• Title/Summary/Keyword: 나노 위성

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Air-Launching Rocket System Design for Nanosat using DMU (DMU를 이용한 극소형 위성 공중발사 로켓 시스템 설계)

  • Lee Y.J.;Kim J.H.;Choi Y.C.;Lee J.W.;Byun Y.H.;Lee S.T.
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2005.11a
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    • pp.293-298
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    • 2005
  • Air-Launching is an effective method that can launch the 'Nanosat' with low launching cost. In this study, system and subsystem design of the air launching rocket for nanosats which perform a simple mission, have been performed. Foe this purpose, the WBS of the Air-launching Rocket System, and the subsystem schematics have been defined first. Based on these results, detailed configuration and DMU have been developed.

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Low-Cost Small Satellite Research and Development as an Education Tool (교육용 도구로서의 저가 소형위성 연구 및 개발)

  • 문병영;장영근;이병훈
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.34 no.10
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    • pp.80-91
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    • 2006
  • A method of multidisciplinary education has been implemented for satellite design, based on HAUSAT-1 and 2 ultra-small satellite development projects, in order to provide practical knowledge and experience to students studying satellite engineering. HAUSAT-1 was the nation's first 1kg-class ultra-small satellite. HAUSAT-2 nano-satellite is currently under a Proto-Flight Model development. These design projects make it possible to achieve the goal of science and technical research, which is representative of a university function, and the goal of molding professionals through providing an integrated function of system design education. An integrated system design, like satellite system, provides all participating students with an opportunity to directly/indirectly experience the entire system development process and encourage growth of multidisciplinary system education that has lately become an important issue.

MEMS Power Device (초소형 동력 장치)

  • Kwon, Se-Jin
    • Journal of the Korean Society of Propulsion Engineers
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    • v.12 no.1
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    • pp.64-70
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    • 2008
  • Thanks to the breakthroughs in micro fabrication technology, numerous concepts of micro aerospace systems including micro aerial vehicle, nano satellite and micro robot have been proposed. In order to activate these mobile micro systems, high density power in a small scale power source is required. However, we still do not have micro power source that has energy density that can support these systems. In the present article, status of micro power sources are described and alternatives that have been derived from the past experience are proposed.

Analysis of Colloid Thrusters for Nano-satellite Propulsion (나노인공위성 추진용 콜로이드 추력기 해석)

  • Park, Kun-Joong;Kim, Ho-Young;Song, Seung-Jin
    • Proceedings of the Korean Society of Propulsion Engineers Conference
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    • 2007.04a
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    • pp.175-178
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    • 2007
  • The mode transition from cone-jet to dripping in colloid thruster operation has been analytically investigated. The transition has been predicted by the dynamic behavior of a liquid drop at the tip of the cone-jet. Conservation laws are applied to determine the upward motion of the drop, and an instability model of electrified jets is used to determine the jet breakup. Finally, for the first time, the analysis enables prediction of the transition in terms of the Weber number and electric Bond number. The predictions are in good agreement with experimental data.

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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.

Development of SEDT(System Engineering Design Tool) for Small Satellite Conceptual Design (소형위성 개념설계를 위한 SEDT의 개발)

  • Hwang, Ki-Lyong;Lee, Bo-Ra;Kim, Su-Jeoung;Ko, Sung-Hwan;Kwon, Soon-Kyung;Lee, Mi-Hyun;Chang, Young-Keun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.1
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    • pp.93-103
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    • 2005
  • SEDT(System Engineering Design Tool) has been developed for small satellite conceptual design with an aim to verifying the nanosatellite HAUSAT-2 design. The program can calculate the mass and power of whole satellite system having specific mission and estimate the system cost based on mission and user requirements. It is containing various analysis data of more than 200 small satellites. The database will provide the trend analysis results of the small satellites which will become important design factors. This tool has also been verified by applying more than 10 small satellite data through case studies.

A Study on Performance and Sensitivity Improvement of an Off-axis TMA Telescope Optical System by Changing the Aperture-stop Position (조리개 위치 변경을 통한 비축 삼반사 망원경 광학계의 성능 및 민감도 개선 연구)

  • Lee, Han-Yul;Jun, Won-Kyoun;Lee, Sang-min;Kim, Ki-hwan;Seo, Hyun-Ju;Park, Seung-Han;Jung, Mee-Suk
    • Korean Journal of Optics and Photonics
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    • v.32 no.1
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    • pp.9-14
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    • 2021
  • In this paper we have studied an optical system according to the aperture position of an off-axis TMA telescope for satellites. An off-axis TMA telescope should have high resolution and wide field of view (FOV). In addition, the optical system should have a wide tolerance range, because it is structurally located off-axis and is difficult to assemble. However, there are differences in performance and sensitivity according to the aperture-stop position, so it is important to select a suitable aperture-stop position. Therefore, in this paper we have designed each off-axis TMA telescope according to the aperture-stop position, and have analyzed the performance and sensitivity to suggest a suitable aperture-stop position.

Design of Clock Synchronization Scheme for Pseudolite (의사위성 시각동기 기법 설계)

  • Lee, Ju Hyun;Hwang, Soyoung;Yu, Dong-Hui;Lee, Sang Jeong
    • Journal of the Korea Institute of Information and Communication Engineering
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    • v.17 no.6
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    • pp.1312-1317
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    • 2013
  • Pseudolite is a contraction of the term "pseudo-satellite", used to refer to something that is not a satellite which performs a function commonly in the domain of satellites. Pseudolite are most often small transceivers that are used to create a local, ground-based GPS alternative. Pseudo-range measurement of pseudolite has around 300m range error, when time synchronization error of $1{\mu}sec$ occurs. Therefore the time synchronization methods play an important part in navigation augmentation using pseudolite. This paper proposes three clock synchronization methods that are installation method of pseudolite station, method using KRISS-UTC and method using PRN code phase difference for pseudolite. The simulation platform structure is presented for evaluating proposed clock synchronization performance.

A Study on HAUSAT-2 Momentum Wheel Start-up Method (초소형위성 HAUSAT-2 모멘텀 휠 Start-up 방안 연구)

  • Lee, Byung-Hoon;Kim, Soo-Jung;Chang, Young-Keun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.33 no.9
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    • pp.73-80
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    • 2005
  • This paper addresses a newly proposed start-up method of the HAUSAT-2 momentum wheel. The HAUSAT-2 is a 25kg class nanosatellite which is stabilized to earth pointing by 3-axis active control method. A momentum wheel performs two functions. It provides a pitch-axis momentum bias while measuring satellite pitch and roll attitude. Pitch control is accomplished in the conventional way by driving a momentum wheel in response to pitch attitude errors. Precession control and nutation damping are provided by driving the pitch axis magnetic torquer. A momentum wheel is nominally spinning at a particular rate and changes speed. This simulation study investigates the feasibility and performance of a proposed strategy for starting-up the wheel. A proposed strategy to start-up the wheel shows that a pitch momentum wheel can be successfully started-up to its nominal speed from rest and be stabilized to nadir pointing.