Thermophysics and Heat Transfer for Aerospace Applications

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: closed (20 March 2023) | Viewed by 16580

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Guest Editor
Department of Industrial Engineering, University of Rome “Tor Vergata”, 00133 Rome, Italy
Interests: renewable energy sources; energy communities; energy exchange modelling; environment protection through RECs; social Impact of RECs
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Special Issue Information

Dear Colleagues,

The motivation for this Special Issue is to present a series of research articles in various areas of both experimental, numerical and theoretical heat transfer and fluid dynamics studies (and not only) for aerospace applications. Heat exchangers to cool electronic components, design of the thermal protection for a spacecraft, study of the fluid-structure thermal interaction or energy production are topics to face on an aerospace mission. Furthermore, in the recent years new materials are emerging in similar applications for thermal protections, sensors, actuators…. Based on your previous valuable work, we invite you to participate in this Special Issue by submitting a review or research article.

Dr. Sandra Corasaniti
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.

Keywords

  • heat shields
  • Thermophysical properties of composites, green composites and new materials
  • energy harvesting
  • fluid-structure interaction
  • heat exchangers

Published Papers (4 papers)

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Research

13 pages, 3148 KiB  
Article
Investigating the Temperature Shock of a Plate in the Framework of a Static Two-Dimensional Formulation of the Thermoelasticity Problem
by Andry Sedelnikov, Valeria Serdakova, Denis Orlov and Alexandra Nikolaeva
Aerospace 2023, 10(5), 445; https://doi.org/10.3390/aerospace10050445 - 11 May 2023
Cited by 4 | Viewed by 1023
Abstract
The paper investigates the stress–strain state of a homogeneous rectangular plate after a temperature shock. It is believed that the plate is the first approximation of the solar panel model of a small spacecraft. To study the stress–strain state of the plate, a [...] Read more.
The paper investigates the stress–strain state of a homogeneous rectangular plate after a temperature shock. It is believed that the plate is the first approximation of the solar panel model of a small spacecraft. To study the stress–strain state of the plate, a two-dimensional thermoelasticity problem is posed. The problem has a static formulation, since it does not take into account the dynamics of the plate’s natural oscillations. These oscillations affect the stress–strain state through the initial deflection of the plate at the time of the temperature shock. This deflection changes the parameters of the temperature shock and does not allow the use of a one-dimensional formulation of the thermoelasticity problem. As a result of solving the static two-dimensional thermoelasticity problem, approximate solutions are obtained for the components of the plate point’s displacement vector after the temperature shock. An approximation of the temperature field is presented. A numerical simulation is carried out. The correspondence of the obtained approximate analytical dependencies of the components of the plate point’s displacement vector to the numerical simulation data is analyzed. The proposed method can be used to assess the significance of the influence of the small spacecraft’s solar panels temperature shock on the dynamics of its rotational motion. Full article
(This article belongs to the Special Issue Thermophysics and Heat Transfer for Aerospace Applications)
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24 pages, 6153 KiB  
Article
Heat Conduction and Microconvection in Nanofluids: Comparison between Theoretical Models and Experimental Results
by Gianluigi Bovesecchi, Sandra Corasaniti, Girolamo Costanza, Fabio Piccotti, Michele Potenza and Maria Elisa Tata
Aerospace 2022, 9(10), 608; https://doi.org/10.3390/aerospace9100608 - 15 Oct 2022
Cited by 2 | Viewed by 1502
Abstract
A nanofluid is a suspension consisting of a uniform distribution of nanoparticles in a base fluid, generally a liquid. Nanofluid can be used as a working fluid in heat exchangers to dissipate heat in the automotive, solar, aviation, aerospace industries. There are numerous [...] Read more.
