Accession Number : ADA131904

Title :   Alternate T-38 Transparency Development. Part 4. Parametric Studies.

Descriptive Note : Final rept. Jan 80-Feb 81,


Personal Author(s) : Nash,Richard A ; West,Blaine S

PDF Url : ADA131904

Report Date : Jun 1983

Pagination or Media Count : 108

Abstract : Studies conducted to examine the effect of structural parameter variations on the nonlinear, dynamic response of the T-38 student windshield/support structure system to bird impact are described. The studies were conducted using the materially and geometrically nonlinear analysis (MAGNA) finite element computer program. Both static and transient dynamic analyses were conducted, examining the effects of changes to the transparency and support structure stiffness, intensity of the applied load both coupled and uncoupled, and duration of the impact event. Significant results of the finite element analysis include transparency deflection, peak load versus transparency stiffness, and resultant force plots both along the aft arch and around the impact area. A discussion of application of the finite element method to the birdstrike problem is also presented. (Author)

Descriptors :   *Aircraft canopies, *Windshields, *Bird strikes, Impact tests, Loads(Forces), Structural response, Finite element analysis, Dynamic response, Nonlinear analysis, Geometric forms, Peak values, Parametric analysis, Parametric analysis, Deflection, Polycarbonates, Acrylic resins, Laminated plastics, Transparencies, Computer programs, Computer aided diagnosis, Jet training aircraft

Subject Categories : Training Aircraft
      Laminates and Composite Materials
      Numerical Mathematics

Distribution Statement : APPROVED FOR PUBLIC RELEASE