Prediction of airplane steady spin conditions by a parameter optimization scheme
Loading...
Authors
Keith, Stephen Thomas
Subjects
Aircraft
Steady spin prediction
Cylindrical coordinate model
Lagrange derivation of equations
Parameter optimization
Computer prediction program
Density variation effect
Steady spin prediction
Cylindrical coordinate model
Lagrange derivation of equations
Parameter optimization
Computer prediction program
Density variation effect
Advisors
Redlin, Michael H.
Date of Issue
1973-09
Date
September 1973
Publisher
Monterey, California: Naval Postgraduate School
Language
eng
Abstract
To aid in the modeling of a steady state spin, the equations of motion of an airplane are formulated in a cylindrical coordinate reference frame. The derivation of the equations is
presented and the resulting equations are simplified for the equilibrium spin condition. These simplified equations are used in an unconstrained computer parameter optimization technique that algebraically solves the differential equations for the equilibrium state. The results of the computer work are presented and compared with previous prediction schemes. The potential of the method is demonstrated by application to a study of the effects of density variation.
Type
Thesis
Description
Series/Report No
Department
Aeronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funding
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.