Aerospace Combustion Engineering (2nd Edition)

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

Deadline for manuscript submissions: 28 February 2025 | Viewed by 4774

Special Issue Editors


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Department of Industrial Engineering, Alma Mater Studiorum Università di Bologna, 47121 Forli, Italy
Interests: aerospike; solid propellants; solid motors modelling; plasma thrusters; plasma modelling and simulation
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Guest Editor
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, 20133 Milano, Italy
Interests: hybrid rocket propulsion; propellants; space propulsion; metal fuels
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

We are pleased to announce a second edition of the Special Issue on Aerospace Combustion Engineering, with its aim being to explore the latest advancements and research in combustion for aerospace applications. Combustion remains a critical aspect of various systems that require high energy density, even in the context of a greener economy. Thermo-chemical systems will continue to play a dominant role in rocketry and long-range aeroengines, necessitating a deeper understanding of combustion fundamentals and their applications.

One of the key challenges in aerospace engineering is the quest for cleaner thrust production. To achieve this, it is imperative to enhance the efficiency of energy utilization while simultaneously reducing the environmental impact, particularly in terms of CO2 and other pollutant emissions. This Special Issue provides a platform for publishing cutting-edge research and investigations focused on combustion fundamentals and applications.

We invite submissions that explore novel techniques and instrumentations for monitoring and diagnosing flow characteristics within flames and expanding gases. Characterization methods and novel data dealing with reacting flow field properties in combustion chambers and plumes will be of interest. Additionally, we welcome contributions that explore new types of fuels and propellants as well as improved combustors or burner architectures. Furthermore, contributions exploring the integration of fuel cell technologies with combustion systems, such as novel hybrid power systems, advanced fuel cell architectures, and optimized thermal management strategies, are highly encouraged. Finally, we are interested in the development of enhanced modeling and simulation techniques for understanding the complex processes involved in combustion, including heat transfer, flame dynamics, turbulence, mixing, chemical reactions, and equilibrium.

Submissions can encompass a wide range of aerospace applications, including solid, liquid, and hybrid rockets; gas turbines, internal combustion engines, fuel cells, aerospikes, ramjets, and scramjets; as well as fundamental combustion studies with a particular focus on aerospace-related aspects.

We encourage researchers and experts in the field to share their ground-breaking work, ideas, and insights to foster advancements in aerospace combustion engineering. We look forward to receiving your contributions to this Special Issue on Aerospace Combustion Engineering. 

Prof. Dr. Fabrizio Ponti
Prof. Dr. Filippo Maggi
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.

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Related Special Issue

Published Papers (3 papers)

