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Aerospace
Special Issues
Advanced Thermodynamics for Aerospace Application
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Advanced Thermodynamics for Aerospace Application

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

Deadline for manuscript submissions: closed (1 December 2022) | Viewed by 9016

Special Issue Editor

Prof. Dr. Sang Hun Kang

E-Mail Website
Guest Editor
Department of Mechanical and Aerospace Engineering, Konkuk University, Seoul 05029, Korea
Interests: scramjet; ramjet; combined cycle engines; liquid rocket engines; hall thrusters; supersonic windtunnel

Special Issue Information

Dear Colleagues,

Due to the rapid development and combination of the private-led NewSpace industry and information and communication technology, the demand for various technologies to overcome the extreme conditions of the high-altitude atmosphere and space is increasing. Many types of sensitive electronic devices within aerospace vehicles should have the ability to operate in severe environmental condtions and, therefore, be appropriately protected.

This Special Issue invites researchers who attempt to overcome the extreme conditions for aerospace vehicles. The research topics can be regarding not only vehicle protection techniques, but also research on the damage characteristics caused by extreme conditions. The recommended topics include, but are not limited to, the following:

  • Thermal protection techniques in general;
  • Thermal cracking and coking in regenerative cooling;
  • Thermo-structural analysis with external/internal heating conditions;
  • Ablation and damage of materials in hypersonic flows;
  • Effects of non-equilibrium hypersonic flow on aerospace vehicles;
  • Thermal management techniques for aerospace vehicles;
  • Other updates in thermodynamic applications for aerospace vehicles.

Prof. Dr. Sang Hun Kang
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

  • thermal damage
  • thermal protection
  • regenerative cooling
  • thermo-structural analysis
  • ablation
  • hypersonic flows
  • thermal management

Published Papers (3 papers)

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Research

16 pages, 3656 KiB  
Article
PIC-DSMC Simulation of a Hall Thruster Plume with Charge Exchange Effects Using pdFOAM
by Sang Hun Kang
Aerospace 2023, 10(1), 44; https://doi.org/10.3390/aerospace10010044 - 3 Jan 2023
Cited by 4 | Viewed by 2215
Abstract
To develop technologies for the stable operation of electric propulsion systems, the effects of charge exchange (CEX) on the exhaust plume of a Hall thruster were studied using the particle-in-cell direct simulation Monte Carlo (PIC-DSMC) method. For the numerical analysis, an OpenFOAM-based code, [...] Read more.
To develop technologies for the stable operation of electric propulsion systems, the effects of charge exchange (CEX) on the exhaust plume of a Hall thruster were studied using the particle-in-cell direct simulation Monte Carlo (PIC-DSMC) method. For the numerical analysis, an OpenFOAM-based code, pdFOAM, with a simple electron fluid model was employed. In an example problem using the D55 Hall thruster exhaust plume, the results showed good agreement with experimental measurements of the plasma potential. In the results, CEX effects enhanced Xe+ particle scattering near the thruster exit. However, due to the increase in the plasma potential with CEX effects, fewer Xe2+ particles were near the thruster exit with CEX effects than without CEX effects. Full article
(This article belongs to the Special Issue Advanced Thermodynamics for Aerospace Application)
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24 pages, 7193 KiB  
Article
Simulation and Application of a New Multiphase Flow Ablation Test System for Thermal Protection Materials Based on Liquid Rocket Engine
by Qingdong Su, Bailin Zha, Jinjin Wang, Mingxia Yan, Yong Gao, Zhensheng Sun and Weifeng Huang
Aerospace 2022, 9(11), 701; https://doi.org/10.3390/aerospace9110701 - 9 Nov 2022
Cited by 6 | Viewed by 3765
Abstract
Internal flow field ablation is an important issue in thermal protection materials for rocket engines and hypersonic vehicles. In this paper, a new multiphase flow ablation test system, with an Al2O3 particle delivery device based on an oxygen-kerosene liquid rocket [...] Read more.
Internal flow field ablation is an important issue in thermal protection materials for rocket engines and hypersonic vehicles. In this paper, a new multiphase flow ablation test system, with an Al2O3 particle delivery device based on an oxygen-kerosene liquid rocket engine, is designed and manufactured. A general variable-precision modular system simulation method is proposed to analyze the dynamic characteristics of the system. In addition, a unique internal flow field ablation test was performed on the 4D C/C composite simulating the working conditions of the SRM. The results show that the system can provide a wide temperature range (756~3565 K) and pressure range (0.2~4.2 MPa). The multi-disciplinary dynamic variable-precision system simulation method is helpful for more accurate design and test analysis, and the maximum error is less than 5%. The ablation tests show that the line ablation rate of the C/C composite nozzle at 3380 K and 1 MPa is 0.053 mm/s, verifying the combined effect of thermochemical and mechanical ablation. The ablation environment is controllable, which provides an effective way for the ablation test of thermal protection materials. In addition, the variable-precision dynamic simulation method has important reference value for the system design related to liquid rocket engine. Full article
(This article belongs to the Special Issue Advanced Thermodynamics for Aerospace Application)
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21 pages, 12617 KiB  
Article
Numerical Investigation on the Jet Characteristics and the Heat and Drag Reductions of Opposing Jet in Hypersonic Nonequilibrium Flows
by Wenqing Zhang, Xiaowei Wang, Zhijun Zhang and Tianyi Su
Aerospace 2022, 9(10), 554; https://doi.org/10.3390/aerospace9100554 - 26 Sep 2022
Cited by 1 | Viewed by 1593
Abstract
We adopted the transient numerical method for the simulation of an ELECTRE vehicle with an opposing jet at an altitude of 53.3 km and 13 Ma to explore the jet characteristics as well as the performance in heat and drag reductions of the [...] Read more.
We adopted the transient numerical method for the simulation of an ELECTRE vehicle with an opposing jet at an altitude of 53.3 km and 13 Ma to explore the jet characteristics as well as the performance in heat and drag reductions of the opposing jet in hypersonic nonequilibrium flows. The time-accurate, nonequilibrium N-S equations coupled with the five-species Park chemical kinetic model and vibrational energy excitation were applied, and an open source solver Hy2FOAM based on the OpenFOAM platform was adopted. Three opposing jets with different jet radii (R7 jet, R14 jet, and R21 jet) were investigated. The results show that with the increasing jet flow rate, the jet mode of the opposing jet with a small jet radius varies from the overflow mode to the long penetration mode (LPM) and finally to the short penetration mode (SPM), while that with a large jet radius directly changes from the overflow mode to the SPM. The state of the jet in the overflow mode is stable, whereas in SPM and LPM, it is unstable. The investigation of the heat and drag reductions for the R7, R14, and R21 jets shows that except for the jet in LPM, the jet in SPM and overflow mode can provide effective thermal protection, and the thermal protection is enhanced with the increasing jet flow rate. Moreover, the jet in both LPM and SPM can effectively reduce the aerodynamic drag, but the jet in overflow mode cannot provide effective drag reduction. Moreover, the jet with a large radius and in the overflow mode has a better thermal protection effect, and a small jet radius contributes to the drag reduction. Full article
(This article belongs to the Special Issue Advanced Thermodynamics for Aerospace Application)
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