Pub Date : 2020-08-31DOI: 10.15866/irease.v13i4.17343
K. C. Udaiyakumar, K. Iyer, V. Akhil, Anshul Motwani, Vibhor Rajesh Bhaise
The objective of this paper is to present a design and an analysis procedure for a highly efficient aerospike nozzle that uses Liquid Oxygen and Liquid Hydrogen (LOX/LH2) as fuel for a Single Stage to Orbit (SSTO) spacecraft. This paper provides a simple method to design an aerospike nozzle contour in addition to the results of the Computational Fluid Dynamics (CFD) analysis carried out for this nozzle with and without truncation. The results have been compared with the theoretical values, and the changes in specific thrust with different level of truncation have been shown. The geometry of the nozzle has been created using the method of characteristics and python codes, and flow analysis have been carried out using ANSYS FLUENT for the optimum working condition of the nozzle. The nozzles have been able to achieve excellent altitude compensation, and the nozzle with 40% truncation has come out to be the most efficient.
{"title":"Numerical Simulation and Contour Design of Aerospike Nozzle: a Behavioural Study on Truncation Effects of Nozzle","authors":"K. C. Udaiyakumar, K. Iyer, V. Akhil, Anshul Motwani, Vibhor Rajesh Bhaise","doi":"10.15866/irease.v13i4.17343","DOIUrl":"https://doi.org/10.15866/irease.v13i4.17343","url":null,"abstract":"The objective of this paper is to present a design and an analysis procedure for a highly efficient aerospike nozzle that uses Liquid Oxygen and Liquid Hydrogen (LOX/LH2) as fuel for a Single Stage to Orbit (SSTO) spacecraft. This paper provides a simple method to design an aerospike nozzle contour in addition to the results of the Computational Fluid Dynamics (CFD) analysis carried out for this nozzle with and without truncation. The results have been compared with the theoretical values, and the changes in specific thrust with different level of truncation have been shown. The geometry of the nozzle has been created using the method of characteristics and python codes, and flow analysis have been carried out using ANSYS FLUENT for the optimum working condition of the nozzle. The nozzles have been able to achieve excellent altitude compensation, and the nozzle with 40% truncation has come out to be the most efficient.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"71 1","pages":"141-149"},"PeriodicalIF":0.0,"publicationDate":"2020-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82155791","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-08-31DOI: 10.15866/irease.v13i4.18897
Mostafa A. Rushdi, Tarek N. Dief, A. M. Halawa, S. Yoshida
The traction force of a kite system can be utilized for extracting energy from high-altitude wind. This paper discusses a system identification algorithm derived to obtain real-time governing equations for the kite system based on real-flight data, obtained from a 6 m2 kite power system developed in Kyushu University as an airborne wind energy project. The paper presents the system set-up, the design, the experimental results, a system identification algorithm, and the parameters identified for the kite used. The current stage of the project considers the kite application as a fixed-tether length system with a ground kite control unit. The control strategy is designed to work as a hardware-in the-loop to keep receiving the data and controlling the kite in real time. The experimental tests employed are divided into four distinct ones, and the data of the kite’s attitude, position, and tension forces are recorded. The tension forces resulted from these tests are presented for different wind speeds and flight modes. Ultimately, a novel system identification algorithm that evaluates the correlation between the tension force and the kite’s rolling angle over the four tests is applied, thereby enabling to study the kite behavior as a preliminary step for the achievement of autonomous flight.
{"title":"System Identification of a 6 m2 Kite Power System in Fixed-Tether Length Operation","authors":"Mostafa A. Rushdi, Tarek N. Dief, A. M. Halawa, S. Yoshida","doi":"10.15866/irease.v13i4.18897","DOIUrl":"https://doi.org/10.15866/irease.v13i4.18897","url":null,"abstract":"The traction force of a kite system can be utilized for extracting energy from high-altitude wind. This paper discusses a system identification algorithm derived to obtain real-time governing equations for the kite system based on real-flight data, obtained from a 6 m2 kite power system developed in Kyushu University as an airborne wind energy project. The paper presents the system set-up, the design, the experimental results, a system identification algorithm, and the parameters identified for the kite used. The current stage of the project considers the kite application as a fixed-tether length system with a ground kite control unit. The control strategy is designed to work as a hardware-in the-loop to keep receiving the data and controlling the kite in real time. The experimental tests employed are divided into four distinct ones, and the data of the kite’s attitude, position, and tension forces are recorded. The tension forces resulted from these tests are presented for different wind speeds and flight modes. Ultimately, a novel system identification algorithm that evaluates the correlation between the tension force and the kite’s rolling angle over the four tests is applied, thereby enabling to study the kite behavior as a preliminary step for the achievement of autonomous flight.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"26 1","pages":"150-158"},"PeriodicalIF":0.0,"publicationDate":"2020-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82281480","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-08-31DOI: 10.15866/irease.v13i4.18355
A. Ismaiel, S. Yoshida
As an extension to a previous research made by the authors, this paper represents an aeroelastic analysis for the side-booms supporting the two rotors of a coplanar twin-rotor wind turbine. For a better understanding of the turbine dynamic behavior, the inhouse aeroelastic tool developed by the authors, which is considered as the first approach to study the aeroelasticity of multi-rotor wind turbines, has been extended to model the side-booms and compare three different configurations of the boom size during the analysis. The model is based on deterministic models, where aerodynamic loads are calculated using blade element momentum theory, and virtual work method with a modal approach is used for structure analysis. The three configurations of the side-booms have three different diameters while all other geometrical parameters are kept constant. The bigger the boom diameter, the higher the bending stiffness becomes. It was found that the weight of the rotor is dominant over the fluctuating aerodynamic loads in the in-plane direction, while the deflection is highly affected by the turbulence in the out-of-plane direction. It was also found that the relation between the stiffness and the mean side-boom deflection is of second order, hence, a thorough compromise between weight and strength should be done when designing the side-booms.
{"title":"Aeroelastic Analysis for Side-Booms of a Coplanar Twin-Rotor Wind Turbine","authors":"A. Ismaiel, S. Yoshida","doi":"10.15866/irease.v13i4.18355","DOIUrl":"https://doi.org/10.15866/irease.v13i4.18355","url":null,"abstract":"As an extension to a previous research made by the authors, this paper represents an aeroelastic analysis for the side-booms supporting the two rotors of a coplanar twin-rotor wind turbine. For a better understanding of the turbine dynamic behavior, the inhouse aeroelastic tool developed by the authors, which is considered as the first approach to study the aeroelasticity of multi-rotor wind turbines, has been extended to model the side-booms and compare three different configurations of the boom size during the analysis. The model is based on deterministic models, where aerodynamic loads are calculated using blade element momentum theory, and virtual work method with a modal approach is used for structure analysis. The three configurations of the side-booms have three different diameters while all other geometrical parameters are kept constant. The bigger the boom diameter, the higher the bending stiffness becomes. It was found that the weight of the rotor is dominant over the fluctuating aerodynamic loads in the in-plane direction, while the deflection is highly affected by the turbulence in the out-of-plane direction. It was also found that the relation between the stiffness and the mean side-boom deflection is of second order, hence, a thorough compromise between weight and strength should be done when designing the side-booms.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"2 1","pages":"135-140"},"PeriodicalIF":0.0,"publicationDate":"2020-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89761950","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-08-31DOI: 10.15866/irease.v13i4.18949
Lakhdar Limam, K. Hatanaka, J. Gonzalez-Llorente, Masayuki Miyazaki, Takeya Chikashi, Kei-Ichi Okuyama
Satellites must endure the hostile environement during their launching to space via rocket; therefore, they should be exposed to the real launch conditions for ground testing, including all subsystems and components which should be carefully tested. Several solid-state-ceramic batteries have been selected to be evaluated under the launch environment after been evaluated under the space environment, which has shown so far good results. This paper focuses on the physical degradation and the electrical performances of the batteries based on the discharge capacity, the open-circuit voltage, and charge/discharge modes. Batteries have been exposed to shock, then tested under vibration within different frequencies’ levels with sinewave, sine burst, and random. Before and after the test, the physical properties of all batteries have been checked, several cycles of discharge and charge have been performed to check their performances and survivability after the evaluation test. With 95% of capacity, batteries could demonstrate their ability to withstand the launch conditions successfully, they could be able to operate during several cycles after the test, so far, showing no degradation on their performances within the limits. Also, the paper is providing the main requirements and criteria for batteries’ launch ground testing for the small satellite project.
