研究者詳細 - 趙　孟佑

論文 - 趙　孟佑

分割表示643 件中 141 - 160 件目／全件表示 >>

Development of UiTMSAT-1: An approach to lean satellite concept 査読有り国際誌

Mohamad Rahim, S.N., Mustafa, S.N.K., Azami, M.H., Zaki, S.B.M., Enche A Rahim, S.A., Jusoh, M.H. Cho, M., BIRDS-2 Members

ASM Science Journal 12 ( Special Issue 2 ) 62 - 71 2019年08月

ESD Experiment Results on Ground Using Experiment Model of HORYU-IV 査読有り国際誌

Hiroshi Fukuda, Tatsuo Shimizu, Kazuhiro Toyoda, Mengu Cho

Journal of Spacecraft and Rockets Published Online:5 Aug 2019https://doi.org/10.2514/1.A34497 2019年08月

CubeSat bus interface with Complex Programmable Logic Device 査読有り国際誌

Tumenjargal T., Kim S., Masui H., Cho M.

Acta Astronautica 160 331 - 342 2019年07月

担当区分：最終著者記述言語：英語掲載種別：研究論文（学術雑誌）

© 2019 IAA A standardized interface for different CubeSat missions is one of the keys to reducing costs and delivery time. A backplane interface approach, proposed by the University of Würzburg in Germany as UWE-3, was implemented in three CubeSat projects at the Kyushu Institute of Technology (Kyutech) to shorten the development and assembly times. The backplane approach also helped to reduce the risk of workmanship errors associated with the harness. However, changes to the proposed standard interface board were necessary in every CubeSat project, to comply with the mission requirements. To obtain more flexibility, especially for data connections, this work introduces a novel idea of a software-configurable bus interface with a backplane board. A Complex Programmable Logic Device (CPLD) was used instead of hardware routing so that we can reconfigure the bus interface by reprogramming the CPLD. The concept was validated by a functional test with a breadboard module. A radiation test verified that the selected CPLD has enough strength to survive total ionization doses of more than 2 years in low Earth orbit. A new backplane board with CPLD has been integrated into the engineering model of the fourth CubeSat project at Kyutech, the BIRDS-3 project, and system level verification has been conducted.

DOI： 10.1016/j.actaastro.2019.04.047

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85065082066&origin=inward

A New Split Pitch Square Shape Metamaterial Absorber for X band Application 査読有り

Hoque A., Islam M.T., Azim R., Singh M.J., Mat K., Cho M.

International Conference on Space Science and Communication, IconSpace 2019-July 85 - 90 2019年07月

記述言語：英語掲載種別：研究論文（学術雑誌）

© 2019 IEEE. Metamaterial electromagnetic wave absorbers may provide perfect absorption over a significant range of electromagnetic spectrum. Microwave absorber for X-band application mostly unable to maintain high bandwidth with good absorption and require RF shielding in few applications. In this paper, design, simulation and measurements of a X band (8-12 GHz) metamaterial broadband absorber presented. The proposed absorber developed by following transmission line principle making pitch on each square arm with the split in edge and middle of the structure. The Square arm will steer electromagnetic (EM) resonance to acquire significant absorption (90%) and Double-Negative (DNG) metamaterial property to ensure perfect shielding for microwave signals. Proposed metamaterial absorber with DNG characteristics has potential application sector like microwave shielding, satellite remote sensing, dielectric property measurement of material etc.

DOI： 10.1109/IconSpace.2019.8905969

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85078036736&origin=inward

Analysis of lifetime extension capabilities for CubeSats equipped with a low-thrust propulsion system for Moon missions 査読有り国際誌

Cordova Alarcon J., Orger N., Kim S., Cho M.

