Generalized Guidance Law for Homing Missiles

Ciann Dong Yang, Fei Bin Hsiao, Fang Bo Yeii

Research output: Contribution to journalArticlepeer-review

34 Citations (Scopus)


The utmost purpose of using a guidance law for a homing missile is to turn the heading of the missile toward some desired direction as rapidly as possible by commanding the acceleration of the missile proportional to the angular rate of such direction. Such a direction may be simply along the line of sight, the missile collision course, or any other appropriate direction. The generalized guidance law presented here covers a wide variety of guidance laws; some have appeared in the literature, while most of them are totally new. Based on the exact nonlinear equations of motion, general analytical expressions for capture area, missile commanded acceleration, and homing time duration are derived in closed forms. An optimal nonlinear guidance law originating from this generalized guidance law, which minimizes a weighted linear combination of the time of capture and energy expenditure, is also derived. The efficiency and mechanization of the generalized guidance law and the comparisons with various existing guidance laws are demonstrated in a simulation study. The miss distance due to seeker/autopilot dynamics, maneuvering targets, acceleration saturation, and measurement bias is also investigated.

Original languageEnglish
Pages (from-to)197-212
Number of pages16
JournalIEEE Transactions on Aerospace and Electronic Systems
Issue number2
Publication statusPublished - 1989 Mar

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Electrical and Electronic Engineering


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