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

Authors

  • 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.

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Published

2006-10-01

How to Cite

Kumar, D., & Mishra, R. N. (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

License

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