Acta Astronautica 160 558 - 571 2019年07月

担当区分：責任著者記述言語：英語掲載種別：研究論文（学術雑誌）

In this paper, we analyze the mission lifetime extension capability for a CubeSat smaller than 3U in a circular lunar orbit at a 100-km altitude, assuming the utilization of a state-of-the-art low-thrust electric propulsion system such as pulsed plasma thrusters with an impulse bit (Ibit)and velocity change (ΔV)below 60 μNs and 120 m/s, respectively. Because of the non-spherical gravity field of the Moon and its strong influence on low-altitude lunar orbits, a long orbital lifetime is achievable only within a set of stable orbits which mainly depends on initial inclination and right ascension of the ascending node (RAAN); moreover, as a piggyback on a main mission, the deployment of CubeSats in those stable orbits is not guaranteed. For this reason, we propose an orbit correction strategy whose performance is constrained to the initial orbital parameters of the CubeSat (i.e., inclination and RAAN), its solar power generation capacity, its attitude control strategy, and its propulsion subsystem features, such as the thruster Ibit and budgeted ΔV. By analyzing the required time to perform the orbit correction maneuvers to extend the orbital lifetime and the minimum altitude achieved throughout the mission lifetime of the spacecraft, we demonstrated that a one-year mission can be achieved within initial orbital inclination values greater than 65°. For unstable orbits bounded by initial orbital inclination values smaller than 65°, the orbit lifetime can also be extended from a few days to up to one year. Better performance with our proposed orbit correction strategy can be achieved by using an electric propulsion system featuring Ibit and ΔV values greater than 40 μNs and 80 m/s, respectively. Our results show the feasibility of performing any orbit correction maneuver for the enhancement of the mission lifetime of a CubeSat, expanding the performance capabilities of CubeSats to any mission in a lunar orbit by reducing the limitation of deploying them in unstable orbits.

DOI： 10.1016/j.actaastro.2018.11.040

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85062266669&origin=inward

Demonstration of lean satellite (1U CubeSat) testing using PeTT vacuum chamber 査読有り

Bonsu B., Masui H., Cho M.

Proceedings of 9th International Conference on Recent Advances in Space Technologies, RAST 2019 959 - 966 2019年06月

担当区分：責任著者記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

© 2019 IEEE. There has been a high demand for low-cost thermal vacuum testing facility for Lean satellite (1U CubeSat) program in emerging space economies. Most often, CubeSat testing is performed in a complex and expensive thermal vacuum chamber equipped with for example shroud filled liquid nitrogen (boiling point is-195.7oC) for simulating the cold temperature environment as close to the cold heat sink of outer space in a simulated low pressure (>10-3 Pa) chamber environment. This paper introduces PeTT vacuum chamber as a low cost and easy access testing facility suitable for simulating cold temperature plateaus for performing a functional test of the internal subsystems of Lean satellite (1U CubeSat) functional test. Under ISO 19683: 'Design Qualification and Acceptance Test of Spacecraft and Units', the test requirement for cold temperature plateau is equal to-or more than-15oC. The PeTT vacuum chamber has been developed to achieve ISO 19683 test requirements. The PeTT vacuum chamber consists of a Peltier cooling device integrated inside a vacuum chamber. The Peltier cooling device consists of 4multi-stage Peltier elements sandwiched in-between a copper surface plate and water cooler has a mass of 3.4kg and size 152mm length × 127mm width × 40 mm height. The Peltier cooling device is targeted for performing 1U Cubesat functional test by conduction heat transfer. The Peltier cooling device has a total maximum exchange heat capability of 400W which runs by water cooling system and varying DC power supply. The vacuum chamber has an inner diameter of 55cm equipped with a rotary pump and diffusion pump to achieve a low pressure around 10-4 Pa. The main goal of this paper is to provide low cost and easy access testing technique for space activities in emerging space economies especially universities space research and development laboratories, to build their capacity in the installation and operation of a thermal vacuum testing facility. This paper provides details of the design and development of the PeTT vacuum chamber, cost, and results for testing 1U dummy CubeSat.

DOI： 10.1109/RAST.2019.8767775

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85073896800&origin=inward

An experimental and theoretical study of spatial langmuir probe plasma system for a small lean satellite called ten-koh 査読有り

Bendoukha S., Tapia I., Okuyama K., Cho M.

International Review of Aerospace Engineering 12 ( 3 ) 131 - 140 2019年06月

記述言語：英語掲載種別：研究論文（学術雑誌）

© 2019 Praise Worthy Prize S.r.l.-All rights reserved. Ten-Koh is a small lean satellite developed by Kyushu Institute of Technology which was launched in piggyback with GOSAT2 and KhalifaSat on 29thOctober 2018, at 13:08 Japan Standard Time through the H-IIA-202 rocket of Tanegashima space center of Japan, that exploits different progress techniques to accomplish less cost growth and rapid delivery. One of the significant primary mission of satellite is double Langmuir probe system, this process incorporates a ground-validated system to observe the LEO space plasma environment. Several approaches were developed to estimate plasma density by using the single probes which is more difficult to use in nanosatellite because of the high saturation current flow. Double Langmuir probes coated by gold were designed and tested in plasma chamber, where an RF source generates Xenon gas with a 1.05×10-2 Torr pressure and an average plasma density of 1010 to 1012 m-3 for subtracting the current flow between both installed probes. Numerous simulations and ground experiments were conducted using SLP and DLP to measure space plasma parameters as current-voltage characteristics, electron density and electron temperature. The ground outcomes plasma data of Ten-Koh satellite, which is 23 kg of mass and 50 cm hexagonal shape, were analyzed and compared with ground and orbital measurements probes data of the launched satellite (Horyu IV). Copyright © 2019 Praise Worthy Prize S.r.l.-All rights reserved.

