Accession Number : AD0742929

Title :   The Derivation, Solution, and Analysis of Airplane Spin Equations Modeled in an Inertial Coordinate System.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : Buehler, Roy Robert

Report Date : MAR 1972

Pagination or Media Count : 66

Abstract : The general equations of motion for a rigid body are derived in cylindrical coordinates by Lagrangian dynamics and used to model the motion of an airplane in a steady spin. After simplification, the equations are cast into a form utilizing conventional aerodynamic derivatives along with other derivatives which may be significant in spins. An iterative numerical solution procedure is outlined which should simplify the problem of solving the nonlinear differential equations, and relationships between the Euler Angles used in the equations and the more familiar ordered set of pitch, roll, and yaw are derived to permit computer input and output of orientation to be more easily visualized. (Author)

Descriptors :   *AERONAUTICS, SPINNING(MOTION), EQUATIONS OF MOTION, ITERATIONS, EULER ANGLES, AERODYNAMIC LOADING, MATHEMATICAL MODELS, THESES.

Subject Categories : Aerodynamics

Distribution Statement : APPROVED FOR PUBLIC RELEASE