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Applied Sciences
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Morphing Enabling Technologies for Aerospace Systems
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Morphing Enabling Technologies for Aerospace Systems

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

Deadline for manuscript submissions: 20 December 2024 | Viewed by 6525

Special Issue Editors

Dr. Ignazio Dimino

E-Mail Website
Guest Editor
Adaptive Structures Tech Research Unit, CIRA, The Italian Aerospace Research Centre, 81043 Capua, CE, Italy
Interests: morphing technology; smart structures; active control; topology optimization
Special Issues, Collections and Topics in MDPI journals
Dr. Cristian Vendittozzi

E-Mail Website
Guest Editor
Associate Professor, Course of Aerospace Engineering, FGA-Campus, UnB, Brasilia 72444-240, DF, Brazil
Interests: smart materials; space systems; photonic sensors; adaptive solutions; biomimetics
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Flexible morphing deployable aeroshells are increasingly emerging as novel and alternative concepts for performing the controlled re-entry and precise landing of space vehicles. Shape morphing during entry could enable trajectory control by providing enhanced versatility and flight maneuverability, otherwise not achievable with the current rigid decelerators. Additionally, a tailored heat flux and an optimal induced temperature distribution can effectively protect the payload from the re-entry environment.

This Special Issue is dedicated to novel perspectives in modern de-orbiting and re-entry systems featuring advanced mechanisms for the structural shape control of both inflatable and mechanically deployable systems to accomplish the desired entry trajectories and improved landing accuracy by modulating lift over drag. In the development of solutions to these challenges, articles may address various topics, ranging from the structural design of deployment mechanisms (the physical obstruction producing aerodynamic drag) to the aeroshell’s ability to reduce the peak heating rates through a decreased ballistic coefficient, including novel design concepts, entry vehicle trajectory simulations, aerothermal assessments, multibody analyses, and multi-objective optimization.

This initiative is the result of the long-term scientific and technical cooperation between Italy and Brazil concerning space science. The Guest Editors are the PIs of the SPLASH (Self-Deployable Flexible Aeroshell for De-Orbiting and Space Re-Entry) project, funded in part by a grant from the Italian Ministry of Foreign Affairs and International Cooperation (MAECI) for the Italian side, and by CONFAP through the involved State Funding Agencies (FAPs) for the Brazilian side.

Dr. Ignazio Dimino
Dr. Cristian Vendittozzi
Guest Editors

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. 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
  • aerothermodynamics
  • entry trajectories estimation
  • multibody simulations

Published Papers (3 papers)

