Next Article in Journal
A Novel Dual-Band (38/60 GHz) Patch Antenna for 5G Mobile Handsets
Next Article in Special Issue
Multi-Addressed Fiber Bragg Structures for Microwave-Photonic Sensor Systems
Previous Article in Journal
Theoretical Modeling of Multi-Channel Intracavity Spectroscopy Technology Based on Mode Competition in Er-Doped Fiber Ring Laser Cavity
Previous Article in Special Issue
Wearable Hand Module and Real-Time Tracking Algorithms for Measuring Finger Joint Angles of Different Hand Sizes with High Accuracy Using FBG Strain Sensor
Open AccessArticle

On the Evaluation of a Coupled Sequential Approach for Rotorcraft Landing Simulation

1
Dipartimento di Meccanica, Politecnico di Milano, 20156 Milano, Italy
2
Air Force Institute of Technology, Airworth, Division, 01-494 Warsaw, Poland
*
Author to whom correspondence should be addressed.
Sensors 2020, 20(9), 2540; https://doi.org/10.3390/s20092540
Received: 31 March 2020 / Revised: 25 April 2020 / Accepted: 26 April 2020 / Published: 29 April 2020
(This article belongs to the Special Issue Fiber Bragg Grating Based Sensors and Systems)
Maximum loads acting on aircraft structures generally arise when the aircraft is undergoing some form of acceleration, such as during landing. Landing, especially when considering rotorcrafts, is thus crucial in determining the operational load spectrum, and accurate predictions on the actual health/load level of the rotorcraft structure cannot be achieved unless a database comprising the structural response in various landing conditions is available. An effective means to create a structural response database relies on the modeling and simulation of the items and phenomena of concern. The structural response to rotorcraft landing is an underrated topic in the open scientific literature, and tools for the landing event simulation are lacking. In the present work, a coupled sequential simulation strategy is proposed and experimentally verified. This approach divides the complex landing problem into two separate domains, namely a dynamic domain, which is ruled by a multibody model, and a structural domain, which relies on a finite element model (FEM). The dynamic analysis is performed first, calculating a set of intermediate parameters that are provided as input to the subsequent structural analysis. Two approaches are compared, using displacements and forces at specific airframe locations, respectively, as the link between the dynamic and structural domains. View Full-Text
Keywords: fiber Bragg gratings; landing simulation; rotorcraft; coupled sequential method; landing structural response; finite element analysis (FEA) fiber Bragg gratings; landing simulation; rotorcraft; coupled sequential method; landing structural response; finite element analysis (FEA)
Show Figures

Figure 1

MDPI and ACS Style

Cristiani, D.; Colombo, L.; Zielinski, W.; Sbarufatti, C.; Cadini, F.; Dziendzikowski, M.; Giglio, M. On the Evaluation of a Coupled Sequential Approach for Rotorcraft Landing Simulation. Sensors 2020, 20, 2540.

Show more citation formats Show less citations formats
Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Article Access Map by Country/Region

1
Search more from Scilit
 
Search
Back to TopTop