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Polynomial Guidance Laws Considering Terminal Impact Angle and Acceleration Constraints

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4 Author(s)
Chang-Hun Lee ; Dept. of Aerosp. Eng., Korea Adv. Inst. of Sci. & Technol. (KAIST), Daejeon, South Korea ; Tae-Hun Kim ; Min-Jea Tahk ; Ick-Ho Whang

The work presented here investigates proposed impact angle control guidance laws with terminal acceleration constraints for a stationary or slowly moving target. These laws, called time-to-go polynomial guidance (TPG), assume the guidance command as a polynomial function of time-to-go and determine the coefficients of the guidance command to satisfy the specified terminal constraints. The closed-form trajectory solutions of the guidance command and the target look angle for lag-free systems are derived and their characteristics are investigated. Based on the results we propose a systematic method to find the guidance gains that satisfy practical limits, such as the actuator's command limit and the seeker's field-of-view (FOV) limit. A time-to-go estimation method is also discussed for implementing TPG. Nonlinear and adjoint simulations are performed to investigate the performance of TPG.

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Aerospace and Electronic Systems, IEEE Transactions on  (Volume:49 ,  Issue: 1 )