Angular Steering for Proportional Navigation-commanded Surface-to-air Guided Missile

  • Deepak Kumar Indian Institute of Technology Roorkee, Roorkee
  • R. N. Mishra Indian Institute of Technology Roorkee, Roorkee
DOI: https://doi.org/10.14429/dsj.56.1910
Keywords: Surface-to-air missile trajectories, surface-to-air missile launch equations, proportional navigation guidance

Abstract

The paper briefly reviews the guidance laws and their implementation in surface-to-air
missiles. The trajectories for the line-of-sight and proportional navigation guidance laws are
discussed and the effect of steering on demand for increased lateral acceleration is appreciated.
The mathematical model is then evolved to estimate the launch angle of the missile, ie, bearing
and elevation, in the direction of the future position of the moving air target as well as the
steering commands in pitch and yaw planes in accordance with the proportional navigation
guidance law, to enable collision with the target.
Published
2006-10-01
How to Cite
Kumar, D., & Mishra, R. (2006). Angular Steering for Proportional Navigation-commanded Surface-to-air Guided Missile. Defence Science Journal, 56(4), 437-449. https://doi.org/10.14429/dsj.56.1910
Issue
Vol 56 No 4
Section
Aeronautical Systems
Copyright (c) 2016 Defence Science Journal

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