Instantaneous Impact Point (IIP) guidance and its applications순간 낙하점 변화 유도와 그 응용

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This thesis proposes a feedback guidance law of a rocket to move an instantaneous impact point (IIP) to a desired impact point. To develop this guidance law, IIP dynamics which describes the motion of the IIP on the surface of the Earth is established in the Earth-Centered Earth-Fixed (ECEF) frame by introducing the time derivatives of the IIP. A near time-optimal feedback guidance law for following the shortest path between the current IIP and desired location is developed by utilizing IIP dynamics. Through the various case studies, this study figures out that the efficiency of the developed IIP guidance law becomes lower as the change in a crossrange direction or backwards direction of downrange increases, while the IIP guidance law performs a near-optimal capability in the downrange direction. Moreover, for the application on practical missions which require specific purposes (engine cut-off insensitive, fixed burn time and return to launch site), this thesis enhances the developed IIP guidance law and provides an additional function. First, the IIP guidance law is improved to handle the event of an engine cut-off failure of the rocket by developing the IIP hold guidance law which can maintain the IIP at the same location in the presence of the thrust, and the mode switching algorithm which makes the necessary transition between the IIP guidance law and IIP hold guidance law while taking the angular rate limitation of the rocket into account. Secondly, the guidance law for changing the IIP for the rocket with fixed burn time is developed. Lastly, the guidance law that can control the flight path angle of the rocket is developed, in order to improve the performance of the IIP guidance law for IIP change in the negative downrange direction. The effectiveness of the IIP guidance law and improved guidance laws, in comparison with the optimal solution obtained from GPOPS, is demonstrated through the case studies on the landing guidance of the 1st stage of Falcon 9, developed by Space X.
Advisors
Ahn, Jaemyungresearcher안재명researcher
Description
한국과학기술원 :항공우주공학과,
Publisher
한국과학기술원
Issue Date
2019
Identifier
325007
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 항공우주공학과, 2019.8,[v, 119 p. :]

Keywords

Instantaneous impact point▼aIIP rate▼arocket guidance law▼aengine cut-off insensitive▼aimpact point targeting▼aflight path angle control▼areusable launch vehicle▼alanding guidance; 순간 낙하점▼a순간 낙하점 변화율▼a로켓 유도 법칙▼a엔진 컷오프 둔감성▼a낙하점 타게팅▼a비행 경로각 제어▼a재사용 발사체▼a착륙 유도

URI
http://hdl.handle.net/10203/283349
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=871524&flag=dissertation
Appears in Collection
AE-Theses_Ph.D.(박사논문)
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