• Title/Summary/Keyword: Nanosatellite

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Vibration Analysis of a Nanosatellite for Microgravity Science Missions (마이크로중력 과학 임무 수행용 초소형 위성의 진동 해석)

  • Kim, Jin-Hyuk;Jang, Jung-Ik;Park, Seul-Hyun
    • Journal of the Korean Society of Manufacturing Process Engineers
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    • v.18 no.12
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    • pp.104-110
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    • 2019
  • A nanosatellite designed by the Korea Microgravity Science Laboratory (KMSL) is currently under development. The KMSL nanosatellite is designed to perform two different scientific missions in space. To successfully complete missions, a variety of tests must be conducted to verify the performance of the designed satellite before launch. As part of the qualification test campaign, the KMSL nanosatellite underwent high level vibrational tests (to comply with Falcon 9 qualification level) to demonstrate the integrity of the system. The purpose of this study is to demonstrate that the primary structure and all electronic and mechanical components can withstand the vibrations and the loads experienced during the launch period. To this end, the KMSL nanosatellite was exposed to static and dynamic loads and various types of vibrations that are inevitably produced during the space vehicle launch period. The vibration test results clearly demonstrated that all avionics and mechanical components can withstand the vibrations and the loads applied to the KMSL nanosatellite's body through a Pico-satellite Orbital Deployer (POD).

Case Studies and Lessons Learned from Launch Environmental Test for Nanosatellites (나노급 초소형위성 발사환경시험 사례 및 교훈)

  • Kim, Min-Ki;Kim, Hae-Dong;Choi, Won-Sub;Kim, Jin-Hyung;Kim, KiDuck;Kim, Ji-Seok;Cho, Dong-Hyun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.50 no.6
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    • pp.423-433
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    • 2022
  • This paper introduces the case studies of launch environmental test for cube nanosatellites and lessons learned of the design and integration from those. Generally, nanosatellites are launched and deployed in space while being contained in nanosatellite deployers, mechanical loads of launch are transferred through the deployer. This characteristic make nanosatellites under larger loads and higher possibilities of mechanical failure. This study represents guidelines of the design and the integration of the nanosatellites by showing the cases of launch environmental test of nanosatellite system. Moreover, it is suggested that the modern nanosatellite deployer with the capability of fixing the internal nanosatellite be preferable to conventional deployer by comparing the test results with those deployers.

DEVELOPMENT AND PERFORMANCE VALIDATION OF INTEGRATED ELECTRONIC UNIT FOR NANOSATELLITE (나노위성용 통합형 전장박스의 개발 및 성능검증)

  • Chang Jin-Soo;Kim Dong-Woon;Lee Byung-Hoon;Moon Byoung-Young;Chang Young-Keun
    • Bulletin of the Korean Space Science Society
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    • 2006.04a
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    • pp.133-136
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    • 2006
  • Unlike large satellites, small satellites, such as nanosatellite and microsatellite, provide a limited interior space for components mounting. In order to mitigate this issue, the compact Bus Electronic Unit (BEU) that integrates satellite electronic modules, combining most of bus subsystems and payloads electronic modules into one unit, has been developed for HAUSAT-2 nanosatellite. This paper addresses the design and environmental test result analyses of BEU.

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Results and Lessons Learned From Nanosatellite Space Environment Test (나노급 초소형위성 우주환경시험 : 결과 및 교훈)

  • Kim, Hae-Dong;Choi, Won-Sub;Kim, Min-Ki;Kim, Jin-Hyung;Kim, KiDuck;Kim, Ji-Seok;Cho, Dong-Hyun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.49 no.11
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    • pp.919-931
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    • 2021
  • In the recent New Space era, Nanosatellites are being used to carry out space business and practical missions by private space companies, government agencies and military reconnaissance organizations, away from satellite system education tools. In Korea, the development of nanosatellite satellites, which started with universities at the center, is gradually being attempted by various subjects, including private industries. However, it is not easy to find relevant information to share the experience and prepare for the space environment test, test results, and the various problems that may arise in the process, which can increase the chances of mission success for nanosatellites. In this paper, we expect that the subjects who want to develop the nanosatellite(SNIPE) will be used as useful references for reducing trial and error and increasing the possibility of mission success by organizing the 6U-class space environment test, test process, test results and problems.

Development of Drag Augmentation Device for Post Mission Disposal of Nanosatellite (초소형위성의 폐기 기동을 위한 항력 증대 장치 개발)

  • Kim, Ji-Seok;Kim, Hae-Dong
    • Journal of Space Technology and Applications
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    • v.2 no.1
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    • pp.1-12
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    • 2022
  • In this paper, we described the development of a drag augmentation device for nanosatellite. Recently, space industry has entered the New Space era, and barriers to entry into Low Earth Orbit (LEO) for artificial objects such as small rockets and nanosatellite mega constellations have been significantly lowered. As a result, the number of space debris is increasing exponentially, and it is approaching as a major threat to satellite currently in operation as well as satellites to be launched in near future. To prevent this, international organizations like Inter-Agency Space Debris Coordination Committee (IADC) have been proposed space debris mitigation guidelines. The Korea Aerospace Research Institute (KARI) conducted KARI Rendezvous & Docking demonstration SATellite (KARDSAT) project, the first nanosatellites for rendezvous and docking technology demonstration in Korea, and we also developed drag augmentation device for KARDSAT Target nanosatellite that complied with the international guideline of post-mission disposal.

