Guidance law with terminal time constraint using lyapunov stability theorem = 리아프노프 안정성 정리를 이용한 종말시간 구속조건을 갖는 유도법칙 설계

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This paper proposes the nonlinear guidance laws satisfying terminal time constraint for two- and three-dimensional problems. A salvo attack problem of missiles and a formation flight problem of UAVs are considered for two- and three-dimensional cases, respectively. In two-dimensional problem, each missile should simultaneously impact the target at a designated impact time to enhance the survivability of the anti-ship missile group against CIWS. In three-dimensional problem, also, UAVs have to precisely complete the desired formation shape at a specified formation time and maintain the formation shape. To derive the guidance law, appropriate Lyapunov function candidates, i.e., positive definite function consisting of an expected terminal collision error and the zero-effort-miss, are selected for each problem. The guidance commands are finally determined to ensure the negative definiteness of the time derivative of the proposed Laypunov function. The previous guidance laws to control impact time in two-dimensional case are mostly derived by solving the optimal control problem based on the linearized governing equation under the small angle assumption. Hence, the time-to-go estimation process is basically required for real application and the guidance performance depends on the accuracy of the time-to-go estimation. However, this main drawback is eliminated in the guidance law proposed in this paper because it is obtained by using Lyapunov stability theorem and directly applied the full nonlinear governing equation. Furthermore, the proposed guidance law for salvo attack to impact a stationary target at the designated impact time is also extended to a slowly moving target. The guidance law for three-dimensional problem, i.e, formation flight of UAVs, is determined in the similar manner as two-dimensional problem and its final guidance command is a velocity vector. The velocity vector command can be easily transformed into the typical autopilot commands of an UAV...
Advisors
Tahk, Min-Jearesearcher탁민제
Description
한국과학기술원 : 항공우주공학전공,
Publisher
한국과학기술원
Issue Date
2014
Identifier
568621/325007  / 020045088
Language
eng
Description

학위논문(박사) - 한국과학기술원 : 항공우주공학전공, 2014.2, [ vi, 77 p. ]

Keywords

Nonlinear Guidance Law; 리아프노프 안정성 정리; 편대 비행; 동시 공격; 종말시간 구속조건; 비선형 유도법칙; Terminal Time Constraint; Salvo Attack; Formation Flight; Lyapunov Stability Theorem

URI
http://hdl.handle.net/10203/196178
Link
http://library.kaist.ac.kr/search/detail/view.do?bibCtrlNo=568621&flag=dissertation
Appears in Collection
AE-Theses_Ph.D.(박사논문)
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