A new design framework for impact time control
Başlık çevirisi mevcut değil.
- Tez No: 539790
- Danışmanlar: Prof. Dr. FLORIAN HOLZAPFEL
- Tez Türü: Doktora
- Konular: Hava ve Uzay Hekimliği, Havacılık Mühendisliği, Uçak Mühendisliği, Air and Space Medicine, Aeronautical Engineering, Aircraft Engineering
- Anahtar Kelimeler: Impact Time Control, Trajectory Shaping, Constrained Guidance, Varying Speed
- Yıl: 2018
- Dil: İngilizce
- Üniversite: Technische Universität München
- Enstitü: Yurtdışı Enstitü
- Ana Bilim Dalı: Belirtilmemiş.
- Bilim Dalı: Belirtilmemiş.
- Sayfa Sayısı: 219
Özet
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Özet (Çeviri)
This dissertation focuses on the problem of impact time control by utilizing a new design framework that is stated as shaping the fundamental states of the engagement via polynomials in time. The specific application considered in the study is missile guidance; however, the techniques developed are in principle applicable to any practical setting that concerns the time of arrival. Identifying the range and the look angle as the fundamental states that define the nonlinear engagement kinematics between a missile and a stationary target, three different guidance laws to control the impact time are derived by means of the proposed framework. Through these methods, none of which require the time-to-go to be estimated, the time domain solutions of various engagement variables are made available. The first guidance law is the result of shaping the range as a general form polynomial, whose coefficients are derived for any order. The method can be implemented either as open loop or as closed loop, the latter showing robustness in the presence of disturbing factors such as noise and autopilot lag. The second guidance law is based on a multi-phased look angle profile, where the phases are characterized by straight line segments. This structure makes it possible to calculate the minimum and maximum impact times under the acceleration and look angle constraints. The third guidance law follows from a similar approach as the first one. The look angle is shaped in the form of a general order polynomial. Both open- and closed-loop mechanizations are possible. Unlike the previous ones, the guidance gain must be obtained either by solving an integral equation or by linearizing the system. In addition, the impact time control problem is solved under varying speed, which is typically caused by drag and gravity. For this purpose, a predictive-adaptive algorithm, which adapts the gain of the third guidance law with respect to the predicted mean speed, is proposed.
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