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Morphing-Enabling Technologies for Aerospace Systems: 2nd Edition

A special issue of Applied Sciences (ISSN 2076-3417). This special issue belongs to the section "Aerospace Science and Engineering".

Deadline for manuscript submissions: 31 August 2026 | Viewed by 1735

Special Issue Editors


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Guest Editor
Adaptive Structures Operative Unit, The Italian Aerospace Research Centre (CIRA), 81043 Capua, Italy
Interests: aerostructural analysis; aeroelasticity; morphing systems; design optimization; adaptive structures
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Special Issue Information

Dear Colleagues,

Following the success of the first edition, this Special Issue, ‘Morphing-Enabling Technologies for Aerospace Systems: 2nd Edition’, broadens its focus by addressing morphing technologies for both space and aeronautic applications across different configurations and categories.   

This initiative highlights innovative solutions for de-orbiting and re-entry systems of space vehicles, utilizing flexible deployment mechanisms and smart-materials-based concepts to achieve precise entry trajectories and enhanced landing accuracy through lift-to-drag modulation.

Furthermore, this Special Issue will explore various aeronautic applications of rigid-body linkages and compliant mechanisms, where high reliability, accuracy, and demanding performance standards are met through multidisciplinary and multi-objective design processes. These applications range from aircraft morphing wing devices, such as morphing flaps and winglets, to adaptive systems using smart materials.

This Special Issue invites original research articles and comprehensive reviews from a diverse group of professionals, including researchers, academicians, and industry experts. The initiative represents the outcome of long-standing scientific and technical cooperation between Italy and Brazil in aerospace science, supported by funding from the Italian Ministry of Foreign Affairs and International Cooperation (MAECI) for Italy, and CONFAP through its State Funding Agencies (FAPs) for Brazil.

Dr. Ignazio Dimino
Dr. Maria Chiara Noviello
Guest Editors

Manuscript Submission Information

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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. Applied Sciences is an international peer-reviewed open access semimonthly 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.

Keywords

  • morphing aeroshells
  • space mechanisms
  • re-entry vehicles
  • mechanically deployable systems
  • inflatable systems
  • adaptive shape-changing mechanisms
  • design methodologies and optimization
  • rigid-body mechanisms for aerospace
  • compliant mechanisms for aerospace
  • multibody simulations
  • mechanism design and optimization
  • safety and reliability

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Published Papers (2 papers)

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Research

26 pages, 2807 KB  
Article
An Engineering Framework for Adaptive Winglet Design: Identification of the Optimal Morphing Mode and Envelope
by Wei Li, Benjamin King Sutton Woods and Dazhong Wang
Appl. Sci. 2026, 16(3), 1645; https://doi.org/10.3390/app16031645 - 6 Feb 2026
Viewed by 554
Abstract
Adaptive winglets improve aerodynamic efficiency by enabling geometry adjustments tailored to flight conditions. In this study, an engineering-oriented optimization framework is developed and applied to numerical aerodynamic evaluations based on the wing–winglet configuration of a KC-135 aircraft, under representative takeoff, climb, and cruise [...] Read more.
Adaptive winglets improve aerodynamic efficiency by enabling geometry adjustments tailored to flight conditions. In this study, an engineering-oriented optimization framework is developed and applied to numerical aerodynamic evaluations based on the wing–winglet configuration of a KC-135 aircraft, under representative takeoff, climb, and cruise conditions. A Plackett–Burman design is employed to screen the 10 kinds of winglet geometric parameters, from which the dominant variables affecting drag are identified. Subsequently, response surface methodology is used to construct surrogate models and determine optimal parameter combinations for each flight phase, thereby defining a feasible morphing envelope for adaptive winglet operation. The results indicate that a coupled morphing of winglet height and cant angle constitutes the most effective morphing mode. Across the takeoff, climb, and cruise phases, the optimal morphing envelope involves a continuous transition from Height = 0.20b/2 and Cant angle = 86.3° at takeoff, to Height = 0.192b/2 and Cant angle = 8.2° during climb, and finally approaching the baseline configuration (Height = 0.135b/2, Cant angle = 20°) at cruise, while achieving a maximum drag reduction efficiency improvement of up to 8.8% at the climb phase. Full article
(This article belongs to the Special Issue Morphing-Enabling Technologies for Aerospace Systems: 2nd Edition)
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13 pages, 1978 KB  
Article
Model Predictive Control for Gliding Descent on Mars
by Jhonathan Murcia-Piñeros, Antônio F. B. A. Prado and Ignazio Dimino
Appl. Sci. 2025, 15(19), 10400; https://doi.org/10.3390/app151910400 - 25 Sep 2025
Viewed by 806
Abstract
This paper proposes a closed-loop nonlinear model predictive control for the first time for the trajectory tracking of a spaceplane descending and gliding on Mars. Previous studies presented the optimization of descending trajectory solving optimal control problems to reach a specific region (longitude, [...] Read more.
This paper proposes a closed-loop nonlinear model predictive control for the first time for the trajectory tracking of a spaceplane descending and gliding on Mars. Previous studies presented the optimization of descending trajectory solving optimal control problems to reach a specific region (longitude, latitude, and altitude) by the end of the atmospheric flight. Following those approaches, in this work, an optimal trajectory was selected for a semi-optimal controller, specifically the nonlinear model predictive control. This controller and its robustness were validated through Monte Carlo simulations, demonstrating that it is robust enough to direct the spaceplane along the reference path, even when the atmospheric density changes by 15% of the standard deviation. Full article
(This article belongs to the Special Issue Morphing-Enabling Technologies for Aerospace Systems: 2nd Edition)
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