A Development of Docking Phase Analysis Tool for Nanosatellite

  • Jeong, Miri;Cho, Dong-Hyun;Kim, Hae-Dong
    • Journal of Astronomy and Space Sciences
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    • v.37 no.3
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    • pp.187-197
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    • 2020
  • In order to avoid the high cost and high risk of demonstration mission of rendezvous-docking technology, missions using nanosatellites have recently been increasing. However, there are few successful mission cases due to many limitations of nanosatellites like small size, power limitation, and limited performances of sensor, thruster, and controller. To improve the probability of rendezvous-docking mission success using nanosatellite, a rendezvous-docking phase analysis tool for nanosatellites is developed. The tool serves to analyze the relative position and attitude control of the chaser satellite at the docking phase. In this tool, the Model Predictive Controller (MPC) is implemented as a controller, and Extended Kalman Filter (EKF) is adopted as a filter for noise filtering. To verify the performance and effectiveness of the developed tool for nanosatellites, simulation study was conducted. Consequently, we confirmed that this tool can be used for the analysis of relative position and attitude control for nanosatellites in the rendezvous-docking phase.

Introduction of Military Nanosatellite Communication System Using Anti-Jamming and Low Probability of Detection (LPD) Waveforms (항재밍/저피탐 웨이브폼이 적용된 군 초소형 위성 통신체계 소개)

  • Ju Hyung Lee;Hae-Won Park;Kil Soo Jeong
    • Journal of Space Technology and Applications
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    • v.3 no.2
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    • pp.144-153
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    • 2023
  • The existing military satellite communication system was based on geostationary satellites equipped with special communication payloads against enemy's jamming and signal reception. With the advent of new weapon systems such as unmanned systems, the need for low-orbit satellite-based communication system is increasing. This paper introduces various waveform technologies suitable for cube satellite-based communication system and the operational concept of a future military nanosatellite communication system.

A Case Study of the Implementation of Deployment Switch for Nanosatellites (나노위성 전개스위치 구현 사례 및 고찰)

  • Min Ki Kim
    • Journal of Space Technology and Applications
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    • v.3 no.1
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    • pp.72-85
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    • 2023
  • Most Nanosatellites are launched in nanosatellite deployers. Nanosatellites in the deployer are turned off during launch, and they start boot sequence after deploying at their mission orbit. For this reason, nanosatellites must have deployment switch. Most of the nanosatellite deployment switch has two part, first is electric switch to boot the satellite system and second is mechanical assembly to push the switch. In most cases, electric switches are installed in the satellite main body, and the switch operations are translated via the mechanical assembly. These implementations are mechanically complicated and hard to guarantee the appropriate operation without the problems due to friction between pusher and satellite structure. This paper proposes the another implementation method of deployment switch for nanosatellites by installing the electric switch outside the main body without any kind of mechanical parts.

Launch Environment Test for Scale magNetospheric and Ionospheric Plasma Experiment (SNIPE) Engineering Qualification Model (초소형위성 SNIPE(Scale Magnetospheric and Ionospheric Plasma Experiment) 시제인증모델의 발사환경시험 및 분석)

  • Kim, Min-Ki;Kim, Hae-Dong;Choi, Won-Sub;Kim, Jin-Hyung;Kim, KiDuck;Kim, Ji-Seok;Cho, Dong-Hyun
    • Journal of Space Technology and Applications
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    • v.1 no.3
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    • pp.319-336
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    • 2021
  • This paper discusses the results of launch environment tests for the engineering qualification model (EQM) of nanosatellite Scale magNetospheric and Ionospheric Plasma Experiment (SNIPE) for scientific missions and lessons learned for the design of nanosatellites. SNIPE is a group of four formation-flying 6U nanosatellites with a range of payloads for missions including space weather measurement. We developed the EQM to verify the preliminary design prior to fabricating the flight model. Launch environment test of EQM was conducted for the first time in 2019, and all failures were corrected and verified at the second test conducted in 2021. A notable point of the two tests is that the nanosatellite deployer used in the first test is different from that of the second test. The second deployer has the capability to fix the internal satellite whereas the first deployer just contains and deploys the satellite. Thus actual mechanical loads the satellite receives is reduced for the second test compared to the first test. This work compares the mechanical responses of two tests and proposes general guidelines for structural design of nanosatellites.

Development and Performance Validation of Integrated Bus Electronic Unit for Small Satellite (소형위성용 통합형 전장박스의 개발 및 성능검증)

  • Chang, Jin-Soo;Kim, Dong-Woon;Kang, Suk-Jin;Lee, Byung-Hoon;Moon, Byoung-Young;Chang, Young-Keun
    • Journal of the Korean Society for Aeronautical & Space Sciences
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    • v.35 no.4
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    • pp.353-362
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    • 2007
  • Unlike large satellites, small satellites, such as nanosatellite and microsatellite, can provide a limited interior space for components mounting. In order to mitigate this issue, the compact Bus Electronic Unit(BEU) that integrates satellite electronic modules, combining most of bus subsystems and payload electronic modules into one unit, has been developed for HAUSAT-2 nanosatellite. This paper addresses the design and environmental test result analyses of BEU. The vibration and thermal vacuum tests were conducted at qualification level for the verification of design margin of newly developed BEU. The performance of individual electronic subsystem modules has been verified through performance tests before and after the qualification tests. It was confirmed that the natural frequency of BEU satisfies the design stiffness requirement without structural damage in the vibration test. Thermal analysis results were also almost consistent with test results through modified thermal analysis modeling.