Accession Number:

ADA050763

Title:

Certification Procedures for Composite Structures.

Descriptive Note:

Corporate Author:

ADVISORY GROUP FOR AEROSPACE RESEARCH AND DEVELOPMENT NEUILLY-SUR-SEINE (FRANCE)

Personal Author(s):

Report Date:

1978-01-01

Pagination or Media Count:

43.0

Abstract:

The Naval Air Systems Command NAVAIR anticipates that graphiteepoxy composites will be in used in the wings of production aircraft of the Model F-18 and AV-8B Advanced Harrier aircraft. The F-18 wing will utilize composite, full span, upper and lower skins. The AV-8B wing will incorporate composite sine wave substructure as well as full span upper and lower skins. This paper describes the criteria which presently determine the permissible use of composites in production aircraft and the adaptation of an existing framework of aircraft certification practices to the special characteristics of composites. Factors involving the scheduling of full-scale static and fatigue tests and their effect on the use of composites are discussed. Static and fatigue design and test loads are described. Small and large scale element testing is covered. Some of the structural design problems and loadstrain criteria are described. Typical procedures governing the development and interpretation of design data, laboratory and flight tests are explained. Author

Subject Categories:

  • Attack and Fighter Aircraft
  • Ceramics, Refractories and Glass
  • Laminates and Composite Materials
  • Plastics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE