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
On-Board Systems Design for Aerospace Vehicles (2nd Edition)
share announcement

On-Board Systems Design for Aerospace Vehicles (2nd Edition)

A special issue of Aerospace (ISSN 2226-4310). This special issue belongs to the section "Aeronautics".

Deadline for manuscript submissions: 30 June 2025 | Viewed by 4509

Special Issue Editors

Dr. Davide Ferretto

E-Mail Website
Guest Editor
DIMEAS - Department of Mechanical and Aerospace Engineering, Politecnico di Torino, Turin, Italy
Interests: model-based systems engineering; aircraft conceptual design (conventional and high-speed); preliminary design of on-board systems
Special Issues, Collections and Topics in MDPI journals
Dr. Fabrizio Stesina

E-Mail Website
Guest Editor
DIMEAS - Department of Mechanical and Aerospace Engineering, Politecnico di Torino, Turin, Italy
Interests: advanced spacecraft design; spacecraft subsystems development; assembly, integration and verification strategies
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

We are pleased to announce a new edition of the open access Special Issue on the MDPI journal “Aerospace” dedicated to on-board systems design for aerospace vehicles. The aim of this Special Issue is to collect the most recent research advancements in the field of on-board systems design, belonging to both aeronautics and space vehicles, with focus on innovative concepts and technologies. In fact, systems engineering in the aerospace domain represents one of the most complex challenges of our time and we strongly believe that the dissemination of relevant results in this field is crucial to support and inspire the work of the scientific community. As Guest Editors of this Special Issue, we kindly invite you to submit full-research articles manuscripts addressing (but not being limited to) the following topics:

  • High-level design of on-board systems including functional architecture definition and concept of operation;
  • Model-Based Systems Engineering practices for aerospace systems design;
  • Aerospace systems modelling and simulation;
  • Heterogeneous simulation techniques for dynamic performance assessment of aerospace systems.
  • Digital twin concepts for aerospace systems analysis and design;
  • Reliability and safety assessment of on-board systems;
  • Innovative on-board systems architectures;
  • Multi-functional plants for energy management;
  • On-board power generation;
  • Environmental control and ice protection system architectures;
  • Flight control and attitude control systems;
  • Propellant management and green fuels;
  • Hybrid-electric system to support green propulsion plants;
  • Avionic systems and on-board computer architectures;
  • On-board systems for unconventional vehicle configurations;
  • Fault Detection, Identification and Recovery (FDIR) systems and strategies
  • Onboard autonomy
  • Development of Ground Support Equipment
  • Innovative Guidance, Navigation and Control systems for satellites
  • Communication system: Intersatellite links and multi-beams communication

Dr. Davide Ferretto
Dr. Fabrizio Stesina
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

  • on-board systems design
  • aerospace systems engineering
  • systems modelling and simulation
  • systems verification

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 polices can be found here.

