC method was used to simulate Plume Density by KM residual thrust and the simulation showed that the trajectory of Naro Science Satellite was safe.