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摘要
This paper presents a new approach in nonlinear guidance law design. The new guidance law is developed based on partial stability theorem and enables the missile to intercept highly maneuvering targets with zero-miss-distance within a finite interception time. The approach is advantageous from practical view-points since it leads to classification of state variables of the guidance system dynamic with respect to their required stability properties and tries to adapt with practical situations. Effectiveness of the proposed guidance law in achieving zero-miss-distance within a finite interception time is demonstrated analytically and through computer simulations.
- 出版日期2012-5
