In this paper there are some results of the European project AISHA. The project aim is the aircraft health monitoring, using ultrasonic Lamb’s waves technology. The final link in the health assessment process is: using information about the extent of size to predict the remaining strength and lifetime. Fatigue phenomenon is the main cause of growth damage for different kinds of initial damages (stress concentration, corrosion, impact) and different kinds of structures (the rivet-joint of metal sheets, long fiber composite, sandwich composites). Both the classical parameter of initial damage, as well as the new ones where analyzed. The prospective fatigue damage parameters are: density and the average size surface fatigue microcracks. Using ...
AbstractThe study deals with an integral skin-stringer wing panel made of AA 7475-T7351. DT solution...
A conceptual structural health monitoring (SHM) system to monitor fatigue damage is discussed in thi...
The study has been intended to determine the most essential mechanical and fatigue properties as wel...
Individual aircraft life monitoring is required to ensure safety and economy of aircraft structure, ...
This project involved development of a method to predict the fatigue crack propagation process in th...
An experimental fatigue life analysis was performed using the Air Force Growth(AFGROW) crack life pr...
Damage Tolerance method for structural integrity evaluation of helicopters fuselages requests a deta...
This subject is connected with the structural health monitoring (SHM) of aircraft. Progressive metho...
In accordance with the airworthiness standards, the aircraft structure must be operationally surviva...
There the study objects are the statistic characteristics of appearance of fitigue macrocracks in th...
Commercial transport aircraft are required to operate under the concept of damage tolerance. Because...
The paper describes the general proposal, function and performance of a prognostics system for fatig...
Material fatigue is the basic factor limiting aircraft's durability. It comes from the fact that cha...
This work presents total fatigue life prediction methodology of aircraft structural components under...
This area research is focused to application of general principles and models for prediction of the ...
AbstractThe study deals with an integral skin-stringer wing panel made of AA 7475-T7351. DT solution...
A conceptual structural health monitoring (SHM) system to monitor fatigue damage is discussed in thi...
The study has been intended to determine the most essential mechanical and fatigue properties as wel...
Individual aircraft life monitoring is required to ensure safety and economy of aircraft structure, ...
This project involved development of a method to predict the fatigue crack propagation process in th...
An experimental fatigue life analysis was performed using the Air Force Growth(AFGROW) crack life pr...
Damage Tolerance method for structural integrity evaluation of helicopters fuselages requests a deta...
This subject is connected with the structural health monitoring (SHM) of aircraft. Progressive metho...
In accordance with the airworthiness standards, the aircraft structure must be operationally surviva...
There the study objects are the statistic characteristics of appearance of fitigue macrocracks in th...
Commercial transport aircraft are required to operate under the concept of damage tolerance. Because...
The paper describes the general proposal, function and performance of a prognostics system for fatig...
Material fatigue is the basic factor limiting aircraft's durability. It comes from the fact that cha...
This work presents total fatigue life prediction methodology of aircraft structural components under...
This area research is focused to application of general principles and models for prediction of the ...
AbstractThe study deals with an integral skin-stringer wing panel made of AA 7475-T7351. DT solution...
A conceptual structural health monitoring (SHM) system to monitor fatigue damage is discussed in thi...
The study has been intended to determine the most essential mechanical and fatigue properties as wel...