The Rivet Parameter Influence in Fatigue Strength

• Autorzy: Fuiorea I. , Bartis D. , Nedelcu R. , Mocanu A.

Identyfikatory

DOI

10.2478/v10164-010-0005-y

• Języki publikacji: EN

Abstrakty

EN

The paper deals with the experimental analysis of the influence of the rivet parameters upon the fatigue strength of aircraft structures. Different riveted samples were tested on fatigue machine taking into account the diameter of the rivet and the forming pressure influence. By superposing the resulting Wöhler curves on the same graphic, some interesting conclusions were pointed.

• Wydawca: Wydawnictwa Naukowe Sieci Badawczej Łukasiewicz - Instytutu Lotnictwa
• Czasopismo: Fatigue of Aircraft Structures
• Rocznik: 2009
• Tom: Iss. 1
• Strony: 50--57
• Opis fizyczny: Bibliogr. 13 poz., fot., rys., tab., wykr., wzory

Twórcy

autor

Fuiorea I.

• Military Technical Academy, Bucuresti, Romania

autor

Bartis D.

• Military Technical Academy, Bucuresti, Romania

autor

Nedelcu R.

• Military Technical Academy, Bucuresti, Romania

autor

Mocanu A.

• Polytechnic University, Bucuresti, Romania

Bibliografia

• [1] Aktepe, B., & Molent, L. (1999). Management of Airframe Fatigue Through Individual Aircraft Loads Monitoring Programs. Defense Science and Technology Organization, Aeronautical and Maritime Research Laboratory, Victoria, Australia.
• [2] Apicella, A., Armentani, E., & Citarella, R. (1998). Crack Propagation in MultiSite Damage Condition for a riveted Joint. Fisciano: Department of Mechanical Engineering, University of Salerno.
• [3] Apicella, A., Armentani, E., & Citarella, R. (1997). Bidimensional Stress Analysis and SIF’s Assessement of a Cracked Aeronautic Doubler-Skin Assembly by BEM and FEM. Fisciano: Department of Mechanical Engineering, University of Salerno.
• [4] Bakuckas, J., Jr. (January 06, 2005). Structural Integrity of transport Airplanes. Airworthiness Assurance Branch, AAR–480, Atlantic City International Airport, from http://airportaircraftsafetyrd.tc.faa.gov/Programs/agingaircraft/Structural/index.htm
• [5] Bruhn, E. (1965). Analisys and design of flight vehicle structures. Cincinnati, Ohio: Tri-State Offset Company.
• [6] Cali, C., Citarella, R., & Soprano, A. (1998). FEM-BEM coupled methodolgy for cracked stiffened panels. Boundary Element Comunications Journal, 8(4).
• [7] Findlay, S., & Harrison, N. D. (2002). Why aircraft fail. Materials Today, November 2002, ISSN: 1369 7021. Hampshire, United Kingdom: Elsevier Science Ltd. 2002, QinetiQ Ltd.
• [8] Keller, E. (2001, May). Real-Time Sensing of Fatigue Crack Damage for Information-Based Decision and Control. A thesis in Mechanical Engineering, The Pennsylvania State University, The Graduate School College of Engineering.
• [9] Khor, K., & Ubhi, H. (2001). Fatigue Crack Closure Studies In Advanced Airframe Aluminium Alloys. Materials Research Group, School of Engineering, Highfield, United Kingdom: University of Southhampton.
• [10] Ko, L. W. (1987, May). Prediction of Service Life of Aircraft Structural Components Using the Half-Cycle Method. Ames Research Center, Dryden Flight Research Facility, Edwards, California: NASA Technical Memorandum 86812.
• [11] Rusmee, P. (2005, September). Fatigue Crack Growth. Retrieved July 27, 2010, from www.mech.utah.edu/~rusmeeha/lab Notes/fatigue.html
• [12] Silva, A. (1997). Multiple Site Damage in Riveted Lap-Joints Specimens. Warrington, United Kingdom: EMAS Publishing.
• [13] Vlieger, H., & Ottens, H. (1998, October). Uniaxial and biaxial tests on riveted fuselage lap joints specimens. Office of Aviation Research Washington, U. S. Departament of Transportation, Federal Aviation Administration. (DOT/FAA/AR-98/33)