Advances in Detonative Propulsion (2nd Edition)

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

Deadline for manuscript submissions: 31 August 2025 | Viewed by 1127

Special Issue Editors


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Guest Editor
Institute of Mechanics, Chinese Academy of Sciences, Beijing 100190, China
Interests: oblique detonation engine; detonative propulsion; supersonic combustion; scramjets; high-enthalpy shock tunnel; high-temperature gas dynamics; hypersonic aerodynamics and aerothermal dynamics
Special Issues, Collections and Topics in MDPI journals

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Guest Editor
School of Power and Energy, Northwestern Polytechnical University, Xi’an 710072, China
Interests: combustion and flow; detonation; two-phase flow; low-carbon fuel; optimization; power and energy

Special Issue Information

Dear Colleagues,

Detonative propulsion represents the new generation of hypersonic propulsion techniques. Research in this field is booming, and many advances have been made globally in recent years. This Special Issue aims to publish these cutting-edge research results to promote the development of detonative propulsion and the cooperation of researchers in this field.

The topics for this Special Issue are broad, including (but not limited to):

  • Oblique detonation engines;
  • Rotating detonation engines;
  • Pulsed detonation engines;
  • Shock-induced supersonic combustion;
  • Detonation-assisted scramjets;
  • Propulsive performance analysis of detonation engines;
  • The fundamental physics of gaseous detonation and multiphase detonation;
  • The design of detonation engines;
  • Other research related to detonative propulsion techniques.

We invite authors to contribute new research results to this Special Issue.

Dr. Yunfeng Liu
Prof. Dr. Zhiwu Wang
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

  • oblique detonation engine
  • rotating detonation engine
  • pulsed detonation engine
  • shock-induced supersonic combustion
  • detonation-assisted scramjets
  • propulsive performance analysis
  • gaseous detonation
  • multiphase detonation

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Published Papers (1 paper)

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Research

21 pages, 5057 KiB  
Article
Reduced-Order Model for Performance Simulation and Conceptual Design of Rocket-Type Pulse Detonation Engines
by Luis Sánchez de León, Francisco Sastre, Elena Martin and Angel Velazquez
Aerospace 2025, 12(2), 132; https://doi.org/10.3390/aerospace12020132 - 10 Feb 2025
Viewed by 712
Abstract
A model-based method has been developed for the performance simulation and conceptual design of rocket-type pulse detonation engines (PDEs). A reduced-order model (ROM) has been generated based on the high order singular value decomposition of a data tensor obtained from CFD computations. This [...] Read more.
A model-based method has been developed for the performance simulation and conceptual design of rocket-type pulse detonation engines (PDEs). A reduced-order model (ROM) has been generated based on the high order singular value decomposition of a data tensor obtained from CFD computations. This ROM could be used to solve the direct (performance) and inverse (design) problems in the context of the early phases of pulse detonation engine design. Output performance parameters are predicted from prescribed input operation/geometry parameters in the direct problem, and vice versa in the inverse problem. The focus of this method is industrial application in situations where large parametric searches are to be performed with a reasonable level of fidelity at a low computational cost. It was found that the performance and conceptual design tool thus developed provides results that deviate, on average, by less than 10% from the CFD results. Regarding practical implementation, the method allows for shifting the heavier computational load off-line. In this way, when working on-line, the user can obtain results in less than a second for every single case. The main contribution of this study is showing that a model-based approach that combines CFD and tensor decomposition has the potential to extract a maximum of information from a given computational effort. This characteristic makes the method of interest for early design phases in the aerospace industry. Full article
(This article belongs to the Special Issue Advances in Detonative Propulsion (2nd Edition))
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