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Lift Force Measurement in Landing Gears Dynamic Tests

机译:起落架动态测试中的升力测量

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© 2021 Zbigniew Skorupka, published by Sciendo.As one of the key components of the aircraft in terms of both operation and safety landing gears are of special interest of the aviation regulations. During the touch down landing gears need to dissipate as much of the energy as possible maintaining the lowest volume and weight as required by the aviation design restrictions. According to the aviation regulations landing gears have to be tested in order to prove the dissipation of the calculated landing energy and to evaluate actual loads acting on the fuselage via the mounting nodes of the landing gears. The tests need to replicate the real landing conditions as closely as possible - including the lift force (or lift) acting on the aircraft during landing. The lift force during landing is not sufficient to maintain the aircraft in flight but acts as the relief force to the aircraft weight resulting in lowering loads applied to the fuselage and decreasing landing energy needed to be dissipated. The lift force or lift has to be taken into account during laboratory tests of landing gears. The lift force needs to be simulated in all of the landing gears dynamic tests: performance optimization, proof of the operation for the certification, and the fatigue evaluation. There are two main methods of applying the lift during the tests: equivalent/effective mass or direct lift application. The latter is used at the Landing Gear Laboratory of the Lukasiewicz Research Network - Institute of Aviation (where author works on daily basis). The lift is applied by the pneumatic cylinders built in the test stand. Until recently the control of the lift force value was performed indirectly by the measurement of the pressure inside the pneumatic system. Recently the experimental direct measurement system using force transducers was introduced in order to directly measure the lift force during every test. In the presented paper, the author gives an overview of the lift force measurement system including its design and the results of the preliminary use evaluation.
机译:© 2021 Zbigniew Skorupka,由 Sciendo.As 出版,是飞机在操作和安全起落架方面的关键部件之一,对航空法规特别感兴趣。在着陆期间,起落架需要尽可能多地耗散能量,保持航空设计限制所要求的最低体积和重量。根据航空法规,必须对起落架进行测试,以证明计算出的着陆能量的耗散,并评估通过起落架的安装节点作用在机身上的实际载荷。测试需要尽可能接近真实着陆条件 - 包括着陆期间作用在飞机上的升力(或升力)。着陆时的升力不足以维持飞机飞行,而是作为飞机重量的释放力,从而降低施加在机身上的载荷并减少需要耗散的着陆能量。在起落架的实验室测试中,必须考虑升力或升力。在所有起落架动态测试中都需要模拟升力:性能优化、认证操作证明和疲劳评估。在测试过程中应用升力有两种主要方法:等效/有效质量或直接升力应用。后者用于Lukasiewicz研究网络 - 航空研究所的起落架实验室(作者每天在那里工作)。升力由试验台上内置的气缸施加。直到最近,升力值的控制都是通过测量气动系统内部的压力来间接进行的。最近引入了使用力传感器的实验直接测量系统,以便在每次测试中直接测量升力。在本文中,作者概述了升力测量系统,包括其设计和初步使用评估的结果。

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