Pub Date : 2022-11-18DOI: 10.3846/aviation.2022.17636
S. Terenchuk, Yuliia Riabchun, M. Delembovskyi
In the conditions of effective training in aviation for dispatchers and pilots, it requires the use of infocommunication systems capable of working under conditions of fuzzy uncertainty in real time. The functioning of such systems is based on fuzzy inference systems. However, the development and implementation of these systems requires the creation of fuzzy knowledge bases. Therefore, special attention in this study is paid to the creation of a system of fuzzy inferences and the formation of a fuzzy knowledge base of this system. The result is a lozenge-type fuzzy inference system. The fuzzy knowledge base of the system contains the rules according to which, based on the results of test computer game problems of varying complexity, a conclusion is formed about the applicant’s ability to acquire knowledge and skills in a certain specialty.When developing the rules, both the results of passing different levels of professionally oriented computer test games were taken into account, and the interest of dispatchers and pilots was taken into account. Therefore, the proposed fuzzy rules of the knowledge base of the fuzzy inference system make it possible to assess not only the ability of the controller or pilot to solve certain problems. This dependence of the input dataset on time allows the implementation of a fuzzy inference system of the Sugeno type, using clear input data in the formation of inferences.
{"title":"IDENTIFICATION OF ENTRANT’S ABILITIES ON THE BASIS OF SUGENO-TYPE FUZZY INFERENCE SYSTEMS","authors":"S. Terenchuk, Yuliia Riabchun, M. Delembovskyi","doi":"10.3846/aviation.2022.17636","DOIUrl":"https://doi.org/10.3846/aviation.2022.17636","url":null,"abstract":"In the conditions of effective training in aviation for dispatchers and pilots, it requires the use of infocommunication systems capable of working under conditions of fuzzy uncertainty in real time. The functioning of such systems is based on fuzzy inference systems. However, the development and implementation of these systems requires the creation of fuzzy knowledge bases. Therefore, special attention in this study is paid to the creation of a system of fuzzy inferences and the formation of a fuzzy knowledge base of this system. The result is a lozenge-type fuzzy inference system. The fuzzy knowledge base of the system contains the rules according to which, based on the results of test computer game problems of varying complexity, a conclusion is formed about the applicant’s ability to acquire knowledge and skills in a certain specialty.When developing the rules, both the results of passing different levels of professionally oriented computer test games were taken into account, and the interest of dispatchers and pilots was taken into account. Therefore, the proposed fuzzy rules of the knowledge base of the fuzzy inference system make it possible to assess not only the ability of the controller or pilot to solve certain problems. This dependence of the input dataset on time allows the implementation of a fuzzy inference system of the Sugeno type, using clear input data in the formation of inferences.","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-11-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"42108900","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 : 2022-11-15DOI: 10.3846/aviation.2022.17910
Zhou-Tai Tian, Daojie Yu
With the widespread use of unmanned aerial vehicles (UAVs) in life, the real-time recognition of UAVs has become an important issue. The authors of this paper mainly studied the application of the random forest (RF) algorithm in the outdoor real-time recognition of UAVs. Mel-Frequency Cepstral Coefficient (MFCC) features were extracted from sound signals firstly, and then the RF method was combined with weighted voting to obtain the improved random forest (IRF) method to identify UAV sounds and environmental sounds. An experimental analysis was conducted. The modeling time of the IRF method increased by 9.52% compared with the RF method, and the recognition rate of the IRF method decreased with the increase of the distance from the microphone; however, the recognition rate of the IRF method was always higher than that of the RF method, and the recognition rate of the IRF method for the mixed samples was always higher than 90%. When the distance was 10 m, the IRF method still had a recognition rate of 91.29%. The experimental results verify the effectiveness of the IRF method for the outdoor real-time recognition of UAVs and its practical application feasibility.
