• 한국위성정보통신학회논문지
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• 제6권2호
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• pp.102-106
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• 2011

태양폭발, 코로나물질방출(Corona Mass Ejection, CME)등의 태양활동을 포함한 우주환경(space environment)은 결코 인간에게 우호적이지만은 않다. 특히 인공위성에게는 치명적일 수 있다. 그 중에서 정지궤도에 있는 통신위성에게는 상기와 같은 급격한 태양활동뿐만 아니라 지속적으로 끊임없이 배출되는 전자, 양성자등 플라즈마 입자들로 인해 수명이 단축되고 있다. 통신위성을 구성하는 능동부품들은 플라즈마 입자들에 특히 약하기 때문이다. 이를 방지하기 위하여 방사능 차폐(Radiation Shielind)등을 하지만 이에 대한 비용이 매우 많이 드는 것이 사실이다. 그러므로 적절한 차폐가 필요하며 이를 위해서는 우주환경의 연구가 필요하다. 본 연구에서는 저궤도부터 우주탐사용 위성까지 모든 궤도영역의 인공위성의 이상현상등을 분석한 후 이것이 태양폭발, 지자기 폭풍등 우주환경이벤트와의 연관성을 조사해보고자 한다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.407-412
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• 2008

"KAGUYA"(SELENE) is a Japanese Lunar Explorer launched by H-IIA rocket from Tanegashima Space Center on 14 September 2007. The dual-mode bipropellant propulsion subsystem of KAGUYA includes two fuel tanks, an oxidizer tank, propellant and pressurant control components, twelve monopropellant 20N thrusters, eight monopropellant 1N thrusters, and a bipropellant 500N Orbit Maneuver Engine(OME). Once the KAGUYA separated from the rocket, it circled the Earth twice and traveled to the Moon, where it entered lunar orbit. All maneuvers were performed through multiple 500N OME/20N thruster firings. This paper describes the in-space performance of KAGUYA Lunar Explorer bipropellant propulsion subsystem.

• Journal of Astronomy and Space Sciences
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• 제36권3호
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• pp.181-186
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• 2019

The attitude information of spacecraft can be obtained by the sensors attached to it using a star tracker, three-axis magnetometer, three-axis gyroscope, and a global positioning signal receiver. By using these sensors, the spacecraft can be maneuvered by actuators that generate torques. In particular, electromagnetic-torque bars can be used for attitude control and as a momentum-canceling instrument. The spacecraft momentum can be created by the current through the electrical circuits and coils. Thus, the current around the electromagnetic-torque bars is a critical factor for precisely controlling the spacecraft. In connection with these concerns, a solar-cell array can be considered to prevent generation of a magnetic dipole moment because the solar-cell array can introduce a large amount of current through the electrical wires. The maximum value of a magnetic dipole moment that cannot affect precise control is $0.25A{\cdot}m^2$, which takes into account the current that flows through the reaction-wheel assembly and the magnetic-torque current. In this study, we designed a 300-W solar cell array and presented an optimal wire-routing method to minimize the magnetic dipole moment for space applications. We verified our proposed method by simulation.

• 한국항공우주학회지
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• 제46권11호
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• pp.902-910
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• 2018

본 논문은 지구의 J2 섭동을 고려한 비공면 타원궤도에서의 우주비행체의 요격 문제를 다룬다. J2에 의한 영향은 지구를 돌고 있는 우주비행체 궤도를 변화시키는 주된 요인이 되며, 이를 해결하기 위해 실시간 요격 방법을 제안한다. 구형의 지구와 순간추력을 고려한 운동방정식을 기반으로 최적화 문제를 구성하고 수치적으로 얻어진 최적해를 인터셉터의 추진방향으로 설정한다. 위치 오차는 최적화 문제를 반복적으로 해결하고 인터셉터의 추진방향을 수정하는 방식으로 해결한다. 다양한 궤도를 상황을 고려하여 제안하는 방법을 검증한다.

• International Journal of Computer Science & Network Security
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• 제23권3호
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• pp.94-100
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• 2023

The primary goal of any communication spacecraft is to provide communication in variety of frequency bands based on mission requirements within the Indian mainland. Some of the spacecrafts operating in S-band utilizes a 6m or larger aperture Unfurlable Antenna (UFA for S-band links and provides coverage through five or more S-band spot beams over Indian mainland area. The Unfurlable antenna is larger than the satellite and so the antenna is stowed during launch. Upon reaching the orbit, the antenna is deployed using motors. The deployment status of any deployment mechanism will be monitored and verified by the telemetered values of micro-switch position before the start of deployment, during the deployment and after the completion of the total mechanism. In addition to these micro switches, a camera onboard will be used for capturing still images during primary and secondary deployments of UFA. The proposed checkout system is realized for validating the performance of the onboard camera as part of Integrated Spacecraft Testing (IST) conducted during payload checkout operations. It is designed for acquiring the payload data of onboard camera in real-time, followed by archiving, processing and generation of images in near real-time. This paper presents the architecture, design and implementation features of the acquisition, processing and Image generation system for Camera onboard spacecraft. Subsequently this system can be deployed in missions wherever similar requirement is envisaged.

