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Micro Power Technologies for Air and Space Vehicles
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Micro Power Technologies for Air and Space Vehicles

A special issue of Applied Sciences (ISSN 2076-3417). This special issue belongs to the section "Energy Science and Technology".

Deadline for manuscript submissions: closed (20 September 2021) | Viewed by 5340

Special Issue Editors

Dr. Maria Grazia De Giorgi

E-Mail Website
Guest Editor
Department of Engineering for Innovation, University of Salento, Via per Monteroni, 73100 Lecce, Italy
Interests: energy systems; micropropulsion; jet engine; active control; combustion
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Manish Jugroot

E-Mail Website
Guest Editor
Department of Mechanical and Aerospace Engineering, Royal Military College of Canada, PO Box 17000, Station Forces Kingston, Kingston, ON, Canada
Interests: aerospace propulsion; active flow control; micro thruster; plasma simulation
Dr. Pénélope Leyland

E-Mail Website
Guest Editor
SCI-STI-PO, EPFL, Station 9, Ecole Polytechnique Fédérale de Lausanne (EPFL), CH-1015 Lausanne, Switzerland
Interests: turbomachinery; plasma; combustion; material science

Special Issue Information

Dear Colleagues,

Micro power technology has great potential to be enabled in space propulsion systems, i.e., in primary propulsion as well as precision pointing and orbital maneuvering. Moreover, micro power systems enable sensors and actuators, which can be easily integrated to form intelligent onboard systems for both micro unmanned air vehicles and small satellite platforms. These advancements are the result of significant experimental and modeling efforts, as well as technology demonstration missions. This Special Issue aims to seek the high-quality papers from academics and industry-related researchers in the areas of power technology at the micro scale for propulsion systems applied to air and space vehicles, e.g.:

  • High-performing micro power technology, assessment of existing technologies, and development of breakthrough technologies
  • Micropropulsion systems, thermochemical propulsion, electric propulsion, hybrid propulsion, MEMS technologies
  • Microfluidics, microcombustion, and free molecular flows
  • Micro actuators
  • Numerical techniques and computational fluid dynamics
  • Small satellite platforms and micro UAVs

Prof. Dr. Maria Grazia De Giorgi
Prof. Dr. Manish Jugroot
Dr. Pénélope Leyland
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. Applied Sciences is an international peer-reviewed open access semimonthly 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

  • MEMS
  • microfluidics
  • small satellite
  • microcombustion
  • microactuators
  • micro UAV

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Published Papers (2 papers)

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Research

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20 pages, 6641 KiB  
Article
Thrust Augmentation of Micro-Resistojets by Steady Micro-Jet Blowing into Planar Micro-Nozzle
by Donato Fontanarosa, Maria Grazia De Giorgi and Antonio Ficarella
Appl. Sci. 2021, 11(13), 5821; https://doi.org/10.3390/app11135821 - 23 Jun 2021
Cited by 1 | Viewed by 1805
Abstract
The present work investigates the impact of steady micro-jet blowing on the performance of a planar micro-nozzle designed for both liquid micro-thrusters and nitrogen cold-gas micro-resistojets. Two micro-injectors have been placed into the divergent region along the sidewalls, injecting a secondary flow of [...] Read more.
The present work investigates the impact of steady micro-jet blowing on the performance of a planar micro-nozzle designed for both liquid micro-thrusters and nitrogen cold-gas micro-resistojets. Two micro-injectors have been placed into the divergent region along the sidewalls, injecting a secondary flow of propellant perpendicularly to the wall where they have been located. The micro-jet actuator configuration is characterized by the dimensionless momentum coefficient cμ. The best performance improvement is retrieved at the maximum cμ for both water vapor (Δ%T,jet = +22.6% and Δ%Isp,Tjet = +2.9% at cμ = 0.168) and nitrogen gaseous flows (Δ%T,jet = +36.1% and Δ%Isp,Tjet = +9.1% at cμ = 0.297). The fields of the Mach number and the Schlieren computations, in combination with the streamline visualization, reveal the formation of two vortical structures in the proximity of secondary jets, which energize the core flow and enhance the expansion process downstream secondary jets. The compressible momentum thickness along the width-wise direction θxy in presence of secondary injection reduces as a function of cμ. In particular, it becomes smaller than the one computed for the baseline configuration at cμ > 0.1, decreasing up to about and -57% for the water vapor flow at cμ = 0.168, and -64% for the nitrogen gaseous flow at cμ = 0.297. Full article
(This article belongs to the Special Issue Micro Power Technologies for Air and Space Vehicles)
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Review

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18 pages, 6994 KiB  
Review
MEMS Vaporazing Liquid Microthruster: A Comprehensive Review
by Donato Fontanarosa, Luca Francioso, Maria Grazia De Giorgi and Maria Rosaria Vetrano
Appl. Sci. 2021, 11(19), 8954; https://doi.org/10.3390/app11198954 - 26 Sep 2021
Cited by 6 | Viewed by 2565
Abstract
The interest in developing efficient nano and pico-satellites has grown in the last 20 years. Secondary propulsion systems capable of serving specific maneuvers are an essential part of these small satellites. In particular, Micro-Electro-Mechanical Systems (MEMS) Vaporizing Liquid Microthrusters (VLM), using water as [...] Read more.
The interest in developing efficient nano and pico-satellites has grown in the last 20 years. Secondary propulsion systems capable of serving specific maneuvers are an essential part of these small satellites. In particular, Micro-Electro-Mechanical Systems (MEMS) Vaporizing Liquid Microthrusters (VLM), using water as a propellant, represent today a smart choice in terms of simplicity and cost. In this paper, we first propose a review of the international literature focused on MEMS VLM development, reviewing the different geometries and heating solutions proposed in the literature. Then, we focus on a critical aspect of these micro thrusters: the presence of unstable phenomena. In particular, the boiling instabilities and reverse channel flow substantially impact the MEMS VLMs’ performance and limit their applicability. Finally, we review the research focused on the passive and active control of the boiling instabilities, based on VLM geometry optimization and active heating strategies, respectively. Today, these ones represent the two principal research axes followed by the scientific community to mitigate the drawbacks linked to the use of MEMS VLMs. Full article
(This article belongs to the Special Issue Micro Power Technologies for Air and Space Vehicles)
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