{"title":"A STUDY OF REAL-TIME RECOGNITION OF UNMANNED AERIAL VEHICLES IN OUTDOOR AREAS BASED ON A RANDOM FOREST ALGORITHM","authors":"Zhou-Tai Tian, Daojie Yu","doi":"10.3846/aviation.2022.17910","DOIUrl":"https://doi.org/10.3846/aviation.2022.17910","url":null,"abstract":"With the widespread use of unmanned aerial vehicles (UAVs) in life, the real-time recognition of UAVs has become an important issue. The authors of this paper mainly studied the application of the random forest (RF) algorithm in the outdoor real-time recognition of UAVs. Mel-Frequency Cepstral Coefficient (MFCC) features were extracted from sound signals firstly, and then the RF method was combined with weighted voting to obtain the improved random forest (IRF) method to identify UAV sounds and environmental sounds. An experimental analysis was conducted. The modeling time of the IRF method increased by 9.52% compared with the RF method, and the recognition rate of the IRF method decreased with the increase of the distance from the microphone; however, the recognition rate of the IRF method was always higher than that of the RF method, and the recognition rate of the IRF method for the mixed samples was always higher than 90%. When the distance was 10 m, the IRF method still had a recognition rate of 91.29%. The experimental results verify the effectiveness of the IRF method for the outdoor real-time recognition of UAVs and its practical application feasibility.","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-11-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47166688","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 : 2022-10-25DOI: 10.3846/aviation.2022.17788
B. Hevko, Yurij Bondar
The external loads from the continuous turbulence on the elastic high aspect ratio wing of the transport category aircraft are calculated by Dynamics of Turbulence Air (DTA) and Interactive Multidisciplinary Aircraft Design (IMAD) methods. The response to continuous turbulence was determined taking into account the requirements of CS-25.341(b). The model of the aircraft structure is directed by symmetrical spatial beam schematization. Determination of aerodynamic forces and moments was performed using the methods of linear computational aerodynamics: the panel method of Doublet-Lattice and Constant Pressures (DLM/CPM) and the method of circulation. Comparison of the results of load determination showed that, in general, the values of the loads calculated using IMAD are lower than the values calculated using DTA. Therefore, when designing an aircraft, it is advisable to combine these methods: calculate the loads using IMAD, as a more functional method, and then the loads obtained in the critical points of the calculated flight area should be confirmed using the DTA method. Thus, this study determined the difference between the results of the calculation of loads from the continuous turbulence on the elastic wing of the transport category aircraft using DTA and IMAD methods.
{"title":"COMPARISON OF TWO METHODS TO CALCULATE EXTERNAL LOADS AT FLIGHT IN CONTINUOUS TURBULENCE","authors":"B. Hevko, Yurij Bondar","doi":"10.3846/aviation.2022.17788","DOIUrl":"https://doi.org/10.3846/aviation.2022.17788","url":null,"abstract":"The external loads from the continuous turbulence on the elastic high aspect ratio wing of the transport category aircraft are calculated by Dynamics of Turbulence Air (DTA) and Interactive Multidisciplinary Aircraft Design (IMAD) methods. The response to continuous turbulence was determined taking into account the requirements of CS-25.341(b). The model of the aircraft structure is directed by symmetrical spatial beam schematization. Determination of aerodynamic forces and moments was performed using the methods of linear computational aerodynamics: the panel method of Doublet-Lattice and Constant Pressures (DLM/CPM) and the method of circulation. Comparison of the results of load determination showed that, in general, the values of the loads calculated using IMAD are lower than the values calculated using DTA. Therefore, when designing an aircraft, it is advisable to combine these methods: calculate the loads using IMAD, as a more functional method, and then the loads obtained in the critical points of the calculated flight area should be confirmed using the DTA method. Thus, this study determined the difference between the results of the calculation of loads from the continuous turbulence on the elastic wing of the transport category aircraft using DTA and IMAD methods.","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-10-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43631747","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 : 2022-10-20DOI: 10.3846/aviation.2022.17728
T. Leśniewski, M. Stosiak, M. Lubecki, J. Krawczyk
The paper presents tribological tests of selected materials used as liners in a composite hydraulic cylinder. Three coating materials were used for the analysis: Sika F180 polyurethane, Huntsman Araldite LY1564 with Aradur 3487 amine hardener and Bezlona 1111 Super Metal. In addition, uncoated carbon epoxy laminate (CFRP) samples were used as reference material. The instantaneous course of the friction force, its maximum and average value, were the analysed parameters. Ball-on-disk tests were performed on a specialised tester that allows, among other things, to control the operating conditions (clamping force, operating temperature, speed, friction path) and measurement of the instantaneous value of the friction force. After these tests, the friction paths were observed using a Leica DCM8 contactless profilometer with an EPI 20x lens. The amount of energy dissipated due to friction was also determined. The conducted tests and comparative analyses allowed to conclude that the F180 material is the most desirable in terms of tribological properties.
