Special Issue "Rotorcraft"

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

Deadline for manuscript submissions: 31 October 2021.

Special Issue Editor

Dr. Jacopo Serafini
E-Mail Website
Guest Editor
Department of Engineering, Roma Tre University, Via della Vasca Navale, 79, 00144 Roma, Italy
Interests: aerodynamics, aeroelasticity, flight dynamics, aeroacoustics of rotorcraft; structural characterization and shape sensing; electric aircraft/rotocraft

Special Issue Information

Dear Colleagues,

Although representing a relatively small market segment in the aeronautical sector, rotary wing aircraft has historically been deeply studied due to the peculiar technical and scientific challenges they propose. In recent years, the sector has dramatically changed due to the introduction of several types of rotorcraft, ranging from multicopter to compound helicopters and tiltrotors, enlarging the spectrum of operations. This has been made possible by the advancement of the various disciplines involved in the design of rotary wing aircraft. However, several issues still remain open, requiring theoretical and technological development. Moreover, many of the theories developed for rotorcraft have found another field of application, especially in the wind turbine sector.
This Special Issue aims to present the most recent advancement in the disciplines related to rotorcraft, including but not limited to:

  • Aerodynamics
  • Aeroelasticity
  • Autonomous flight
  • Electric rotorcraft
  • Flight dynamics and simulation
  • Flight control systems/navigation systems
  • Crashworthiness/ditching
  • Health and usage monitoring and predictive maintenance
  • Innovative rotorcraft design
  • Multicopters
  • Noise
  • Operations
  • Rotorcraft–pilot interactions
  • Sensors and avionics
  • Structures and materials
  • Transmissions
  • Vibrations

Dr. Jacopo Serafini
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 papers will be 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 1400 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 (3 papers)

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Research

Article
In-Flight Test Campaign to Validate PIO Detection and Assessment Tools
Aerospace 2020, 7(9), 136; https://doi.org/10.3390/aerospace7090136 - 10 Sep 2020
Viewed by 1152
Abstract
This paper describes a joint research campaign conducted by the German Aerospace Center (DLR) and the National Research Council Canada (NRC) to explore methods and techniques to expose rotorcraft pilot-induced oscillations (PIOs) during flight testing. A flight test campaign was conducted at NRC [...] Read more.
This paper describes a joint research campaign conducted by the German Aerospace Center (DLR) and the National Research Council Canada (NRC) to explore methods and techniques to expose rotorcraft pilot-induced oscillations (PIOs) during flight testing. A flight test campaign was conducted at NRC using the Bell 205 experimental aircraft. Results show that, particularly for the lateral axis, ADS-33 tasks can be successfully applied to expose PIO tendencies. Novel subjective and objective criteria were used during the test campaign. PIO prediction boundaries of the objective phase-aggression criteria (PAC) detection algorithm were validated through results obtained. This was the first use of PAC with data recorded in-flight. To collect subjective feedback, the aircraft–pilot coupling (APC) scale was used. This was the first use of the novel scale in-flight and received favourable feedback from the evaluation pilot. Modifications to ADS-33 mission tasks were found to successfully improve the ability to consistently expose PIOs. Full article
(This article belongs to the Special Issue Rotorcraft)
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Article
Mathematical Modelling of Gimballed Tilt-Rotors for Real-Time Flight Simulation
Aerospace 2020, 7(9), 124; https://doi.org/10.3390/aerospace7090124 - 28 Aug 2020
Viewed by 1188
Abstract
This paper introduces a novel gimballed rotor mathematical model for real-time flight simulation of tilt-rotor aircraft and other vertical take-off and landing (VTOL) concepts, which improves the previous version of a multi-purpose rotor mathematical model developed by ZHAW and Politecnico di Torino as [...] Read more.
This paper introduces a novel gimballed rotor mathematical model for real-time flight simulation of tilt-rotor aircraft and other vertical take-off and landing (VTOL) concepts, which improves the previous version of a multi-purpose rotor mathematical model developed by ZHAW and Politecnico di Torino as part of a comprehensive flight simulation model of a tilt-rotor aircraft currently implemented in the Research and Didactics Simulator of ZHAW and used for research activities such as handling qualities studies and flight control systems development. In the novel model, a new formulation of the flapping dynamics is indroduced to account for the gimballed rotor and better suit current tilt-rotor designs (XV-15, V-22, AW-609). This paper describes the mathematical model and provides a generic formulation as well as a specific one for 3-blades proprotors. The method expresses the gimbal attitude but also considers the variation of each blade’s flapping due to the elasticity of the blades, so that the rotor coning angle can be represented. A validation of the mathematical model is performed against the available literature on the XV-15 Tilt-rotor aircraft and a comparison between the previous model is provided to show the improvements achieved. The results show a good correlation between the model and the reference data and the registered performance allow real-time flight simulation with pilot and hardware in the loop. Full article
(This article belongs to the Special Issue Rotorcraft)
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Article
Cabin Layout Optimization for Vibration Hazard Reduction in Helicopter Emergency Medical Service
Aerospace 2020, 7(5), 59; https://doi.org/10.3390/aerospace7050059 - 15 May 2020
Cited by 1 | Viewed by 1943
Abstract
Helicopter Emergency and Medical Service (HEMS) vehicles require a specially configured cabin that supports the quick transport of a rescue team to the site of an emergency and return of patients back to a full capacity hospital, while sustaining the patients’ health using [...] Read more.
Helicopter Emergency and Medical Service (HEMS) vehicles require a specially configured cabin that supports the quick transport of a rescue team to the site of an emergency and return of patients back to a full capacity hospital, while sustaining the patients’ health using specifically designed, but otherwise state-of-the-art life-support equipment. The effectiveness and safety of the service may be challenged by the vibratory level, which could be improved by optimally positioning the affected subjects within the cabin. However, the bare dynamical response of the airframe can lead to erroneous evaluation of vibration performance, since pilots, crew, patients, and medical equipment dynamically interact with the helicopter through their interfaces with the structure. Therefore, layout optimization of a HEMS vehicle for low vibration requires the capability to efficiently analyze a large set of candidate coupled helicopter-interface-subject configurations, reaching a suitable trade-off between model detail and computational cost. This work presents an effective vibration rating of medical helicopters to support vibration hazard reduction by minimization of cabin interior accelerations. The tool is able to model high-fidelity rotorcraft aeroservoelasticity, easily connect formulations representing the dynamics of humans, equipment, and their interfaces, and calculate the vibration performance of the resulting coupled models. The approach is applied to a medium-weight helicopter to find its lowest vibration HEMS configuration. It is demonstrated that the optimal positioning of HEMS subjects can significantly reduce vibration hazard and improve operation safety, nearly as effectively as the application of vibration attenuation solutions with a fixed cabin layout. Full article
(This article belongs to the Special Issue Rotorcraft)
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