Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
3.0
2.6
Journals
Aerospace
Special Issues
Advances in Rotorcraft Dynamics
share announcement

Advances in Rotorcraft Dynamics

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: closed (31 March 2024) | Viewed by 4132

Special Issue Editor

Prof. Dr. Sung N. Jung

E-Mail Website
Guest Editor
School of Mechanical and Aerospace Engineering, Konkuk University, 120 Neungdong-ro, Gwangjin-gu, Seoul 05029, Republic of Korea
Interests: rotorcraft dynamics; aeroelasticity; composite structural mechanics; smart structures; optimum design

Special Issue Information

Dear Colleagues,

Modern rotorcraft designs have constantly evolved to meet various lifting configurations, such as compound helicopters, tilt rotors, ducted fans, and multi-rotor AAM (Advanced Air Mobility), and stringent mission goals (e.g., particular speed, noise emission, and mobility requirements). Even with the advancements of sophisticated computational power, it is difficult to accurately capture the close coupling behavior between different structural (elastic) components and the unsteady aerodynamic environment. Low-level vibration/noise rotor technologies are critical due to the ever-increased demand for the “jet smooth” ride quality of rotary wing vehicles, particularly for enabling civil mobility missions.

This Special Issue aims to establish an outlook on recent advances in the areas of rotorcraft dynamics and aeroelasticity, focusing on the prediction of loads and vibration/noise and their reduction via active or passive means. Innovative modelling techniques that will improve our current understanding or knowledge of key rotorcraft aeromechanics are welcome. Original research articles or review papers that address all aspects of rotorcraft dynamics and aeroelasticity are encouraged, including, but not limited to: 

  • Rotorcraft loads and vibration;
  • Low-level vibration/noise designs;
  • Integrated multi-body (rotor–rotor, rotor–body, and rotor–drive systems, etc.) dynamics;
  • Vibration/noise reduction (active or passive);
  • Aeromechanical instability;
  • Analytical modelling techniques;
  • Fluid–structure interaction approach;
  • Surrogate-based, multidisciplinary optimization.

Prof. Dr. Sung N. Jung
Guest Editor

Manuscript Submission Information

Manuscripts should be submitted online at www.mdpi.com by registering and logging in to this website. Once you are registered, click here to go to the submission form. Manuscripts can be submitted until the deadline. All submissions that pass pre-check are peer-reviewed. Accepted papers will be published continuously in the journal (as soon as accepted) and will be listed together on the special issue website. Research articles, review articles as well as short communications are invited. For planned papers, a title and short abstract (about 100 words) can be sent to the Editorial Office for announcement on this website.

Submitted manuscripts should not have been published previously, nor be under consideration for publication elsewhere (except conference proceedings papers). All manuscripts are thoroughly refereed through a single-blind peer-review process. A guide for authors and other relevant information for submission of manuscripts is available on the Instructions for Authors page. Aerospace is an international peer-reviewed open access monthly journal published by MDPI.

Please visit the Instructions for Authors page before submitting a manuscript. The Article Processing Charge (APC) for publication in this open access journal is 2400 CHF (Swiss Francs). Submitted papers should be well formatted and use good English. Authors may use MDPI's English editing service prior to publication or during author revisions.

Published Papers (4 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Research

30 pages, 12760 KiB  
Article
Combination of Advanced Actuator Line/Disk Model and High-Order Unstructured Finite Volume Solver for Helicopter Rotors
by Minghao Yang, Shu Li and Weicheng Pei
Aerospace 2024, 11(4), 296; https://doi.org/10.3390/aerospace11040296 - 10 Apr 2024
Viewed by 403
Abstract
In the research field of rotorcraft aerodynamics, there are two fundamental challenges: resolving the complex vortex structures in rotor wakes and representing the moving rotor blades in the ambient airflow. In this paper, we address the first challenge by utilizing a third-order unstructured [...] Read more.
In the research field of rotorcraft aerodynamics, there are two fundamental challenges: resolving the complex vortex structures in rotor wakes and representing the moving rotor blades in the ambient airflow. In this paper, we address the first challenge by utilizing a third-order unstructured finite volume solver, which exhibits lower numerical dissipation than its second-order counterpart. This allows for sufficient resolution of small vortex structures on relatively coarse meshes. With this flow solver, the second challenge is addressed by modeling each rotor as an actuator disk (i.e., the actuator disk model (ADM)) or modeling each blade as an actuator line (i.e., the actuator line model (ALM)). Both of the two models are equipped with an improved tip loss correction, which is introduced in detail in the methodology section. In the section of numerical experiments, the numerical convergence properties of the two types of solvers have been compared in the case of two-dimensional infinite wing. In addition, the relationship between the ALM and the lifting line theory is discussed in the cases of fixed-wing calculations. Another goal of these cases is to validate the tip loss correction presented. The validation of the ALM/ADM and comparisons of computational efficiency are also demonstrated in simulations involving both hover and forward flight rotors. It was found that the combination of the third-order finite volume solver and the ALM/ADM with the improved tip loss correction presents an efficient way of performing the aerodynamic analysis of rotor-induced downwash flow. Full article
(This article belongs to the Special Issue Advances in Rotorcraft Dynamics)
►▼ Show Figures