{"title":"WEAR RESISTANCE OF SELECTED ANTI-WEAR COATINGS USED IN MULTI-MATERIAL COMPOSITE HYDRAULIC CYLINDERS","authors":"T. Leśniewski, M. Stosiak, M. Lubecki, J. Krawczyk","doi":"10.3846/aviation.2022.17728","DOIUrl":"https://doi.org/10.3846/aviation.2022.17728","url":null,"abstract":"The paper presents tribological tests of selected materials used as liners in a composite hydraulic cylinder. Three coating materials were used for the analysis: Sika F180 polyurethane, Huntsman Araldite LY1564 with Aradur 3487 amine hardener and Bezlona 1111 Super Metal. In addition, uncoated carbon epoxy laminate (CFRP) samples were used as reference material. The instantaneous course of the friction force, its maximum and average value, were the analysed parameters. Ball-on-disk tests were performed on a specialised tester that allows, among other things, to control the operating conditions (clamping force, operating temperature, speed, friction path) and measurement of the instantaneous value of the friction force. After these tests, the friction paths were observed using a Leica DCM8 contactless profilometer with an EPI 20x lens. The amount of energy dissipated due to friction was also determined. The conducted tests and comparative analyses allowed to conclude that the F180 material is the most desirable in terms of tribological properties.","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-10-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48111945","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 : 2022-10-12DOI: 10.3846/aviation.2022.17751
M. Karpenko
Reliability and maintenance analysis in aviation industry focused on a main objective of the accident and incident investigations what are help to better understand the causes of accidents. In the article suggested the underlying concept by scorecard of situations what lead to aviation accidents. In the present research, the aviation accident connected with a landing gear and a problem of failure to follow maintenance instructions during a maintenance on aircraft landing gear hydraulic drive was under an investigation, on an example of root cause analysis of the failure of hydraulic flexible highpressure hoses. The approach presented in this research of experimental measurements, based on fluid pressure measuring, high-pressure hoses vibration measuring and frequency’s analysis. By spectrum analyses was found that high-pressure hoses are most susceptible to deformation at frequencies to the response of the fluid within, as well as at hoses material resonance frequencies. The compact version of hoses is more deformational on the resonance points than a standard version of hose. In final according to analyses, was established that disrespect of the frequency conditions was leaded to causes irreversible degradation changes of the hose inner structure and occurrence of material defects inside layers contact what lead in final step to hose failure.
{"title":"LANDING GEAR FAILURES CONNECTED WITH HIGH-PRESSURE HOSES AND ANALYSIS OF TRENDS IN AIRCRAFT TECHNICAL PROBLEMS","authors":"M. Karpenko","doi":"10.3846/aviation.2022.17751","DOIUrl":"https://doi.org/10.3846/aviation.2022.17751","url":null,"abstract":"Reliability and maintenance analysis in aviation industry focused on a main objective of the accident and incident investigations what are help to better understand the causes of accidents. In the article suggested the underlying concept by scorecard of situations what lead to aviation accidents. In the present research, the aviation accident connected with a landing gear and a problem of failure to follow maintenance instructions during a maintenance on aircraft landing gear hydraulic drive was under an investigation, on an example of root cause analysis of the failure of hydraulic flexible highpressure hoses. The approach presented in this research of experimental measurements, based on fluid pressure measuring, high-pressure hoses vibration measuring and frequency’s analysis. By spectrum analyses was found that high-pressure hoses are most susceptible to deformation at frequencies to the response of the fluid within, as well as at hoses material resonance frequencies. The compact version of hoses is more deformational on the resonance points than a standard version of hose. In final according to analyses, was established that disrespect of the frequency conditions was leaded to causes irreversible degradation changes of the hose inner structure and occurrence of material defects inside layers contact what lead in final step to hose failure.","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-10-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43338715","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 : 2022-10-12DOI: 10.3846/aviation.2022.17555
K. Kosacki, A. Tomczyk
This article presents basic methodology and some algorithms for estimating attitude and heading angles of an unmanned or optionally piloted aircraft in the event of a partial failure of the on-board measurement systems. The aim of the research is to develop effective estimation algorithms of non-measurable aircraft state variables. Correlation between quantities describing kinematics of the aircraft’s movement in space were used. Properties of the estimation algorithms are illustrated by exemplary calculations using real data recorded during test flights of the optionally controlled MP-02A Czajka airplane. Quality of the estimated signals allows to continue flight in case of a non-catastrophic failure of the measurement systems. Developed algorithms are used in control systems designed at the Department of Avionics and Control of the Rzeszów University of Technology, dedicated to unmanned and optionally controlled light aircraft.
