Aerospace Human–Machine and Environmental Control Engineering

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

Deadline for manuscript submissions: 31 December 2024 | Viewed by 2945

Special Issue Editors


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Guest Editor
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China
Interests: man–machine–environment system engineering; aircraft energy and thermal management; cockpit human–machine system evaluation; intelligent allocation of human–machine functions

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Guest Editor
School of Mechanical Engineering, Beijing Institute of Technology, Beijing 10081, China
Interests: man–machine–environment system engineering; thermal management of aircraft and ground vehicles; thermal protection of hypersonic vehicles; heat and mass transfer in complex structure

Special Issue Information

Dear Colleagues,

Currently, human–machine–environment system engineering is considered the most important field in aerospace system engineering, and its aim is to promote and optimize aerospace engineering design to ensure safety, efficiency, and economy. Aerospace human–machine and environmental control engineering mainly focuses on the relationship between human, machines and the environment, and studies the optimization combination of human–machine and environmental systems.

Environmental control engineering and human–machine engineering are considered the two most important fields in the engineering of human–machine environmental systems. Aerospace environmental control includes aerospace thermal management and cabin environmental control. Its aims to meet the environmental parameter requirements of different flight stages of aerospace vehicles, dissipating the waste heat generated by the operation of aerospace equipment, and providing a suitable cabin environment for personnel. With the development of artificial intelligence, the field of aerospace human–machine engineering has exhibited new vitality. It is seeking novel technological approaches that maximize human–machine adaptability in controlled environments, enhance the efficiency of human–machine collaboration efficiency, and reduce cognitive load. This Special Issue of Aerospace covers recent research on environmental control and the human–machine performance of aerospace vehicles, including the related systems of spacecrafts, aerospace vehicles, and aircrafts. These human machine and environmental control systems pose significant challenges to the design and optimization of aerospace vehicle systems. Some of these challenges include optimizing environmental control, thermal management and energy utilization in aerospace flight, intelligent design and the evaluation of human–machine–environment systems, and flexible interaction between human and machine.

The editor of this Special Issue invites authors to submit papers addressing the challenges presented in the modeling and optimization of aerospace human machine and environmental control for aerospace vehicles, and in evaluating the capabilities of human–machine systems in aerospace vehicles.

Prof. Dr. Liping Pang
Dr. Chen Ding
Guest Editors

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Keywords

  • aerospace man–machine–environment system engineering
  • aerospace environmental control
  • aerospace thermal management and energy utilization
  • aerospace human–machine–environment efficiency monitoring and evaluation
  • aerospace human–machine interaction and interface design
  • aerospace human machine function allocation

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Published Papers (4 papers)

