Propulsion Solutions for Enhancing the Small Launchers’ Competitiveness
A special issue of Aerospace (ISSN 2226-4310).
Deadline for manuscript submissions: 31 December 2025 | Viewed by 111
Special Issue Editor
Interests: chemical propulsion; fluid dynamics
Special Issues, Collections and Topics in MDPI journals
Special Issue Information
Dear Colleagues,
As we know, we are witnessing the continuous, remarkable expansion of the small-satellite market, driven by the rise of constellations and Low-Earth Orbit (LEO) applications.
Currently, the most common orbit insertion technique for nano- and micro-satellites is to take advantage of ride-share opportunities on a heavy launch rocket, typically dedicated to a primary customer.
However, dedicated launch options, where the payload owner does not have to share space with other missions, offer a more predictable and reliable schedule, as well as a customized trajectory and target orbit. This means that the payload is not subject to delays caused by other ride-share customers, which allows for a more flexible timeline.
This growing need calls for dedicated and affordable launch strategies, which can be created by improving the small-launch vehicle technology that has been in development and operation since the mid-1950s.
A small-lift launch vehicle is commonly defined as a rocket capable of launching up to a 2000 kg payload to LEO, in contrast to a heavy launcher like, for instance, the SpaceX’s Falcon 9 rocket, which brings 22800 kg to LEO.
Despite some recent signs of slowdown, the field of small launchers continues to grow; the main challenge in this area is reducing the launch cost per kilogram of payload, which, compared to the ride-share option, is still an order of magnitude higher. This effort focuses on searching for more efficient systems, which requires reducing the structural mass through advances in lightweight materials, as well as component miniaturization and integration. In this context, the propulsion system plays a key role.
Historically, on the one hand, liquid rocket engines have been well established, offering reliability and the highest performance. On the other hand, hybrid rockets, though considerably less mature, combine simplicity with inherent safety, leading to shorter development times and lower costs. By properly tailoring the configuration of both propulsion systems, significant benefits can be gained in optimizing the overall launcher architecture.
This Special Issue will explore varied topics related to advancing small-launcher technology. It will collect papers that contribute substantially to the state of the art in both propulsion systems, with a particular emphasis on methods to reduce launch costs, such as the following:
(i) The use of low-cost, green propellants;
(ii) Customized solutions for turbo or electric pumps;
(iii) The utilization of new technologies for manufacturing composite structures;
(iv) Novel 3D printing techniques.
Dr. Carmine Carmicino
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
- green propellants
- hybrid rockets
- liquid rockets
- efficient propulsion systems
- small-satellites
- light-weight composite structures
- 3D printing
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