Near-Optimal Guidance Law for Ballistic Missile Interception-Reference-Cited by-同舟云学术

Near-Optimal Guidance Law for Ballistic Missile Interception

Published:1997-03 Issue:2 Volume:20 Page:355-361
ISSN:0731-5090
Container-title:Journal of Guidance, Control, and Dynamics
language:en
Short-container-title:Journal of Guidance, Control, and Dynamics

Author:

Dougherty John J.¹,Speyer Jason L.²

Affiliation:

1. TRW Systems Integration Group, San Bernardino, California 92402

2. University of California, Los Angeles, Los Angeles, California 90095

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Applied Mathematics,Electrical and Electronic Engineering,Space and Planetary Science,Aerospace Engineering,Control and Systems Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/2.4046

Reference18 articles.

1. 3Feeley, T. S. “Approximate Optimal Guidance for the Advanced Launch System,” Ph.D. Thesis, Dept. of Aerospace Engineering and Engineering Mechanics,Univ. of Texas, Austin, TX,1991.

2. Techniques for developing approximate optimal advanced launch system guidance

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