Published Papers (6 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

24 pages, 3589 KiB  
Article
Methods for Analyzing Avionics Reliability Reflecting Atmospheric Radiation in the Preliminary Development Phase: An Integrated Failure Rate Analysis
by Dongmin Lee and Jongwhoa Na
Aerospace 2025, 12(2), 118; https://doi.org/10.3390/aerospace12020118 - 3 Feb 2025
Viewed by 99
Abstract
Abstract: Advances in deep submicron semiconductor technology have increased the significance of studying soft errors caused by atmospheric radiation in avionics systems. Atmospheric radiation particles, such as protons and neutrons, can induce Single Event Upsets (SEUs) in sensitive electronic components, leading to system [...] Read more.
Abstract: Advances in deep submicron semiconductor technology have increased the significance of studying soft errors caused by atmospheric radiation in avionics systems. Atmospheric radiation particles, such as protons and neutrons, can induce Single Event Upsets (SEUs) in sensitive electronic components, leading to system malfunctions and data corruption. Traditional reliability analysis based on older IC or LSI components may fail to account for radiation-induced effects. However, modern avionics systems equipped with state-of-the-art VLSI components are increasingly susceptible to Single Event Upsets (SEUs), potentially leading to underestimated failure rates in these advanced systems. This study introduces an integrated failure rate analysis that incorporates both the physics of failure rates resulting from aging and wear-out and soft error rates induced by atmospheric radiation. The proposed failure rate analysis of the reliability of avionics operating at altitudes of up to 18 km by combining the physics of failure rates with radiation-induced failure rates was derived using a semi-empirical SEU estimation method. Case studies using the Zynq 7000 board, sourced from AMD (San Jose, USA), confirmed that the integrated failure rate analysis provides more accurate reliability predictions compared to conventional analysis. This approach is expected to improve the accuracy of safety assessments during the preliminary development stages, leading to a shortened development timeline and enhanced design quality. Full article
(This article belongs to the Special Issue On-Board Systems Design for Aerospace Vehicles (2nd Edition))
27 pages, 4291 KiB  
Article
Digital Twin-Driven Design of an Ice Prediction Model
by Andrea Serino, Alberto Dagna, Eugenio Brusa and Cristiana Delprete
Aerospace 2025, 12(2), 107; https://doi.org/10.3390/aerospace12020107 - 31 Jan 2025
Viewed by 269
Abstract
This paper describes the development of an ice creation model to be used within the framework of a model-based systems engineering approach to predict the amount of ice growing on aircraft wings during flight. This model supports the preliminary design of the ice [...] Read more.
This paper describes the development of an ice creation model to be used within the framework of a model-based systems engineering approach to predict the amount of ice growing on aircraft wings during flight. This model supports the preliminary design of the ice protection system, as well as the implementation of a control system, in real-time. When the aircraft meets a high concentration of super-cooled water in the atmosphere and a low temperature, the risk of ice formation on its external surfaces is significant. This causes a decrease in aerodynamic performance, with potential loss of control of the aircraft. To mitigate this effect, ice prevention and protection systems are crucial. The characteristics of the icing phenomena are first defined, then their effects on aircraft behavior during operation are evaluated. This allows us to develop a highly parametric predictive model of the actual icing conditions experienced by the aircraft during a given flight mission. To precisely predict the ice accretion and to design an ice protection system, estimating heat fluxes involving the aircraft’s wing surfaces and the external environment is required. To allow for this, this study also develops a thermal model that is specifically applied to the above-mentioned analysis. This model includes many factors characterizing the atmospheric conditions responsible for ice creation upon the aerodynamic surfaces, and it enables an accurate estimation and quantification of all the parameters necessary to design an appropriate ice protection system. Full article
(This article belongs to the Special Issue On-Board Systems Design for Aerospace Vehicles (2nd Edition))
18 pages, 5101 KiB  
Article
Implications of Output Impedance Mask Stability on Power Bus Architectures Used in Space Platforms
by José A. Carrasco, Juan B. Ejea, Ausias Garrigós, Esteban Sanchis, José M. Blanes, Agustín Ferreres, David Marroquí and David Gilabert
Aerospace 2025, 12(2), 80; https://doi.org/10.3390/aerospace12020080 - 24 Jan 2025
Viewed by 338
Abstract
The European Power Standard, used when designing and implementing spacecraft power buses, imposes stringent impedance requirements for high reliability and robustness, unlike other standards such as those from the American Institute for Aeronautics and Astronautics, SAE International, or the International Deep Space Interoperability [...] Read more.
The European Power Standard, used when designing and implementing spacecraft power buses, imposes stringent impedance requirements for high reliability and robustness, unlike other standards such as those from the American Institute for Aeronautics and Astronautics, SAE International, or the International Deep Space Interoperability Standard. These strict requirements, however, may limit innovations leveraging new technologies resulting from recent component advancements. This work examines the implications of the European Power Standard’s output impedance criteria for stability and its impact on payload power supplies, focusing on the potential to increase operational frequencies in power supply topologies to reduce system volume and mass, which are key factors in space technology. Full article
(This article belongs to the Special Issue On-Board Systems Design for Aerospace Vehicles (2nd Edition))
►▼ Show Figures

Figure 1

29 pages, 2494 KiB  
Article
A Conceptual Comparison of Hydraulic and Electric Actuation Systems for a Generic Fighter Aircraft
by Alessandro Dell’Amico and Christopher Reichenwallner
Aerospace 2025, 12(1), 1; https://doi.org/10.3390/aerospace12010001 - 24 Dec 2024
Viewed by 521
Abstract
This paper presents a methodology for evaluating different flight control actuation system architectures in the early conceptual design phase. In particular, this paper shows how hydraulic and electric actuators can be modeled even if very little is known about the aircraft design or [...] Read more.
This paper presents a methodology for evaluating different flight control actuation system architectures in the early conceptual design phase. In particular, this paper shows how hydraulic and electric actuators can be modeled even if very little is known about the aircraft design or requirements while still including the most dominant static and dynamic characteristics. Singular Value Decomposition is used to estimate model parameters and actuator characteristics from industrial data. This is a quick way to estimate what is needed with little input. The purpose of the models is to predict the power consumption, cooling needs, weight, and size. This is performed by integrating the actuator models in a dynamic simulation framework that also includes a flight simulator and surrounding systems. The results from subsystem studies support the aircraft design process, where actuator characteristics affect the engine performance and aircraft sizing. The methodology is applied to a generic fighter by comparing hydraulic and electric actuation system architectures. Besides providing a generic approach to the actuator modeling, the parameters that affect both the static and dynamic characteristics of an electromechanical and electrohydrostatic actuator are estimated with reasonably good accuracy with only four design parameters as input. Full article
(This article belongs to the Special Issue On-Board Systems Design for Aerospace Vehicles (2nd Edition))
►▼ Show Figures

