Accession Number : ADP005999

Title :   An Analysis Method for Bolted Joints in Primary Composite Aircraft Structure,

Corporate Author : SAAB-SCANIA A B LINKOEPING (SWEDEN)

Personal Author(s) : Eriksson, Ingvar

Report Date : MAR 1988

Pagination or Media Count : 19

Abstract : The analysis of bolted joints in composite structure requires, like structural analysis in general, methods for determining the stress distributions and relevant failure criteria. The stress analysis procedure discussed in this paper starts by addressing the joints as an integrated part of the overall structure. The stresses in the vicinity of the hole boundary are obtained through a series of finite element analyses, which starts with an overall load distribution analysis and ends with a 2-dimensional detailed contact stress analysis of the most highly stressed region in the joint. Strength is predicted for two basic failure modes occuring in a joint, net-tension and bearing failure. The failure hypotheses for these failure modes are described. Both the stress analysis and failure hypotheses are performed and established, respectively under certain idealizations. The conditions, in a real joint in an aircraft may differ from these idealizations. Hence, further work is required and is also proposed in this paper. The analysis procedure described in this paper is based on today's powerful computer facilities and offer great advantages compared with more empirical procedures. The procedure is presently used at Saab Aircraft Division. (SDW)

Descriptors :   *BOLTED JOINTS, *COMPOSITE STRUCTURES, *STRESS ANALYSIS, AIRCRAFT, COMPOSITE AIRCRAFT, COMPUTERS, DISTRIBUTION, FACILITIES, FAILURE, FINITE ELEMENT ANALYSIS, HYPOTHESES, LOAD DISTRIBUTION, REGIONS, STRESSES, STRUCTURAL ANALYSIS.

Subject Categories : Couplers, Fasteners, and Joints
      Laminates and Composite Materials
      Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE