Search for Articles:
Title / Keyword
Author / Affiliation / Email
Journal
Article Type
 
 
Advanced Search
 
Section
Special Issue
Volume
Issue
Number
Page
 
3.4
2.1
Journals
Aerospace
Special Issues
From Satellite Systems Design, Verification and Testing to Spacecraft Operations
share announcement

From Satellite Systems Design, Verification and Testing to Spacecraft Operations

A special issue of Aerospace (ISSN 2226-4310).

Deadline for manuscript submissions: 20 December 2025 | Viewed by 5918

Special Issue Editor

Dr. Andrea Colagrossi

E-Mail Website
Guest Editor
Department of Aerospace Science and Technology, Politecnico di Milano, Via La Masa, 34, 20156 Milano, Italy
Interests: spaceflight mechanics; spacecraft guidance; dynamics and control; attitude determination and control; space system engineering; modelling of spacecraft dynamics; modelling of space systems; sensors and actuators
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

The landscape of spacecraft engineering and satellite operations is rapidly evolving, driven by the increasing sophistication and demands of modern space missions. Today, the design and deployment of spacecraft involve a complex workflow—from initial concept development to in-orbit operations—that requires advanced methodologies and technologies to ensure the success of missions.

Our Special Issue, entitled "From Satellite Systems Design, Verification and Testing to Spacecraft Operations", seeks to explore the intricacies of this evolving field. We invite scholars and researchers to contribute their insights and innovations across the spacecraft lifecycle.

Satellites play a pivotal role in our daily lives, supporting communication, navigation, Earth observation, and scientific exploration. With advancements in technology, satellites are becoming more capable, compact, and autonomous. This evolution presents new challenges in the design, verification, testing, and operational management of this technology. From the conception phase, in which designs are refined to meet stringent mission requirements, to the critical phase of in-orbit testing and operational deployment, every aspect of spacecraft engineering demands precision and efficiency.

In this Special Issue, we welcome research focusing on the design of spacecrafts, encompassing not only the initial phases of satellite system design, but also extending to the verification and testing phases. We are particularly interested in submissions that explore innovative approaches to subsystems and on-board software design, and advanced methodologies for verifying and testing both hardware and software components. We encourage the submission of contributions that discuss digital twin facilities, processor-in-the-loop and hardware-in-the-loop test benches, software solutions that aim to automate and optimize spacecraft operations, as well as results from in-orbit testing activities.

The scope of this Special Issue includes spacecraft system modeling, the design and integration of subsystems, advanced verification techniques, software development methodologies, and operational optimization strategies. We welcome the submission of original research articles, short communications, and reviews that delve into theoretical studies and practical applications, utilizing both analytical, numerical, and experimental approaches.

By fostering collaboration and the sharing of knowledge in this multidisciplinary domain, we aim to advance the state of the art in spacecraft engineering and contribute to the success of future space missions.

We look forward to your valuable contributions to this exciting and transformative field.

Dr. Andrea Colagrossi
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

  • spacecraft design
  • satellite systems
  • verification and testing
  • in-orbit testing
  • spacecraft operations
  • on-board software
  • hardware-in-the-loop testing
  • digital twin
  • operational efficiency
  • autonomous spacecraft
  • software automation
  • mission readiness

Benefits of Publishing in a Special Issue

  • Ease of navigation: Grouping papers by topic helps scholars navigate broad scope journals more efficiently.
  • Greater discoverability: Special Issues support the reach and impact of scientific research. Articles in Special Issues are more discoverable and cited more frequently.
  • Expansion of research network: Special Issues facilitate connections among authors, fostering scientific collaborations.
  • External promotion: Articles in Special Issues are often promoted through the journal's social media, increasing their visibility.
  • e-Book format: Special Issues with more than 10 articles can be published as dedicated e-books, ensuring wide and rapid dissemination.

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

Published Papers (5 papers)

Download All Papers
Order results
Result details
Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:

Research

33 pages, 3295 KiB  
Article
Integrating Model-Based Systems Engineering into CubeSat Development: A Case Study of the BOREALIS Mission
by Lorenzo Nardi, Stefano Carletta, Parsa Abbasrezaee, Giovanni Palmerini, Nicola Lovecchio, Nunzio Burgio, Alfonso Santagata, Massimo Frullini, Donato Calabria, Massimo Guardigli, Elisa Michelini, Maria Maddalena Calabretta, Martina Zangheri, Elisa Lazzarini, Andrea Pace, Marco Montalti, Dario Mordini, Liyana Popova, Saverio Citraro, Daniela Billi, Fabio Lorenzini, Alessandro Donati, Mara Mirasoli and Augusto Nascettiadd Show full author list remove Hide full author list
Aerospace 2025, 12(3), 256; https://doi.org/10.3390/aerospace12030256 - 18 Mar 2025
Viewed by 640
Abstract
The Biofilm Onboard Radiation Exposure Assessment Lab In Space (BOREALIS) mission is a 6U CubeSat initiative funded by the Italian Space Agency under the ALCOR program, executed through a collaboration among the School of Aerospace Engineering of Sapienza University of Rome, Interdepartmental Centre [...] Read more.
The Biofilm Onboard Radiation Exposure Assessment Lab In Space (BOREALIS) mission is a 6U CubeSat initiative funded by the Italian Space Agency under the ALCOR program, executed through a collaboration among the School of Aerospace Engineering of Sapienza University of Rome, Interdepartmental Centre for Industrial Aerospace Research (CIRI Aerospace) of the University of Bologna and Kayser Italia Srl. BOREALIS is equipped with a lab-on-chip payload for studying the effects of microgravity and ionising radiation on microbial biofilms, which are crucial for understanding and preventing persistent infections in space environments. The satellite will operate across multiple orbits, moving from low to medium Earth orbit, to distinctly analyse the impacts of radiation separate from microgravity. The required orbital transfer not only tests the autonomy of its on-board systems in challenging conditions but also places BOREALIS among the first and few CubeSats to have ever attempted such a complex manoeuvre. This study explores the systematic application of Model-Based Systems Engineering to satellite design, from conceptualisation to trade-offs, using a tradespace analysis approach supported by Monte Carlo simulations to optimise mission configurations against performance and cost. Additionally, the adaptability of Model-Based Systems Engineering tools and the reusability of such an approach for other satellite projects are discussed, illustrating the BOREALIS mission as a case study for small mission design considering constraints and requirements. Full article
(This article belongs to the Special Issue From Satellite Systems Design, Verification and Testing to Spacecraft Operations)
►▼ Show Figures

Figure 1

14 pages, 3069 KiB  
Article
An Initial Trajectory Design for the Multi-Target Exploration of the Electric Sail
by Zichen Fan, Fei Cheng, Wenlong Li, Guiqi Pan, Mingying Huo and Naiming Qi
Aerospace 2025, 12(3), 196; https://doi.org/10.3390/aerospace12030196 - 28 Feb 2025
Viewed by 331
Abstract
The electric sail (E-sail), as an emerging propulsion system with an infinite specific impulse, is particularly suitable for ultra-long-distance multi-target deep-space exploration missions. If multiple gravity assists are considered during the exploration process, it can effectively improve the exploration efficiency of the E-sail. [...] Read more.
The electric sail (E-sail), as an emerging propulsion system with an infinite specific impulse, is particularly suitable for ultra-long-distance multi-target deep-space exploration missions. If multiple gravity assists are considered during the exploration process, it can effectively improve the exploration efficiency of the E-sail. This paper proposes a fast optimization algorithm for deep-space multi-target exploration trajectories for the E-sail, which achieves the exploration of multiple celestial bodies and solar-system boundaries in one flight, and introduces a gravity assist to improve the flight speed of the E-sail during the exploration process. By comparing simulation examples under different conditions, the effectiveness of the algorithm proposed in this paper has been demonstrated. This is of great significance for the initial rapid design of complex deep-space exploration missions such as the E-sail multi-target exploration. Full article
(This article belongs to the Special Issue From Satellite Systems Design, Verification and Testing to Spacecraft Operations)
►▼ Show Figures

Figure 1

12 pages, 3740 KiB  
Article
GPU-Accelerated CNN Inference for Onboard DQN-Based Routing in Dynamic LEO Satellite Networks
by Changgeun Yu, Daeyeon Kim, Heoncheol Lee and Myonghun Han
Aerospace 2024, 11(12), 1028; https://doi.org/10.3390/aerospace11121028 - 16 Dec 2024
Viewed by 929
Abstract
This paper addresses the issue of onboard inference for AI-based routing algorithms in dynamic LEO (Low Earth Orbit) satellite networks. In dynamic LEO networks, it is essential to maintain communication performance across varying topologies while considering link disconnections and overcoming computational constraints for [...] Read more.
This paper addresses the issue of onboard inference for AI-based routing algorithms in dynamic LEO (Low Earth Orbit) satellite networks. In dynamic LEO networks, it is essential to maintain communication performance across varying topologies while considering link disconnections and overcoming computational constraints for real-time inference on embedded boards. This paper proposes a GPU-based inference acceleration method to reduce the computation time required for real-time onboard inference of a Dueling DQN (Deep Q-Network)-based routing algorithm in dynamic LEO satellite networks. The approach is composed of memory management, low-level operations, and efficient indexing methods, which collectively enhance computational efficiency. As a result, the proposed method achieves approximately 2.4 times faster inference compared to conventional CPU-based approaches. Additionally, the kernel performance analysis reveals that the proposed method reaches 10% of the peak computational performance and 20% of the peak memory performance. This demonstrates the compatibility of the proposed method for integration with additional applications in the multitasking systems of LEO satellites. Full article
(This article belongs to the Special Issue From Satellite Systems Design, Verification and Testing to Spacecraft Operations)
►▼ Show Figures