Figure 1

32 pages, 8258 KiB  
Article
Mixed-Flow Turbofan Engine Model for the Conceptual Design of Sustainable Supersonic Airplanes
by Grazia Piccirillo, Antonio Gregorio, Roberta Fusaro, Davide Ferretto and Nicole Viola
Aerospace 2024, 11(9), 740; https://doi.org/10.3390/aerospace11090740 - 10 Sep 2024
Viewed by 1723
Abstract
Current research efforts on commercial supersonic flight aim to overcome past challenges by designing a new generation of sustainable supersonic airplanes. Achieving this goal requires careful consideration of the propulsion system during the design process. This study proposes a mixed-flow turbofan engine model [...] Read more.
Current research efforts on commercial supersonic flight aim to overcome past challenges by designing a new generation of sustainable supersonic airplanes. Achieving this goal requires careful consideration of the propulsion system during the design process. This study proposes a mixed-flow turbofan engine model coupled with emission estimation routines to increase the reliability of the conceptual design of future supersonic aircraft. The model enables parametric analyses by analyzing variations in main engine design parameters (πc,πf, BPR) as function of the system and mission requirements, such as the Mach number, and suggesting applicability boundaries. The overall methodology was applied to a low-boom Mach 1.5 case study, allowing for both on-design and off-design analyses and generating a propulsive database to support preliminary mission simulations and chemical emission estimation. Finally, the accuracy and reliability of the engine model was validated against GSP 11 data for a generic mixed-flow turbofan engine. A modified version of the Fuel Flow Method, originally developed by Boeing, allows for emissions estimation throughout the mission for a supersonic engine using biofuels. The application of the methodology led to the definition of an engine with a πc  of 30 and BPR of 0.7 for the selected case study, which was successful in meeting the initial mission requirements. Full article
(This article belongs to the Special Issue On-Board Systems Design for Aerospace Vehicles (2nd Edition))
►▼ Show Figures

Figure 1

18 pages, 6775 KiB  
Article
SE-CBAM-YOLOv7: An Improved Lightweight Attention Mechanism-Based YOLOv7 for Real-Time Detection of Small Aircraft Targets in Microsatellite Remote Sensing Imaging
by Zhenping Kang, Yurong Liao, Shuhan Du, Haonan Li and Zhaoming Li
Aerospace 2024, 11(8), 605; https://doi.org/10.3390/aerospace11080605 - 24 Jul 2024
Cited by 1 | Viewed by 1145
Abstract
Addressing real-time aircraft target detection in microsatellite-based visible light remote sensing video imaging requires considering the limitations of imaging payload resolution, complex ground backgrounds, and the relative positional changes between the platform and aircraft. These factors lead to multi-scale variations in aircraft targets, [...] Read more.
Addressing real-time aircraft target detection in microsatellite-based visible light remote sensing video imaging requires considering the limitations of imaging payload resolution, complex ground backgrounds, and the relative positional changes between the platform and aircraft. These factors lead to multi-scale variations in aircraft targets, making high-precision real-time detection of small targets in complex backgrounds a significant challenge for detection algorithms. Hence, this paper introduces a real-time aircraft target detection algorithm for remote sensing imaging using an improved lightweight attention mechanism that relies on the You Only Look Once version 7 (YOLOv7) framework (SE-CBAM-YOLOv7). The proposed algorithm replaces the standard convolution (Conv) with a lightweight convolutional squeeze-and-excitation convolution (SEConv) to reduce the computational parameters and accelerate the detection process of small aircraft targets, thus enhancing real-time onboard processing capabilities. In addition, the SEConv-based spatial pyramid pooling and connected spatial pyramid convolution (SPPCSPC) module extracts image features. It improves detection accuracy while the feature fusion section integrates the convolutional block attention module (CBAM) hybrid attention network, forming the convolutional block attention module Concat (CBAMCAT) module. Furthermore, it optimizes small aircraft target features in channel and spatial dimensions, improving the model’s feature fusion capabilities. Experiments on public remote sensing datasets reveal that the proposed SE-CBAM-YOLOv7 improves detection accuracy by 0.5% and the mAP value by 1.7% compared to YOLOv7, significantly enhancing the detection capability for small-sized aircraft targets in satellite remote sensing imaging. Full article
(This article belongs to the Special Issue On-Board Systems Design for Aerospace Vehicles (2nd Edition))
►▼ Show Figures

Figure 1

Show export options expand_more Show export options expand_less
Select all
Export citation of selected articles as:
 
Displaying articles 1-6
Back to TopTop