{"title":"Launch Environment Ground Test Evaluation with Multi-axis Vibration and Shock for Pouch Solid-State-Ceramic Battery Advanced Energy Storage","authors":"Lakhdar Limam, K. Hatanaka, J. Gonzalez-Llorente, Masayuki Miyazaki, Takeya Chikashi, Kei-Ichi Okuyama","doi":"10.15866/irease.v13i4.18949","DOIUrl":"https://doi.org/10.15866/irease.v13i4.18949","url":null,"abstract":"Satellites must endure the hostile environement during their launching to space via rocket; therefore, they should be exposed to the real launch conditions for ground testing, including all subsystems and components which should be carefully tested. Several solid-state-ceramic batteries have been selected to be evaluated under the launch environment after been evaluated under the space environment, which has shown so far good results. This paper focuses on the physical degradation and the electrical performances of the batteries based on the discharge capacity, the open-circuit voltage, and charge/discharge modes. Batteries have been exposed to shock, then tested under vibration within different frequencies’ levels with sinewave, sine burst, and random. Before and after the test, the physical properties of all batteries have been checked, several cycles of discharge and charge have been performed to check their performances and survivability after the evaluation test. With 95% of capacity, batteries could demonstrate their ability to withstand the launch conditions successfully, they could be able to operate during several cycles after the test, so far, showing no degradation on their performances within the limits. Also, the paper is providing the main requirements and criteria for batteries’ launch ground testing for the small satellite project.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"4 1","pages":"126-134"},"PeriodicalIF":0.0,"publicationDate":"2020-08-31","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82207858","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-06-30DOI: 10.15866/irease.v13i3.18374
S. A. Salman, Muzoun Al Dhaheri, Peter J. Dawson, S. Anavatti
{"title":"Autonomous Water Sampling Payload Design","authors":"S. A. Salman, Muzoun Al Dhaheri, Peter J. Dawson, S. Anavatti","doi":"10.15866/irease.v13i3.18374","DOIUrl":"https://doi.org/10.15866/irease.v13i3.18374","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"45 1","pages":"120"},"PeriodicalIF":0.0,"publicationDate":"2020-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"75402923","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-06-30DOI: 10.15866/irease.v13i3.18758
Adwaith Ravichandran, J. Storey, D. Kirk
{"title":"A Thermo-Fluid Model of Droplet Evaporation and Pressure Variation in Venturi Liquid-Gas Mixers","authors":"Adwaith Ravichandran, J. Storey, D. Kirk","doi":"10.15866/irease.v13i3.18758","DOIUrl":"https://doi.org/10.15866/irease.v13i3.18758","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"165 1","pages":"108"},"PeriodicalIF":0.0,"publicationDate":"2020-06-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80441226","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-04-30DOI: 10.15866/irease.v13i2.18317
F. Stesina, S. Corpino
CubeSats have achieved a place of relevance in the modern space missions. However, CubeSats need improvements in terms of new technologies, mission and system reliability, and management of the entire product life cycle. A major lack of knowledge exists about the operations of past and current CubeSats in orbit. Operations planning and re-planning, failures and anomalies management, step-by-step procedures and rules of execution are crucial but poorly analyzed aspects that can increase the success rate of a mission. Moreover, information about the programmatic and technical achievements and lessons learned during the operation phases is often not available or incomplete. However, the sharing of the results, especially for educational programs, becomes fundamental to improve the quality of missions and to prevent mistakes. This paper aims at reducing this gap of knowledge and at sharing the experience and the lessons learned gained by the CubeSat Team of Politecnico di Torino over the three years of in-orbit operations of the E-ST@R-II mission. The flexible approach adopted for the operations planning, the management of anomalies and the re-planning of the operations are presented. Simple yet effective tools have been developed for mission planning and root causes identification, and they are presented through the discussion of the main technical and educational results. The paper provides also a list of good practices and recommendations applicable to future CubeSat missions.
