PL
 |
EN
Preferencje help
Polish version English version Język
Widoczny [Schowaj] Abstrakt
Liczba wyników

Znaleziono wyników: 4

Liczba wyników na stronie
first rewind previous Strona / 1 next fast forward last
Wyniki wyszukiwania
Wyszukiwano:
w słowach kluczowych:  full scale fatigue tests
help Sortuj według:

help Ogranicz wyniki do:
first rewind previous Strona / 1 next fast forward last
1
Content available Stress Analysis of the PZL M28’s Airframe Subjected to Repairs During Fatigue Tests
Brzęczek J., Gruszecki H., Pieróg L., Deszcz F., Pietruszka J.
Fatigue of Aircraft Structures
|
2014
|
Iss. 6
107--112
EN
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.
2
Content available Selected Aspects Related to the Applied Loads Control During Fatigue Tests of a Metallic Airframe
Brzęczek J., Chodur J., Pietruszka J.
Fatigue of Aircraft Structures
|
2014
|
Iss. 6
102--106
EN
Service life of the PZL M28 is computed based on the results of the full-scale fatigue tests of the structure [1]. As the PZL M28 is a commuter category airplane according to the 14 CFR Part 23 and CS-23 regulations, the test objects are: (1) wing and wing load carry-through structure, (2) empennage and attached fuselage structure. Additionally, there are fatigue tests carried out for the landing gear and other selected elements including control system elements. The aircraft load carry-through structure is metallic and the cabin is unpressurized. The fatigue tests are conducted stage-by-stage. As tests progress, it is possible to extend the aircraft target service life, applying the safe life philosophy with reference to the primary components of the load carry-through structure. The article brings into attention the issue of the applied loads control in conducting fatigue tests of the metallic airframe.
3
Content available Selected Aspects Related to Preparation of Fatigue Tests of a Metallic Airframe
Brzęczek J., Chodur J., Pietruszka J.
Fatigue of Aircraft Structures
|
2014
|
Iss. 6
95--101
EN
The basis for the computation of the service life of the PZL M28 was the results of the full-scale fatigue tests of the structure [1]. As the PZL M28 is a commuter category airplane according to the 14 CFR Part 23 and CS-23 regulations, the test objects were: (1) wing and wing load carrythrough structure, (2) empennage and attached fuselage structure. Additionally, there were fatigue tests carried out for the landing gear and other selected elements including control system elements. The aircraft load carry-through structure is metallic and the cabin is unpressurized. The fatigue tests were conducted stage-by-stage. As the tests progressed, it was possible to extend the aircraft’s target service life, applying a safe life philosophy with reference to the primary components of the load carry-through structure. This paper brings into attention selected issues related to the fatigue tests preparation (the stage following the preparation of the test plan), with focus on the wing and wing load carrythrough structure.
4
Content available Selected Aspects Related to Preparation of a Fatigue Test Plan of a Metallic Airframe
Brzęczek J., Gruszecki H., Pieróg L., Pietruszka J.
Fatigue of Aircraft Structures
|
2014
|
Iss. 6
88--94
EN
Service life of the PZL M28 is computed based on the results of the full-scale fatigue tests of the structure [1]. As the PZL M28 is a commuter category airplane according to the 14 CFR Part 23 and CS-23 regulations, the test objects were: (1) wing and wing load carry-through structure, (2) empennage and attached fuselage structure. Additionally, there were fatigue tests carried out for the landing gear and other selected elements including control system elements. The aircraft load carry-through structure is metallic and the cabin is unpressurized. The fatigue tests were conducted stage-by-stage. As tests progressed, it was possible to extend the aircraft target service life, applying the safe-life philosophy with reference to the primary components of the load carrythrough structure. The article brings into attention selected issues related to the fatigue tests plan preparation, with focus on wing and wing load carry-through structure test.
first rewind previous Strona / 1 next fast forward last
JavaScript jest wyłączony w Twojej przeglądarce internetowej. Włącz go, a następnie odśwież stronę, aby móc w pełni z niej korzystać.