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Aerospace
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Green Propulsion: Present Solutions and Perspectives for Powering Environmentally Friendly...
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Green Propulsion: Present Solutions and Perspectives for Powering Environmentally Friendly Space Missions (2nd Edition)

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Astronautics & Space Science".

Deadline for manuscript submissions: 31 October 2025 | Viewed by 769

Special Issue Editors

Dr. Filippo Maggi

E-Mail Website
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
Dr. Paravan Christian

E-Mail Website
Guest Editor
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, 20133 Milano, Italy
Interests: hybrid rocket propulsion; metal combustion; nano-sized materials; green propellants
Special Issues, Collections and Topics in MDPI journals
Dr. Stefania Carlotti

E-Mail Website
Guest Editor
Dipartimento di Scienze e Tecnologie Aerospaziali, Politecnico di Milano, 20133 Milano, Italy
Interests: hybrid rocket propulsion; green propellants; space propulsion

Special Issue Information

Dear Colleagues,

The pursuit of increased sustainability permeates research in many different fields, including space industry and propulsion. While many propulsion systems still rely on performing solutions that offer a strong heritage but feature high toxicity, space agencies have accelerated the development of new green propellants and technologies. Green propellants aim to combine performance with safer, more eco-friendly, and more sustainable life cycles.

Following the first Special Issue on this topic, edited by Prof. Filippo Maggi and Prof. Christian Paravan, “Green Propulsion: Present Solutions and Perspectives for Powering Environmentally Friendly Space Missions (2nd Edition)” aims to collect contributions on the latest advancements and future challenges in this rapidly evolving field.

We invite submissions in the field of thermochemical propulsion covering experimental, numerical, and theoretical research on green propellants for launchers and in-space operations. Potential topics include, but are not limited to, the following:

  • Development of non-toxic solid, liquid, and hybrid propellants, including the use of eco-friendly materials, advanced composites, and 3D-printed materials.
  • Studies exploring the design, development, and optimization of green thermochemical propulsion, including AI-assisted investigations.
  • Life cycle assessments of green propulsion technologies on environment and humans, from manufacturing to disposal.
  • Status advancement/final conclusions of projects concerning green propulsion topics.
  • Literature surveys, trade-off analyses, and evaluation studies on green propulsion solutions.

Dr. Filippo Maggi
Dr. Paravan Christian
Dr. Stefania Carlotti
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

  • green propulsion
  • solid propulsion
  • liquid propulsion
  • hybrid propulsion
  • propellant
  • pollution
  • environmental impact
  • space industry
  • clean technologies

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Related Special Issue

Published Papers (2 papers)

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Research

14 pages, 2013 KiB  
Article
Lab-Scale Thermal Decomposition of Hydrogen Peroxide as Green Propellant over Low-Cost Catalysts Based on Copper Deposited on Different Supports
by Imane Remissa, Ahmed E. S. Nosseir, Amit Tiwari, Ahmed Bachar, Assia Mabrouk and Rachid Amrousse
Aerospace 2025, 12(5), 440; https://doi.org/10.3390/aerospace12050440 - 15 May 2025
Viewed by 120
Abstract
The thermal decomposition of hydrogen peroxide (H2O2) as a promising green propellant was performed over free-noble metallic-based catalysts deposited on abundant supports. A 30% (w/w) H2O2 liquid was decomposed over 1 wt.% [...] Read more.
The thermal decomposition of hydrogen peroxide (H2O2) as a promising green propellant was performed over free-noble metallic-based catalysts deposited on abundant supports. A 30% (w/w) H2O2 liquid was decomposed over 1 wt.% of copper-based catalysts deposited on three different supports: γ-alumina, graphite and monocrystal clay. In this research work, the catalytic performance of the thermal decomposition of H2O2 was carried out by measuring the differential pressure (ΔP) versus time at initial constant temperatures and, for the first time, by the DTA-TG technique and by the DIP-MS technique at atmospheric pressure. The obtained preliminary results showed that copper deposited on alumina and on graphite are promising catalysts for the decomposition of the H2O2 liquid propellant. Moreover, the natural clay can be valorized on the thermal decomposition of H2O2 due to its high resistivity and high surface area. The N2-physisorption technique and scanning electron microscopy technique were used to characterize the effect of the texture properties on the decomposition and to understand the morphological characteristics of the catalyst. Full article
(This article belongs to the Special Issue Green Propulsion: Present Solutions and Perspectives for Powering Environmentally Friendly Space Missions (2nd Edition))
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18 pages, 8128 KiB  
Article
Investigation of Performance Stability of a Nytrox Hybrid Rocket Propulsion System
by Shih-Sin Wei, Jui-Cheng Hsu, Hsi-Yu Tso and Jong-Shinn Wu
Aerospace 2025, 12(5), 372; https://doi.org/10.3390/aerospace12050372 - 25 Apr 2025
Viewed by 330
Abstract
Nitrous oxide is a highly suitable oxidizer for hybrid rockets due to its self-pressurizing properties, moderate cost, and high accessibility. However, its vapor pressure and density are highly dependent on ambient temperature, requiring careful consideration of temperature variations in real applications. To mitigate [...] Read more.
Nitrous oxide is a highly suitable oxidizer for hybrid rockets due to its self-pressurizing properties, moderate cost, and high accessibility. However, its vapor pressure and density are highly dependent on ambient temperature, requiring careful consideration of temperature variations in real applications. To mitigate this issue, an oxidizer called Nytrox was produced by adding a small fraction of oxygen to bulk nitrous oxide. This modification enables the hybrid rocket propulsion system to maintain a nearly constant average thrust and total impulse across a wide range of ambient temperatures. A series of 7 s hot-fire tests of a small Nytrox/polypropylene hybrid rocket engine operating at ~60 barA of running tank pressure demonstrated a consistent average thrust of 45.3 ± 0.7 kgf and a total impulse of 307.6 ± 3.9 kgf·s within a N2O temperature range of 5.9–22.6 °C, compared to highly varying values of the N2O/polypropylene one within a N2O temperature range of 10.8–29.8 °C. Furthermore, the specific impulse of the Nytrox hybrid rocket engine increases mildly with decreasing temperature because of the increasing amount of added oxygen that benefits the combustion for generating the thrust. Full article
(This article belongs to the Special Issue Green Propulsion: Present Solutions and Perspectives for Powering Environmentally Friendly Space Missions (2nd Edition))
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