• Title/Summary/Keyword: 발사진동

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A Study on the Vibrational Environment Test of KSLV-1 Demonstration Satellite (한국형 위성 발사체 성능 검증위성의 진동환경에 관한 연구)

  • Seo, Hyun-Suk;Kim, Hong-Bae;Woo, Sung-Hyun;Chae, Jang-Soo;Oh, Tae-Sik
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2005.05a
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    • pp.966-970
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    • 2005
  • On the basis of the development of KSLV-1, KoDSat was designed and manufactured to demonstrate the performance of KSLV-1. KoDSat is exposed to a severe vibrational environment at launch. The structural reliability of KoDSat has to be verified using vibrational test. The structural compatibility and verification of components between analysis and test can be proved using environmental vibration test. In this paper, we review the structural characteristic of thruster control unit for a space launch vehicle and design TCU housing using mathematical model. In order to verify the structural compatibility and reliability, half-sine shock, random and sing sweep vibration test was performed. Especially, sing sweep vibration test result is compared with analysis result and mathematical model is verified.

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KSLV-I 하이드라진 추력기 제어기의 진동 해석 및 검증 시험

  • Kim, Ji-Hun;Jung, Ho-Lak;Jeon, Sang-Woon;Choi, Hyung-Don
    • Aerospace Engineering and Technology
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    • v.4 no.2
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    • pp.203-208
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    • 2005
  • Electronic components for space launch vehicles are exposed to a severe vibrational environment at launch and flight. The structural reliability of each component can be verified using mathematical approaches. In order to verify the structural reliability, an important parameter is the natural frequency of PCB(Printed Circuit Board) assembly mounted electronic components on and housing mounted PCB assembly in. In this paper, in order to find natural frequencies of PCB assemblies and the housing of hydrazine TCU(Thruster Control Unit), FEM(Finite Element Method) is adapted. The analytical result of FEM is verified by experimental method.

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HAUSAT-2 STM(Structural-Thermal Model) Development and Launch Environment Test Result Analyses (HAUSAT-2 위성 STM 개발 및 발사환경시험 분석)

  • Chang, Jin-Soo;Hwang, Ki-Lyong;Chang, Young-Keun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.11
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    • pp.95-105
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    • 2005
  • The HAUSAT-2 nanosatellite which is scheduled to launch in 2008 is being developed by SSRL(Space System Research Lab.). The HAUSAT-2 STM(Structural-Thermal Model) was developed as the first system model to verify structural and thermal design margin. The qualification level vibration and thermal tests have been conducted on STM. This paper addresses the comparison of structural analysis and test results of HAUSAT-2 STM. It was shown that the natural frequency of HAUSAT-2 STM satisfies the stiffness requirements without structural damage in the random vibration test. The assembly and integration validity were also checked out through STM.

Pyroshock and Vibration Characteristics of PEEK Washer Shock Absorbers (PEEK 와셔를 적용한 충격저감장치의 파이로 충격 및 진동 특성)

  • Youn, Se-Hyun;Jang, Young-Soon;Han, Jae-Hung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.36 no.3
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    • pp.285-290
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    • 2008
  • Pyrotechnic shock or pyroshock is characterized as a transient vibration phenomena which shows large acceleration and high frequency range up to 10kHz during the operation of separation devices where explosives are used. During the flight of a launch vehicle, pyro-shock is mainly generated at several events such as satellite separation, fairing separation and stage separation. In this paper, characteristics of pyroshock are introduced briefly, and PEEK washer shock absorber is applied for the reduction of pyroshock in the high frequency range. With some electronic devices, reduction characteristic of pyroshock using washer type shock absorber are studied. Random vibration tests are also performed for the verification of vibrational characteristics.

Development of Deployment Test Simulator for Satellite Solar Array (위성체 태양전지판 전개시험용 모사장치 개발)

  • 김홍배;문상무;우성현;오진호
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2001.05a
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    • pp.984-984
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    • 2001
  • 위성체의 태양전지판과 안테나와 같은 구조물은 발사시 체적을 최소화하기 위하여 설정궤도에 도달하기 전까지 접혀진 상태로 운반되며, 설정궤도에 도달 후 고유의 임무를 수행하기 위하여 안테나, 태양전지판 및 로보트 팔과 같은 이차 부착물의 전개 작업을 수행한다. 이러한 작업은 위성체 및 발사체의 고유임무를 수행하는데 매우 중요한 작업이며, 이 작업의 성공 유무가 우주비행체 임무의 성패를 좌우한다.

