Application of H Control to pitch autopilot of missiles

S. M. Yang, N. H. Huang

Research output: Contribution to journalArticlepeer-review

19 Citations (Scopus)


The pitch rate control of a missile is analyzed by an H controller. The system dynamics governing the aerodynamic stability derivatives and airframe structure vibration is formulated in a generalized state space realization form. This formulation facilitates the γ-iteration method in solving the associated Ricatti equation of the 4-block H control problem. It is shown that the H controller, because of its loop shaping capabilities, can provide improved tracking performance and stability robustness compared with H2 (linear-quadratic-Gaussian (LQG)) and classical proportional-integral-derivative (PID) controller in the rigid airframe model. When airframe flexibility effect is considered, the H controller is also shown to be robust under structure natural frequency variations.

Original languageEnglish
Pages (from-to)426-433
Number of pages8
JournalIEEE Transactions on Aerospace and Electronic Systems
Issue number1
Publication statusPublished - 1996

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Electrical and Electronic Engineering


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