Two stage damage tolerance evaluation of an aircraft fuselage panel with a circumferential crack and a broken stringer

This chapter presents a new alternative approach to the analysis of the fatigue life of aircraft fuselage parts considering the compliance of internal elements to replace the classical model of critical crack size. In this case, from a global–local analysis using the boundary element method (BEM), induced stresses at a macro model, and their effects on micro models are evaluated. The BEM enables efficient simulations of the propagation of initial defects to assess the damage tolerance. For this purpose, computational techniques were developed that allowed evaluating these models, through a probabilistic treatment to assess damage tolerance and fatigue life. Finally, this technique is shown as an alternative to ensure the integrity and proper operation of fuselage panels avoiding reaching a Limit State during its projected lifespan.

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Damage Tolerance Analysis of Aircraft Fuselage Riveted Joint Panel

International Journal of Engineering Research and ◽

10.17577/ijertv4is050886 ◽

2015 ◽

Vol V4 (05) ◽

Author(s):

S. Sivakumar ◽

S. Balaji ◽

Keyword(s):

Damage Tolerance ◽

Tolerance Analysis ◽

Aircraft Fuselage ◽

Riveted Joint ◽

Damage Tolerance Analysis

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An Engineer'S Viewpoint on Design and Analysis of Aircraft Structural Joints

Proceedings of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering ◽

10.1243/pime_proc_1995_209_278_02 ◽

1995 ◽

Vol 209 (2) ◽

pp. 105-129 ◽

Cited By ~ 20

Author(s):

L J Hart-Smith

Keyword(s):

Composite Structures ◽

Damage Tolerance ◽

Weak Link ◽

Basic Structure ◽

High Load ◽

Adhesively Bonded ◽

Aircraft Fuselage ◽

New Ideas ◽

Mechanically Fastened ◽

Wing Skin

The design of structurally efficient joints in aircraft fuselage structures and wing skin splices is addressed. It is contended that the joints should be designed first and the gaps in between filled in afterwards, taking pains not to optimize the basic structure first and then discover that it either cannot be assembled or that, when it is assembled, it is full of weak-link fuses. Both adhesively bonded and mechanically fastened joints are covered. Analogies are drawn between the characteristics of both classes of joints. The aspects of static joint strength and fatigue lives are included. The work is applicable to metallic as well as composite structures, and covers both high-load wing joints which have already been tested and new ideas for fuselage splices which have not. The effects of flaws and defects are associated with the need for damage tolerance, particularly in fuselage structures.

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Two-stage self-seeding method for preparation of single crystals of poly(phenylene sulfide)

Proceedings, annual meeting, Electron Microscopy Society of America ◽

10.1017/s0424820100153816 ◽

1989 ◽

Vol 47 ◽

pp. 368-369

Author(s):

Sengshiu Chung ◽

Peggy Cebe

Keyword(s):

Single Crystals ◽

High Performance ◽

Dilute Solution ◽

Two Stage ◽

Annealing Behavior ◽

High Performance Polymers ◽

Seeding Method ◽

Phenylene Sulfide

We are studying the crystallization and annealing behavior of high performance polymers, like poly(p-pheny1ene sulfide) PPS, and poly-(etheretherketone), PEEK. Our purpose is to determine whether PPS, which is similar in many ways to PEEK, undergoes reorganization during annealing. In an effort to address the issue of reorganization, we are studying solution grown single crystals of PPS as model materials.Observation of solution grown PPS crystals has been reported. Even from dilute solution, embrionic spherulites and aggregates were formed. We observe that these morphologies result when solutions containing uncrystallized polymer are cooled. To obtain samples of uniform single crystals, we have used two-stage self seeding and solution replacement techniques.

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