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Aerospace
Special Issues
Aircraft Thermal Management Technologies
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Aircraft Thermal Management Technologies

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: 31 December 2025 | Viewed by 2411

Special Issue Editors

Dr. Yongqi Xie

E-Mail Website
Guest Editor
School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China
Interests: advanced loop heat pipe technologies; electronics’ thermal management; flow and heat transfer analysis
Prof. Dr. Hongwei Wu

E-Mail Website
Guest Editor
School of Physics, Engineering and Computer Science, University of Hertfordshire, Hatfield AL10 9AB, UK
Interests: sustainable manufacturing; fluid–solid conjugate heat transfer; battery thermal management system (BTMS); two-phase and multiphase flow; modelling/simulation methods (CFD); AI and machine learning (ML)
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Aircraft thermal management technologies are critical to ensuring the reliable operation of modern aircraft systems, particularly as advancements in avionics, propulsion, and power systems have led to significant increases in heat generation. Effective thermal management is essential to maintaining optimal performance, ensuring safety, and extending the lifespan of various aircraft components. As aircraft designs become more complex and integrate advanced technologies, the need for sophisticated thermal management solutions has become increasingly important.

The primary focus of this Special Issue is to share new cutting-edge research, progress, and insights in this prominent research area worldwide. Contributions are invited to address a wide range of applications, spanning topics including but not limited to the following:

  • modelling and simulation of thermal management systems;
  • fuel thermal management technologies;
  • environmental control technologies;
  • effective thermal transport technologies;
  • passive cooling technologies;
  • active cooling technologies;
  • thermoelectric conversion technology;
  • waste heat recovery and utilization in aircrafts;
  • advanced materials for aircraft thermal management;
  • heat exchanger design and optimization in aircrafts.

Dr. Yongqi Xie
Prof. Dr. Hongwei Wu
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

  • thermal management
  • thermal transport
  • environmental control
  • active/passive cooling
  • thermoelectric conversion
  • waste heat recovery
  • heat exchanger
  • energy storage
  • hybrid cooling systems

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Published Papers (2 papers)

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Research

34 pages, 10843 KiB  
Article
Study on Multi-Heat-Source Thermal Management of Hypersonic Vehicle Based on sCO2 Brayton Cycle
by Xin Qi, Zhihong Zhou, Huoxing Liu and Zhongfu Tang
Aerospace 2025, 12(7), 575; https://doi.org/10.3390/aerospace12070575 - 25 Jun 2025
Viewed by 353
Abstract
To address the thermal protection challenges of multiple high-temperature components and the electrical power deficiency in hypersonic vehicles, this study proposes twelve multi-heat-source thermoelectric conversion schemes based on the sCO2 Brayton cycle. A three-dimensional evaluation system for thermal management is established, incorporating [...] Read more.
To address the thermal protection challenges of multiple high-temperature components and the electrical power deficiency in hypersonic vehicles, this study proposes twelve multi-heat-source thermoelectric conversion schemes based on the sCO2 Brayton cycle. A three-dimensional evaluation system for thermal management is established, incorporating thermal efficiency, coolant mass flow rate, and system mass as key metrics. A comprehensive parameter sensitivity analysis was conducted on the twelve dual-heat-source cycle configurations. For systematic performance comparison, the Non-dominated Sorting Genetic Algorithm II (NSGA-II) was employed for multi-objective optimization, with Pareto fronts analyzed to determine optimal configurations. The results demonstrate that appropriately increasing the minimum cycle temperature can significantly reduce coolant flow requirements. Multi-objective optimization reveals the following: (1) The pre-compressed aero-comb configuration achieves optimal performance in the efficiency-mass flow rate optimization scenario; (2) Both pre-compressed aero-comb and re-compressed comb-aero configurations show superiority in the efficiency-mass optimization scenario; (3) The pre-compressed aero-comb configuration exhibits lower system mass in low coolant flow regions for the mass flow rate-mass optimization scenario. Overall, the performance of the precompression aero-comb configuration is relatively superior. This work provides an important reference for the design of thermal management systems for hypersonic vehicles. Full article
(This article belongs to the Special Issue Aircraft Thermal Management Technologies)
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28 pages, 11218 KiB  
Article
Transient Temperature Evaluation and Thermal Management Optimization Strategy for Aero-Engine Across the Entire Flight Envelope
by Weilong Gou, Shiyu Yang, Kehan Liu, Yuanfang Lin, Xingang Liang and Bo Shi
Aerospace 2025, 12(6), 562; https://doi.org/10.3390/aerospace12060562 - 19 Jun 2025
Viewed by 500
Abstract
With the enhancement of thermodynamic cycle parameters and heat dissipation constraints in aero-engines, effective thermal management has become a critical challenge to ensure safe and stable engine operation. This study developed a transient temperature evaluation model applicable to the entire flight envelope, considering [...] Read more.
With the enhancement of thermodynamic cycle parameters and heat dissipation constraints in aero-engines, effective thermal management has become a critical challenge to ensure safe and stable engine operation. This study developed a transient temperature evaluation model applicable to the entire flight envelope, considering fluid–solid coupling heat transfer on both the main flow path and fuel systems. Firstly, the impact of heat transfer on the acceleration and deceleration performance of a low-bypass-ratio turbofan engine was analyzed. The results indicate that, compared to the conventional adiabatic model, the improved model predicts metal components absorb 4.5% of the total combustor energy during cold-state acceleration, leading to a maximum reduction of 1.42 kN in net thrust and an increase in specific fuel consumption by 1.18 g/(kN·s). Subsequently, a systematic evaluation of engine thermal management performance throughout the complete flight mission was conducted, revealing the limitations of the existing thermal management design and proposing targeted optimization strategies, including employing Cooled Cooling Air technology to improve high-pressure turbine blade cooling efficiency, dynamically adjusting low-pressure turbine bleed air to minimize unnecessary losses, optimizing fuel heat sink utilization for enhanced cooling performance, and replacing mechanical pumps with motor pumps for precise fuel supply control. Full article
(This article belongs to the Special Issue Aircraft Thermal Management Technologies)
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