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| Year of publication | 2010 |
|---|---|
| Category | Dom. Conference |
| Subject | |
| Title | 발사체 상단의 정밀 궤도진입을 위한 유도기법 연구 |
| Author | 박상혁, 유창경, 김현중 |
| Journal title | 국방과학연구소 창설 40주년 기념 종합학술대회 논문집 |
| Publication date | |
| Volume & Other data | |
| Abstract | Trajectory optimization has been usually performed to determine the thrust attitude profile for a launch
vehicle during the powered flight for the orbit insertion of a satellite. However, mere following such an optimized thrust attitude profile does not be guaranteed the exact orbit insertion due to uncertainties included in the launch vehicle and the environment. In this paper, an explicit guidance scheme for a upper stage is presented for exact orbit insertion of a payload. The proposed guidance scheme separately produces the guidance in the vertical and the horizontal channel. A difference between desired altitude and current altitude is reduced by the vertical guidance command and a difference between desired inclination and current inclination is reduced by the horizontal guidance command. |
| Keywords | Orbit insertion, Upper stage, Closed-loop guidance |
| Issn Number | |
| File |  발사체 상단의 정밀 궤도진입을 위한 유도기법 연구.pdf (390.5K) [13] DATE : 2014-06-03 22:18:02 |
