Procedural guide for modelling and analyzing the flight characteristics of a helicopter design using Flightlab
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Authors
McVaney, Gary P.
Subjects
Helicopter design
Analysis
Flight characteristics
Flight simulation
Computer modeling
Analysis
Flight characteristics
Flight simulation
Computer modeling
Advisors
Wood, E. Roberts
Date of Issue
1993-09
Date
September 1993
Publisher
Monterey, California. Naval Postgraduate School
Language
en_US
Abstract
This thesis presents one method for modelling and analyzing a helicopter design using Flightlab. Flightlab is a computer program that provides for engineering design, analysis and simulation of aircraft using non-linear dynamic modeling techniques. The procedure to model a single main rotor helicopter is outlined using the sample helicopter design in the book 'Helicopter Performance, Stability, and Control' by Ray Prouty. The analysis procedure contains computer program scripts for determining the time response of the helicopter to standard control inputs such as a longitudinal impulse, a lateral step, and a pedal doublet. A linear model of the helicopter can be extracted from the non-linear model, and a comparison of the time response to the control inputs based on these two models is presented. The procedure for conducting frequency sweep testing for the linear model is also discussed. This guide to using Flightlab for aircraft modelling and analysis is designed to make it easier to use Flightlab for creating additional aircraft models for use in control system analysis and additional engineering design.
Type
Thesis
Description
Series/Report No
Department
Department of Aeronautics and Astronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
143 p.
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.