Analytical Determination of Aircraft Spin Modes.
Abstract
Six non-linear equations of motion for a rigid body are used to model the aircraft's motion while in a spin. After applying the conditions for an equilibrium spin, the resulting six non-linear simultaneous equations are solved using a method that is accurate and well suited for use with a high-speed digital computer. The solution yields the equilibrium spin conditions and these solutions were usually obtained with less than three seconds of computer time. These results are compared with the results from previous prediction schemes. The linear characteristics of the aircraft about the equilibrium points are also presented. The model chosen for this study was a delta-wing fighter configuration.
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1974
- Accession Number
- ADA004798
Entities
People
- David L. Westgate
Organizations
- Air Force Institute of Technology