DOI： 10.15866/irease.v12i3.15927

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85073359756&origin=inward

Experimental investigation on silica dust lofting due to charging within micro-cavities and surface electric field in the vacuum chamber 査読有り国際誌

Orger N., Toyoda K., Masui H., Cho M.

Advances in Space Research 63 ( 10 ) 3270 - 3288 2019年05月

担当区分：責任著者記述言語：英語掲載種別：研究論文（学術雑誌）

© 2019 COSPAR The charged dust particles can be mobilized electrostatically by the repulsion between the adjacent grains and the surface electric field due to the incoming electron current and the charge accumulation within the micro-cavities. In this study, the experimental results of the initial vertical launching velocities and the maximum dust heights are compared with the estimated values for the lofted spherical dust grains by the patch surface charging equations. Silica particles with the sizes between <6 and 45 µm in radius are loaded on a graphite plate, and they are exposed to the electron beam with 450 eV energy under 4 × 10 −3 Pa vacuum chamber pressure. During the first set of the experiments, the dust samples are tested without an initial compression process and an additional horizontal electric field. Second, the dust samples are compressed by two different weights in order to increase the packing density under approximately 780.7 Pa and 3780 Pa. Finally, the dust grains are placed between the two parallel aluminum plates to apply approximately 2000 V/m and 4800 V/m horizontal electric field. A high-speed camera is used to record the transportation of the dust grains together with a microscopic telescope, and the results point out that the patch surface dust-charging model estimations are in agreement with the first experiments. On the other hand, the dust particles from the compressed samples are lofted with higher velocities than the estimations, and the number of the dust lofting observations decreases significantly, which demonstrates the importance of the micro-cavities and the increased charging requirement to overcome the contact forces. When the horizontal electric field is present, the initial vertical launching velocities are measured to be lower than the other experiments, which can be attributed to the decreased charging requirement for the dust lofting as a result of inter-particle collisions and rolling motion. According to the experimental results, the electrostatic dust transportation can be controlled not only by the ambient plasma and the solar irradiation on the airless planetary bodies, but also by the surface properties such as the contact surfaces between the dust grains, the number of the micro-cavities related to the packing density, and the presence of the horizontal electric field contributing to the external forces by other particle motions.

DOI： 10.1016/j.asr.2019.01.045

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85061634330&origin=inward

Design, Analysis and Testing of Monopole Antenna Deployment Mechanism for BIRDS-2 CubeSat Applications 査読有り国際誌

Zaki S., Azami M., Yamauchi T., Kim S., Masui H., Cho M.

Journal of Physics: Conference Series 1152 ( 1 ) 2019年03月

担当区分：責任著者記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

© Published under licence by IOP Publishing Ltd. This paper presents an approach to design a feasible and reliable monopole antennae deployment mechanism for CubeSat applications. Nano-satellite has faced problems in designing antennae deployment system due to space and deployment mechanism constraints. In BIRDS-2 CubeSat, the nichrome wire burning release mechanism was used when activated, it will be heated up and thermally cut through fishing line, allowing the two monopole antennas to be deployed on +Y board and at +Z axis direction of the satellite. These antennae involved amateur radio frequencies in UHF and VHF bands due to its low cost and high accessibility by the end users. The UHF frequency band was used for command uplink, mission, telemetry, and CW beacon downlink whilst the VHF frequency band was used specifically for APRS-DP/S&F-RDC mission for both uplink and downlink. In order to achieve the effectiveness of the BIRDS-2 CubeSat communication system agreed with the link budget estimation, the dimensions of antennae on the CubeSat structure depend on the required gain and operating frequency. The paper discusses detailed results of mechanical and electrical interfaces of the two monopole antennas deployment mechanism with the satellite body and the nichrome wire burning release mechanism analysis. The tests results of the mechanism were analyzed particularly on the deployment time and the nichrome wire temperature differences.

