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Aerospace
Special Issues
Small Satellite Missions
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Small Satellite Missions

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

Deadline for manuscript submissions: 31 January 2025 | Viewed by 6982

Special Issue Editors

Dr. Paolo Marzioli

E-Mail Website
Guest Editor
Department of Mechanical and Aerospace Engineering, Sapienza University of Rome, via Eudossiana 18, 00184, Rome, Italy
Interests: CubeSats; small satellites; satellites system engineering; satellite constellations; in-orbit experiments; satellite navigation; space system development and operations; space traffic management; space debris
Special Issues, Collections and Topics in MDPI journals
Dr. Necmi Cihan Örger

E-Mail Website
Guest Editor
Laboratory of Small Satellite Enterprises and In-Orbit Experiments (LaSeine), Kyushu Institute of Technology, via 1-1, Kitakyushu 804-8550, Japan
Interests: CubeSats; small satellites; satellite system engineering; earth observation; remote sensing; space weather; space environment; in-orbit experiments; optical payloads

Special Issue Information

Dear Colleagues,

The miniaturization of spacecraft and in-orbit technologies is leading to a broader usage of small satellite platforms for technology demonstration, scientific experiments, and New Space businesses in the Earth's orbit. Given the number and the significance of the small satellite market and the exploitation of such platforms for scientific purposes, we propose the Aerospace Special Issue on “Small Satellite Missions”.

This aims to bring together cutting-edge research on the development of novel technologies, experiments, and methodologies for the development, assurance, and operations of small satellites. We encourage submissions that explore a wide range of innovative techniques and technologies, including but not limited to:

  • Small satellite (mini-, micro-, nano-, and pico-satellite) missions design and development.
  • Miniaturization of technologies for implementation in small satellites.
  • Assembly, Integration and Verification (AIV) approaches to small satellite missions and constellations.
  • Constellation and swarms design and operations.
  • Distributed ground segment networks for small satellite missions.
  • Innovative approaches to system engineering applied to small satellite missions.
  • Subsystems development and operations for small satellite missions and operators.
  • New mission profiles (MEO, HEO, Near-Earth, Lunar, Deep Space, Planetary) for small satellite missions.
  • Trajectory design and navigation systems.
  • Small satellites tracking and space traffic management.

Authors are encouraged to present original research articles that provide a comprehensive overview of the state-of-the-art in this rapidly evolving field.

Dr. Paolo Marzioli
Dr. Necmi Cihan Örger
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

  • small satellites
  • CubeSats
  • nano-satellites
  • micro-satellites
  • mini-satellites
  • AIV
  • system engineering
  • space systems
  • mission analysis
  • space traffic management

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Further information on MDPI's Special Issue polices can be found here.

Published Papers (7 papers)

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Research

18 pages, 8038 KiB  
Article
Efficient Power Conditioning: Enhancing Electric Supply for Small Satellite Missions
by Shoaib Ahmed Khan, Anwar Ali, Mustafa Tahir and Zou Tao
Aerospace 2024, 11(11), 920; https://doi.org/10.3390/aerospace11110920 - 8 Nov 2024
Viewed by 375
Abstract
Electric power supply (EPS) is the heart of any aerospace mission and plays an important role in improving the performance and service lifetime of spacecraft. It generates, converts, stores, and distributes power to different voltage levels. The EPS is composed of solar panels, [...] Read more.
Electric power supply (EPS) is the heart of any aerospace mission and plays an important role in improving the performance and service lifetime of spacecraft. It generates, converts, stores, and distributes power to different voltage levels. The EPS is composed of solar panels, a power conditioning unit (PCU), batteries, and a power distribution unit (PDU). This paper describes the design and analysis of an efficient power conditioning system for a CubeSat standard small satellite. For this purpose, the aim of this paper is to propose a two-input maximum power point tracker (MPPT)-based interleaved boost converter. The design copes with the fact that when a satellite revolves around the Earth, a single panel or at most two panels face solar radiation at different angles. In order to extract maximum power from the panels, the designed converter drives the solar panels at the maximum power point (MPP). A small signal model is drawn for the converter, and the closed-loop gain of the converter is analyzed using a Bode diagram. To improve the phase margin and gain, a PID compensator is designed and added to the closed loop of the converter. Finally, the performance of the proposed converter is validated by the simulation results. Full article
(This article belongs to the Special Issue Small Satellite Missions)
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25 pages, 3319 KiB  
Article
Preliminary Design of a GNSS Interference Mapping CubeSat Mission: JamSail
by Luis Cormier, Tasneem Yousif, Samuel Thompson, Angel Arcia Gil, Nishanth Pushparaj, Paul Blunt and Chantal Cappelletti
Aerospace 2024, 11(11), 901; https://doi.org/10.3390/aerospace11110901 - 31 Oct 2024
Viewed by 514
Abstract
The JamSail mission is an educational CubeSat aiming to design, develop, and demonstrate two new technologies on a small satellite, tentatively scheduled for launch no earlier than 2026. When launched, JamSail will demonstrate the functionality of two new payloads in low Earth orbit. [...] Read more.
The JamSail mission is an educational CubeSat aiming to design, develop, and demonstrate two new technologies on a small satellite, tentatively scheduled for launch no earlier than 2026. When launched, JamSail will demonstrate the functionality of two new payloads in low Earth orbit. First, a flexible, low-cost GNSS interference detection payload capable of characterising and geolocating the sources of radio interference regarding the E1/L1 and E5a/L5 bands will be demonstrated on a global scale. The data produced by this payload can be used to target anti-interference actions in specific regions and aid in the design of future GNSS receivers to better mitigate specific types of interference. If successful, the flexibility of the payload will allow it to be remotely reconfigured in orbit to investigate additional uses of the technology, including a potential demonstration of GNSS reflectometry aboard a CubeSat. Second, a compact refractive solar sail will be deployed that is capable of adjusting the orbit of JamSail in the absence of an on-board propellant. This sail will be used to gradually raise the semi-major axis of JamSail over the span of the mission before being used to perform rapid passive deorbit near the end-of-life juncture. Additionally, self-stabilising optical elements within the sail will be used to demonstrate a novel method of performing attitude control. JamSail is currently in the testing phase, and the payloads will continue to be refined until the end of 2024. This paper discusses the key objectives of the JamSail mission, the design of the payloads, the expected outcomes of the mission, and future opportunities regarding the technologies as a whole. Full article
(This article belongs to the Special Issue Small Satellite Missions)
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22 pages, 3215 KiB  
Article
Flexible Natural Language-Based Image Data Downlink Prioritization for Nanosatellites
by Ezra Fielding and Akitoshi Hanazawa
Aerospace 2024, 11(11), 888; https://doi.org/10.3390/aerospace11110888 - 28 Oct 2024
Viewed by 742
Abstract
Nanosatellites increasingly produce more data than can be downlinked within a reasonable time due to their limited bandwidth and power. Therefore, an on-board system is required to prioritize scientifically significant data for downlinking, as described by scientists. This paper determines whether natural language [...] Read more.