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Research

27 pages, 12457 KiB  
Article
Heat Transfer Model Based on Flow Pattern during Flow Boiling in Rectangular Microchannels
by Jiamin Zhu, Peng Zhang, Sicong Tan, Tao Wang, Chaohong Guo and Yuyan Jiang
Aerospace 2024, 11(9), 733; https://doi.org/10.3390/aerospace11090733 - 6 Sep 2024
Viewed by 270
Abstract
In thermal management applications using two-phase flow boiling, rectangular microchannels hold significant promise due to their ease of manufacturing and effective heat transfer characteristics. In this work, we combined experimental and theoretical analyses to propose a theoretical model based on thin liquid film [...] Read more.
In thermal management applications using two-phase flow boiling, rectangular microchannels hold significant promise due to their ease of manufacturing and effective heat transfer characteristics. In this work, we combined experimental and theoretical analyses to propose a theoretical model based on thin liquid film evaporation for predicting heat transfer performance in rectangular cross-sectional microchannels. The heat transfer model is segmented into five zones based on two-phase flow patterns and transient liquid film thickness. These zones represent different flow boiling heat transfer mechanisms over time in microchannels: the liquid slug zone, elongated bubble zone, long-side wall dryout zone, corner liquid evaporation zone, and full dryout zone. The new model comprehensively explains experimental phenomena observed, including long-side wall dryout and thinning of the liquid film on the short-side wall. To validate our model, numerical solutions were computed to study the spatial and temporal variations in heat transfer coefficients. The results exhibited a consistent trend with experimental data regarding average heat transfer coefficients. We also analyzed factors influencing flow boiling characteristics, such as microchannel aspect ratio, hydraulic diameter, measurement location, fluid mass flux, and wall heat flux. Full article
(This article belongs to the Special Issue Aerospace Human–Machine and Environmental Control Engineering)
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17 pages, 5200 KiB  
Article
Optimisation Design of Thermal Test System for Metal Fibre Surface Combustion Structure
by Bin Qi, Rong A, Dongsheng Yang, Ri Wang, Sujun Dong and Yinjia Zhou
Aerospace 2024, 11(8), 668; https://doi.org/10.3390/aerospace11080668 - 14 Aug 2024
Viewed by 438
Abstract
The metal fibre surface combustion structure has the characteristics of strong thermal matching ability, short response time, and strong shape adaptability. It has more advantages in the thermal test of complex hypersonic vehicle surface inlet, leading edge, etc. In this paper, a method [...] Read more.
The metal fibre surface combustion structure has the characteristics of strong thermal matching ability, short response time, and strong shape adaptability. It has more advantages in the thermal test of complex hypersonic vehicle surface inlet, leading edge, etc. In this paper, a method of aerodynamic thermal simulation test based on metal fibre surface combustion is proposed. The aim of the study was to create a uniform target heat flow on the inner wall surface of a cylindrical specimen by matching the gas jet flow rate and the geometry of the combustion surface. The research adopted the optimisation design method based on the surrogate model to establish the numerical calculation model of a metal fibre combustion jet heating cylinder specimen. One hundred sample points were obtained through Latin hypercube sampling, and a database of design parameters and heat flux was established through numerical simulation. The kriging surrogate model and the non-dominated sequencing genetic optimisation algorithm with elite strategy were adopted. A bi-objective optimisation design was carried out with the optimisation objective of the coincidence between the predicted and the target heat flux on the inner wall of the specimen. The results showed that the average relative errors of heat flow density on the specimen surface were 8.8% and 6% through the leave-one-out cross-validation strategy and the validation of six test sample points, respectively. The relative error values in most regions were within 5%, which indicates that the established kriging surrogate model has high prediction accuracy. Under the optimal solution conditions, the numerical calculation results of the heat flow on the inner wall of the specimen were in good agreement with the target heat flow values, with an average relative error of less than 5% and a maximum value of less than 8%. These results show that the optimisation design method based on the kriging surrogate model can effectively match the thermal test parameters of metal fibre combustion structures. Full article
(This article belongs to the Special Issue Aerospace Human–Machine and Environmental Control Engineering)
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18 pages, 3418 KiB  
Article
Exploring the Psychological Well-Being of Flight Cadets through a Comprehensive Survey Analysis of Self-Awareness and Self-Acceptance
by Dan Miao, Xiaodong Cao, Bingxu Zhao, Yuan Shi and Yunze Shi
Aerospace 2024, 11(6), 441; https://doi.org/10.3390/aerospace11060441 - 30 May 2024
Viewed by 637
Abstract
A robust level of self-awareness and self-acceptance is crucial for flight cadets. In this study, a total of 106 flight cadets from various grades and flight training sites were assessed using the self-awareness and self-acceptance scale. The scales were optimized through item analysis, [...] Read more.
A robust level of self-awareness and self-acceptance is crucial for flight cadets. In this study, a total of 106 flight cadets from various grades and flight training sites were assessed using the self-awareness and self-acceptance scale. The scales were optimized through item analysis, reliability, and validity assessments. The finalized scales demonstrated an acceptable level of reliability and validity. Upon analyzing the collected data, it was observed that the overall self-awareness and -acceptance levels among the evaluated pilot students fell within the normal range. However, identifying positive symptoms directly proved challenging. The tested flight cadets exhibited moderate symptoms across each factor, with instances of severe symptoms in academic self-awareness. Notably, flight cadets trained abroad exhibited a lower level of self-awareness and -acceptance compared to those trained in China. But this phenomenon was not reflected in grade difference. Regression analysis revealed that physical and emotional self-awareness dimensions accounted for 62% of the variations in the psychological dimension, while passive self-acceptance explained 72% of the changes in active self-acceptance. Finally, in view of the issues found in the research, corresponding management measures and recommendations are presented to enhance the self-awareness and -acceptance levels of flight cadets. Full article
(This article belongs to the Special Issue Aerospace Human–Machine and Environmental Control Engineering)
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20 pages, 4497 KiB  
Article
Workload Measurement Method for Manned Vehicles in Multitasking Environments
by Chenyuan Yang, Liping Pang, Jie Zhang and Xiaodong Cao
Aerospace 2024, 11(5), 406; https://doi.org/10.3390/aerospace11050406 - 16 May 2024
Viewed by 742
Abstract
Workload (WL) measurement is a crucial foundation for human–machine collaboration, particularly in high-stress multitasking environments such as manned vehicle operations during emergencies, where operators often experience High Workload (HWL) levels, increasing the risk of human error. To address this challenge, this study introduces [...] Read more.
Workload (WL) measurement is a crucial foundation for human–machine collaboration, particularly in high-stress multitasking environments such as manned vehicle operations during emergencies, where operators often experience High Workload (HWL) levels, increasing the risk of human error. To address this challenge, this study introduces a novel WL measurement method that combines Task Demand Load (TDL) and Subject Load Capacity (SLC) to quantitatively assess operator workload. This method was validated through experiments with 45 subjects using the Environmental Control and Atmospheric Regeneration (ECAR) system. The statistical results showed that as the designed WL levels increased, the Average Workload (AWL), the NASA-TLX score, and the work time percentage increased significantly, while the task accuracy and the fixation duration decreased significantly. These results also revealed the impact of WL levels on human responses (such as subjective feeling, work performance, and eye movement). In addition, very strong correlations were found between AWL measurements and NASA-TLX scores (r = 0.75, p < 0.01), task accuracy (r = −0.73, p < 0.01), and work time percentage (r = 0.97, p < 0.01). Overall, these results proved the effectiveness of the proposed method for measuring WL. On this basis, this study defined WL thresholds by integrating task accuracy with AWL calculations, providing a framework for the dynamic management of task allocation between humans and machines to maintain operators within optimal WL ranges. Full article
(This article belongs to the Special Issue Aerospace Human–Machine and Environmental Control Engineering)
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