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Aerospace
Special Issues
Heat Transfer and Cooling Systems for Aerospace Equipment
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Heat Transfer and Cooling Systems for Aerospace Equipment

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

Deadline for manuscript submissions: closed (31 January 2024) | Viewed by 11628

Special Issue Editors

Dr. Reinaldo R. Souza

E-Mail Website
Guest Editor
Mechanical Engineering Department, Minho University, Campus de Azurém, 4800-058 Guimarães, Portugal
Interests: heat transfer; nanofluids; thermal conductivity; pool boiling; two-phase flows; metal foams; micropillars; nanocoating techniques; renewable energy
Dr. Ana Moita

E-Mail Website
Co-Guest Editor
1. CINAMIL—Centro de Investigação Desenvolvimento e Inovação da Academia Militar, Academia Militar, Instituto Universitário Militar, Rua Gomes Freire, 1169-203 Lisboa, Portugal
2. IN+—Center for Innovation, Technology and Policy Research, Instituto Superior Técnico, Universidade de Lisboa, Avenida Rovisco Pais, 1049-001 Lisboa, Portugal
Interests: energy; solar pannels; cooling; nanofluids; microfluidics; biofluids
Special Issues, Collections and Topics in MDPI journals
Dr. João Ribeiro

E-Mail Website
Co-Guest Editor
Department of Mechanical Technology, School of Technology and Management, Polytechnic Institute of Bragança, Santa Apolónia Campus, 5300-253 Bragança, Portugal
Interests: prosthetic materials; design, control, and biomechanics of prosthesis; manufacturing processes of prosthesis
Special Issues, Collections and Topics in MDPI journals
Dr. Rui A. Lima

E-Mail Website
Co-Guest Editor
Mechanical Engineering Department, Minho University, Campus de Azurém, 4800-058 Guimarães, Portugal
Interests: biomicrofluidics; microcirculation; biofluid mechanics; blood-on-chips; conventional and confocal micro-PIV; nanofluids; energy and environment
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

In this Special Issue on “heat transfer and cooling systems for aerospace equipment”, we welcome review articles and original fundamental, applied, theoretical, numerical or experimental research on the topic of the thermal control of equipment and internal environments of spacecraft, satellites, space laboratories such as space stations and fixed bases on other celestial bodies. Studies should be focused on systems that use a thermofluid. Potential topics include, but are not limited to: the improved performance of cooling systems already used in space, such as heat pipes; new thermofluids and cooling tools applied in space; proposals for the use of materials that have a smaller environmental impact; studies on the behavior of thermofluids in microgravity environments and/or with large thermal amplitudes; the combination of different cooling methods applied in a space environment; the transport and wettability of fluids under microgravity with the potential for space applications; and harnessing extraplanetary resources in cooling systems.

Dr. Reinaldo R. Souza
Dr. Ana Moita
Dr. João Ribeiro
Dr. Rui A. Lima
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. 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 transfer
  • thermofluids
  • mass transport
  • heat transport
  • nanofluids
  • computational fluid dynamics
  • mixing
  • heat sinks

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Published Papers (5 papers)

