Special Issue "Advanced Actuators for Aerospace Systems"

A special issue of Actuators (ISSN 2076-0825). This special issue belongs to the section "Aircraft Actuators".

Deadline for manuscript submissions: 31 October 2021.

Special Issue Editor

Prof. Dr. Ronald M. Barrett
E-Mail Website
Guest Editor
Adaptive Aerostructures and Aircraft Design Laboratories, The University of Kansas, 2120 Learned Hall, Lawrence, KS 66045, USA
Interests: adaptive aerostructures; enhancement of transportation related technologies; missiles and munitions

Special Issue Information

Dear Colleagues,

This Special Issue is devoted to coverage of advanced actuators and their associated power delivery and control systems for aerospace vehicles, systems, and sub- and super-systems. This Special Issue will include both endoatmospheric and exoatmospheric actuator classes for vehicles as small as subscale munitions, microsats, and microdrones to jumbo jets and solar panel deployment mechanisms. Papers covering primary and secondary flight control, undercarriage extension, and retraction, as well as active flutter suppression, vibration mitigation, launch load accommodation, mission package deployment, and staging actuators are sought. Advanced approaches using pneumatics, electrostatics, electrohydrostatic, modern ultra-high-pressure hydraulics, rare-earth rotary and linear motors, shape-memory alloys, and piezoelectric and other classes of adaptive materials are of interest.

Prof. Dr. Ronald M. Barrett
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. Actuators 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 1600 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.

Keywords

  • aerospace actuator
  • flight control
  • electrohydrostatic
  • pneumatic
  • hydraulic
  • adaptive
  • smart
  • active
  • piezoelectric

Published Papers (2 papers)

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Research

Article
Sensing, Actuation, and Control of the SmartX Prototype Morphing Wing in the Wind Tunnel
Actuators 2021, 10(6), 107; https://doi.org/10.3390/act10060107 - 21 May 2021
Viewed by 612
Abstract
This paper presents a study on trailing edge deflection estimation for the SmartX camber morphing wing demonstrator. This demonstrator integrates the technologies of smart sensing, smart actuation and smart controls using a six module distributed morphing concept. The morphing sequence is brought about [...] Read more.
This paper presents a study on trailing edge deflection estimation for the SmartX camber morphing wing demonstrator. This demonstrator integrates the technologies of smart sensing, smart actuation and smart controls using a six module distributed morphing concept. The morphing sequence is brought about by two actuators present at both ends of each of the morphing modules. The deflection estimation is carried out by interrogating optical fibers that are bonded on to the wing’s inner surface. A novel application is demonstrated using this method that utilizes the least amount of sensors for load monitoring purposes. The fiber optic sensor data is used to measure the deflections of the modules in the wind tunnel using a multi-modal fiber optic sensing approach and is compared to the deflections estimated by the actuators. Each module is probed by single-mode optical fibers that contain just four grating sensors and consider both bending and torsional deformations. The fiber optic method in this work combines the principles of hybrid interferometry and FBG spectral sensing. The analysis involves an initial calibration procedure outside the wind tunnel followed by experimental testing in the wind tunnel. This method is shown to experimentally achieve an accuracy of 2.8 mm deflection with an error of 9%. The error sources, including actuator dynamics, random errors, and nonlinear mechanical backlash, are identified and discussed. Full article
(This article belongs to the Special Issue Advanced Actuators for Aerospace Systems)
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Article
Finite Time Convergence Incremental Nonlinear Dynamic Inversion-Based Attitude Control for Flying—Wing Aircraft with Actuator Faults
Actuators 2020, 9(3), 70; https://doi.org/10.3390/act9030070 - 17 Aug 2020
Cited by 3 | Viewed by 1111
Abstract
In this paper, a two-loop fault-tolerant attitude control scheme is proposed for flying-wing aircraft with actuator faults. A regular nonlinear dynamic inversion (NDI) control is used in the outer attitude loop, and a finite time convergence incremental nonlinear dynamic inversion (FINDI) control combined [...] Read more.
In this paper, a two-loop fault-tolerant attitude control scheme is proposed for flying-wing aircraft with actuator faults. A regular nonlinear dynamic inversion (NDI) control is used in the outer attitude loop, and a finite time convergence incremental nonlinear dynamic inversion (FINDI) control combined with control allocation strategy is used in the inner angular rate loop. Prescribed performance bound (PPB) is designed to constrain the tracking errors within a residual set, so the prescribed system performance can be guaranteed. An optimal anti-windup (AW) compensator is introduced to solve the actuator saturation problem. Simulation results demonstrate the effectiveness of the proposed approach. Full article
(This article belongs to the Special Issue Advanced Actuators for Aerospace Systems)
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