• Title/Summary/Keyword: Satellite Launcher

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RF Compatibility Test Results of COMS satellite with Launch Vehicle (천리안위성의 발사체와의 전자파 적합성 시험결과 분석)

  • CHOI, Jae-Dong
    • Proceedings of the KIPE Conference
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    • 2010.11a
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    • pp.215-217
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    • 2010
  • This paper describes the test results of radiated compatibility with Ariane 5 launcher performed on the COMS Satellite test facility. Firstly, the Radiated Emission test results are analyzed in compliance with the Radiated Susceptibility requirement specification of Ariane 5 launcher. The satellite nominal operation is monitored during injection a radiated electric field corresponding to the launcher emissions levels in critical frequency ranges. And also, E-field are measured through a probe located at external units level in order to assess the EMC safety margin in Radiated mode.

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The Analysis of Mechanical Environment of Small Satellite Launcher (소형위성 발사체의 기계적 환경 분석)

  • Lee, Sung-Sae;Park, Jong-Oh;Rhee, Seung-Wu
    • Aerospace Engineering and Technology
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    • v.9 no.2
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    • pp.123-128
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    • 2010
  • Science and Technology SATellite-3 (STSAT-3) is science purpose satellite which weighs below 170kg. This is classified as small satellite or micro satellite more specifically. The launch vehicles (launchers) for small satellite has their own requirements for environmental interface. Since the small satellites are usually launched with cluster or multiple payloads, the selection option for appropriate launcher is limited. Therefore, the satellite should be designed with the consideration of environmental requirements of these launchers. In this paper, the environmental requirement of most candidated launchers for small satellite is summarized and give satellite environmental requirement to accommodate all launchers requirements.

Very Small Satellite Program for Expending the Space Technology Base: CanSat Competition (우주기술 저변확대를 위한 초소형위성 프로그램: 캔위성 경연대회)

  • Won, Su-Hee;Jun, Hyoung-Yoll;Kim, Sung-Hoon;Lee, Sang-Ryool
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.40 no.7
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    • pp.636-645
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    • 2012
  • This paper presented the CanSat competition as one of very small satellite programs for expending the space technology base. The CanSat was compared and characterized with a real satellite and the foreign CanSat competition cases and domestic CanSat development trends were summarized. On the basis of the above information, the organizational structure and function were suggested for domestic CanSat competition and the required technologies, such as satellite, launcher and ground station were described. And also, the prior plan for competition, including mission, education and schedule were suggested.

Analysis of Flight Performance Reserve for Upper Stage of Satellite Launch Vehicles (위성발사체 상단의 비행성능여유 분석)

  • Song, Eun-Jung;Choi, Jiyoung;Cho, Sang-bum;Sun, Byung-Chan
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.45 no.5
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    • pp.386-392
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    • 2017
  • This paper considers the analysis of the flight performance reserve, which is required propellant to compensate various launch vehicle performance deviations, to inject the payload of a 3-staged launch vehicle to a circular sun synchronous orbit at a height of 700 km. The various error sources, which affect the orbit injection accuracy, and their uncertainty are defined first. Then the sensitivity analysis, which has the advantage that each error source effect can be investigated independently, is performed for the extreme ${\pm}3{\sigma}$ conditions of the launch vehicle performance errors. Monte carlo simulations are also conducted to compute the propellant reserve, which can consider the combined effects of each error source. Finally the obtained flight performance reserves by the two approaches are compared and it is confirmed that they show similar results.

Staging and Mission Design of a Two-Staged Small Launch Vehicle Based on the Liquid Rocket Engine Technology (액체로켓 기반 2단형 소형발사체의 스테이징 및 임무설계)

  • Seo, Daeban;Lee, Junseong;Lee, Keejoo;Park, Jaesung
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.50 no.4
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    • pp.277-285
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    • 2022
  • There has been significant increase in demand of launch opportunities from the small satellite sector that represents the new space era. Providing smallsat-dedicated launch service at an affordable price is a new business model many startup companies have pursued, which requires innovative solutions for cost reduction in combination of low cost components, volume production and optimized manufacturing. We set out a preceding study at KARI to develop a suite of critical and cost-cutting technologies in preparation for a two-staged small launch vehicle development, based on the liquid rocket engine technologies developed from the Nuri program in accordance with the 3rd master plan for national space development. In this work, we introduce the concept of a two-staged small launch vehicle that aims to be innovative and cost competitive for small satellites, and describe mission design results including staging as well as overall vehicle configuration of the launch vehicle.

Mechanism Design of Cube Satellite for Multi-deployable Structures and Autonomous System Operation after Launcher Separation (복수구조 전개 및 발사체 분리직후 시스템 자동운용을 위한 큐브위성의 메커니즘 설계)

  • Lee, Myoung-Jae;Jung, Hyun-Mo;Oh, Hyun-Ung
    • Journal of Aerospace System Engineering
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    • v.7 no.3
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    • pp.20-25
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    • 2013
  • In case of cube satellite, it is difficult to realize the same performance as commercial satellite due to its highly restricted unit accommodation space. To maximize the performance of the cube satellite, design concept considering the multi-function of satellite is required. In this paper, mechanism design of cube satellite which is applicable for the holding and release of multi-deployable structures has been proposed and investigated. In addition, a switch mechanism design for the autonomous system operation just after the cube satellite separation from P-POD has also been proposed. The effectiveness of the mechanism design for holding and release of multi-deployable structures has been demonstrated by EM test of the holding and release mechanism.