Development of an Aeroelastic In-Flight Testing System for a Flexible Wing Unmanned Aerial Vehicle using Acceleration and Strain Sensors-Reference-Cited by-同舟云学术

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Development of an Aeroelastic In-Flight Testing System for a Flexible Wing Unmanned Aerial Vehicle using Acceleration and Strain Sensors

Published:2019-01-06 Issue: Volume: Page:
ISSN:
Container-title:AIAA Scitech 2019 Forum
language:
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Author:

Castillo Zuñiga David F.¹,Giacobini Souza Alain¹,Goes Luiz Carlos S.¹

Affiliation:

1. Technological Institute of Aeronautics (ITA)

Publisher

American Institute of Aeronautics and Astronautics

Link

https://arc.aiaa.org/doi/pdf/10.2514/6.2019-2033

Reference18 articles.

1. A new method to determine dynamically equivalent finite element models of aircraft structures from modal test data

2. Wing Shape Sensing from Measured Strain

3. Flutter Prediction from Flight Flutter Test Data

Cited by 5 articles. 订阅此论文施引文献订阅此论文施引文献，注册后可以免费订阅5篇论文的施引文献，订阅后可以查看论文全部施引文献

1. System identification in time domain of flexible aircraft using panel methods;Journal of Physics: Conference Series;2024-06-01

2. In-flight modal identification by operational modal analysis;Journal of the Brazilian Society of Mechanical Sciences and Engineering;2023-04-28

3. Response and Operational Modal Analysis from Wind Tunnel Test of the EOLO Flexible Aircraft;AIAA Scitech 2021 Forum;2021-01-04

4. Flight dynamics modeling of a flexible wing unmanned aerial vehicle;Mechanical Systems and Signal Processing;2020-11

5. Aeroelastic Vibration Measurement Based on Laser and Computer Vision Technique;Experimental Techniques;2020-09-11

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