Nanosatellites increasingly produce more data than can be downlinked within a reasonable time due to their limited bandwidth and power. Therefore, an on-board system is required to prioritize scientifically significant data for downlinking, as described by scientists. This paper determines whether natural language processing can be used to prioritize remote sensing images on CubeSats with more flexibility compared to existing methods. Two approaches implementing the same conceptual prioritization pipeline are compared. The first uses YOLOv8 and Llama2 to extract image features and compare them with text descriptions via cosine similarity. The second approach employs CLIP, fine-tuned on remote sensing data, to achieve the same. Both approaches are evaluated on real nanosatellite hardware, the VERTECS Camera Control Board. The CLIP approach, particularly the ResNet50-based model, shows the best performance in prioritizing and sequencing remote sensing images. This paper demonstrates that on-orbit prioritization using natural language descriptions is viable and allows for more flexibility than existing methods. Full article
(This article belongs to the Special Issue Small Satellite Missions)
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26 pages, 4402 KiB  
Article
Fuel-Efficient and Fault-Tolerant CubeSat Orbit Correction via Machine Learning-Based Adaptive Control
by Mahya Ramezani, Mohammadamin Alandihallaj and Andreas M. Hein
Aerospace 2024, 11(10), 807; https://doi.org/10.3390/aerospace11100807 - 30 Sep 2024
Viewed by 765
Abstract
The increasing deployment of CubeSats in space missions necessitates the development of efficient and reliable orbital maneuvering techniques, particularly given the constraints on fuel capacity and computational resources. This paper presents a novel two-level control architecture designed to enhance the accuracy and robustness [...] Read more.
The increasing deployment of CubeSats in space missions necessitates the development of efficient and reliable orbital maneuvering techniques, particularly given the constraints on fuel capacity and computational resources. This paper presents a novel two-level control architecture designed to enhance the accuracy and robustness of CubeSat orbital maneuvers. The proposed method integrates a J2-optimized sequence at the high level to leverage natural perturbative effects for fuel-efficient orbit corrections, with a gated recurrent unit (GRU)-based low-level controller that dynamically adjusts the maneuver sequence in real-time to account for unmodeled dynamics and external disturbances. A Kalman filter is employed to estimate the pointing accuracy, which represents the uncertainties in the thrust direction, enabling the GRU to compensate for these uncertainties and ensure precise maneuver execution. This integrated approach significantly enhances both the positional accuracy and fuel efficiency of CubeSat maneuvers. Unlike traditional methods, which either rely on extensive pre-mission planning or computationally expensive control algorithms, our architecture efficiently balances fuel consumption with real-time adaptability, making it well-suited for the resource constraints of CubeSat platforms. The effectiveness of the proposed approach is evaluated through a series of simulations, including an orbit correction scenario and a Monte Carlo analysis. The results demonstrate that the integrated J2-GRU system significantly improves positional accuracy and reduces fuel consumption compared to traditional methods. Even under conditions of high uncertainty, the GRU-based control layer effectively compensates for errors in thrust direction, maintaining a low miss distance throughout the maneuvering period. Additionally, the GRU’s simpler architecture provides computational advantages over more complex models such as long short-term memory (LSTM) networks, making it more suitable for onboard CubeSat implementations. Full article
(This article belongs to the Special Issue Small Satellite Missions)
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39 pages, 9779 KiB  
Article
The 3Cat-4 Spacecraft Thermal Analysis and Thermal Vacuum Test Campaign Results
by Jeimmy Nataly Buitrago-Leiva, Ines Terraza-Palanca, Luis Contreras-Benito, Lara Fernandez, Guillem Gracia-Sola, Cristina del Castillo Sancho, Lily Ha, David Palma, Malgorzata Solyga and Adriano Camps
Aerospace 2024, 11(10), 805; https://doi.org/10.3390/aerospace11100805 - 30 Sep 2024
Viewed by 631
Abstract
3Cat-4 is the fourth member of the CubeSat series of UPC’s NanoSat Lab, and it was selected by the ESA Academy’s Fly Your Satellite! program in 2017. This mission aims at demonstrating the capabilities of nano-satellites, and in particular those based in [...] Read more.
3Cat-4 is the fourth member of the CubeSat series of UPC’s NanoSat Lab, and it was selected by the ESA Academy’s Fly Your Satellite! program in 2017. This mission aims at demonstrating the capabilities of nano-satellites, and in particular those based in the 1-Unit CubeSat standard, for challenging Earth Observation (EO) using Global Navigation Satellite System-Reflectometry (GNSS-R) and L-band microwave radiometry, as well as for Automatic Identification Systems (AIS). The following study presents the results of the thermal analysis carried out for this mission, evaluating different scenarios, including the most critical cases at both high and low temperatures. The results consider different albedos and orbital parameters in order to establish the optimal temperatures to achieve the best mission performance within the nominal temperatures, and in all operational modes of the satellite. Simulation results are included considering the thermal performance of other materials, such as Kapton, as well as the redesign of the optical properties of the satellite’s solar panels. The correlation with the thermal model and the TVAC test campaign was conducted at the ESA ESEC-GALAXIA facilities in Belgium. Full article
