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H Design of the F/A-18A Automatic Carrier Landing System

Chapter
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Part of the Systems Control: Foundations & Applications book series (SCFA)

Abstract

In this chapter a design of the F/A-18A Automatic Carrier Landing System is accomplished using finite horizon H techniques. If the final time is sufficiently large, the dynamic Riccati equations involved in the design of the suboptimal output feedback controller give rise to constant solutions. Only longitudinal equations of motion are considered, and thrust is incorporated as a control variable. The object of the design is to maintain a constant flight path angle under worst-case conditions of vertical gust and sensor noise during carrier landing. The design yields satisfactory response for vertical rate command as well.

Keywords

Output Feedback Sensor Noise Finite Horizon Output Feedback Controller Flight Control System 
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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References

  1. [1]
    Urnes, J. M., Hess, R. K., Moomaw, R. F., And Huff, R. W., “Development of the Navy H-dot Automatic Carrier Landing System Designed to give Improved Approach Control in Air Turbulence,” Proceedings of the AIAA Guidance and Control Conference, Boulder, Colorado, 1979, pp. 491–501.Google Scholar
  2. [2]
    Urnes, J. M. And Hess, R. K., “Development of the F/A-18A Automatic Carrier Landing System,” Journal of Guidance, Control, and Dynamics, Vol. 8, May-June 1985, pp. 289–295.CrossRefGoogle Scholar
  3. [3]
    “F/A-18A Flight Control System Design Report,” Vols. I,II, and III, Report No. MDC A7813, McDonnell Aircraft Company, St. Louis, Missouri, September 1988.Google Scholar
  4. [4]
    Subrahmanyam, M. B., “General Formulae for Suboptimal H∞ Control over a Finite Horizon,” International Journal of Control, Vol. 57, No. 2, 1993, pp. 365–375.MathSciNetzbMATHCrossRefGoogle Scholar
  5. [5]
    “Automatic Carrier Landing System, Airborne Subsystem, General Requirements for,” AR-40A, Naval Air Systems Command, Washington, D.C., May 1975.Google Scholar
  6. [6]
    “Control and Stabilization Systems: Automatic Piloted Aircraft, General Specifications for,” MIL-C-18244A, Bureau of Naval Weapons, Department of the Navy, Washington, D.C., December 1962.Google Scholar

Copyright information

© Birkhäuser Boston 1995

Authors and Affiliations

  1. 1.Flight Dynamics and Control Branch Air Vehicle & Crew Systems Technoly Dept.Naval Warfare Center Aircraft DivisionWarminsterUSA

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