{"title":"In Orbit Operations of an Educational Cubesat: the e-st@r-II Experience","authors":"F. Stesina, S. Corpino","doi":"10.15866/irease.v13i2.18317","DOIUrl":"https://doi.org/10.15866/irease.v13i2.18317","url":null,"abstract":"CubeSats have achieved a place of relevance in the modern space missions. However, CubeSats need improvements in terms of new technologies, mission and system reliability, and management of the entire product life cycle. A major lack of knowledge exists about the operations of past and current CubeSats in orbit. Operations planning and re-planning, failures and anomalies management, step-by-step procedures and rules of execution are crucial but poorly analyzed aspects that can increase the success rate of a mission. Moreover, information about the programmatic and technical achievements and lessons learned during the operation phases is often not available or incomplete. However, the sharing of the results, especially for educational programs, becomes fundamental to improve the quality of missions and to prevent mistakes. This paper aims at reducing this gap of knowledge and at sharing the experience and the lessons learned gained by the CubeSat Team of Politecnico di Torino over the three years of in-orbit operations of the E-ST@R-II mission. The flexible approach adopted for the operations planning, the management of anomalies and the re-planning of the operations are presented. Simple yet effective tools have been developed for mission planning and root causes identification, and they are presented through the discussion of the main technical and educational results. The paper provides also a list of good practices and recommendations applicable to future CubeSat missions.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"76 1","pages":"40-50"},"PeriodicalIF":0.0,"publicationDate":"2020-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86926565","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-04-30DOI: 10.15866/irease.v13i2.18582
Lakhdar Limam, K. Hatanaka, J. Gonzalez-Llorente, Maeda Chihiro, Takeya Chikashi, Kei-Ichi Okuyama
The desired capabilities of small satellites to enable their applications in communication, earth observation, and new scientific instruments require advanced energy storage to face the design’s challenges with the constraints of volume and mass. Small batteries with high energy density may be the solution. New lithium-ion battery technologies areimproved in order to meet these requirements by bringing higher energy density and a wide temperature range than the commercially available ones as well as a lower risk of explosion. In this paper, the ability of solid-state-ceramic batteries to withstand the vacuum and thermal vacuum for low earth orbit applications has been demonstrated, with a minimum safety issue. So far, this technology has never been flown in space. This paper also provides a guideline for the battery evaluation test where the main lines are represented. Batteries are tested under vacuum and thermal vacuum, where they are discharged and charged during several cycles between two temperatures limits. The evaluation focuses on analyzing the physical degradation, the discharge capacity, and the internal resistance before and after each test. Batteries have showed promising results regarding their survivability to thermal vacuum. After several cycles, they have kept almost the same performances, with the same internal resistance and 98% of capacity.
{"title":"Space Environment Evaluation Test of Solid-State-Ceramic Battery Advanced Energy Storage Under Vacuum and Thermal Vacuum","authors":"Lakhdar Limam, K. Hatanaka, J. Gonzalez-Llorente, Maeda Chihiro, Takeya Chikashi, Kei-Ichi Okuyama","doi":"10.15866/irease.v13i2.18582","DOIUrl":"https://doi.org/10.15866/irease.v13i2.18582","url":null,"abstract":"The desired capabilities of small satellites to enable their applications in communication, earth observation, and new scientific instruments require advanced energy storage to face the design’s challenges with the constraints of volume and mass. Small batteries with high energy density may be the solution. New lithium-ion battery technologies areimproved in order to meet these requirements by bringing higher energy density and a wide temperature range than the commercially available ones as well as a lower risk of explosion. In this paper, the ability of solid-state-ceramic batteries to withstand the vacuum and thermal vacuum for low earth orbit applications has been demonstrated, with a minimum safety issue. So far, this technology has never been flown in space. This paper also provides a guideline for the battery evaluation test where the main lines are represented. Batteries are tested under vacuum and thermal vacuum, where they are discharged and charged during several cycles between two temperatures limits. The evaluation focuses on analyzing the physical degradation, the discharge capacity, and the internal resistance before and after each test. Batteries have showed promising results regarding their survivability to thermal vacuum. After several cycles, they have kept almost the same performances, with the same internal resistance and 98% of capacity.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"4 1","pages":"68-79"},"PeriodicalIF":0.0,"publicationDate":"2020-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"73558165","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-04-30DOI: 10.15866/irease.v13i2.17751
