Polynomial Guidance Laws Considering Terminal Impact Angle and Acceleration Constraints

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...

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Bibliographic Details
Published inIEEE transactions on aerospace and electronic systems Vol. 49; no. 1; pp. 74 - 92
Main Authors Lee, Chang-Hun, Kim, Tae-Hun, Tahk, Min-Jea, Whang, Ick-Ho
Format Journal Article
LanguageEnglish
Published New York IEEE 01.01.2013
The Institute of Electrical and Electronics Engineers, Inc. (IEEE)
Subjects
Acceleration
Gravity
Kinematics
Missiles
Polynomials
Trajectory
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Summary: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.
ISSN:0018-9251
1557-9603
DOI:10.1109/TAES.2013.6404092