Aero-Elastic Motion of a Spin-Stabilized Projectile
Abstract
The elastic flight motion of a slowly spinning finned missile has been successfully described by the finite element method (FEM). With the addition of a Magnus force distribution function, this analysis was used to describe the elastic flight motion of a spin-stabilized projectile. Transient frequencies and damping rates for a 10-cal. cone cylinder have been calculated. The elastic frequencies for a rapidly spinning projectile can be substantially different from those for zero spin. A slightly bent projectile can have a large deflection when its spin rate is near an elastic frequency. Resonant motion is demonstrated when the spin is near the first positive elastic frequency. The maximum strain associated with this motion can exceed the plastic limit.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 01, 2005
- Accession Number
- ADA441027
Entities
People
- Charles H. Murphy
- William H. Mermagen Sr
Organizations
- United States Army Research Laboratory