Figure 1

19 pages, 3890 KiB  
Article
Long-Baseline Real-Time Kinematic Positioning: Utilizing Kalman Filtering and Partial Ambiguity Resolution with Dual-Frequency Signals from BDS, GPS, and Galileo
by Deying Yu, Houpu Li, Zhiguo Wang, Shuguang Wu, Yi Liu, Kaizhong Ju and Chen Zhu
Aerospace 2024, 11(12), 970; https://doi.org/10.3390/aerospace11120970 - 26 Nov 2024
Viewed by 992
Abstract
This study addresses the challenges associated with single-system long-baseline real-time kinematic (RTK) navigation, including limited positioning accuracy, inconsistent signal reception, and significant residual atmospheric errors following double-difference corrections. This study explores the effectiveness of long-baseline RTK navigation using an integrated system of the [...] Read more.
This study addresses the challenges associated with single-system long-baseline real-time kinematic (RTK) navigation, including limited positioning accuracy, inconsistent signal reception, and significant residual atmospheric errors following double-difference corrections. This study explores the effectiveness of long-baseline RTK navigation using an integrated system of the BeiDou Navigation Satellite System (BDS), Global Positioning System (GPS), and Galileo Satellite Navigation System (Galileo). A long-baseline RTK approach that incorporates Kalman filtering and partial ambiguity resolution is applied. Initially, error models are used to correct ionospheric and tropospheric delays. The zenith tropospheric and inclined ionospheric delays and additional atmospheric error components are then regarded as unknown parameters. These parameters are estimated together with the position and ambiguity parameters via Kalman filtering. A two-step method based on a success rate threshold is employed to resolve partial ambiguity. Data from five long-baseline IGS monitoring stations and real-time measurements from a ship were employed for the dual-frequency RTK positioning experiments. The findings indicate that integrating additional GNSSs beyond the BDS considerably enhances both the navigation precision and the rate of ambiguity resolution. At the IGS stations, the integration of the BDS, GPS, and Galileo achieved navigation precisions of 2.0 cm in the North, 5.1 cm in the East, and 5.3 cm in the Up direction while maintaining a fixed resolution exceeding 94.34%. With a fixed resolution of Up to 99.93%, the integration of BDS and GPS provides horizontal and vertical precision within centimeters in maritime contexts. Therefore, the proposed approach achieves precise positioning capabilities for the rover while significantly increasing the rate of successful ambiguity resolution in long-range scenarios, thereby enhancing its practical use and exhibiting substantial application potential. Full article
(This article belongs to the Special Issue From Satellite Systems Design, Verification and Testing to Spacecraft Operations)
►▼ Show Figures

Figure 1

15 pages, 7281 KiB  
Article
Implementation of a 6U CubeSat Electrical Power System Digital Twin
by Pablo Casado, Cristian Torres, José M. Blanes, Ausiàs Garrigós and David Marroquí
Aerospace 2024, 11(8), 688; https://doi.org/10.3390/aerospace11080688 - 21 Aug 2024
Cited by 2 | Viewed by 1992
Abstract
This paper presents the design of a digital twin for a 6U CubeSat electrical power system, including the solar arrays, solar array regulators, battery, power distribution unit, and load subsystems. The digital twin is validated by comparing its real-time outputs with those of [...] Read more.
This paper presents the design of a digital twin for a 6U CubeSat electrical power system, including the solar arrays, solar array regulators, battery, power distribution unit, and load subsystems. The digital twin is validated by comparing its real-time outputs with those of the physical system. Experimental tests confirm its feasibility, showing that the digital twin’s real-time outputs closely match those of the physical system. Additionally, the digital twin can be used for control-hardware-in-the-loop and power-hardware-in-the-loop tests, allowing the real-time integration of simulated subsystems with hardware. This capability facilitates testing of new subsystems and optimization during the project’s development phases. Additionally, to demonstrate the advanced capabilities of this model, the digital twin is used to simulate the CubeSat electrical power system behavior in real time throughout a complete orbital cycle in low Earth orbit conditions. This simulation provides valuable insights into the CubeSat operation by capturing the transient and steady-state responses of the EPS components under real orbital conditions. The results obtained indicate that the digital twin significantly enhances the testing and optimization process of new subsystems during the development phases of the project. Moreover, the capabilities of the digital twin can be further augmented by incorporating real-time telemetry data from the CubeSat, resulting in a highly accurate replication of the satellite’s in-orbit behavior. This approach is crucial for identifying and diagnosing failures or malfunctions in the electrical power system, ensuring the robust and reliable operation of the CubeSat. Full article
(This article belongs to the Special Issue From Satellite Systems Design, Verification and Testing to Spacecraft Operations)
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-5
Back to TopTop