• Journal of Astronomy and Space Sciences
• /
• 제28권4호
• /
• pp.273-284
• /
• 2011

A method of stellar source selection for validating the quality of image is investigated for a low Earth orbit optical remote sensing satellite. Image performance of the optical payload needs to be validated after its launch into orbit. The stellar sources are ideal source points that can be used to validate the quality of optical images. For the image validation, stellar sources should be the brightest as possible in the charge-coupled device dynamic range. The time delayed and integration technique, which is used to observe the ground, is also performed to observe the selected stars. The relations between the incident radiance at aperture and V magnitude of a star are established using Gunn & Stryker's star catalogue of spectrum. Applying this result, an appropriate image performance index is determined, and suitable stars and areas of the sky scene are selected for the optical payload on a remote sensing satellite to observe. The result of this research can be utilized to validate the quality of optical payload of a satellite in orbit.

• International Journal of Aeronautical and Space Sciences
• /
• 제18권2호
• /
• pp.334-343
• /
• 2017

The optimum design of an SAR (Synthetic Aperture Radar) satellite constellation is developed herein using a genetic algorithm. The performance of Earth observations using a satellite constellation can be improved by minimizing the maximum revisit time. Classical orbit design using analytic methods has limitations when addressing orbit dynamics due to various disturbances. To overcome this issue, an optimization technique based on a genetic algorithm is used. STK (Systems Tool Kit) is utilized to propagate the satellite orbit when considering external disturbances, and the maximum revisit time on the earth observation area is calculated. By minimizing the performance index using a genetic algorithm, the optimum orbit of the satellite constellation is designed. Numerical results are provided to demonstrate the performance of the proposed method.

• 항공우주기술
• /
• 제7권2호
• /
• pp.82-87
• /
• 2008

본 연구에서는 우주에서 가시광 영역으로 지구의 지표면을 고해상도로 촬영하는 위성탑재카메라를 위한 복사에너지 신호량을 모델링하였다. 복사에너지 모델링은 광원으로서의 태양과 지구대기 및 지표면 반사도, 카메라의 특성 등을 포함하며 최종 계산 결과는 광전자카메라의 광검지기에서 생성되는 전자의 수로 나타난다.

• 대한원격탐사학회:학술대회논문집
• /
• 대한원격탐사학회 2005년도 Proceedings of ISRS 2005
• /
• pp.11-13
• /
• 2005

The Third Assessment Report of the Intergovernmental Panel on Climate Change (IPCC) concluded that many collective observations gave a aspect of a global warming and other changes in the climate system. Future earth observation using satellite data should monitor global climate change, and should contribute to social benefits. Especially, human activities has given the big impacts to earth environment This is a very complex affair, and nature itself also impacts the clouds, namely the seasonal variations. JAXA (former NASDA) has the plan of the Global Change Observation Mission (GCOM) for monitoring of global environmental change. SGLI (Second Generation GLI) onboard GCOM-C (Climate) satellite, which is one of this mission, is an optical sensor from Near-UV to TIR. This sensor is the GLI follow-on sensor, which has the various new characteristics. Polarized/multi-directional channels and 250m resolution channels are the unique characteristics on this sensor. This sensor can be contributed to clarification of coastal change in sea surface. This paper shows the introduction of the unique aspects and characteristics of the next generation satellite sensor, SGLIIGCOM-C, and shows the preliminary research for this sensor.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2005년도 춘계학술대회논문집
• /
• pp.805-808
• /
• 2005

This paper is a study on an optical bench satisfying stiffness and thermal pointing error requirements for LEO earth observation satellite. According to shape and stiffness requirements, optical bench type 1 is designed. Because type 1 does not satisfy the thermal pointing error requirement, an optical bench type 2 is suggested. Although the type 2 has better results than type 1, it still does not meet the thermal pointing error requirement. Using the results of optical bench type 1&2, the optical bench type 3 is finally designed, which satisfies both the stiffness and thermal pointing error requirements.

