{"title":"Design of an Elliptical Orbit for High-Resolution Optical Observation at a Very Low\u0000 Altitude over the Korean Peninsula","authors":"Dongwoo Kim, Taejin Chung","doi":"10.5140/jass.2023.40.1.35","DOIUrl":"https://doi.org/10.5140/jass.2023.40.1.35","url":null,"abstract":"Surveillance and reconnaissance intelligence in the space domain will become\u0000 increasingly important in future battlefield environments. Moreover, to assimilate the\u0000 military provocations and trends of hostile countries, imagery intelligence of the\u0000 highest possible resolution is required. There are many methods for improving the\u0000 resolution of optical satellites when observing the ground, such as designing satellite\u0000 optical systems with a larger diameter and lowering the operating altitude. In this\u0000 paper, we propose a method for improving ground observation resolution by using an\u0000 optical system for a previously designed low orbit satellite and lowering the operating\u0000 altitude of the satellite. When the altitude of a satellite is reduced in a circular\u0000 orbit, a large amount of thrust fuel is required to maintain altitude because the\u0000 satellite’s altitude can decrease rapidly due to atmospheric drag. However, by using the\u0000 critical inclination, which can fix the position of the perigee in an elliptical orbit\u0000 to the observation area, the operating altitude of the satellite can be reduced using\u0000 less fuel compared to a circular orbit. This method makes it possible to obtain a\u0000 similar observational resolution of a medium-sized satellite with the same weight and\u0000 volume as a small satellite. In addition, this method has the advantage of reducing\u0000 development and launch costs to that of a small-sized satellite. As a result, we\u0000 designed an elliptical orbit. The perigee of the orbit is 300 km, the apogee is 8,366.52\u0000 km, and the critical inclination is 116.56°. This orbit remains at its lowest altitude\u0000 to the Korean peninsula constantly with much less orbit maintenance fuel compared to the\u0000 300 km circular orbit.","PeriodicalId":44366,"journal":{"name":"Journal of Astronomy and Space Sciences","volume":"2 1","pages":""},"PeriodicalIF":0.5,"publicationDate":"2023-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87929133","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}