{"title":"APPLICATION OF ANALYTICAL REDUNDANCY OF MEASUREMENTS TO INCREASE THE RELIABILITY OF AIRCRAFT ATTITUDE CONTROL","authors":"K. Kosacki, A. Tomczyk","doi":"10.3846/aviation.2022.17555","DOIUrl":"https://doi.org/10.3846/aviation.2022.17555","url":null,"abstract":"This article presents basic methodology and some algorithms for estimating attitude and heading angles of an unmanned or optionally piloted aircraft in the event of a partial failure of the on-board measurement systems. The aim of the research is to develop effective estimation algorithms of non-measurable aircraft state variables. Correlation between quantities describing kinematics of the aircraft’s movement in space were used. Properties of the estimation algorithms are illustrated by exemplary calculations using real data recorded during test flights of the optionally controlled MP-02A Czajka airplane. Quality of the estimated signals allows to continue flight in case of a non-catastrophic failure of the measurement systems. Developed algorithms are used in control systems designed at the Department of Avionics and Control of the Rzeszów University of Technology, dedicated to unmanned and optionally controlled light aircraft.","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-10-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44472194","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 : 2022-10-12DOI: 10.3846/aviation.2022.17592
M. Papis, Tomasz Krawczyk
Because the Polish Air Force currently uses F-16 and MiG-29 aircraft, the aim of the study was to conduct a comparison of the susceptibility to destruction in combat of these two aircraft. The first part of the work concerned the analysis of individual critical components, such as: general characteristics of the airframe structure, aircraft engine, flight control system, fuel system, aircraft weapons, radar system. The index of susceptibility to destruction in combat was defined considering the listed critical components and the following types of enemy weapon: aircraft gun, air-to-air missile, anti-aircraft gun, surface-to-air missile. The analysis proved that the aircraft have similar susceptibility to damage in combat, a slight advantage of the F-16 aircraft in this respect was determined. The presented scheme can be used to analyze other aircraft. Proposals of aircraft modifications, directions of further actions, possibilities of using the described method were presented. The method can be used to making decisions by governments regarding the purchase aircraft for their fleets and identify aircraft critical components with high susceptibility to destruction in order to introduce appropriate modifications by military aircraft manufacturers.
{"title":"COMPARISON OF MIG-29 AND F-16 AIRCRAFT IN THE FIELD OF SUSCEPTIBILITY TO DESTRUCTION IN COMBAT","authors":"M. Papis, Tomasz Krawczyk","doi":"10.3846/aviation.2022.17592","DOIUrl":"https://doi.org/10.3846/aviation.2022.17592","url":null,"abstract":"Because the Polish Air Force currently uses F-16 and MiG-29 aircraft, the aim of the study was to conduct a comparison of the susceptibility to destruction in combat of these two aircraft. The first part of the work concerned the analysis of individual critical components, such as: general characteristics of the airframe structure, aircraft engine, flight control system, fuel system, aircraft weapons, radar system. The index of susceptibility to destruction in combat was defined considering the listed critical components and the following types of enemy weapon: aircraft gun, air-to-air missile, anti-aircraft gun, surface-to-air missile. The analysis proved that the aircraft have similar susceptibility to damage in combat, a slight advantage of the F-16 aircraft in this respect was determined. The presented scheme can be used to analyze other aircraft. Proposals of aircraft modifications, directions of further actions, possibilities of using the described method were presented. The method can be used to making decisions by governments regarding the purchase aircraft for their fleets and identify aircraft critical components with high susceptibility to destruction in order to introduce appropriate modifications by military aircraft manufacturers.","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-10-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43188835","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 : 2022-06-28DOI: 10.3846/aviation.2022.17161
E. Bezvesilnaya, A. Tkachuk
The following article is being retracted from publication in Aviation Journal: Corrected gyrocompass synthesis as a system with changeable structure for aviation gravimetric system with piezoelectric gravimeter, by Elena Nikolaevna Bezvesilnaya and Andriy Hennadiiovych Tkachuk, Volume 18, Issue 3, 2014, pp. 134–140, Aviation, https://doi.org/10.3846/16487788.2014.969878 https://journals.vilniustech.lt/index.php/Aviation/article/view/2941 Received 20 November 2013; published online 02 October 2014, since the same results are published in Deutsche Gesellschaft für Ortung und Navigation article Corrected Gyrocompass Synthesis as a System with Changeable Structure, by Bezvesilnaya O. N., Ivanov S. V., Ryzhkov L. M. and Staritskiy L. P., Proceeding of Symposium Gyro Technology 2003, Stuttgart, Germany, 2003, 12.0–12.8 (ISSN 1439-4502). The Editors and publishers of the journal, Vilnius Gediminas Technical University, note that we received, peer-reviewed, accepted and published the article on the basis that the authors are presenting original results and are not intending to publish them in any other journal. The retracted article will remain online to maintain the scholarly record, but it will be digitally watermarked on each page as “retracted”.
