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    Polynomial Guidance Laws Considering Terminal Impact Angle and Acceleration Constraints  
    Chang-Hun Lee(KAIST)
    Korea | IEEE Transactions on Aerospace and Electronic Syst
    2013 | 바로가기
    Acceleration, Missiles, Polynomials, Trajectory, Kinematics, Gravity
    Cited by 141

    ■ View full text

    IEEE Transactions on Aerospace and Electronic Systems, Vol. 49, No. 1,

    https://ieeexplore.ieee.org/abstract/document/6404092

     

     

    ■ Researchers

    Chang-Hun Lee

    Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology (KAIST)

    C. H. Lee*, T. H. Kim, M. J. Tahk, and I. H. Whang

     

     

    ■ Abstract

    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 is command limit and the seeker is 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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