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Review of Propellant Vibration and Control of Liquid Rocket Fuselage Feeding System (액체로켓 기체공급계의 추진제 진동특성 및 제어기술 동향)

  • Cho, Nam-Kyung;Kho, Hyun-Seok;Han, Sang-Yeop;Cho, In-Hyun
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2010.05a
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    • pp.89-94
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    • 2010
  • Fuselage propellant feeding system should supply propellants to engine with required flow rate, temperature and pressure. Propellant vibration in engine and feeding line changes feeding characteristics, and frequently inhibits to satisfy the required feeding requirements. Sloshing and POGO vibration are known to be the major vibration phenomena. Concerning sloshing and POGO, vehicle control and structural dynamics aspects are extensively studied, whereas, its effect on propellant feeding performance is not clearly understood. This paper focuses on the deviation of required feeding performance due to propellant vibration. Overall characteristics of propellant vibration and its effect on propellant supply to engine are reviewed and control mechanism for suppressing vibration is introduced.

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Determination excitation spectrum for the sinusoidal vibration test of the small satellite launch vehicle (소형 위성 발사체의 정현파 진동 시험을 위한 가진 입력 결정)

  • Park, S.H.;Youn, S.H.;Seo, S.H.;Jeong, H.K.;Jang, Y.S.
    • Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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    • 2006.05a
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    • pp.193-196
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    • 2006
  • Vibration overtests have been common problems in aerospace industry. A test item can be overtested at its resonances when it is excited by the traditional spectrum enveloping peaks in the field acceleration spectrum. This paper introduces the method of modifying the excitation specification to alleviate the overtesting problem. A vibration analysis was performed to estimate interface forces and acceleration responses. A finite element model that was verified by an extensive modal test enabled us to shape the acceleration input accurately The produced notched input will be used in the sinusoidal vibration test of the small satellite launch vehicle.

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LAUNCH ENVIRONMENTAL TEST FOR KITSAT-3 FM (우리별 3호 비행모델에 대한 발사환경시험)

  • 이상현;장영순;배정석;이동우;정연황;성단근
    • Journal of Astronomy and Space Sciences
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    • v.16 no.1
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    • pp.79-88
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    • 1999
  • The satellite experiences the severe launch environment such as vibration, acceleration, shock, and acoustics induced by rocket. Therefore, the satellite should be designed and manufactured to endure such severe launch environments. In this paper, we describe the structure of the KITSAT-3 FM(Flight Model) and the processes and results of the launch environmental test to ensure the reliability during launch period.

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Structural Reliability Evaluation on Solder Joint of BGA and TSSOP Components under Random Vibration using Reliability and Life Prediction Tool of Sherlock (신뢰성 수명예측 도구 Sherlock을 활용한 랜덤진동에서의 BGA 및 TSSOP 솔더 접합부의 구조 신뢰성 평가)

  • Park, Tae-Yong;Park, Jong-Chan;Park, Hoon;Oh, Hyun-Ung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.12
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    • pp.1048-1058
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    • 2017
  • One of the failure mechanism of spaceborne electronics is a fatigue fracture on solder joint under launch random vibration. Thus, a necessity of early diagnosis through the fatigue life evaluation on solder joint arises to prevent such potential risk of failure. The conventional life prediction methods cannot assure the accuracy of life estimation results if the packaging type changes, and also requires much time and effort to construct the analysis model of highly integrated PCB with various packaging types. In this study, we performed life prediction of PCB based on a reliability and life prediction tool of sherlock as a new approach for evaluating the structural reliability on solder joint, and those prediction results were validated by fatigue tests. In addition, we also investigated an influence of solder height on the fatigue life of solder joint. These results indicated that the Sherlock is applicable tool for evaluating the structural reliability of spaceborne electronic.

Statistical Analysis of Initial Behavior of a Vertically-launched Missile from Surface Ship (수상함에서 발사된 수직 발사 유도탄 초기 거동의 통계적 해석)

  • Kim, Kyung-Tae
    • Transactions of the Korean Society for Noise and Vibration Engineering
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    • v.22 no.9
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    • pp.889-895
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    • 2012
  • A vertical launching system(VLS) is a system for holding and firing missiles on surface ships. When a missile is launched in VLS, relative motion between canister and missile and drag force induced by wind can cause initial unstability of a missile. Thus dynamic analysis of initial behavior of vertically launched missile should be performed to prevent collision with any structure of a ship. In this study, dynamic analyses of initial behavior of vertically launched missile are performed using Monte-Carlo simulation, which relys on random sampling and probabilistic distribution of variables. Each parameter related with dynamic behavior of a missile is modeled with probability variables and Recurdyn, a commercial software for multi body dynamic analysis, is used to perform Monte-Carlo simulation. As a result, initial behavior of a missile is evaluated with respect to various performance indexes in a probabilistic sense and sensitivity of the each parameters is calculated.