• Journal of Space Technology and Applications
• /
• v.1 no.1
• /
• pp.76-84
• /
• 2021

Because solar panels of normal satellites are faced to the sun, the power generation by the Earth Albedo is almost neglected in satellite's power analysis. However, many cubesats don't have deployable solar panels and in this case the Earth Albedo is not negligible because solar panels are in six sides facing different directions. In this paper, we calculated satellite's power generation by the Earth Albedo. We divided the Earth's surface into grids based on polar coordinate system. We modeled power generation in each solar cell by reflection on these grids. We simulated 1 U cubesat which flies in sun synchronous orbit and 500 km altitude so that we calculated satellite's power generation by the Earth Albedo.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.49 no.12
• /
• pp.1027-1035
• /
• 2021

We presents a design of 3U cubesat MIMAN (Monochrome imaging for monitoring aerosol by nano-satellite) for aerosol monitoring mission with high spatial resolution. The main objective of MIMAN mission is to take images of aerosols around Korea and to provide auxiliary data for GK 2B cloud masking. For this mission, we derived mission requirements and constraints for the MIMAN mission. We designed the mission architecture and concept of operations. To reduce risk factors in space operation, we considered the safety of the communication. In every operation modes, UHF communication is available so that the cubesat can operate based on the ground commands. So, we can handle every problem at the ground station during mission operations. Based on the mission and concept of operations, we confirmed that the system design satisfied the system requirements. We designed the system interface considering data flow of each hardware, and evaluated the safety of the system with system budget analysis.

• International Journal of Aeronautical and Space Sciences
• /
• v.17 no.4
• /
• pp.579-592
• /
• 2016

CNUSAIL-1, to be launched into low-earth orbit, is a cubesat-class satellite equipped with a $2m{\times}2m$ solar sail. One of CNUSAIL's missions is to deploy its solar sail system, thereby deorbiting the satellite, at the end of the satellite's life. This paper presents the design results of the attitude control system for CNUSAIL-1, which maintains the normal vector of the sail by a 3-axis active attitude stabilization approach. The normal vector can be aligned in two orientations: i) along the anti-nadir direction, which minimizes the aerodynamic drag during the nadir-pointing mode, or ii) along the satellite velocity vector, which maximizes the drag during the deorbiting mode. The attitude control system also includes a B-dot controller for detumbling and an eigen-axis maneuver algorithm. The actuators for the attitude control are magnetic torquers and reaction wheels. The feasibility and performance of the design are verified in high-fidelity nonlinear simulations.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.168.1-168.1
• /
• 2012

TRIO-CINEMA(TRiplet Ionospheric Observatory-Cubesat for Ion, Neutral, Electron, MAgnetic fields)는 중량 3 kg의 초소형 인공위성 3기로 구성되며, 그 임무는 근 지구 플라즈마 입자 검출 및 자기장계측이다. 3기 중 1기는 UC Berkeley에서, 2기는 경희대학교에서 제작 및 운용된다. 경희대학교 천문대에 IGSS(Integrated Ground Support Software), TNC(Terminal Node Controller), 송신기, 안테나제어기와 안테나로 구성된 지상국을 구축하였으며 위성에 명령을 전달하는 기능을 수행한다. 위성으로부터 데이터 수신은 한국천문연구원의 안테나와 수신기를 이용할 예정이다. 2기의 위성을 하나의 지상국에서 운용하기 위해서는 각 위성에 대한 송신 주파수 변경 및 패스스케줄(pass schedule) 조정이 필요하며, 이를 수행할 수 있는 RF Chain을 구축하였다. 본 연구는 RF Chain 구축과 검증과정을 기술하였으며, 시스템의 검증으로 원거리 필드 테스트, 데이터 통신 테스트, 링크 여유 분석 등을 수행하였다.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.230.2-230.2
• /
• 2012

경희대학교에서 제작중인 초소형 위성 TRIO-CINEMA (TRiplet Ionosphere Observatory-Cubesat for Ion, Neutral, Electron and MAgnetic fields)에 탑재될 입자검출기 STEIN (SupraThermal Electron, Ion, Neutral)은 정전 편향기를 이용하여 4~300keV의 대전입자 혹은 중성입자들을 분리하여 검출하도록 이루어져있다. CINEMA 운용 궤도에서는 STEIN 정전 편향기를 통하지 않고 검출기 내부로 들어오는 입자들로부터 생기는 배경계수가 포함되어 검출될 것으로 예상되므로 STEIN 검출기의 결과값의 신뢰성을 높이기 위해 배경계수값을 예측할 필요성이 있다. 본 연구에서는 SPENVIS (The Space Environment Information System)를 통해 CINEMA 운용 궤도에 존재하는 입자들의 유량을 계산하였고 GEANT4 (GEometry ANd Tracking)를 통해 CINEMA 운용 궤도상의 STEIN의 외부 환경을 모사하여 배경계수값을 예측하였다. 향후 STEIN의 측정값에 배경계수값을 차감한다면 측정값의 신뢰성이 높아질 것으로 기대된다.

• Journal of Aerospace System Engineering
• /
• v.11 no.5
• /
• pp.65-75
• /
• 2017

This study proposes development of 3U CubeSat standard platform whose function and performance are verified via KAUSAT-5 development. 3U CubeSat platform specification was selected for the design of 3U Cubesat standard platform by examining existing CubeSat and state-of-art technology, and consequently a universally usable 3U CubeSat platform was designed. Standard platform was manufactured in 1.5U size and developed with a modular concept to be able to add and expand payloads and ADCS actuators for meeting the user's needs. In addition, in case of the power system, the solar panel, the battery, and the deployment mechanism are designed to be configured by the user. In the mechanical system design of a standard platform, subsystem and micro equipment functions/performance could be integrated and miniaturized on micro-sized PCBs and maximized electrical capability to accommodate multiple payloads. In the development of the 3U CubeSat, the satellite platform adopts the developed standard platform, which can reduce the cost and schedule for the whole satellite development by reducing the additional function verification.