F. Ismagilov, V. Vavilov, I. Yamalov, R. Karimov
{"title":"Fault-Tolerant Electric Motors with Permanent Magnets and Electromagnetic Shunting","authors":"F. Ismagilov, V. Vavilov, I. Yamalov, R. Karimov","doi":"10.15866/irease.v13i2.17751","DOIUrl":"https://doi.org/10.15866/irease.v13i2.17751","url":null,"abstract":"","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"12 1","pages":"51"},"PeriodicalIF":0.0,"publicationDate":"2020-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77731122","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2020-04-30DOI: 10.15866/irease.v13i2.18077
E. O. Bykova, G. R. Kamaletdinova, A. Sorokin
Human safety and ergonomics are the key aspects for engineers working on the design of flight suits. The most important is the prevention of skin damage, the protection of the entire human body, especially from an aggressive environment, and the provision of comfort comparable to everyday clothes. The study is conducted by the Moscow Aviation Institute (National Research University) and is aimed to identify the main problems of modern design of flight suits, which can then be compared and applied to spacesuits. Different spacesuits have been analyzed to prove an importance of high flexibility of the spacesuit’s elements. Pre- and postflight tests stressed high risk of human body injuries in more flexible places comparing to solid ones. At the same time, the bending elements of the suit play crucial role in the operational performance. Based on these overviews a specific glove for spacesuits has been selected and analyzed in details, as an example of the most flexible and important part of the flight kit. This study is aimed to find the most effective way to allow flexibility of the elements of the glove and, as a result, to improve safety and ergonomic markers of the whole spacesuit. For this reason, a mathematical model of human performance (in different operations as bending, holding etc.) has been created and a comparative analysis of joints has been made based on quantitative data on the number of elements, including adhesion, tightening, etc. The experiments have been carried out using tests with a probability level of 0.05. As a result, this article discusses methodological recommendations and safety requirements as well as ways to improve modern gloves. It can potentially affect the direction of its further development identifying a general approach to the flight suit design. This paper also gives an overview of potential spin-off of selected technology.
{"title":"Study of the Mechanics of the Spacesuit Gloves","authors":"E. O. Bykova, G. R. Kamaletdinova, A. Sorokin","doi":"10.15866/irease.v13i2.18077","DOIUrl":"https://doi.org/10.15866/irease.v13i2.18077","url":null,"abstract":"Human safety and ergonomics are the key aspects for engineers working on the design of flight suits. The most important is the prevention of skin damage, the protection of the entire human body, especially from an aggressive environment, and the provision of comfort comparable to everyday clothes. The study is conducted by the Moscow Aviation Institute (National Research University) and is aimed to identify the main problems of modern design of flight suits, which can then be compared and applied to spacesuits. Different spacesuits have been analyzed to prove an importance of high flexibility of the spacesuit’s elements. Pre- and postflight tests stressed high risk of human body injuries in more flexible places comparing to solid ones. At the same time, the bending elements of the suit play crucial role in the operational performance. Based on these overviews a specific glove for spacesuits has been selected and analyzed in details, as an example of the most flexible and important part of the flight kit. This study is aimed to find the most effective way to allow flexibility of the elements of the glove and, as a result, to improve safety and ergonomic markers of the whole spacesuit. For this reason, a mathematical model of human performance (in different operations as bending, holding etc.) has been created and a comparative analysis of joints has been made based on quantitative data on the number of elements, including adhesion, tightening, etc. The experiments have been carried out using tests with a probability level of 0.05. As a result, this article discusses methodological recommendations and safety requirements as well as ways to improve modern gloves. It can potentially affect the direction of its further development identifying a general approach to the flight suit design. This paper also gives an overview of potential spin-off of selected technology.","PeriodicalId":14462,"journal":{"name":"International Review of Aerospace Engineering","volume":"63 1","pages":"59-67"},"PeriodicalIF":0.0,"publicationDate":"2020-04-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88472224","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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