DOI： 10.1088/1742-6596/1152/1/012007

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85063894990&origin=inward

A Dual-Port Circular Polarized S-Band Antenna for Nanosatellite Communication System 査読有り国際誌

Alam T., Tariqul Islam M., Cho M.

Journal of Physics: Conference Series 1152 ( 1 ) 2019年03月

担当区分：責任著者記述言語：英語掲載種別：研究論文（学術雑誌）

© Published under licence by IOP Publishing Ltd. In recent years, the development of the nanosatellite is not for the just research purpose but commercial opportunities as well. The antenna is a very important part of the nanosatellite communication system. This paper presents an S-band circular polarized (CP) antenna for nanosatellite space mission communication system. The antenna is designed on Rogers 5880 substrate materials and the electrical dimension of the antenna is 0.39λ × 0.39λ × 0.03λ. The result shows that the antenna has a-10dB reflection coefficient bandwidth of 15.625%, 3dB axial-ratio bandwidths of 70MHz and peak gain of around 6.68dB.

DOI： 10.1088/1742-6596/1152/1/012003

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85063901487&origin=inward

BIRDS-2: A Constellation of Joint Global Multi-Nation 1U CubeSats 査読有り国際誌

Azami M., Maeda G., Faure P., Yamauchi T., Kim S., Masui H., Cho M.

Journal of Physics: Conference Series 1152 ( 1 ) 2019年03月

担当区分：責任著者記述言語：英語掲載種別：研究論文（学術雑誌）

© Published under licence by IOP Publishing Ltd. BIRDS-2, the second generation of the Joint Global Multi-Nation Birds (JGMNB) project is a constellation of 1U CubeSats from Laboratory of Spacecraft Environment Interaction Engineering (LaSEINE), Kyushu Institute of Technology, Japan. The BIRDS-2 project consists of three identical 1U built by a group of students from four nations; Japan, Malaysia, Philippines, and Bhutan. It consists of 6 missions; Camera, Automatic Radio Packet Service-Digipeater (APRS-DP), Store and Forward (S&F), COTS GPS, Anisotropic Magneto Resistance Magnetometer (AMR-MM), and detection of single-event latch-up (SEL). The objective of BIRDS-2 is to provide an opportunity to learn the entire satellite system cycle, to lay down the foundation of the sustainable space program, and to create international networks of the ground station to assist the infant space program of the participating country. A total of 11 members learns the satellite development in a lean concept of 30m radius of the work area. The paper will describe the bus system of the BIRDS-2 CubeSats and the development process throughout the one year and three months of the project timeline. Completion of BIRDS-2 flight models remarks the successful design of the CubeSats bus system and waiting for the launch and deploy from International Space Station (ISS) around 3rd quarter of this year.

DOI： 10.1088/1742-6596/1152/1/012008

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85063862346&origin=inward

A Dual-Port Circular Polarized S-Band Antenna for Nanosatellite Communication System 査読有り国際誌

Alam T., Tariqul Islam M., Cho M

Journal of Physics: Conference Series 1152 ( 1 ) 2019年03月

BIRDS-2: A Constellation of Joint Global Multi-Nation 1U CubeSats 査読有り国際誌

Azami M., Maeda G., Faure P., Yamauchi T., Kim S., Masui H., Cho M.

Journal of Physics: Conference Series 1152 ( 1 ) 2019年03月

Electrostatic Discharge Threshold on Coverglass Used to Protect Solar Cells in the Low Earth Orbit 査読有り国際誌

Khan A., Minh N., Toyoda K., Cho M.

IEEE Transactions on Plasma Science 47 ( 2 ) 1445 - 1452 2019年02月

担当区分：責任著者記述言語：英語掲載種別：研究論文（学術雑誌）

© 1973-2012 IEEE. Coverglass has been widely used to cover the solar cells of solar arrays for space power generation. Coverglass with high antireflection is widely used to protect the solar arrays from performance deterioration due to irradiation of space ultraviolet, protons, electrons, atomic oxygen (AO), and so on. Along with these, thermal cycles and/or shock may accelerate the decay synergistically affecting the threshold voltage of electrostatic discharge (ESD) on the coverglass. In order to reveal the effect of aging due to AO interaction on the ESD threshold, several coverglass samples have been exposed to low earth orbit grade AO generated by the CO 2 laser on the ground. Later, both pristine and AO-exposed coverglasses have been irradiated by energetic electrons to generate artificial arcing (ESD) under high vacuum system. Statistical analysis and Weibull distribution confirm that the threshold voltage of ESD is lower on the aged coverglass than virgin.