以下文章已从《航空杂志》上撤回:压电式重力仪航空重力测量系统的可变结构修正陀螺罗盘合成系统，Elena Nikolaevna Bezvesilnaya和Andriy Hennadiiovych Tkachuk, 2014年第18卷第3期，134-140页，Aviation,https://doi.org/10.3846/16487788.2014.969878https://journals.vilniustech.lt/index.php/Aviation/article/view/2941Received 2013年11月20日;2014年10月2日在网上发表了相同的结果，因为相同的结果发表在德国研究与导航协会杂志上，Bezvesilnaya O. N.， Ivanov S. V.， Ryzhkov L. M.和Staritskiy L. P.， 2003陀螺技术研讨会进展，德国斯图加特，2003,12.0-12.8 (ISSN 1439-4502)。该期刊的编辑和出版商维尔纽斯·格迪米纳斯技术大学(Vilnius Gediminas Technical University)指出，我们收到、同行评审、接受和发表这篇文章的基础是，作者展示的是原创成果，不打算在任何其他期刊上发表。撤回的文章将保留在网上，以保持学术记录，但每页都会有数字水印标记为“撤回”。
{"title":"RETRACTION NOTICE TO “CORRECTED GYROCOMPASS SYNTHESIS AS A SYSTEM WITH CHANGEABLE STRUCTURE FOR AVIATION GRAVIMETRIC SYSTEM WITH PIEZOELECTRIC GRAVIMETER” [AVIATION 18(3), 134–140, 2014]","authors":"E. Bezvesilnaya, A. Tkachuk","doi":"10.3846/aviation.2022.17161","DOIUrl":"https://doi.org/10.3846/aviation.2022.17161","url":null,"abstract":"The following article is being retracted from publication in Aviation Journal:\u0000Corrected gyrocompass synthesis as a system with changeable structure for aviation gravimetric system with piezoelectric gravimeter, \u0000by Elena Nikolaevna Bezvesilnaya and Andriy Hennadiiovych Tkachuk,\u0000Volume 18, Issue 3, 2014, pp. 134–140, Aviation,\u0000https://doi.org/10.3846/16487788.2014.969878\u0000https://journals.vilniustech.lt/index.php/Aviation/article/view/2941\u0000Received 20 November 2013; published online 02 October 2014, since the same results are published in Deutsche Gesellschaft für Ortung und Navigation article Corrected Gyrocompass Synthesis as a System with Changeable Structure, \u0000by Bezvesilnaya O. N., Ivanov S. V., Ryzhkov L. M. and Staritskiy L. P., Proceeding of Symposium Gyro Technology 2003, Stuttgart, Germany, 2003, 12.0–12.8 (ISSN 1439-4502).\u0000The Editors and publishers of the journal, Vilnius Gediminas Technical University, note that we received, peer-reviewed, accepted and published the article on the basis that the authors are presenting original results and \u0000are not intending to publish them in any other journal. The retracted article will remain online to maintain the scholarly record, but it will be digitally watermarked on each page as “retracted”.","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-06-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48812782","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 : 2022-06-23DOI: 10.3846/aviation.2022.17000
A. Kubit, T. Trzepieciński, Ł. Święch, R. Fejkiel
The aim of the research described in this paper is analysis of the deformation of the aircraft tyre subjected to static load. Based on the results of experimental tests with a different value of inflation pressure, favorable pressure conditions for use in the tyre of an ultralight aircraft were determined. The deflection characteristics of the tyre depending on the nominal pressure was determined using the digital image correlation technique. In the range of loads not leading to excessive tyre deflection, quite linear relation between vertical deflection and vertical force is observed. The safe minimum pressure in tyre loaded with a force of 12 kN is 2.5 bar. The experimental results will be used to select a shock absorber for a 600 kg ultralight, light sport aircraft commercialised by the company Ekolot (Krosno, Poland).
