Integrated missile guidance law and autopilot design using linear optimal control

Taylor L Hughes, Michael B. McFarland

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Optimal guidance laws and autopilots for missiles are typically developed separately. Since this separation may result in an inefficient implementation, it is desirable to investigate integrated design approaches. In this paper, a simplified planar model for missile intercept dynamics is examined. Feedback linearization and simple linear approximations are considered for transforming the dynamics into a linear form suitable for the application of optimal control techniques. Control commands are then computed to minimize miss distance directly, without intermediate acceleration commands. Preliminary results obtained from simulations of an aerodynamically stable vehicle against non-maneuvering targets indicate that this implementation is comparable to traditional proportional navigation with a high navigation gain. For unstable systems, however, achieving both target intercept and attitude stabilization proves problematic because of limitations inherent in the problem formulation.

Original languageEnglish (US)
Title of host publicationAIAA Guidance, Navigation, and Control Conference and Exhibit
DOIs
StatePublished - Dec 1 2000
Externally publishedYes
EventAIAA Guidance, Navigation, and Control Conference and Exhibit 2000 - Dever, CO, United States
Duration: Aug 14 2000Aug 17 2000

Publication series

NameAIAA Guidance, Navigation, and Control Conference and Exhibit

Other

OtherAIAA Guidance, Navigation, and Control Conference and Exhibit 2000
Country/TerritoryUnited States
CityDever, CO
Period8/14/008/17/00

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering

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