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Research

16 pages, 3790 KiB  
Article
A Morphing Deployable Mechanism for Re-Entry Capsule Aeroshell
by Ignazio Dimino, Cristian Vendittozzi, William Reis Silva, Salvatore Ameduri and Antonio Concilio
Appl. Sci. 2023, 13(5), 2783; https://doi.org/10.3390/app13052783 - 21 Feb 2023
Cited by 2 | Viewed by 1873
Abstract
Morphing technology is increasingly emerging as a novel and alternative approach for performing the controlled re-entry and precise landing of space vehicles by using adaptive aeroshell structure designs. This work is intended as a preliminary conceptual design of an innovative shape-changing mechanism for [...] Read more.
Morphing technology is increasingly emerging as a novel and alternative approach for performing the controlled re-entry and precise landing of space vehicles by using adaptive aeroshell structure designs. This work is intended as a preliminary conceptual design of an innovative shape-changing mechanism for the controlled re-entry and safe recovery of CubeSat class systems aimed at recovering payloads and data from LEO at low cost for post flight inspections and experimentations. Such an adaptive and mechanically deployable aeroshell consists of a multi-hinge assembly based on a set of finger-like articulations having two-modal capabilities. The deployable surface can be modulated by a single translational actuator in order to adapt the lift-to-drag ratio for guided entry. Furthermore, once deployed, the system can activate eight small movable aerodynamic flaps that can be individually morphed via an SMA-based actuation to enhance the capsule maneuverability during the re-entry trajectory, by using exclusively aerodynamic forces to guarantee additional precision in landing. Multi-body simulations on retraction/deployment of the system are addressed to investigate the most critical aspects for actual implementation of the concept. Additionally, the morphing behavior and the control effect of the shape memory alloy actuation are preliminary assessed through parametric analysis. This paper is framed within a scientific cooperation between Italy and Brazil in the framework of the SPLASH project, funded in part for the Italian side by a grant from the Italian Ministry of Foreign Affairs and International Cooperation (MAECI), and by CONFAP through the involved State Funding Agencies (FAPs) for the Brazilian side. Full article
(This article belongs to the Special Issue Morphing Enabling Technologies for Aerospace Systems)
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12 pages, 5031 KiB  
Article
Study of the Mechanical Properties and Thermal Control Performance of Plasma-Sprayed Alumina Coating on Aluminum Alloy Surface
by Gengchao He, Weiling Guo, Dongyu He, Jiaqiang Zhang, Zhiguo Xing, Zhenlin Lv, Lei Jia and Yanfei Huang
Appl. Sci. 2023, 13(2), 956; https://doi.org/10.3390/app13020956 - 10 Jan 2023
Cited by 3 | Viewed by 1670
Abstract
Thermal control coating is an important means of ensuring that a spacecraft remains operational at high temperatures. Due to limitations regarding preparation technology and material properties, the mechanical properties of the conventional thermal control coatings still need to be improved. To solve this [...] Read more.
Thermal control coating is an important means of ensuring that a spacecraft remains operational at high temperatures. Due to limitations regarding preparation technology and material properties, the mechanical properties of the conventional thermal control coatings still need to be improved. To solve this problem, nanostructured alumina coatings (NCs) and conventional alumina coatings (CCs) were prepared using plasma-spraying technology. The microscopic morphology, phase structure, hardness, and thermal control properties (solar absorptance (αs) and emissivity (ε)) of the nanostructured alumina coatings were investigated and compared with those of conventional alumina coatings. The results show that the NC has a higher hardness value (1168.8 HV) and that its reflectivity exceeds 75% in the wavelength range of 446–1586 nm, while a high degree of emissivity of 0.863–0.87 is still maintained at 300–393 K. Furthermore, the results show that these highly reflective properties are related to the phase composition and internal micromorphology of the NC, whereby the solar absorption of the coating is reduced due to the increase in the alpha phase content (21.4%), the high porosity (5.21%) and the nanoparticles favoring the internal scattering. All these properties can improve the performance of this CC coating with low solar absorptance (αs) and high emissivity (ε). Full article
(This article belongs to the Special Issue Morphing Enabling Technologies for Aerospace Systems)
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13 pages, 1934 KiB  
Article
Calculation of Heat Transfer and Drag Coefficients for Aircraft Geometric Models
by Victor V. Kuzenov, Sergei V. Ryzhkov and Aleksey Yu. Varaksin
Appl. Sci. 2022, 12(21), 11011; https://doi.org/10.3390/app122111011 - 30 Oct 2022
Cited by 10 | Viewed by 2175
Abstract
A numerical model to calculate the heat transfer and resistance coefficients near the bodies of complex geometric shapes moving at high velocity is formulated. The processes of heat and mass transfer and flow around aircraft elements are considered. An algorithm for calculating heat [...] Read more.
A numerical model to calculate the heat transfer and resistance coefficients near the bodies of complex geometric shapes moving at high velocity is formulated. The processes of heat and mass transfer and flow around aircraft elements are considered. An algorithm for calculating heat fluxes and the heat transfer coefficient is proposed. The developed numerical technique can give an idea of the essential features of the flow, heat transfer at the end keels of the wings, and integral layouts of high-speed aircraft. An approximate mathematical model for calculating the heat transfer processes and resistance coefficients near the bodies of complex geometric shapes moving at high speed in the Earth’s atmosphere is formulated. The calculated results for convective heat transfer and friction coefficients for the X-33 and X-43 vehicles are obtained. Full article
(This article belongs to the Special Issue Morphing Enabling Technologies for Aerospace Systems)
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