Health structure monitoring for the design of an innovative UAS fixed wing through inverse finite element method (iFEM)
Health structure monitoring for the design of an innovative UAS fixed wing through inverse finite element method (iFEM)
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DOI：
10.1016/j.ast.2017.07.005
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发表时间：
2017-10-01
影响因子：
5.6
通讯作者：
Iannuzzo, Generoso
中科院分区：
文献类型：
--
作者：
Papa, Umberto;Russo, Salvatore;Iannuzzo, Generoso
结构健康监测（SHM）在载人和无人航空航天运输飞行器的系统健康管理中起着至关重要的作用。无人驾驶飞机系统（UAS）在从军事到民用（搜索和救援，环境监视和监测，娱乐）的各个领域也非常需要。本文提出了一种创新的无人机固定翼设计和控制方法，该方法基于反有限元方法，通过实验测量的表面应变计算三维壳/板变形的全场位移重建。对于机动或阵风引起的无人机载荷的初步设计和检查，全场位移是有用的。本文的目的是验证由于逆有限元法（iFEM）所提供的高精度变形预测。总体公式基于最小二乘泛函的最小化，该泛函使用嵌入式传感器提取的应变与线性一阶剪切变形理论的应变进行比较。试验品是一个薄板，装有嵌入式传感器（应变计传感器），可以实时提取表面应变，用作形状传感的输入数据。在进一步的工作分析中，该板被用于近似UAS翼箱截面。(C) 2017 Elsevier Masson SAS。版权所有。
The structural health monitoring (SHM) plays an essential role in system health management applications for aeronautic and space transportation vehicles, manned and unmanned. The unmanned aircraft systems (UAS) are also extremely needed in various fields of interest, from military to civilian (search and rescue, environmental surveillance and monitoring, entertainment). This work presents an innovative UAS fixed-wing design and control through an inverse finite element method-based, which compute the full field displacements reconstruction of a three-dimensional shell/plate deformations from experimentally measured surface strains. The full-field displacements are useful for the preliminary design and inspections of the UAS loads, caused by maneuvers or gusts. Goal of this paper was to validate the high accuracy predictions of deformations afforded due to the inverse finite element method (iFEM). Overall formulation was based on the minimization of a least-squares functional that uses and compares the strains extracted due to embedded sensors with the strains of linear, first order shear-deformation theory. The test article was a thin plate equipped with embedded sensors (strain gauge sensors) which permit to extract surface strains in real-time, used as input data for shape sensing. The plate was used to approximate an UAS wing box section, in further work analyzed. (C) 2017 Elsevier Masson SAS. All rights reserved.