Study on guidance laws for course-correction-projectile using trajectory error shaping = 궤적 오차 성형을 이용한 탄도수정탄 유도기법 연구

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This dissertation proposes a new guidance law using trajectory errors shaping for a course-correction-projectile (CCP) with very limited maneuverability. Compared to existing approaches, the proposed guidance law is derived directly from collision geometry, which is the fundamental concept of guidance process, so that it allows collisions with minimal guidance command and zero final guidance command. In the proposed method, the collision geometry considering the motions of CCP, called collision-ballistic-trajectory, and the corresponding heading error are first determined using the ballistic trajectory prediction technique, which is based on the partial closed-form solutions of the ballistic trajectory equations in conjunction with the sensitivity technique. The proposed guidance law that nullifies this heading error over a finite time is then derived by using a specific form of error dynamic equation. In this dissertation, the characteristics of the proposed guidance law are also investigated. Finally, numerical simulations demonstrate the characteristics and effectiveness of the proposed guidance law compared to the existing methods.
Advisors
Tahk, Min-Jearesearcher탁민제researcher
Description
한국과학기술원 :항공우주공학과,
Publisher
한국과학기술원
Issue Date
2019
Identifier
325007
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 항공우주공학과, 2019.2,[v, 91 p. :]

Keywords

Course-correction-projectile▼acollision geometry▼atrajectory error shaping▼aguided projectile; 탄도수정탄▼a충돌 기하▼a궤적 오차 성형▼a유도 포탄

URI
http://hdl.handle.net/10203/265441
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=842442&flag=dissertation
Appears in Collection
AE-Theses_Ph.D.(박사논문)
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