Pub Date : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.19
B. A. Nicolin, I. Nicolin
This paper presents the experimental research method of a hydraulic cylinder used for steering the front landing gear wheel. A mechanical-hydraulic steering system is operated by two interchangeable hydraulic cylinders acting in tandem to rotate the movable sub-assembly that contains the front landing gear wheel. Each hydraulic cylinder is designed with a built-in throttle to equalize the speed of the hydraulic cylinder rod traveling in both directions of movement (extension and retraction). During the experiments, three constructive variants of the built-in throttle will be used to obtain the optimal variant.
{"title":"Experimental research of hydraulic cylinder with the built-in throttle for steering the front landing gear wheel","authors":"B. A. Nicolin, I. Nicolin","doi":"10.13111/2066-8201.2022.14.4.19","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.19","url":null,"abstract":"This paper presents the experimental research method of a hydraulic cylinder used for steering the front landing gear wheel. A mechanical-hydraulic steering system is operated by two interchangeable hydraulic cylinders acting in tandem to rotate the movable sub-assembly that contains the front landing gear wheel. Each hydraulic cylinder is designed with a built-in throttle to equalize the speed of the hydraulic cylinder rod traveling in both directions of movement (extension and retraction). During the experiments, three constructive variants of the built-in throttle will be used to obtain the optimal variant.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"48064775","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 : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.6
A. Ionita, Andrei Lungoci, Ion Tomescu
Accurate dynamic modelling of the Tandem Wing Quadcopter Hybrid (TWQH) platform is becoming increasingly important, as strict requirements are progressively being imposed on the UAV (unmanned aerial vehicles) control system in the transition phase from vertical to level flight and vice versa. This work aims to present preliminary design performances in the steady and manoeuvring flight of the platform thrusted by only four rotors directed upward. The aerodynamic effects of tandem wings make a significant contribution to the evaluation of performance, controllability and manoeuvrability in hovering and low speed phase. More specifically, steady, level, symmetrical pull-up and coordinated turns approaches of the quad model are considered and the results obtained in the simulation study are presented and discussed.
{"title":"Quad Performances and Manoeuvrability of TWQH platf","authors":"A. Ionita, Andrei Lungoci, Ion Tomescu","doi":"10.13111/2066-8201.2022.14.4.6","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.6","url":null,"abstract":"Accurate dynamic modelling of the Tandem Wing Quadcopter Hybrid (TWQH) platform is becoming increasingly important, as strict requirements are progressively being imposed on the UAV (unmanned aerial vehicles) control system in the transition phase from vertical to level flight and vice versa. This work aims to present preliminary design performances in the steady and manoeuvring flight of the platform thrusted by only four rotors directed upward. The aerodynamic effects of tandem wings make a significant contribution to the evaluation of performance, controllability and manoeuvrability in hovering and low speed phase. More specifically, steady, level, symmetrical pull-up and coordinated turns approaches of the quad model are considered and the results obtained in the simulation study are presented and discussed.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43625640","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 : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.1
Usman Ali, E. Chadwick, O. Şugar‐Gabor
This research aims to optimise a chordwise slot so that lateral flow control of a flying wing configuration can be enhanced. This was achieved by maximising the airflow rate over the trailing edge control surfaces of the wing. A higher rate of airflow over the trailing edge control surfaces will increase the operationality of control surfaces, resulting in enhanced lateral control of the air vehicle at medium to high angles of attack. Four variables describing the chordwise slot are identified for numerical optimisation. They are: location, width, length, and angle of trajectory of chordwise slot relative to freestream. The results of the airflow rate for the wing with an optimised chordwise slot are compared with a baseline clean configuration. The flying wing configuration with a chordwise slot has shown a higher mass flow rate over the control surfaces of the wing in comparison to the baseline clean configuration, demonstrating that an optimised chordwise slot can be implemented on a flying wing configuration as it successfully controls the lateral flow by maximising the flow rate over the trailing edge control surfaces.
{"title":"An Optimisation of a Chordwise Slot to Enhance Lateral Flow Control on a UCAV","authors":"Usman Ali, E. Chadwick, O. Şugar‐Gabor","doi":"10.13111/2066-8201.2022.14.4.1","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.1","url":null,"abstract":"This research aims to optimise a chordwise slot so that lateral flow control of a flying wing configuration can be enhanced. This was achieved by maximising the airflow rate over the trailing edge control surfaces of the wing. A higher rate of airflow over the trailing edge control surfaces will increase the operationality of control surfaces, resulting in enhanced lateral control of the air vehicle at medium to high angles of attack. Four variables describing the chordwise slot are identified for numerical optimisation. They are: location, width, length, and angle of trajectory of chordwise slot relative to freestream. The results of the airflow rate for the wing with an optimised chordwise slot are compared with a baseline clean configuration. The flying wing configuration with a chordwise slot has shown a higher mass flow rate over the control surfaces of the wing in comparison to the baseline clean configuration, demonstrating that an optimised chordwise slot can be implemented on a flying wing configuration as it successfully controls the lateral flow by maximising the flow rate over the trailing edge control surfaces.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43829301","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 : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.13
Florin-Adrian Stancu, A. Stoica
Interplanetary space missions require spacecraft autonomy in order to fulfill the mission objective. The fault detection and isolation (FDI) system increases the level of autonomy and can ensure the safety of the spacecraft by detecting and isolating potential faults before they become critical. The proposed FDI system is based on an innovative bank of SMOs (sliding mode observers), designed for different fault scenarios cases. The FDI system design aims to detect and isolate actuators and measurement units’ faults used by the satellite control system and considers the nonlinear model of the satellite dynamics. This approach gives the possibility of fault reconstruction based on the information provided by an equivalent injection signal, allowing to reconstruct external perturbances and faults. The SMO chattering phenomenon is avoided by using the pseudo-sliding function, being a linear approximation of the signum function, which gives the possibility of using the equivalent injection signal for fault reconstruction purposes. The proposed fault reconstruction methodology is illustrated by a case study for a 6U Cubesat.