• Journal of the Korean Society for Aeronautical & Space Sciences
• /
• v.50 no.2
• /
• pp.137-146
• /
• 2022

AIS(Automatic Identification System) is a device that automatically transmits and receives ship information and is mounted on the ship. AIS information of ships near the coast can be received on the ground, but when going out to sea more than 50 nautical miles, communication with the ground is cut off. To solve this problem, ship information can be transmitted to the ground through an AIS satellite equipped with an AIS receiver. There is no case of AIS satellite development in Korea yet, and many domestic shipping companies are using overseas AIS services. PNUSAT-1 is a 1U+ CubeSat, developed by Pusan National University, and it is equipped with an AIS receiver for monitoring of ships and transmitting ship information to the ground. Since the mission data of PNUSAT-1 is in text format, the data size is not large. In consideration of this, communication equipment, low-precision sensors, and actuators were selected. In this paper, system preliminary design of PNUSAT-1 was performed, requirements for mission performance, operation scenario and mode design, hardware and software selection, and preliminary design of each subsystem were performed.

• International Journal of Aeronautical and Space Sciences
• /
• v.13 no.4
• /
• pp.484-490
• /
• 2012

This paper is devoted to investigate the feasibility of using a medium power ground-based laser to produce a torque on LEO satellites of various shapes. The laser intensity delivered to a satellite is calculated using a simple model of laser propagation in which a standard atmospheric condition and linear atmospheric interaction mechanism is assumed. The laser force is formulated using a geocentric equatorial system in which the Earth is an oblate spheroid. The torque is formulated for a cylindrical satellite, spherical satellites and for satellites of complex shape. The torque algorithm is implemented for some sun synchronous low Earth orbit cubesats. Based on satellites perigee height, the results demonstrate that laser torque affecting on a cubesat has a maximum value in the order of $10^{-9}$ which is comparable with that of solar radiation. However, it has a minimum value in the order of $10^{-10}$ which is comparable with that of gravity gradient. Moreover, the results clarify the dependency of the laser torque on the orbital eccentricity. As the orbit becomes more circular it will experience less torque. So, we can conclude that the ground based laser torque has a significant contribution on the low Earth orbit cubesats. It can be adjusted to obtain the required control torque and it can be used as an active attitude control system for cubesats.

• International Journal of Aeronautical and Space Sciences
• /
• v.14 no.2
• /
• pp.193-199
• /
• 2013

This work investigates the orbital perturbations of the cubesats that lie on LEO due to Earth albedo. The motivation for this paper originated in the investigation of the orbital perturbations for closed- Earth pico-satellites due to the sunlight reflected by the Earth (the albedo). Having assumed that the Sun lies on the equator, the albedo irradiance is calculated using a numerical model in which irradiance depends on the geographical latitude, longitude and altitude of the satellite. However, in the present work the longitude dependency is disregarded. Albedo force and acceleration components are formulated using a detailed model in a geocentric equatorial system in which the Earth is an oblate spheroid. Lagrange planetary equations in its Gaussian form are used to analyze the orbital changes when $e{\neq}0$ and $i{\neq}0$. Based on the Earth's reflectivity data measured by NASA Total Ozone Mapping Spectrometer (TOMS project), the orbital perturbations are calculated for some cubesats. The outcome of the numerical test shows that the albedo force has a significant contribution on the orbital perturbations of the pico-satellite which can affect the satellite life time.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.1
• /
• pp.67.2-67.2
• /
• 2012

경희대학교와 UC Berkeley, Imperial College London은 우주관측을 위한 초소형 인공위성인 TRIO-CINEMA(TRIO-CINEMA) Project를 수행하고 있다. TRIO-CINEMA는 총 3기의 인공위성으로 경희대학교에서 2기의 위성을, UC Berkeley에서 1기의 위성을, Imperial College에서 3개의 자력계를 제작하고 있다. CINEMA는 Cubesat의 3U 규격으로 크기는 $100mm{\times}100mm{\times}340.5mm$이고 무게는 약 3 kg, 소비전력은 약 3 W이며, 지구 주변의 ENA측정을 위한 주 탑재체인 STEIN(SupraThermal Electrons, Ions, and Neutrals)과 자기장 측정을 위한 부 탑재체인 MAGIC(MAGnetometer from Imperial College)이 탑재되어 약 1년간 800 km 태양동주기 궤도에서 임무를 수행할 예정이다. 위성의 발사는 별도의 POD(Picosatellite Orbital Deployer)라는 Adaptor를 사용해 발사체에 탑재되는데, 발사환경에서 위성이 받을 모든 현상에 관하여 NX Nastran을 사용해 계산을 진행하였다. 계산 결과의 검증을 위해 위성의 Structure Model을 가지고 Random Vibration test를 수행해 위성의 고유 진동수를 측정하였다. 또한 위성이 궤도에서 운용 중 다양하게 받게 되는 열원에 따른 위성의 각 부분의 온도변화를 NX TMG program을 사용하여 계산하였다. 계산 결과의 검증을 위해 3월 Thermal Cycle test 및 Thermal Balance test를 수행할 예정이다. UC Berkeley에서 제작한 위성 1기는 제작완료 후 발사를 위해 발사장으로 배송을 완료하였고, 경희대학교에서 제작 중인 CINEMA 위성 2기는 2012년 후반기 러시아에서 Dnepr 로켓을 사용해 발사 예정이다.