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Aerospace
Special Issues
Combustion of Solid Propellants
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Combustion of Solid Propellants

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

Deadline for manuscript submissions: 31 March 2025 | Viewed by 654

Special Issue Editor

Dr. Wen Ao

E-Mail Website
Guest Editor
National Key Laboratory of Solid Rocket Propulsion, Northwestern Polytechnical University, Xi’an 710072, China
Interests: solid propellant combustion; advanced energy management technologies; metal combustion
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

Solid rocket motors (SRMs), due to their various advantages, including their inherent simplicity, high reliability, and quick response, play an important role in space launch vehicle design and production. Surveying the demands surrounding the continuous performance improvements and technological development of SRMs, high energy, high pressure, and extreme dimensions are the most important development trends. As combustion is the most critical process for energy release from solid propellants, there has been a growing interest in the fundamental issues inherent to it; indeed, combustion modeling, combustion diagnostics, and two-phase flow simulation are the typical technical challenges faced in efforts to increase the reliability of SRMs. Improving combustion efficiency and burning rate adjustment are also an urgent priority. Building on these needs, this Special Issue aims to provide an overview of the most recent advances in the field of SRM combustion. Potential topics include, but are not limited to, combustion modeling, combustion adjustment, high-pressure combustion, combustion instability assessment, metal behavior and two-phase flow simulation.

Dr. Wen Ao
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

  • propellant combustion
  • combustion adjustment
  • combustion modeling
  • high-pressure combustion

Published Papers (2 papers)

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Research

20 pages, 4782 KiB  
Article
Design of Reverse Bleed Slot for Curved Axisymmetric Inlet Based on Kantrowitz Criterion and Flow Field Characteristics
by Yongzhou Li, Di Sun, Xinhui Tian, Yiqi Yuan, Xisheng Luo and Kunyuan Zhang
Aerospace 2024, 11(7), 553; https://doi.org/10.3390/aerospace11070553 - 4 Jul 2024
Viewed by 166
Abstract
Conventional forward bleed slots reduce the hypersonic inlet starting Mach number but suffer from excessive flow leakage after restart. This paper proposes a novel reverse bleed slot design method for curved axisymmetric inlets of a solid-fuel scramjet. Leveraging the Kantrowitz criterion and detailed [...] Read more.
Conventional forward bleed slots reduce the hypersonic inlet starting Mach number but suffer from excessive flow leakage after restart. This paper proposes a novel reverse bleed slot design method for curved axisymmetric inlets of a solid-fuel scramjet. Leveraging the Kantrowitz criterion and detailed flow analysis, the method optimizes bleed slot placement, number, area, and angle. Results show superior aerodynamic performance by placing slots in the non-starting region of the internal compression section, considering both unstarted flow and separation bubble dynamics during restart. Each bleed slot area is calculated successively down-stream based on the Kantrowitz criterion. Finally, the effects of bleed slot angle have been extensively studied. The key inlet performance reaches its optimum at a slot angle of approximately 130°, achieving a significant reduction in the starting Mach number (from 4.80 to 3.65) and a 50% decrease in bleed flow rate compared to the forward slot design. This method demonstrates its feasibility and effectiveness, enabling substantial improvement in inlet starting performance with minimal flow loss. Full article
(This article belongs to the Special Issue Combustion of Solid Propellants)
17 pages, 3699 KiB  
Article
Numerical and Experimental Analyses of the Effect of Water Injection on Combustion of Mg-Based Hydroreactive Fuels
by Shiyao Shao, Songchen Yue, Hong Qiao, Peijin Liu and Wen Ao
Aerospace 2024, 11(7), 542; https://doi.org/10.3390/aerospace11070542 - 1 Jul 2024
Viewed by 265
Abstract
The energy release process of the Mg-based hydroreactive fuels directly affects the performance of water ramjet engines, and the burning rate is one of the key parameters of the Mg-based hydroreactive fuels. However, there is not enough in-depth understanding of the combustion process [...] Read more.
The energy release process of the Mg-based hydroreactive fuels directly affects the performance of water ramjet engines, and the burning rate is one of the key parameters of the Mg-based hydroreactive fuels. However, there is not enough in-depth understanding of the combustion process of Mg-based hydroreactive fuels within the chamber of water ramjet engines, and there is a lack of effective means of prediction of the burning rate. Therefore, this paper aims to examine the flame structure of Mg-based hydroreactive fuels with a high metal content and analyze the impact of the water injection velocity and droplet diameter on the combustion property. A combustion experiment system was designed to replicate the combustion of Mg-based hydroreactive fuels within water ramjet engines, and the average linear burning rate was calculated through the target line method. On the basis of the experiment, a combustion–flow coupling solution model of Mg-based hydroreactive fuels was formulated, including the reaction mechanism between Mg/H2O and the decomposition products from an oxidizer and binder. The model was validated through experimental results with Mg-based hydroreactive fuels at various pressures and water injection velocities. The mean absolute percentage error (MAPE) in the experimental results was less than 5%, proving the accuracy and validity of the model. The resulting model was employed for simulating the combustion of Mg-based hydroreactive fuels under different water injection parameters. The addition of water injection resulted in the creation of a new high-temperature region, namely the Mg/H2O non-premixed combustion region in addition to improving the radial diffusion of the flame. With the increasing water injection velocity, the characteristic distance of Mg/H2O non-premixed combustion region is decreased, which enhances the heat transfer to burning surface and accelerates the fuel combustion. The impact of droplet parameters was investigated, revealing that larger droplets enhance the penetration of the fuel-rich gas, which is similar to the effect of injection velocity. However, when the droplet size becomes too large, the aqueous droplets do not fully evaporate, resulting in a slight decrease in the burning rate. These findings enhance the understanding of the mechanisms behind the burning rate variation in Mg-based hydroreactive fuels and offer theoretical guidance for the optimal selection of the engine operating parameters. Full article
(This article belongs to the Special Issue Combustion of Solid Propellants)
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