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Aerospace
Special Issues
Recent Advances in Flight Testing
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Recent Advances in Flight Testing

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

Deadline for manuscript submissions: 31 December 2024 | Viewed by 4186

Special Issue Editors

Dr. Haichao Hong

E-Mail Website
Guest Editor
School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, China
Interests: flight testing; trajectory optimization; flight mechanics
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Florian Holzapfel

E-Mail Website
Guest Editor
Institute of Flight System Dynamics, Technical University of Munich, Munich, Germany
Interests: guidance and control of manned and unmanned aircrafts; simulation; parameter identification and flight safety; trajectory optimization; sensors, navigation and data fusion; avionics and safety critical systems
Special Issues, Collections and Topics in MDPI journals
Prof. Dr. Shiqiang Hu

E-Mail Website
Guest Editor
School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, China
Interests: image understanding and analysis; autonomous technologies for unmanned systems; nonlinear filtering and state estimation
Special Issues, Collections and Topics in MDPI journals

Special Issue Information

Dear Colleagues,

In the relentless pursuit of aerospace excellence, the significance of flight testing stands as a cornerstone in the edifice of aviation development. Flight testing, a critical phase in the development of aircraft, serves as the bridge between theoretical designs and real-world applications. It is here that the intricate balance of safety, efficiency, and innovation is meticulously examined. The flight test industry, constantly evolving with methodological and technological breakthroughs, demands a platform for scholarly discourse and dissemination of knowledge and experience.

Therefore, we are pleased to announce this Special Issue dedicated to state-of-the-art solutions for aircraft flight testing. Key topics to be explored are challenges in testing and validating new aircraft and designs, flight test data and information exploitation and application, and the integration of cutting-edge technologies in flight test procedures. The Special Issue will highlight how these engineering and methodological advancements contribute to enhancing the reliability, safety, performance, and environmental sustainability of flight tests. Articles addressing civil aircraft flight test engineering problems are particularly welcome.

We look forward to receiving your contributions.

Dr. Haichao Hong
Prof. Dr. Florian Holzapfel
Prof. Dr. Shiqiang Hu
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

  • flight test
  • civil aircraft
  • guidance
  • navigation
  • control
  • flight safety
  • mission planning

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

Published Papers (3 papers)

