• 제목/요약/키워드: Missile agile turn maneuver

검색결과 2건 처리시간 0.016초

Guidance Law for Agile Turn of Air-to-Air Missile During Boost Phase

  • Han, Seungyeop;Bai, Ji Hoon;Hong, Seong-Min;Roh, Heekun;Tahk, Min-Jea;Yun, Joongsup;Park, Sanghyuk
    • International Journal of Aeronautical and Space Sciences
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    • 제18권4호
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    • pp.709-718
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    • 2017
  • This paper proposes the guidance laws for an agile turn of air-to-air missiles during the initial boost phase. Optimal solution for the agile turn is obtained based on the optimal control theory with a simplified missile dynamic model. Angle-of-attack command generating methods for completion of agile turn are then proposed from the optimal solution. Collision triangle condition for non-maneuvering target is reviewed and implemented for update of terminal condition for the agile turn. The performance of the proposed method is compared with an existing homing guidance law and the minimum-time optimal solution through simulations under various initial engagement scenarios. Simulation results verify that transition to homing phase after boost phase with the proposed method is more effective than direct usage of the homing guidance law.

Missile Autopilot Design for Agile Turn Control During Boost-Phase

  • Ryu, Sun-Mee;Won, Dae-Yeon;Lee, Chang-Hun;Tahk, Min-Jea
    • International Journal of Aeronautical and Space Sciences
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    • 제12권4호
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    • pp.365-370
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    • 2011
  • This paper presents the air-to-air missile autopilot design for a $180^{\circ}$ heading reversal maneuver during boost-phase. The missile's dynamics are linearized at a set of operating points for which angle of attack controllers are designed to cover an extended flight envelope. Then, angle of attack controllers are designed for this set of points, utilizing a pole-placement approach. The controllers' gains in the proposed configuration are computed from aerodynamic coefficients and design parameters in order to satisfy designer-chosen criteria. These design parameters are the closed-loop frequency, damping ratio, and time constant; these represent the characteristics of the control system. To cope with highly nonlinear and rapidly time varying dynamics during boost-phase, the global gain-scheduled controller is obtained by interpolating the controllers' gains over variations of the angle of attack, Mach number, and center of gravity. Simulation results show that the proposed autopilot design provides satisfactory performance and possesses good [ed: or "sufficient" or "excellent"] capabilities.