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Research

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21 pages, 12377 KiB  
Article
Numerical Simulation of Heat Pipe Thermal Performance for Aerospace Cooling System Applications
by Roberto Scigliano, Valeria De Simone, Roberta Fusaro, Davide Ferretto and Nicole Viola
Aerospace 2024, 11(1), 85; https://doi.org/10.3390/aerospace11010085 - 17 Jan 2024
Cited by 5 | Viewed by 2283
Abstract
The design of integrated and highly efficient solutions for thermal management is a key capability for different aerospace products, ranging from civil aircraft using hydrogen on board to miniaturized satellites. In particular, this paper discloses a novel numerical tool for the design and [...] Read more.
The design of integrated and highly efficient solutions for thermal management is a key capability for different aerospace products, ranging from civil aircraft using hydrogen on board to miniaturized satellites. In particular, this paper discloses a novel numerical tool for the design and thermal performance assessment of heat pipes. To achieve this goal, a numerical Ansys Parametric Design Language code is set up to verify the effective subtractive heat flux guaranteed by the selected heat pipe arrangement. The methodology and related tool show their ability to provide good thermal performance estimates for different heat pipe designs and operating conditions. Specifically, the paper reports two very different test cases: (1) solid metal heat pipes to cool down the crotch leading-edge area of the air intake of a Mach 8 civil passenger aircraft, and (2) a copper-water heat pipe to cool down a Printed Circuit Board of a generic small LEO satellite. The successful application of the methodology and numerical code confirms the achievement of the ambitious goal of developing in-house tools to support heat pipe thermal performance prediction for the entire aerospace domain. Full article
(This article belongs to the Special Issue Heat Transfer and Cooling Systems for Aerospace Equipment)
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22 pages, 8422 KiB  
Article
Adaptive Neural Network Global Fractional Order Fast Terminal Sliding Mode Model-Free Intelligent PID Control for Hypersonic Vehicle’s Ground Thermal Environment
by Xiaodong Lv, Guangming Zhang, Zhiqing Bai, Xiaoxiong Zhou, Zhihan Shi and Mingxiang Zhu
Aerospace 2023, 10(9), 777; https://doi.org/10.3390/aerospace10090777 - 31 Aug 2023
Cited by 3 | Viewed by 1382
Abstract
In this paper, an adaptive neural network global fractional order fast terminal sliding mode model-free intelligent PID control strategy (termed as TDE-ANNGFOFTSMC-MFIPIDC) is proposed for the hypersonic vehicle ground thermal environment simulation test device (GTESTD). Firstly, the mathematical model of the GTESTD is [...] Read more.
In this paper, an adaptive neural network global fractional order fast terminal sliding mode model-free intelligent PID control strategy (termed as TDE-ANNGFOFTSMC-MFIPIDC) is proposed for the hypersonic vehicle ground thermal environment simulation test device (GTESTD). Firstly, the mathematical model of the GTESTD is transformed into an ultra-local model to ensure that the control strategy design process does not rely on the potentially inaccurate dynamic GTESTD model. Meanwhile, time delay estimation (TDE) is employed to estimate the unknown terms of the ultra-local model. Next, a global fractional-order fast terminal sliding mode surface (GFOFTSMS) is introduced to effectively reduce the estimation error generated by TDE. It also eliminates arrival time, accelerates the convergence speed of the sliding phase, guarantees finite time arrival, avoids the singularity phenomenon, and bolsters robustness. Then, as the upper bound of the disturbance error is unknown, an adaptive neural network (ANN) control is designed to approximate the upper bound of the estimation error closely and mitigate the chattering phenomenon. Furthermore, the stability of the control system and the convergence time are proven by the Lyapunov stability theorem and are calculated, respectively. Finally, simulation results are conducted to validate the efficacy of the proposed control strategy. Full article
(This article belongs to the Special Issue Heat Transfer and Cooling Systems for Aerospace Equipment)
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23 pages, 8302 KiB  
Article
Efficient Uncertainty Analysis of External Heat Flux of Solar Radiation with External Heat Flux Expansion for Spacecraft Thermal Design
by Xiaoyi Fu, Lei Liang, Wenlai Ma, Hutao Cui and Yang Zhao
Aerospace 2023, 10(8), 672; https://doi.org/10.3390/aerospace10080672 - 28 Jul 2023
Cited by 4 | Viewed by 1669
Abstract
Designing spacecraft involves a careful equilibrium to avoid overengineering or underdesigning, which underscores the importance of employing thermal uncertainty analysis. A key part of this analysis is modeling thermal conditions, but this is often a computationally heavy process. This is largely because ray-tracing [...] Read more.
Designing spacecraft involves a careful equilibrium to avoid overengineering or underdesigning, which underscores the importance of employing thermal uncertainty analysis. A key part of this analysis is modeling thermal conditions, but this is often a computationally heavy process. This is largely because ray-tracing calculations require determining the external heat flux of solar radiation across different operating conditions. Ray emission varies across conditions, which can lead to inefficient resource use in uncertainty calculations. Our study aims to address this by introducing a new approach to calculating the external heat flux of solar radiation that is better suited for uncertainty analysis than previous approaches. Our formula only requires ray tracing to be performed for one condition rather than for every condition. The other conditions are handled by simple matrix budgeting, negating the need for complicated ray tracing. In the aforementioned analytical procedure, certain matrices demonstrate sparsity properties. By exploiting this characteristic, optimization computations can be executed by utilizing sparse matrix algorithms. We tested this new formula, which we call the external heat flux expansion (EHFE) formula, on a specific spacecraft and compared the results with those obtained using the traditional method. Our findings suggest that the EHFE formula is ideal for calculating uncertainty. It significantly improves computational efficiency while maintaining accuracy. The formula is also user-adjustable, allowing the accuracy of uncertainty calculation results of the external heat flux of solar radiation to be fine-tuned by changing the value of the cutoff factor. This work establishes an essential theoretical framework pivotal to addressing inherent uncertainties in the thermal design of upcoming deep-space exploration spacecraft, solar observatory satellites, and space solar power stations. Full article
(This article belongs to the Special Issue Heat Transfer and Cooling Systems for Aerospace Equipment)
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26 pages, 4022 KiB  
Article
An Innovative External Heat Flow Expansion Formula for Efficient Uncertainty Analysis in Spacecraft Earth Radiation Heat Flow Calculations
by Xiaoyi Fu, Yuntao Hua, Wenlai Ma, Hutao Cui and Yang Zhao
Aerospace 2023, 10(7), 605; https://doi.org/10.3390/aerospace10070605 - 30 Jun 2023
Cited by 5 | Viewed by 1297
Abstract
Thermal uncertainty analysis of spacecraft is an important method to avoid overdesign and underdesign problems. In the context of uncertainty analysis, thermal models representing multiple operating conditions must be invoked repeatedly, leading to substantial computational costs. The ray tracing calculation of Earth infrared [...] Read more.
Thermal uncertainty analysis of spacecraft is an important method to avoid overdesign and underdesign problems. In the context of uncertainty analysis, thermal models representing multiple operating conditions must be invoked repeatedly, leading to substantial computational costs. The ray tracing calculation of Earth infrared and albedo radiation heat flux is an important reason for the slow calculation speed. As the rays emitted during external heat flux calculations under different operating conditions are independent and unconnected, the rays produced across various conditions are effectively wasted. In this study, the external heat flow equation is thoroughly expanded and the derived factors are clustered and analyzed to develop a novel formula for calculating external heat flow. When this formula is employed to compute the uncertain external heat flux, only one condition necessitates ray tracing, while the remaining conditions utilize simple matrix operations in place of complex ray tracing. Within the aforementioned procedure, certain matrices demonstrate sparse characteristics. The optimization calculations for these matrices can, therefore, benefit from the application of sparse matrix optimization algorithms. Using a spacecraft as an example, the uncertain external heat flux calculation outcomes of the new and traditional formulas are compared and assessed. The findings reveal that the new formula is highly suitable for estimating uncertain Earth radiation heat flow, with a marked improvement in efficiency. The accuracy is essentially equivalent to that of the traditional formula and the calculation precision can be dynamically adjusted to meet user requirements. The methodology can be further generalized to assess the uncertainties associated with radiative external heat fluxes for other celestial bodies within the solar system. This offers a valuable theoretical framework for addressing the uncertainties in the thermal design of deep space exploration vehicles. Full article
(This article belongs to the Special Issue Heat Transfer and Cooling Systems for Aerospace Equipment)
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Review