DOI： 10.1109/TPS.2018.2885926

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85061391677&origin=inward

Estimating sun vector based on limited in-orbit data 査読有り国際誌

Faizullin D., Hiraki K., Cho M.

International Review of Aerospace Engineering 12 ( 2 ) 101 - 108 2019年01月

担当区分：責任著者記述言語：英語掲載種別：研究論文（学術雑誌）

© 2019 Praise Worthy Prize S.r.l.-All rights reserved. This paper introduces an attitude and orbit determination system, in particular a sun vector determination algorithm, for HORYU-IV nano-satellite by Kyushu Institute of Technology (Kyutech). Usually, nano-satellites cannot use sensors with high specs because of limited budget and onboard space. In order to achieve the required accuracy of attitude determination, estimation algorithms combining different sources of attitude information should be used. One of the HORYU-IV missions has required sun vector information. In order to detect the sun angle, six sun sensors, which have originally been designed and developed by the authors, and five solar panels have been used. However, due to the narrow field of view and to the saturation property of these sensors, the duration of sun detection is quite limited. At a non-detection period, a gyro sensor is used in order to propagate the attitude. However, the sensor has the bias error in its measured value. Hence, the Extended Kalman Filter has been used in order to estimate the sun vector and the bias error of gyro sensors. A simulation result shows that the algorithm can estimate the sun vector in 1deg accuracy.

DOI： 10.15866/irease.v12i2.16189

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85070450565&origin=inward

真空アーク推進機（VAT-pi2）の鳳龍四号における軌道上実証査読有り

豊田和弘, アゲエバカテリーナ, 村上弥生, 福田大, 清水達夫, 鳳龍四号開発チーム, 趙孟佑

日本航空宇宙学会誌 ( 一般社団法人日本航空宇宙学会 ) 67 ( 5 ) 158 - 160 2019年01月

担当区分：責任著者記述言語：日本語掲載種別：研究論文（学術雑誌）

<p>キューブサットなどの超小型衛星はその大きさから推進機を搭載することは難しいが，搭載できればミッションの幅が大きく広がる．また，宇宙ゴミにならないように25年以内にデオービットすることもルール化された．このような背景から固体推進剤を用いた真空アーク推進機（VAT-pi2）の開発を行ってきた．陰極である導電性の固体推進剤，陽極，コンデンサおよび電源からなる真空アーク推進機はその簡単な構造から小型化できロバストである．また低地球軌道に存在するプラズマと干渉することで点火装置なしで自発放電をすることが可能である．今回VAT-pi2の軌道上での動作試験を超小型衛星「鳳龍四号」で行った．300V発電太陽電池を電源として動作させている．また放電電流を計測できるオシロスコープを搭載しており，同時に放電の様子を撮影できるカメラも搭載されている．軌道上での実験の結果，VAT-pi2の放電を確認することができた．放電波形および放電画像の取得は引き続き行っていく．</p>

DOI： 10.14822/kjsass.67.5_158

CiNii Article

CiNii Research

その他リンク： https://ci.nii.ac.jp/naid/130007642572

Evaluation of Electron-emitting Film for Spacecraft Charging Mitigation (ELFs Charm) 査読有り

TANAKA Atomu, MATEO VELEZ Jean-Charles, DADOUCH Sarah, OKUMURA Teppei, SAKAMOTO Kenji, IWATA Minoru, TOYODA Kazuhiro, CHO Mengu

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN ( 一般社団法人日本航空宇宙学会 ) 17 ( 1 ) 1 - 6 2019年01月

担当区分：責任著者記述言語：英語掲載種別：研究論文（学術雑誌）

<p>To protect a satellite from accidents due to spacecraft charging, Kyushu Institute of Technology (Kyutech) is developing a device called ELFs-Charm, which stands for ELectron-emitting Film for Spacecraft CHARging Mitigation. Electron emission from ELFs-Charm was already confirmed in Polar Earth Orbit in 2012 via flight experiment onboard HORYU-II. As a next step, we are considering the practical operation for spacecraft charging mitigation. The present emission level is not enough to increase the satellite potential. We focus our efforts on improving two properties, charging property and the emission threshold. The charging property is measured by how well the differential voltage between the ELFs-charm insulator surface and the satellite chassis increases. The emission threshold is measured by the differential voltage when the electron emission starts. This paper reports the laboratory experimental results to measure the two properties of various samples. The sample made of fluorin resin coating had a good combination of the charging property and the emission threshold that makes it possible to emit electron under realistic ambient electron current density in orbit.</p>

DOI： 10.2322/tastj.17.1

CiNii Article

CiNii Research

その他リンク： https://ci.nii.ac.jp/naid/130007542851

Development of UiTMSAT-1: An approach to lean satellite concept 査読有り

Mohamad Rahim S., Mustafa S., Azami M., Zaki S., Enche Ab Rahim S., Jusoh M., Cho M.

