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Designs for Linearized Aircraft Models

  • Gang Tao
  • Shuhao Chen
  • Xidong Tang
  • Suresh M. Joshi
Chapter

Abstract

Actuator failures encountered in aircraft flight control systems may cause severe performance deterioration and even catastrophic instability. The nature of such failures, in terms of which actuators have failed, failure parameters (e.g., position of a stuck control surface), and the time of failures are usually not known. Adaptive failure compensation designs are desirable for handling such system uncertainties, as shown by recent research results (see Section 1.1.1). The goal of this chapter is to apply several adaptive actuator failure compensation control schemes to a linearized aircraft model to verify the desired system performance under different actuator failure situations.

Keywords

State Feedback Pitch Angle Failure Pattern State Tracking Output Tracking 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag London 2004

Authors and Affiliations

  • Gang Tao
    • 1
  • Shuhao Chen
    • 1
  • Xidong Tang
    • 1
  • Suresh M. Joshi
    • 2
  1. 1.Department of Electrical and Computer EngineeringUniversity of VirginiaCharlottesvilleUSA
  2. 2.Langley Research CenterDynamics and Control Branch, NASAHamptonUSA

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