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Crack Propagation Tests for Load Sequences Developed Using Different Flight Parameters of a Trainer Aircraft

100%

Reymer P. , Kowalczyk K. , Baran M. , Nowakowski D. , Dziendzikowski M. , Leski A.

Fatigue of Aircraft Structures

2023

tom Iss.15

155--165

Military aircraft are subjected to highly variable and unpredictable loads due to diverse mission profiles, armament configurations, and individual piloting styles. This variability complicates the definition of precise load spectra, particularly in cases where data loss occurs due to Flight Data Recorder (FDR) malfunctions or data mishandling. This paper investigates the use of different flight parameters, such as load factor (nz), barometric height (Hb), and horizontal velocity (Vp), to define load sequences for the PZL-130 “Orlik” TC-II military trainer aircraft. These sequences were then used to evaluate crack propagation using Compact Tension (CT) specimens. The results show that the incorporation of additional flight parameters improves the accuracy of crack propagation predictions when compared to direct strain measurements. This study highlights the potential of using available flight data to develop reliable load spectra for fatigue life estimation in military aircraft, even when direct load measurements are not financially feasible.

Mi-24 Helicopter Full Scale Fatigue Test Concept

84%

Reymer P. , Zieliński W. , Piątkowski Ł. , Dziendzikowski M. , Kurnyta A. , Wrąbel R. , Cichocki T. , Leśniczak A. , Kurdelski M. , Dragan K.

Fatigue of Aircraft Structures

2019

tom Iss. 11

11--18

This paper presents a general concept of the Full Scale Fatigue Test of the Mi-24 helicopter including the test layout and load distribution, as well as describes the milestones to be achieved. Additionally, some initial work conducted in order to determine both the mass and load distribution in the structure is described. The main goal of the test is to verify the low cycle fatigue life of the helicopter structure (fuselage, tail boom, wings and landing gear). The test will be divided into two main stages at which flight and landing loads will be applied. The authors demonstrate the general test concept, the helicopter’s structure fixture and the arrangement of the hydraulic actuators at both stages in order to achieve representative loads during the test. The proposed concept is based on AFIT’s previous experience in full scale structural testing, available literature and the experience of the test staff.