(This article belongs to the Special Issue Small Satellite Missions)
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17 pages, 8318 KiB  
Article
The Development of a 3D-Printed Compliant System for the Orientation of Payloads on Small Satellites: Material Characterization and Finite Element Analysis of 3D-Printed Polyetherketoneketone (PEKK)
by Morgane Domerg, Benjamin Ostré, Yoann Joliff, Yves-Henri Grunevald and Antoine Dubois Garcia
Aerospace 2024, 11(4), 294; https://doi.org/10.3390/aerospace11040294 - 10 Apr 2024
Cited by 1 | Viewed by 1162
Abstract
This article focuses on the development of a 3D-printed 2-degree-of-freedom (DOF) joint for the payloads’ orientation on small satellites. This system is a compliant mechanism, meaning that this monolithic system composed of cross-axis flexural pivots (CAFPs) produces complex movements through the elastic deformation [...] Read more.
This article focuses on the development of a 3D-printed 2-degree-of-freedom (DOF) joint for the payloads’ orientation on small satellites. This system is a compliant mechanism, meaning that this monolithic system composed of cross-axis flexural pivots (CAFPs) produces complex movements through the elastic deformation of its structure. Using fused filament fabrication (FFF), a demonstrator made of Polyetherketoneketone (PEKK) is printed to determine its potential compatibility with space conditions. Focusing on a segment of the joint, the CAFP, this study aims for an enhancement of its mechanical behavior through the study of its printing direction and the creation of an accurate finite element model of this compliant mechanism. First, material characterization of 3D-printed PEKK is achieved through differential scanning calorimetry tests of the filament and flexural and tensile tests of specimens printed in different printing directions. Then, these data are used to perform a finite element analysis of different CAFP designs and compare their mechanical response of their 3D-printed twin using digital image correlation software. Finally, the CAFP structures were observed by X-ray tomography. The results show that printing direction greatly influences both flexural and tensile strength. Voids induced by the FFF process could impact the mechanical behavior of 3D-printed parts as the simple CAFP design has a better test/model correlation than complex ones. This could influence its resistance to space environment. Full article
(This article belongs to the Special Issue Small Satellite Missions)
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27 pages, 4254 KiB  
Article
A Study on the Derivation of Atmospheric Water Vapor Based on Dual Frequency Radio Signals and Intersatellite Communication Networks
by Ramson Munyaradzi Nyamukondiwa, Necmi Cihan Orger, Daisuke Nakayama and Mengu Cho
Aerospace 2023, 10(9), 807; https://doi.org/10.3390/aerospace10090807 - 15 Sep 2023
Cited by 2 | Viewed by 1551
Abstract
The atmospheric total water vapor content (TWVC) affects climate change, weather patterns, and radio signal propagation. Recent techniques such as global navigation satellite systems (GNSS) are used to measure TWVC but with either compromised accuracy, temporal resolution, or spatial coverage. This [...] Read more.
The atmospheric total water vapor content (TWVC) affects climate change, weather patterns, and radio signal propagation. Recent techniques such as global navigation satellite systems (GNSS) are used to measure TWVC but with either compromised accuracy, temporal resolution, or spatial coverage. This study demonstrates the feasibility of predicting, mapping, and measuring TWVC using spread spectrum (SS) radio signals and software-defined radio (SDR) technology on low Earth-orbiting (LEO) satellites. An intersatellite link (ISL) communication network from a constellation of small satellites is proposed to achieve three-dimensional (3D) mapping of TWVC. However, the calculation of TWVC from satellites in LEO contains contribution from the ionospheric total electron content (TEC). The TWVC and TEC contribution are determined based on the signal propagation time delay and the satellites’ positions in orbit. Since TEC is frequency dependent unlike TWVC, frequency reconfiguration algorithms have been implemented to distinguish TWVC. The novel aspects of this research are the implementation of time stamps to deduce time delay, the unique derivation of TWVC from a constellation setup, the use of algorithms to remotely tune frequencies in real time, and ISL demonstration using SDRs. This mission could contribute to atmospheric science, and the measurements could be incorporated into the global atmospheric databases for climate and weather prediction models. Full article
(This article belongs to the Special Issue Small Satellite Missions)
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