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Applied Sciences
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Recent Advances in Small Satellite Technologies: A LeanSat Approach
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Recent Advances in Small Satellite Technologies: A LeanSat Approach

A Special Issue of Applied Sciences (ISSN 2076-3417) belonging to the section "Aerospace Science and Engineering".

Deadline for manuscript submissions: 20 February 2027 | Viewed by 3805

Editors

Dr. Jorge Javier Hernández Gómez

E-Mail Website
Guest Editor
Faculty of Sciences, National Autonomous University of Mexico (UNAM), Mexico City, Mexico
Interests: LeanSat; satellite; CubeSat; dynamics modelling and control; algorithm design and optimisation; numerical and scientific computation; aerospace; aerospace engineering; physics mathematics
Prof. Dr. Mengu Cho

E-Mail Website
Guest Editor
1. Laboratory of Lean Satellite Enterprises and In-Orbit Experiments (LaSEINE), Kyushu Institute of Technology, 1-1 Sensui-cho, Tobata-ku, Kitakyushu-shi 804-8550, Fukuoka, Japan
2. Department of Space, Semiconductor and Mechatronics Engineering, Chiba Institute of Technology, 2-17-1 Tsudanuma, Narashino 275-0016, Chiba, Japan
3. School of Electrical and Electronic Engineering, Nanyang Technological University, 50 Nanyang Avenue, Singapore 639798, Singapore
Interests: satellite; spacecraft; space environment; space

Special Issue Information

Dear Colleagues,

The increasing number of satellites launched worldwide has created growing demand for more efficient, cost-effective, and resource-conscious solutions in space technology. In response to these challenges, the Lean Satellite (LeanSat) methodology has emerged as a practical and accessible approach for the development of small-satellite missions. By emphasising simplicity, rapid prototyping, and the optimisation of available resources, LeanSat has enabled academic, research, and emerging space institutions to more actively participate in space exploration and the development of space technology, as well as its massification into large constellation missions.

This Special Issue aims to publish high-quality original research and review articles focused on innovative applications, design strategies, and implementation techniques inspired by the LeanSat philosophy. We welcome contributions that highlight recent advancements in, but not limited to, the following areas:

  • The design, development, and testing of LeanSat-based small satellites;
  • System engineering approaches tailored to LeanSat missions;
  • Cost-effective manufacturing and integration methods;
  • Mission planning, operations, and lifecycle management;
  • Lean-based approaches to payload development and scientific instrumentation;
  • Ground segment design for LeanSat missions;
  • Logistical planning and pre-launch preparations for TT&C systems;
  • Education and capacity building through LeanSat initiatives;
  • Lessons learned from LeanSat projects and best practices;
  • LeanSat Constellation developments.

We look forward to receiving your contributions to this Special Issue and continuing to foster discourse on the role of Lean methodologies in the future of small-satellite technologies.

Dr. Jorge Javier Hernández Gómez
Prof. Dr. Mengu Cho
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 250 words) can be sent to the Editorial Office for assessment.

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-anonymized 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

  • Lean Satellite
  • Small-satellite missions
  • Cost-effective space systems
  • Rapid prototyping
  • System engineering
  • CubeSats
  • Educational space missions
  • Mission operations
  • Payload development
  • Space technology innovation

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Published Papers (3 papers)

