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Aerospace
Special Issues
From Satellite Systems Design, Verification and Testing to Spacecraft Operations
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From Satellite Systems Design, Verification and Testing to Spacecraft Operations

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

Deadline for manuscript submissions: 31 March 2025 | Viewed by 1944

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

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

Published Papers (2 papers)

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Research

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 344
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)
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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
Viewed by 1017
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)
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