• Journal of Astronomy and Space Sciences
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• 제27권3호
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• pp.195-204
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• 2010

The optimal Earth-Moon transfer trajectory considering spacecraft's visibility from the Daejeon ground station visibility at both the trans lunar injection (TLI) and lunar orbit insertion (LOI) maneuvers is designed. Both the TLI and LOI maneuvers are assumed to be impulsive thrust. As the successful execution of the TLI and LOI maneuvers are crucial factors among the various lunar mission parameters, it is necessary to design an optimal lunar transfer trajectory which guarantees the visibility from a specified ground station while executing these maneuvers. The optimal Earth-Moon transfer trajectory is simulated by modifying the Korean Lunar Mission Design Software using Impulsive high Thrust Engine (KLMDS-ITE) which is developed in previous studies. Four different mission scenarios are established and simulated to analyze the effects of the spacecraft's visibility considerations at the TLI and LOI maneuvers. As a result, it is found that the optimal Earth-Moon transfer trajectory, guaranteeing the spacecraft's visibility from Daejeon ground station at both the TLI and LOI maneuvers, can be designed with slight changes in total amount of delta-Vs. About 1% difference is observed with the optimal trajectory when none of the visibility condition is guaranteed, and about 0.04% with the visibility condition is only guaranteed at the time of TLI maneuver. The spacecraft's mass which can delivered to the Moon, when both visibility conditions are secured is shown to be about 534 kg with assumptions of KSLV-2's on-orbit mass about 2.6 tons. To minimize total mission delta-Vs, it is strongly recommended that visibility conditions at both the TLI and LOI maneuvers should be simultaneously implemented to the trajectory optimization algorithm.

• 한국항공우주학회지
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• 제44권8호
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• pp.695-701
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• 2016

우주비행체 추진기관은 로켓엔진의 일종으로 인공위성, 우주탐사선 등의 임무수행을 위해 사용되며 인공위성 자세제어 및 궤도조정을 위한 수요에 따라 1950년대 말부터 개발되기 시작하였다. 우주비행체에 사용되는 추진시스템은 발사체와 달리 상대적으로 긴 기간의 임무수행이 요구되며, 이에 따라 추진제의 안정성 및 추진시스템의 내구성이 설계에 매우 중요한 요소가 된다. 최근에 우주추진 분야에서 주목받는 기술은 이온성 액체를 이용한 친환경 추진과 전기추진만으로 추진시스템을 구성하는 기술로 국내에서도 체계적인 연구개발이 필요하다. 본 논문에서는 우주추진기관의 국내외 현황 및 주목받는 기술들을 나열하고 이에 따른 개발 전망을 간략히 소개하였다.

• 한국추진공학회지
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• 제3권4호
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• pp.1-11
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• 1999

단기액체 하이드라진 ($N_2$$H_4$) 추진제를 사용하는 인공위성 추진시스템의 열적 거동을 기술한다. 운용궤도에서 액체추진제의 동결을 방지하기 위한 열제어 성능이 모사궤도환경하에서 시험, 검증되었다. 궤도 열환경은, 우주환경 모사챔버내에서 흡수열유속법에 의해 구현되었다 흡수열유속법은 추진시스템을 감싸고 있는 위성체 버스패널에 인위적인 가열을 하여 열환경을 모사하는 방법이다. 시간대별로 얻어진 추진계 구성품의 온도분포가 제시되고 이 열적 거동은 각 구성품들의 열제어를 위하여 장착된 비행용 히터의 작동 사이클 수로 변환된다. 작동 사이클 수는 전력으로 환산되어 추진시스템의 열제어를 위하여 운용제도에서 요구되는 총전력량을 예측가능하게 한다. 부가적으로, 인공위성의 열평형상태에서 얻어진 추진계구성품들의 주기적 온도가 설계허용온도와 비교되고 시스템검증의 시각에서 평가된다.

• International Journal of Aeronautical and Space Sciences
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• 제16권4호
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• pp.590-601
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• 2015

This paper gives an overview of research on the field of structure vibration-attitude coordinated control of spacecraft. First of all, the importance of the technology has been given an introduction, and then later the research progress of space structure dynamics modeling, research progress of structure vibration-attitude coordinated control of flexible spacecraft have been discussed respectively. Finally, future research on application of structure vibration-attitude coordinated control of spacecraft has been recommended.

• International Journal of Aeronautical and Space Sciences
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• 제16권1호
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• pp.28-40
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• 2015

This paper aims to address the intelligent active vibration control problem of a flexible rectangular plate vibration involving parameter variation and external disturbance. An adaptive sliding mode (ASM) MIMO control strategy and smart piezoelectric materials are proposed as a solution, where the controller design can deal with problems of an external disturbance and parametric uncertainty in system. Compared with the current 'classical' control design, the proposed ASM MIMO control strategy design has two advantages. First, unlike existing classical control algorithms, where only low intelligence of the vibration control system is achieved, this paper shows that high intelligent of the vibration control system can be realized by the ASM MIMO control strategy and smart piezoelectric materials. Second, the system performance is improved due to two additional terms obtained in the active vibration control system. Detailed design principle and rigorous stability analysis are provided. Finally, experiments and simulations were used to verify the effectiveness of the proposed strategy using a hardware prototype based on NI instruments, a MATLAB/SIMULINK platform, and smart piezoelectric materials.