A nanofluid is a suspension consisting of a uniform distribution of nanoparticles in a base fluid, generally a liquid. Nanofluid can be used as a working fluid in heat exchangers to dissipate heat in the automotive, solar, aviation, aerospace industries. There are numerous physical phenomena that affect heat conduction in nanofluids: clusters, the formation of adsorbate nanolayers, scattering of phonons at the solid–liquid interface, Brownian motion of the base fluid and thermophoresis in the nanofluids. The predominance of one physical phenomenon over another depends on various parameters, such as temperature, size and volume fraction of the nanoparticles. Therefore, it is very difficult to develop a theoretical model for estimating the effective thermal conductivity of nanofluids that considers all these phenomena and is accurate for each value of the influencing parameters. The aim of this study is to promote a way to find the conditions (temperature, volume fraction) under which certain phenomena prevail over others in order to obtain a quantitative tool for the selection of the theoretical model to be used. For this purpose, two sets (SET-I, SET-II) of experimental data were analyzed; one was obtained from the literature, and the other was obtained through experimental tests. Different theoretical models, each considering some physical phenomena and neglecting others, were used to explain the experimental results. The results of the paper show that clusters, the formation of the adsorbate nanolayer and the scattering of phonons at the solid–liquid interface are the main phenomena to be considered when φ = 1 ÷ 3%. Instead, at a temperature of 50 °C and in the volume fraction range (0.04–0.22%), microconvection prevails over other phenomena. Full article
(This article belongs to the Special Issue Thermophysics and Heat Transfer for Aerospace Applications)
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16 pages, 5032 KiB  
Article
Numerical Modeling of Heat Exchanger Filled with Octahedral Lattice Frame Porous Material
by Bi Zhao, Jingzhou Zhang and Wenlei Lian
Aerospace 2022, 9(5), 238; https://doi.org/10.3390/aerospace9050238 - 26 Apr 2022
Cited by 1 | Viewed by 2200
Abstract
A numerical investigation into the fluid flow and heat transfer process in a 3D-printed shell-and-tube heat exchanger was carried out. The shell side of the heat exchanger was inserted with octahedral lattice frame porous material to enhance the heat transfer. In order to [...] Read more.
A numerical investigation into the fluid flow and heat transfer process in a 3D-printed shell-and-tube heat exchanger was carried out. The shell side of the heat exchanger was inserted with octahedral lattice frame porous material to enhance the heat transfer. In order to avoid establishing a complex grid system, the porous material of the shell side was modeled by a porous media model. The non-equilibrium model was adopted for the modeling of the heat exchange between the solid and fluid in porous media. An experimental investigation was carried out to validate the feasibility of this approach. The result indicates that the simplified approach is capable of providing an appropriate prediction of the pressure drop and heat transfer efficiency with moderate computational resources. The average error of pressure loss and heat transfer effectiveness is within 4% and 6.1%. Full article
(This article belongs to the Special Issue Thermophysics and Heat Transfer for Aerospace Applications)
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25 pages, 16152 KiB  
Article
New Thermal Design Strategy to Achieve an 80-kg-Class Lightweight X-Band Active SAR Small Satellite S-STEP
by Tae-Yong Park, Bong-Geon Chae, Hongrae Kim, Kyung-Rae Koo, Sung-Chan Song and Hyun-Ung Oh
Aerospace 2021, 8(10), 278; https://doi.org/10.3390/aerospace8100278 - 24 Sep 2021
Cited by 9 | Viewed by 4069
Abstract
The main objective of the S-STEP (the Small Synthetic Aperture Radar (SAR) Technology Experimental Project (S-STEP)) mission is developing an 80-kg-class active X-band SAR observation small satellite. For lighter, smaller, better, and cheaper development of the S-STEP system, a new thermal design strategy [...] Read more.
The main objective of the S-STEP (the Small Synthetic Aperture Radar (SAR) Technology Experimental Project (S-STEP)) mission is developing an 80-kg-class active X-band SAR observation small satellite. For lighter, smaller, better, and cheaper development of the S-STEP system, a new thermal design strategy is essential. Therefore, we proposed a new thermal design strategy in this study. The main features of the proposed thermal design involve the minimization of heater power consumption by optimizing environmental heat fluxes on the satellite, the provision of long-term SAR imaging duration in both right- and left-looking modes, and the use of a lightweight flexible graphite sheet as a thermal interface for some high-power instruments. These features contribute to minimizing the satellite’s mass budget through heater power minimization and achieving on-orbit system performance of S-STEP. The effectiveness of the proposed thermal design was numerically verified by on-orbit thermal analysis of the S-STEP system. In addition, the thermal design on a key payload component and the multifunctional transmit/receive module structure were verified through a space-simulated thermal vacuum test. Full article
(This article belongs to the Special Issue Thermophysics and Heat Transfer for Aerospace Applications)
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