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Research

17 pages, 7100 KiB  
Article
Effects of Fuel Penetration on the RDE Performance with JISC Injector Configuration
by Gyeong-Ui Mo, In-Hoi Koo, Keon-Hyeong Lee, Su-Wan Choi and Jeong-Yeol Choi
Aerospace 2024, 11(9), 752; https://doi.org/10.3390/aerospace11090752 - 13 Sep 2024
Viewed by 759
Abstract
This study investigates the operational characteristics of the Rotating Detonation Engine (RDE), with a focus on fuel injector design. Inspired by the similarity between the fuel injection structure of RDE and the Jet in Supersonic Crossflow (JISC) of a scramjet, experimental research on [...] Read more.
This study investigates the operational characteristics of the Rotating Detonation Engine (RDE), with a focus on fuel injector design. Inspired by the similarity between the fuel injection structure of RDE and the Jet in Supersonic Crossflow (JISC) of a scramjet, experimental research on fuel injectors with jet penetration was conducted. Five injectors were designed, each with a fixed fuel injection area or injection hole diameter. Experiments determined practical injection areas, and an empirical correlation was used to calculate jet penetration heights. Under conditions of a total mass flow rate of 105 ± 5 g/s and an equivalence ratio of 1.05 ± 0.1, combustion modes were analyzed. Initial detonation occurrence was assessed through pressure history, with a detailed analysis via image post-processing. The results indicated that the injector D4N15, with the highest jet penetration height, exhibited deflagration, while D4N23 showed chaotic propagation. The injector D2N60 demonstrated relatively unstable behavior in sustained detonation cases. Thrust comparisons revealed that D4N30, with wider hole spacing and higher jet penetration height, exhibited approximately 12.5% higher specific impulse compared to D1N240. These outcomes confirm the significant impact of jet penetration height and hole spacing on detonation propagation and engine performance. Full article
(This article belongs to the Special Issue Aerospace Combustion Engineering (2nd Edition))
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21 pages, 40654 KiB  
Article
Monoethanolamine-Based Fuels Hypergolic with Rocket-Grade Hydrogen Peroxide
by Luca Caffiero, Stefania Carlotti and Filippo Maggi
Aerospace 2024, 11(4), 309; https://doi.org/10.3390/aerospace11040309 - 16 Apr 2024
Cited by 1 | Viewed by 2175
Abstract
The object of this work is to study the ignition performances of promising catalytically promoted amino-based green fuels to be used in combination with rocket-grade hydrogen peroxide. The main hypergolic parameter, the ignition delay time, was experimentally determined with an automated drop test [...] Read more.
The object of this work is to study the ignition performances of promising catalytically promoted amino-based green fuels to be used in combination with rocket-grade hydrogen peroxide. The main hypergolic parameter, the ignition delay time, was experimentally determined with an automated drop test setup. Additionally, the kinematic viscosity was experimentally measured, while the CEA2 software was used to determine the ideal rocket performances of the propellants. Three inorganic copper salts were selected as catalysts to be used in combination with monoethanolamine in concentrations ranging from 0.5 wt% to 20 wt%. Then, N,N-dimethylethylenediamine was introduced as part of a blend with monoethanolamine to target the high viscosity and low gravimetric specific impulse of the fuel for the pure monoethanolamine case. Due to the reduced monoethanolamine and low additive content, some formulations were observed to be characterized by gravimetric specific impulse higher than 320 s, and kinematic viscosity lower than 5 cSt while retaining ignition delay times shorter than 30 ms with 98 wt% HTP. Finally, the addition of ethanol to the blend was preliminarily investigated to improve the additive solubility. The effects on the ignition delay time were found to depend on the concentration ratio of the two amines. Full article
(This article belongs to the Special Issue Aerospace Combustion Engineering (2nd Edition))
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16 pages, 4767 KiB  
Article
Comparative Study of Numerical Schemes for Granular Combustion of Boron Potassium Nitrate
by Annie Rose Elizabeth, Sumit Sarma, T. Jayachandran, P. A. Ramakrishna and Mondeep Borthakur
Aerospace 2024, 11(4), 251; https://doi.org/10.3390/aerospace11040251 - 23 Mar 2024
Viewed by 1100
Abstract
Multiple applications in aerospace utilize pyrotechnic charges for their operation, and these charges are predominantly in the form of granules. One of the most used charges is boron potassium nitrate (BPN), and the present study focuses on mathematically modeling granular combustion, its experimental [...] Read more.
Multiple applications in aerospace utilize pyrotechnic charges for their operation, and these charges are predominantly in the form of granules. One of the most used charges is boron potassium nitrate (BPN), and the present study focuses on mathematically modeling granular combustion, its experimental recreation, and carrying out a comparative study on three upwind schemes for its numerical simulation. A customized version of the seven-equation compressible multifluid formulation is presented in this paper to model granular combustion mathematically. Three upwind schemes, namely HLLC, AUSM+-up, and HLLC-AUSM, are used for the numerical comparison. Utilizing these, an axisymmetric code is developed for the comparative study. To experimentally replicate granular combustion, granular BPN is fired in a closed bomb test facility, and the experimental pressure history is used for the numerical comparisons. The developed code can adequately predict the physics of granular combustion, and all three schemes are equally capable of numerical prediction. Full article
(This article belongs to the Special Issue Aerospace Combustion Engineering (2nd Edition))
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