ASM Science Journal 12 ( Special Issue 2 ) 62 - 71 2019年01月

担当区分：責任著者記述言語：英語掲載種別：研究論文（学術雑誌）

© Academy of Sciences Malaysia 2019. This paper presents the development of the UiTMSAT-1 nanosatellite and the approach towards a lean satellite concept. The lean satellite concept comes from extensive reports and discussions among many satellite developers and space players with the increased capability and technology in producing small satellites from the introduction of the CubeSat Project. The concept makes aware the importance of low-cost technology and fast delivery system of the satellite as compared with the traditional satellite development process. The UiTMSAT-1, which is the Universiti Teknologi MARA (UiTM)'s first nanosatellite, underwent the lean satellite concept and scheduled development in its BIRDS-2 project. A work breakdown structure was created to have a well-defined description of the divisions involved in the UiTMSAT-1 nanosatellite development. UiTM, as the stakeholder of Malaysia's team in the BIRDS-2 project contributed during the whole process including the installation of the UiTM ground station to track and monitor the nanosatellites. A brief anal ysis was presented based on the UiTMSAT-1's housekeeping data of approximately three months preliminary observations since its deployment into orbit.

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85072177237&origin=inward

The role of CubeSats programs in workforce development for developing countries. 査読有り

Raphael T.T., Welsh C., Oluwatobi A.I., George M., Cho M.

Proceedings of the International Astronautical Congress, IAC 2019-October 2019年01月

担当区分：責任著者記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

Copyright © 2019 by the International Astronautical Federation (IAF). All rights reserved. Benefits from the exploration and eventual applications of space technology are evident in all aspects of our lives on Earth; from earth observation, navigation, communication and innovative spin-offs in all areas of science and technology. Apart from the huge capital investment involved, access to these benefits in part require long term investment in high level education and infrastructural development. In the past, this has been an impediment for developing countries to access space and develop manpower in allied technological areas as expenditures on space programs in such countries may seem inappropriate because of the need for diverting resources from near-term social programs. Recently, this narrative is changing as many developing countries can access space and also develop essential manpower through CubeSat (1U: 10cm cubic, 1kg) programs which offers a cheaper and faster access to space. These programs have shown that long-term economic prosperity of any nation depends in part on investment in human capital development, the advancement of which requires scientific training as well as the use, and eventually the development of new technologies. This paper shall bring to the fore a comparative analysis of several CubeSat projects considering the different models, lessons learned and success stories from Africa, South America and South-East Asia that are providing great scientific impact with near-term benefits through applications such as environmental monitoring, disaster response, and telecommunications to posit a pathway for helping developing and emerging nations to develop their workforce thereby hastening national and regional technology development.

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85079148010&origin=inward

Perovskite solar cell for space application 査読有り

Bautista I., Shuzhang Y., Ma T., Cho M.

Proceedings of the International Astronautical Congress, IAC 2019-October 2019年01月

担当区分：責任著者記述言語：英語掲載種別：研究論文（国際会議プロシーディングス）

Copyright © 2019 by the International Astronautical Federation (IAF). All rights reserved. Satellite developers are continuously doing research on satellite energy sources that are efficient, lightweight and cheap than the current Silicon and triple-junction solar cells being used. The emergence of organic-inorganic metal halide Perovskite solar cells (PSC) which, have high specific power (kW/kg), achieved record power conversion efficiencies greater than 22% and cheap to manufacture, has attracted the attention of scientists for its possibility to replace silicon and triple junction solar cells. These factors make Perovskite solar cells viable candidates for space applications. To determine the feasibility of PSCs in space, samples were tested under simulated Low Earth Orbit (LEO) space environment such as thermal cycle, vacuum, vibration, total ionization dosage and electron radiation. Results showed that PSC has the ability to survive and work in space with thermal variation having the largest effect on the performance of the PSC.

Scopus

その他リンク： https://www.scopus.com/inward/record.uri?partnerID=HzOxMe3b&scp=85079196043&origin=inward

　前のページ - 次のページ　

<趙 孟佑>

論文 - 趙 孟佑

<趙　孟佑>

論文 - 趙　孟佑