• 한국복합재료학회:학술대회논문집
• /
• 한국복합재료학회 2005년도 추계학술발표대회 논문집
• /
• pp.207-210
• /
• 2005

In this paper, technical issues for an optical bench of high precision LEO Earth observation satellite are described. The optical bench should be stable for thermal and dynamic environment. In this point of view, an intermediate type of optical bench is developed. Thermal deformation analysis and modal analysis are performed for two types of FE model. Modal test are performed to verify the analysis results. The test results fit well the analysis results.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2004년도 추계학술대회논문집
• /
• pp.747-750
• /
• 2004

After launching, spacecraft is exposed to extreme environments. So spacecraft should be tested after design/manufacture to verify whether components can be operated functionally. Acceleration transferred from launch vehicle to spacecraft produces quasi-static load, sine vibration and random vibration. Random vibration is also induced by acoustic vibrations transferred by surface of spacecraft. And shock vibration is produced when spacecraft is separated from launch vehicle. To verify operation of spacecraft under these launch environments, separation shock test, sine vibration test, acoustic vibration test and random vibration test should be performed. This paper describes these launch environment test requirements.

• Journal of Astronomy and Space Sciences
• /
• 제40권1호
• /
• pp.35-44
• /
• 2023

Surveillance and reconnaissance intelligence in the space domain will become increasingly important in future battlefield environments. Moreover, to assimilate the military provocations and trends of hostile countries, imagery intelligence of the highest possible resolution is required. There are many methods for improving the resolution of optical satellites when observing the ground, such as designing satellite optical systems with a larger diameter and lowering the operating altitude. In this paper, we propose a method for improving ground observation resolution by using an optical system for a previously designed low orbit satellite and lowering the operating altitude of the satellite. When the altitude of a satellite is reduced in a circular orbit, a large amount of thrust fuel is required to maintain altitude because the satellite's altitude can decrease rapidly due to atmospheric drag. However, by using the critical inclination, which can fix the position of the perigee in an elliptical orbit to the observation area, the operating altitude of the satellite can be reduced using less fuel compared to a circular orbit. This method makes it possible to obtain a similar observational resolution of a medium-sized satellite with the same weight and volume as a small satellite. In addition, this method has the advantage of reducing development and launch costs to that of a small-sized satellite. As a result, we designed an elliptical orbit. The perigee of the orbit is 300 km, the apogee is 8,366.52 km, and the critical inclination is 116.56°. This orbit remains at its lowest altitude to the Korean peninsula constantly with much less orbit maintenance fuel compared to the 300 km circular orbit.

• 대한공간정보학회지
• /
• 제20권1호
• /
• pp.117-123
• /
• 2012

세계 각국은 우주개발에 대한 많은 관심으로 인하여 자국의 지구관측위성을 발사하고 있다. 이로 인해 고해상도 위성영상은 날로 증가하고 있다. 또한 웹 환경의 발달로 인하여 일반 사용자는 위성영상을 쉽게 접하고 있다. 본 연구에서는 위성영상의 활용성을 높이고자 위성의 센서모델링에 대한 해박한 지식이 다소 없더라도 쉽게 3차원 좌표를 획득할 수 있도록 웹 기반 위성사진측량에 대한 기초연구를 수행하였다. 웹 환경에서 고해상도 위성영상을 이용하여 3차원 좌표를 결정하기 위한 여러 요소기술을 분석하고 IKONOS 위성영상을 이용하여 사례연구를 수행하였다. 센서모델링 방법중의 하나인 평행투영모델을 적용하여 에피폴라 영상을 생성하고 웹 환경에서 3차원 위치를 결정할 수 있는 프로토타입 형태의 프로그램을 구현하였다. 이를 통해 일반 사용자도 쉽게 웹 환경에서 3차원 위치를 결정할 수 있었고 기 구축된 공간정보의 갱신과 서비스 분야에 활용될 수 있음을 알았다.

• 한국광학회지
• /
• 제11권1호
• /
• pp.6-12
• /
• 2000

위성에 탑재된 지구관측용 카메라는, 지상의 망원경과 같은 원리로, 우주상공에서 지표면 관측을 자동적으로 수행하고 관측정보를 지상으로 전달해 주는 장치다. 이용 목적에 따라 카메라의 해상도 또는 분해능, 관측대역, 관측폭, 위성의 궤도 등의 규격이 결정된다. 고해상도는 카메라 관련 제반 기술 및 경험이 부족한 국내의 여건에 적합한 소형 위성용 고해상도 카메라의 규격을 제시하며 이에 따른 광학 설계와 제작, 조립 및 측정오차를 제시한다.