Analytical Missile Guidance Laws with a Time-Varying Transformation
A class of proportional navigation guidance laws is derived via an approximation of time-to-go and a transformation of state variables. The optimal guidance problem is developed in polar coordinates. This problem is shown to decompose into two decoupled optimal control problems, where a closed-form control solution is available in the radial direction and a time-varying linear dynamics system is solved for control in the transverse direction.
S. N. Balakrishnan, "Analytical Missile Guidance Laws with a Time-Varying Transformation," Journal of Guidance, Control, and Dynamics, American Institute of Aeronautics and Astronautics (AIAA), Jan 1996.
The definitive version is available at https://doi.org/10.2514/3.21646
Mechanical and Aerospace Engineering
International Standard Serial Number (ISSN)
Article - Journal
© 1996 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.
01 Jan 1996