Study on impact-time-control guidance laws based on time-to-go prediction = 잔여비행시간 예측식을 이용한 충돌시간제어 유도법칙에 대한 연구

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Recently, numbers of study on impact-time-control and/or impact-angle-control guidance laws have been developed and guidance laws considering eld-of-view constraint have also been developed. In this dissertation, a novel approach for guidance law design to satisfy the impact-time constraint for a certain class of homing missiles. The proposed guidance law provides proper lateral acceleration commands that make the impact time error converge to zero by the time of impact. This scheme can be applied to any existing guidance law for which a formula of predicted time-to-go is available. By introducing a new form of error dynamics, the impact time error converges to zero within a nite time. Convergence of time-to-go errors is supported by Lyapunov stability. In order to consider the seeker's FOV constraint, time-varying guidance gain is suggested for the proposed guidance law. Moreover, certain feasible conditions of relationship between desired impact angle, time, and FOV limit are analyzed. The performance of the extended guidance laws is demonstrated by numerical simulation.
Advisors
Tahk, Min Jearesearcher탁민제researcher
Description
한국과학기술원 :항공우주공학과,
Publisher
한국과학기술원
Issue Date
2018
Identifier
325007
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 항공우주공학과, 2018.2,[iv, 110 p. :]

Keywords

Missile Guidance▼aImpact Time Control▼aImpact Angle Control▼aField-of-view Constraint▼aTime-to-go Prediction; 유도법칙▼a충돌시간제어▼a충돌각제어▼a관측시야제한▼a잔여비행시간 예측

URI
http://hdl.handle.net/10203/265435
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=734439&flag=dissertation
Appears in Collection
AE-Theses_Ph.D.(박사논문)
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