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Research

35 pages, 40266 KB  
Article
An Interpretable Anomaly Detection and Identification Framework for Onboard ADCS Fault Management in Nanosatellites
by Karen Wendy Vidaurre Torrez, Franklin Josue Ticona Coaquira, Christian Ricardo Conchari Cabrera, Andres Fernando Aguirre Velez, Litzy Ximena Conde Alvarado, Sol Maria Chamorro Armoa, Jose Rodrigo Cordova Alarcon and Akitoshi Hanazawa
Appl. Sci. 2026, 16(15), 7369; https://doi.org/10.3390/app16157369 - 23 Jul 2026
Viewed by 561
Abstract
Anomaly signals in the Attitude Determination and Control System (ADCS) of nanosatellites can significantly degrade mission performance, especially in the absence of robust Fault Detection, Isolation, and Recovery (FDIR) mechanisms. Thus, traditional threshold-based approaches, while portable and compact, may overlook subtle faults, whereby [...] Read more.
Anomaly signals in the Attitude Determination and Control System (ADCS) of nanosatellites can significantly degrade mission performance, especially in the absence of robust Fault Detection, Isolation, and Recovery (FDIR) mechanisms. Thus, traditional threshold-based approaches, while portable and compact, may overlook subtle faults, whereby abnormal sensor signals or current spikes within the threshold may compromise the operation of the entire ADCS as a subsystem. Furthermore, the lack of interpretable detection methods further limits the development of reliable machine learning (ML) FDIR solutions. To address these limitations, this work presents a wavelet-based anomaly detection framework that introduces a two-stage hybrid architecture combining a lightweight Convolutional Neural Network (CNN) for anomaly detection with logistic regression for fault classification, both based on discrete wavelet transform (DWT) detail coefficients extracted from sensor and actuator data. The framework was validated using a statistics-based anomaly dataset for a 1U CubeSat ADCS simulated in MATLAB, in which anomalies are introduced at the component level with controlled variations in magnitude, frequency, and waveform, ensuring 99% statistical significance. Additionally, to demonstrate operational feasibility, constraints for onboard implementation were considered by executing the proposed framework in a Processor-in-the-Loop (PIL) environment. For benchmarking, lightweight detection and classification algorithms were compared, including Out-Of-Limit (OOL) and compact machine learning approaches. Finally, to identify the framework’s limitations and trace faulty events to physical phenomena, Gradient-weighted Class Activation Mapping (Grad-CAM), SHapley Additive exPlanations (SHAP), and impurity analysis were performed on the proposed algorithms as primary interpretability tools. Consequently, the results demonstrate accurate anomaly detection and identification to support both autonomous FDIR actions and ground operator decision-making. The proposed validation framework and dataset provide a reproducible basis for advancing anomaly detection onboard nanosatellites. Full article
(This article belongs to the Special Issue Recent Advances in Small Satellite Technologies: A LeanSat Approach)
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22 pages, 16268 KB  
Article
Adaptation and Mechanical Validation of a COTS Telescope for LEO Hyperspectral Imaging Using an Additively Manufactured Structure
by Henrik H. Øvrebø, Brage Sterkeby Hole, Henrik Pedersen Hauge, Martin Steinert, Anna Olsen, Fred Sigernes and Joseph L. Garrett
Appl. Sci. 2026, 16(10), 5038; https://doi.org/10.3390/app16105038 - 18 May 2026
Viewed by 644
Abstract
Small satellites provide cost-effective platforms for environmental monitoring. Open-source commercial off-the-shelf (COTS) hyperspectral payloads, such as those launched with HYPSO-1 and -2, have a ground sampling distance (GSD) of 100 m. However, detecting smaller features, such as water quality in lakes, requires a [...] Read more.
Small satellites provide cost-effective platforms for environmental monitoring. Open-source commercial off-the-shelf (COTS) hyperspectral payloads, such as those launched with HYPSO-1 and -2, have a ground sampling distance (GSD) of 100 m. However, detecting smaller features, such as water quality in lakes, requires a GSD below 10 m and a high signal-to-noise ratio. Terrestrial COTS Schmidt–Cassegrain telescopes lack launch-load stiffness and in-orbit refocus capability. This study presents a deployable modified COTS (MCOTS) Schmidt–Cassegrain telescope that uses the original optical COTS components, a 3D-printed high-performance polymer (HPP) structure, and a dual-lead-screw deployment and focusing mechanism. The telescope has a stowed length of 280 mm and deploys to an additional 110 mm, making integration into a 16U platform with a payload length of 290 mm feasible. The modified structure is evaluated using shock and sine-sweep vibration testing, with collimation and focus verified before and after testing. Collimation remained concentric within measurement uncertainty. Complementary random-vibration finite-element simulations predicted a 3σ von Mises stress of 26.5 MPa, yielding a safety factor of 2.8. The results demonstrate a feasible pathway for adapting COTS telescopes toward space-grade COTS (SCOTS) payloads, bridging the gap between rapid production, cost efficiency, and performance for small Earth observation missions. Full article
(This article belongs to the Special Issue Recent Advances in Small Satellite Technologies: A LeanSat Approach)
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24 pages, 10680 KB  
Article
Coverage Ratio–Based Evaluation of Antenna Omnidirectionality for a Pair of Microstrip Patch Antennas on a 6U CubeSat
by Daisuke Nakayama, Kei Sano, Rin Sato, Tohlu Matsushima and Yuki Fukumoto
Appl. Sci. 2026, 16(3), 1552; https://doi.org/10.3390/app16031552 - 3 Feb 2026
Cited by 1 | Viewed by 1057
Abstract
CubeSat missions increasingly rely on microwave-band communication systems, whose antennas often exhibit directional radiation patterns. As a result, multiple antennas are commonly used to improve coverage; however, a quantitative method to evaluate their performance across all spacecraft attitudes has been lacking. This paper [...] Read more.
CubeSat missions increasingly rely on microwave-band communication systems, whose antennas often exhibit directional radiation patterns. As a result, multiple antennas are commonly used to improve coverage; however, a quantitative method to evaluate their performance across all spacecraft attitudes has been lacking. This paper introduces the Coverage Ratio of CubeSat Attitude (CRCA), a metric that quantifies the proportion of orientations for which the antenna gain exceeds a required threshold. CRCA is introduced and demonstrated using the S-band command antenna system of the 6U CubeSat VERTECS. The proposed metric is then used to quantitatively compare multiple antenna placement configurations, clarifying the effect of mounting faces on attitude-dependent coverage. Electromagnetic simulations and three-dimensional radiation pattern measurements using a metal CubeSat enclosure show good agreement when splitter and cable losses are taken into account. The combined radiation pattern achieves greater than −8.0 dBic in 90% of attitudes in simulation, and greater than −10.0 dBic of attitudes in 90% in measurement. Furthermore, a CRCA-based link budget analysis demonstrates that sufficient uplink margin can be conservatively maintained under tumbling conditions. The proposed CRCA framework provides a practical and generalizable approach for evaluating antenna omnidirectionality and attitude-dependent communication performance in CubeSat missions. Full article
(This article belongs to the Special Issue Recent Advances in Small Satellite Technologies: A LeanSat Approach)
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