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Velocity Maximizing Suboptimal Control Law for Agile Turn of Air-to-Air Missile
Seungyeop Han,Min Ki Kim,Min-Jea Tahk,Yun-Young Kim 제어로봇시스템학회 2016 제어로봇시스템학회 국제학술대회 논문집 Vol.2016 No.10
In this paper, optimal control problems considering agile turn of missile as maximizing terminal velocity at boost phase are dealt. The missile in the phase experiences dramatic variation in velocity, mass and angle of attack within finite duration. This research at first, classifies the missile models into two different cases; longitudinal motion and lateral motion, but all of the models neglect aerodynamic forces. Each model has an optimal solution known as Bang-Singular Control, and the corresponding optimal control as well as switching condition for Bang to Singular is analytically derived. After the derivation of optimal solutions, two different suboptimal control laws which are based on the optimal solutions and capable of aerodynamic forces are proposed. The first law uses the optimal solution directly while the other incorporates theoretical aerodynamic equations. A comparison between results from the proposed control laws, results from PD type control law and optimal results from a commercial optimization tool are presented and usefulness of proposed method is validated through the comparison.
Guidance Law for Agile Turn of Air-to-Air Missile During Boost Phase
Seungyeop Han,Ji Hoon Bai,Seong-Min Hong,Heekun Roh,Min-Jea Tahk,Joongsup Yun,Sanghyuk Park 한국항공우주학회 2017 International Journal of Aeronautical and Space Sc Vol.18 No.4
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.
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 The Korean Society for Aeronautical and Space Scie 2017 International Journal of Aeronautical and Space Sc Vol.18 No.4
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.