Wszystkie pola: Brzęczek, M. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: The Fatigue Life of Cables in Aircraft Flight Control Systems
Autorzy:: Kubryn, M.
Gruszecki, H.
Pieróg, L.
Chodura, J.
Pietruszka, J.
Brzęczek, J.
Powiązania:: https://bibliotekanauki.pl/articles/98016.pdf
Data publikacji:: 2018
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: fatigue
cable flight control systems
cable endurance tests
Opis:: The cable flight control systems are commonly used for the control of small airplanes. In these systems, the cables are the only elements transmitting loads from the pilot to the control surfaces. During a flight the cables are moving through pulleys and are subjected to variable loads. A simple analysis of stress in the cable shows that the stress generated by the cyclical bending on the pulleys causes the fatigue of the wires. This phenomenon was noticed on a military aircraft of the M28 family during periodic maintenance inspection in 2007. The endurance tests of KSAN cables of the diameter equal to 3.5 mm and 1.8 mm were performed at the PZL MIELEC. The tests showed the limited fatigue life of the cables due to a progressive increase in the number of broken wires.
Źródło:: Fatigue of Aircraft Structures; 2018, 10; 53-62
2081-7738
2300-7591
Pojawia się w:: Fatigue of Aircraft Structures
Dostawca treści:: Biblioteka Nauki

Artykuł

Skocz do pozycji: 2.

Tytuł:: Stress Analysis of the PZL M28’s Airframe Subjected to Repairs During Fatigue Tests
Autorzy:: Brzęczek, J.
Gruszecki, H.
Pieróg, L.
Deszcz, F.
Pietruszka, J.
Powiązania:: https://bibliotekanauki.pl/articles/97849.pdf
Data publikacji:: 2014
Wydawca:: Sieć Badawcza Łukasiewicz - Instytut Lotnictwa
Tematy:: metallic airframe structure
full scale fatigue tests
Opis:: The PZL M28’s service life is determined based on the fatigue tests of the wing and wing loadscarry-through structure. During the fatigue test, the first occurrence of significance was the appearance of a in the area of the wing where loads are applied from the strut. It was demonstrated during further activities that repairs of the wing and other basic assemblies enabled, when performed at an appropriate time, the airplane’s service life to be significantly increase. In the case of each design change implemented in the airframe subject to the fatigue testing, a stress analysis of the airframe was required in order to check if local changes, i.e. local repairs, did not affect the stress level in other tested areas. This helped to avoid significant stress redistribution in the airframe after the repair, so the fatigue test was still valid for all areas of interest.
Źródło:: Fatigue of Aircraft Structures; 2014, 6; 107-112
2081-7738
2300-7591
Pojawia się w:: Fatigue of Aircraft Structures
Dostawca treści:: Biblioteka Nauki

Artykuł

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