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43 pages, 7008 KiB  
Review
A Review of Novel Heat Transfer Materials and Fluids for Aerospace Applications
by Glauco Nobrega, Beatriz Cardoso, Reinaldo Souza, José Pereira, Pedro Pontes, Susana O. Catarino, Diana Pinho, Rui Lima and Ana Moita
Aerospace 2024, 11(4), 275; https://doi.org/10.3390/aerospace11040275 - 30 Mar 2024
Cited by 6 | Viewed by 3356
Abstract
The issue of thermal control for space missions has been critical since the early space missions in the late 1950s. The demands in such environments are heightened, characterized by significant temperature variations and the need to manage substantial densities of heat. The current [...] Read more.
The issue of thermal control for space missions has been critical since the early space missions in the late 1950s. The demands in such environments are heightened, characterized by significant temperature variations and the need to manage substantial densities of heat. The current work offers a comprehensive survey of the innovative materials and thermal fluids employed in the aerospace technological area. In this scope, the materials should exhibit enhanced reliability for facing maintenance and raw materials scarcity. The improved thermophysical properties of the nanofluids increase the efficiency of the systems, allowing the mass/volume reduction in satellites, rovers, and spacecraft. Herein are summarized the main findings from a literature review of more than one hundred works on aerospace thermal management. In this sense, relevant issues in aerospace convection cooling were reported and discussed, using heat pipes and heat exchangers, and with heat transfer ability at high velocity, low pressure, and microgravity. Among the main findings, it could be highlighted the fact that these novel materials and fluids provide enhanced thermal conductivity, stability, and insulation, enhancing the heat transfer capability and preventing the malfunctioning, overheating, and degradation over time of the systems. The resulting indicators will contribute to strategic mapping knowledge and further competence. Also, this work will identify the main scientific and technological gaps and possible challenges for integrating the materials and fluids into existing systems and for maturation and large-scale feasibility for aerospace valorization and technology transfer enhancement. Full article
(This article belongs to the Special Issue Heat Transfer and Cooling Systems for Aerospace Equipment)
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