The Derivation, Solution, and Analysis of Airplane Spin Equations Modeled in an Inertial Coordinate System.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 1972
- Accession Number
- AD0742929
Entities
People
- Roy Robert Buehler
Organizations
- Naval Postgraduate School