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Research

12 pages, 2944 KiB  
Article
Airborne Lithium Battery Health Assessment: An Improved Support Vector Machine Algorithm for Imbalanced Sample Sets
by Chunxia Yang, Hongjuan Ge, Hui Jin and Shengjun Liu
Aerospace 2024, 11(6), 467; https://doi.org/10.3390/aerospace11060467 - 11 Jun 2024
Viewed by 838
Abstract
The health assessment of airborne lithium batteries is crucial for flight testing, ensuring the safety and reliability of aircraft power systems. This paper proposes a support vector machine-based algorithm for the health assessment of airborne lithium batteries, featuring a dynamic correction mechanism for [...] Read more.
The health assessment of airborne lithium batteries is crucial for flight testing, ensuring the safety and reliability of aircraft power systems. This paper proposes a support vector machine-based algorithm for the health assessment of airborne lithium batteries, featuring a dynamic correction mechanism for the risk loss penalty parameter. The proposed approach systematically adjusts risk loss penalty parameters based on sample misjudgment ratios and incorporates fault identification corrections to meet the safety requirements of the airborne operation. The experimental results demonstrate the stability and reliability of the proposed algorithm in hyperplane deviation suppression as well as significant improvements in fault sample recall rates. When compared with traditional SVM and other baseline methods such as Random Forest and SVR, our method significantly outperformed these algorithms in terms of accuracy, recall rate, and precision rate. This study provides an efficient and reliable method for the health assessment of airborne lithium batteries, with significant application value. Full article
(This article belongs to the Special Issue Recent Advances in Flight Testing)
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27 pages, 3218 KiB  
Article
An Information Integration Technology for Safety Assessment on Civil Airborne System
by Xi Chen, Quan Zou, Jie Bai and Lei Dong
Aerospace 2024, 11(6), 459; https://doi.org/10.3390/aerospace11060459 - 6 Jun 2024
Viewed by 870
Abstract
With the significant expansion of civil aviation, particularly in the low-altitude economy, there is a significant gap between the escalating demand for airworthiness certification of novel aircraft designs, such as electric vertical take-off and landing (eVTOL) vehicles, and the inefficiency of the current [...] Read more.
With the significant expansion of civil aviation, particularly in the low-altitude economy, there is a significant gap between the escalating demand for airworthiness certification of novel aircraft designs, such as electric vertical take-off and landing (eVTOL) vehicles, and the inefficiency of the current safety assessment process. This gap is partially attributed to safety assessors’ limited exposure to these innovative aircraft models in the safety assessment process, necessitating extensive efforts in identifying precedents and their handling strategies. Complicating matters further, pertinent case studies are scattered across diverse, unstandardized digital formats, obliging assessors to navigate voluminous electronic records while concurrently establishing links among fragmented information scattered across multiple files. This study introduces an advanced information integration methodology, comprising a multi-level path-based architecture and a self-updating algorithm. The proposed method not only furnishes safety assessors with pertinent knowledge featuring explicative interconnectedness automatically, but also dynamically enriches this knowledge corpus through operational usage. Additionally, we devise a suite of evaluative criteria to validate the capacity of our method in processing and consolidating relevant safety datasets. Experimental analyses affirm the efficacy of our proposed approach in streamlining and refreshing safety assessment data. The automation of the retrieval of analogous cases, which relieves the reliance on expert knowledge, enhances the efficiency of the overall safety appraisal procedure. Consequently, this research contributes a solution to enhancing the velocity and accuracy of aircraft certification processes. Full article
(This article belongs to the Special Issue Recent Advances in Flight Testing)
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20 pages, 18047 KiB  
Article
Structural Strength Analysis and Optimization of Commercial Aircraft Nose Landing Gear under Towing Taxi-Out Conditions Using Finite Element Simulation and Modal Testing
by Qiwei Lin, Chang Yang, Yuhao Bai and Jiahao Qin
Aerospace 2024, 11(5), 414; https://doi.org/10.3390/aerospace11050414 - 20 May 2024
Cited by 1 | Viewed by 1895
Abstract
In the field of civil aviation, the nose landing gear is a critical component that is prone to damage during taxiing. With the advent of new technologies such as towing taxi-out and hub motors, the nose landing gear faces increasingly complex operational environments, [...] Read more.
In the field of civil aviation, the nose landing gear is a critical component that is prone to damage during taxiing. With the advent of new technologies such as towing taxi-out and hub motors, the nose landing gear faces increasingly complex operational environments, thereby imposing higher performance demands. Ensuring the structural safety of the nose landing gear is fundamental for the successful application of these technologies. However, current research on aircraft nose landing gear under these new conditions is somewhat lacking, particularly in terms of reliable analysis models for real-world scenarios. This study focuses on a typical Class C aircraft, specifically the B-727 model, for which a finite element model of the nose landing gear is developed. Modal testing of the aircraft’s nose landing gear is conducted using the impact hammer method, and the results are compared with those from the simulations. The experimental data indicate that the error range for the first seven natural frequencies is between 0.23% and 9.27%, confirming the high accuracy of the developed landing gear model. Furthermore, with towing taxi-out as the primary scenario, a dynamic model of the aircraft towing system is established, and an analysis on the structural strength and topological optimization of the nose landing gear under various conditions, including high speeds and heavy loads, is performed. The results show that the developed model can effectively support the analysis and prediction of the mechanical behavior of the nose landing gear. Under high-speed, heavy-load conditions, the nose landing gear experiences significantly increased loads, with the maximum deformation primarily occurring at the lower section of the shock strut’s outer cylinder. However, no damage occurred. Additionally, under these conditions, an optimized structural design for the landing gear was identified, which, while ensuring structural strength, achieves a 22.32% reduction in the mass of the outer cylinder, also ensuring safety in towing taxi-out conditions. Full article
(This article belongs to the Special Issue Recent Advances in Flight Testing)
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