Derivation of an automatic aircraft elevator controller

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Authors
Nielsen, Donald Reay.
Subjects
Aircraft landing
Optimal control
Trajectory optimization
Advisors
Strum, Robert D.
Date of Issue
1967-06
Date
June 1967
Publisher
Monterey, California. U.S. Naval Postgraduate School
Language
en_US
Abstract
An automatic elevator controller for the final phase of an Instrument Landing System approach is designed using optimization theory and the practicality of the controller investigated. The problem is discussed and the assumptions stated. Then a mathe- matical model for the aircraft and a desired flare-out approach path are derived. The aircraft and approach limitations are established and the model is tested. Dynamic programming and the Parametric Expansion Method provide the optimal control from which the controller is designed. A computer program is developed to investigate the controller. The results are inconclusive and a recommendation for further study is made.
Type
Thesis
Description
Series/Report No
Department
Department of Electrical Engineering
Organization
Naval Postgraduate School
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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