Abstract
Under the condition of large maneuvering and small overload, the improved trajectory shaping guidance law is easy to implement in engineering, so that the medium and long range missile can not only attack from the front, but also attack vertically from the top or even from the tail or side with large maneuvering, obtain a reasonable impact angle and a small angle of attack, and achieve the best hit effect. Also, maintaining the database security and the capacity of resisting disturbance during the use of trajectory shaping guidance law is an important issue. In this paper, the trajectory shaping guidance law in the case of large maneuvering and small overload is derived and studied, the mathematical model of the remain flight time is derived and the influence of its deviation on the flight trajectory is analyzed. It provides theoretical and simulation support for the missile to complete the mission of high maneuverability and precision attack under the condition of small overload. The security of using database is discussed.
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Miao, L., Lei, W., Chao, X. (2021). Trajectory Shaping Guidance Law of Homing Missile with High Maneuver and Low Overload and Its Database Security. In: Cheng, J., Tang, X., Liu, X. (eds) Cyberspace Safety and Security. CSS 2020. Lecture Notes in Computer Science(), vol 12653. Springer, Cham. https://doi.org/10.1007/978-3-030-73671-2_22
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DOI: https://doi.org/10.1007/978-3-030-73671-2_22
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