서지주요정보
Stability of homing guidance loop with missile dynamics = 미사일 다이내믹스를 고려한 호우밍 유도 루우프의 안정성 해석
서명 / 저자 Stability of homing guidance loop with missile dynamics = 미사일 다이내믹스를 고려한 호우밍 유도 루우프의 안정성 해석 / Dong-Young Rew.
발행사항 [대전 : 한국과학기술원, 1996].
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8006215

소장위치/청구기호

학술문화관(문화관) 보존서고

DAE 96004

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초록정보

New approaches named $t^n$-stability of zero effort miss and short-time stability of guidance loop are introduced for analyzing the stability of homing guidance loop which includes the non-ideal missile/autopilot dynamics. In $t^n$-stability criterion, guidance loop stability is defined as the monotonic convergence of the zero effort miss to zero which is directly related with the miss distance in the intercept engagement. This criterion is applied to the general homing guidance law for which guidance command is proportional to the zero effort miss. Stability conditions for the general homing guidance law show that the guidance loop con be $t^n$-stable until the target interception if the guidance law is proportional to the zero effort miss and the guidance gain increases satisfying the condition derived is this study. This result gives guidelines for selecting the guidance gain of a given homing guidance law. The $t^n$-stability of zero effort miss is also applied to the analysis of a PN guidance loop. Upper bounds and lower bounds of PN guidance gain for $t^n$-stability are derived for the guidance loop with 1st-order missile dynamics. The short-time stability criterion is extended to accommodate time-varying state weights and time-varying bounds of the state norm, and it is applied to the PN guidance loop stability analysis. An interval during which the guidance loop is stable is defined as stability region and the lower bound of the stability region in the sense of short-time stability is derived. Different from the previous results based on the Popov stability or hyperstability, this condition depends on the total flight time in such a way that the lower bounds of the stability region is reduced. A comparison study of stability conditions based on the Popov stability criterion, $t^n$-stability theorem, and short-time stability theorem shows that the Popov stability condition is most conservative and the short-time stability condition is least conservative. To extend the stability region, the time-to-go freezing technique is introduced. Effects of time-to-go freezing on guidance loop stability is analyzed by using the short-time stability theorem developed in this study. Short-time stability theory is used to determine the time of time-to-go freezing. Simulation results of PN guidance loop with time-to-go freezing show that the time to go freezing technique enhances the stability of the guidance loop.

서지기타정보

서지기타정보
청구기호 {DAE 96004
형태사항 ix, 90 p. : 삽화 ; 26 cm
언어 영어
일반주기 저자명의 한글표기 : 류동영
지도교수의 영문표기 : Min-Jea Tahk
지도교수의 한글표기 : 탁민제
학위논문 학위논문(박사) - 한국과학기술원 : 항공우주공학과,
서지주기 Reference : p. 88-92
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