Figure 1

25 pages, 18750 KiB  
Article
Vibration Qualification Campaign on Main Landing Gear System for High-Speed Compound Helicopter
by Antonio Chiariello, Carmine Carandente Tartaglia, Maurizio Arena, Vincenzo Quaranta, Giovanni Bruno, Marika Belardo and Martina Castaldo
Aerospace 2024, 11(2), 130; https://doi.org/10.3390/aerospace11020130 - 01 Feb 2024
Viewed by 1088
Abstract
Vibrations in helicopters have strong implications for their performance and safety, leading to the increased fatigue of components and reduced operational efficiency. As helicopters are designed to land on several types of surfaces, the landing gear system dissipates the impact on the ground [...] Read more.
Vibrations in helicopters have strong implications for their performance and safety, leading to the increased fatigue of components and reduced operational efficiency. As helicopters are designed to land on several types of surfaces, the landing gear system dissipates the impact on the ground and maintains stability during landing and take-off. These vibrations can arise from a variety of sources, such as aerodynamic loads, mechanical imbalances, and engine instabilities. In the present work, the authors describe the vibration qualification process of the main landing gear tailored to fast helicopters within the Clean Sky 2 Racer program. The method entails devising preliminary load sets that deform the structure in its key excited mode shapes to assess stresses and address the experimental campaign. A full-scale prototype model is then tested for sine sweep and random vibrations as per the Airbus Helicopter requirements in order to reach the final qualification and acceptance stage. Although the discussion centers on a landing gear structure, the described process could be extended to other critical equipment as well. Full article
(This article belongs to the Special Issue Advances in Rotorcraft Dynamics)
►▼ Show Figures

Figure 1

19 pages, 8746 KiB  
Article
Air and Structural Loads Analysis of a 5-Ton Class Rotorcraft in a Pull-Up Maneuver Using CFD/CSD Coupled Approach
by Seong Hyun Hong, Young Jin Kim, Soo Hyung Park, Sung Nam Jung and Ki Ro Kim
Aerospace 2024, 11(2), 102; https://doi.org/10.3390/aerospace11020102 - 23 Jan 2024
Viewed by 1070
Abstract
The air and structural loads of a 5-ton class light helicopter (LH) rotor in a 2.24 g pull-up maneuver are investigated using a coupling between the computational structural dynamics (CSD) and computational fluid dynamics (CFD) methods. The LH rotor is characterized by a [...] Read more.
The air and structural loads of a 5-ton class light helicopter (LH) rotor in a 2.24 g pull-up maneuver are investigated using a coupling between the computational structural dynamics (CSD) and computational fluid dynamics (CFD) methods. The LH rotor is characterized by a five-bladed system with elastomeric bearings and inter-bladed dampers. The periodic trim solution along with the converged CFD/CSD delta airloads obtained in steady-level flight (advance ratio of 0.287) are used to perform the transient CSD maneuver analysis. The resulting vehicle attitude angles and velocity profiles of the aircraft are then prescribed in the quasi-static (QS) CFD maneuver analysis. It is demonstrated that the present QS approach provides an effective means for the maneuver loads’ analysis. The important flow behaviors such as BVI (blade–vortex interaction)-induced oscillations and the negative pitching moment peaks met in maneuver flight are captured nicely with the proposed method. Either the vortex trajectories or the surface pressure distributions are examined to identify the sources of the oscillations. A loose CFD/CSD coupling (LC) is used to predict the blade elastic motions, structural moments, and pitch link loads at the specified maneuver revolution of the rotor and also to correlate these with the transient CSD-based predictions. A reasonable correlation is obtained. The LC results show more pronounced 5P (five per revolution) oscillations on the structural response than those of the CSD-based methods. Full article
(This article belongs to the Special Issue Advances in Rotorcraft Dynamics)
►▼ Show Figures

Figure 1

21 pages, 9740 KiB  
Article
Development of a High-Performance Low-Weight Hydraulic Damper for Active Vibration Control of the Main Rotor on Helicopters—Part 2: Preliminary Experimental Validation
by Antonio Carlo Bertolino, Matteo Gaidano, Stefano Smorto, Paolo Giovanni Porro and Massimo Sorli
Aerospace 2023, 10(10), 868; https://doi.org/10.3390/aerospace10100868 - 05 Oct 2023
Viewed by 1111
Abstract
Vibrations generated by the main rotor-gearbox assembly in a helicopter are the principal cause of damage to cockpit instruments and crew discomfort in terms of cabin noise. The principal path of vibration transmission to the fuselage is through the gearbox’s rigid support struts. [...] Read more.
Vibrations generated by the main rotor-gearbox assembly in a helicopter are the principal cause of damage to cockpit instruments and crew discomfort in terms of cabin noise. The principal path of vibration transmission to the fuselage is through the gearbox’s rigid support struts. This article is Part 2 of a two-part paper presenting an innovative solution involving the replacement of rigid struts with low-weight, high-performance active dampers for vibration control developed by Elettronica Aster S.p.A. Part 1 provided a comprehensive overview of the system layout obtained through a model-based design process and presented a thorough description of the adopted nonlinear mathematical model. Part 2 focuses on the physical realization of the damper and its dedicated experimental test bench. The mathematical model parameter fitting procedure is presented in detail, as it has been used to help in the definition and optimization of the control schemes and the verification of the expected performance. The experimental results obtained in Part 2 not only demonstrate the compliance of the active damper prototype with the acceptance tests outlined in the ATP but also provide compelling evidence reinforcing the promise of the presented solution for effective vibration reduction. Full article
(This article belongs to the Special Issue Advances in Rotorcraft Dynamics)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-4
Back to TopTop