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Design of Linear Flight Control Systems Using Optimal Control Theory.


AD600694

Publication Date 1964
Personal Author Rynaski, E. G.; Reynolds, P. A.; Shed, W. H.
Page Count 2
Abstract This report describes a study of the application of optimal control techniques based on a generalized quadratic performance index to the primary control system design of an X-15type aircraft and a large flexible booster. The following aspects of the application of optimal theory were studied: (1) The use of mathematical models to obtain desirable transient characteristics; (2) realizability of feedback configurations; (3) a comparison between optimal and conventional design techniques; (4) relationships between the weighting factor of the performance index and the dynamics of the optimal system; and (5) the use of an IBM 7090 program to obtain optimal solutions of the control problems. (Author)
Keywords
  • FLIGHT CONTROL SYSTEMS
  • OPTIMIZATION
  • AIRCRAFT EQUIPMENT
  • LINEAR SYSTEMS
  • AERODYNAMIC CHARACTERISTICS
  • MATHEMATICAL MODELS
  • DIFFERENTIAL EQUATIONS
  • PROGRAMMING (COMPUTERS)
  • PERFORMANCE (ENGINEERING)
Corporate Authors Cornell Aeronautical Lab Inc Buffalo N Y
Document Type Technical Report
NTIS Issue Number 196501
Contract Number
  • AF33 657 7498
Design of Linear Flight Control Systems Using Optimal Control Theory.
Design of Linear Flight Control Systems Using Optimal Control Theory.
AD600694

  • FLIGHT CONTROL SYSTEMS
  • OPTIMIZATION
  • AIRCRAFT EQUIPMENT
  • LINEAR SYSTEMS
  • AERODYNAMIC CHARACTERISTICS
  • MATHEMATICAL MODELS
  • DIFFERENTIAL EQUATIONS
  • PROGRAMMING (COMPUTERS)
  • PERFORMANCE (ENGINEERING)
  • AF33 657 7498
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