{"title":"EXPERIMENTAL ANALYSIS OF ULTRALIGHT AIRCRAFT TYRE BEHAVIOUR UNDER AIRCRAFT LANDING PHASE","authors":"A. Kubit, T. Trzepieciński, Ł. Święch, R. Fejkiel","doi":"10.3846/aviation.2022.17000","DOIUrl":"https://doi.org/10.3846/aviation.2022.17000","url":null,"abstract":"The aim of the research described in this paper is analysis of the deformation of the aircraft tyre subjected to static load. Based on the results of experimental tests with a different value of inflation pressure, favorable pressure conditions for use in the tyre of an ultralight aircraft were determined. The deflection characteristics of the tyre depending on the nominal pressure was determined using the digital image correlation technique. In the range of loads not leading to excessive tyre deflection, quite linear relation between vertical deflection and vertical force is observed. The safe minimum pressure in tyre loaded with a force of 12 kN is 2.5 bar. The experimental results will be used to select a shock absorber for a 600 kg ultralight, light sport aircraft commercialised by the company Ekolot (Krosno, Poland).","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-06-23","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46353872","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 : 2022-06-21DOI: 10.3846/aviation.2022.16901
R. P.S., Jeyan J. V. Muruga Lal
Due to its compactness, agility, good hover performance, and ease of carriage, coaxial rotor Mini UAV is apt for various military and civilian applications in mountain terrain. This paper examines various factors to arrive at viable configurations of coaxial rotor Mini UAV for applications in mountain terrain. A consideration of the coaxial rotor Mini UAV to analyse the suitability for mountain terrain is presented. Coaxial rotor design is evaluated to assess the design requirements of mountain terrain. Various design parameters are analysed to arrive at viable design configurations for coaxial rotor Mini UAVs to operate in mountain terrain. Due to mechanical complexities, more than three blades per rotor for a small coaxial rotary wing aircraft is not recommended. The compact frame of the coaxial rotor Mini UAV is a key advantage, so rotor blades with a radius bigger than 1 m are not desirable. With a radius smaller than 1 m, a range of 0.9 m to 1.2 m, and an rotor speed between 900 RPM and 1200 RPM for 3-blade and 2-blade coaxial rotors, the Mini UAV offers a variety of options for applications in mountain terrain.
{"title":"HOVER PERFORMANCE ANALYSIS OF COAXIAL MINI UNMANNED AERIAL VEHICLE FOR APPLICATIONS IN MOUNTAIN TERRAIN","authors":"R. P.S., Jeyan J. V. Muruga Lal","doi":"10.3846/aviation.2022.16901","DOIUrl":"https://doi.org/10.3846/aviation.2022.16901","url":null,"abstract":"Due to its compactness, agility, good hover performance, and ease of carriage, coaxial rotor Mini UAV is apt for various military and civilian applications in mountain terrain. This paper examines various factors to arrive at viable configurations of coaxial rotor Mini UAV for applications in mountain terrain. A consideration of the coaxial rotor Mini UAV to analyse the suitability for mountain terrain is presented. Coaxial rotor design is evaluated to assess the design requirements of mountain terrain. Various design parameters are analysed to arrive at viable design configurations for coaxial rotor Mini UAVs to operate in mountain terrain. Due to mechanical complexities, more than three blades per rotor for a small coaxial rotary wing aircraft is not recommended. The compact frame of the coaxial rotor Mini UAV is a key advantage, so rotor blades with a radius bigger than 1 m are not desirable. With a radius smaller than 1 m, a range of 0.9 m to 1.2 m, and an rotor speed between 900 RPM and 1200 RPM for 3-blade and 2-blade coaxial rotors, the Mini UAV offers a variety of options for applications in mountain terrain.","PeriodicalId":51910,"journal":{"name":"Aviation","volume":" ","pages":""},"PeriodicalIF":1.0,"publicationDate":"2022-06-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45081992","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：