{"title":"Actuator fault reconstruction using FDI system based on sliding mode observers","authors":"Florin-Adrian Stancu, A. Stoica","doi":"10.13111/2066-8201.2022.14.4.13","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.13","url":null,"abstract":"Interplanetary space missions require spacecraft autonomy in order to fulfill the mission objective. The fault detection and isolation (FDI) system increases the level of autonomy and can ensure the safety of the spacecraft by detecting and isolating potential faults before they become critical. The proposed FDI system is based on an innovative bank of SMOs (sliding mode observers), designed for different fault scenarios cases. The FDI system design aims to detect and isolate actuators and measurement units’ faults used by the satellite control system and considers the nonlinear model of the satellite dynamics. This approach gives the possibility of fault reconstruction based on the information provided by an equivalent injection signal, allowing to reconstruct external perturbances and faults. The SMO chattering phenomenon is avoided by using the pseudo-sliding function, being a linear approximation of the signum function, which gives the possibility of using the equivalent injection signal for fault reconstruction purposes. The proposed fault reconstruction methodology is illustrated by a case study for a 6U Cubesat.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47462822","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 : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.2
Viorel Anghel, S. Sorohan, D. Hodor
The paper deals with Finite Element Modeling of catenary type structures starting from practical problems related to a single cable segment in the case of an electric transmission line. Finite element models allow the analysis of the resulting deformed position and stress state for a given configuration obtained by using the geometric and physical data of a cable. Beam type linear/nonlinear finite element models which can take into account also the temperature variation and extra loading on the cable were developed. Another application of this type of models is for the case of form finding of aerial refueling cable subjected to dynamic pressure. The results were obtained by the commercial finite element software ANSYS.
{"title":"FEM Applications of Catenary Type Structures","authors":"Viorel Anghel, S. Sorohan, D. Hodor","doi":"10.13111/2066-8201.2022.14.4.2","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.2","url":null,"abstract":"The paper deals with Finite Element Modeling of catenary type structures starting from practical problems related to a single cable segment in the case of an electric transmission line. Finite element models allow the analysis of the resulting deformed position and stress state for a given configuration obtained by using the geometric and physical data of a cable. Beam type linear/nonlinear finite element models which can take into account also the temperature variation and extra loading on the cable were developed. Another application of this type of models is for the case of form finding of aerial refueling cable subjected to dynamic pressure. The results were obtained by the commercial finite element software ANSYS.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45337816","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 : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.16
Ionut Valentin Lom
Aviation insurance represents a special form of activity related to providing financial protection for companies operating in the aviation field. Aviation insurance is intended for the aerospace industry to cover the risks associated with its activities. It provides general liability coverage for air transport of passengers and cargo; losses caused by military operations or terrorist activities; physical damage; and liability to passengers and third parties. The recent changes in the global market situation, influenced by a complex of factors, determine the general development of aviation insurance. On the other hand, rising costs in aviation insurance and limiting the activities of service providers may hinder market growth in the medium term.
{"title":"Current global trends of aviation insurance","authors":"Ionut Valentin Lom","doi":"10.13111/2066-8201.2022.14.4.16","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.16","url":null,"abstract":"Aviation insurance represents a special form of activity related to providing financial protection for companies operating in the aviation field. Aviation insurance is intended for the aerospace industry to cover the risks associated with its activities. It provides general liability coverage for air transport of passengers and cargo; losses caused by military operations or terrorist activities; physical damage; and liability to passengers and third parties. The recent changes in the global market situation, influenced by a complex of factors, determine the general development of aviation insurance. On the other hand, rising costs in aviation insurance and limiting the activities of service providers may hinder market growth in the medium term.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"44429993","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 : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.18
B. A. Nicolin, I. Nicolin
The mechanical-hydraulic steering system of a military training aircraft is a technical problem for specialized engineers and it must be investigated and solved in a scientific manner using theoretical knowledge, calculus programs such as Mathcad, and CAD applications for design such as CATIA V5 which allows the preservation of practical experience and favors its dissemination for future similar calculation. The scope of this calculus is to demonstrate that the active moment developed by the two hydraulic cylinders is always bigger than the resisting moment opposing the steering action of the nose landing gear wheel generated by the frictional forces between the wheel and the running way.
{"title":"Calculation of steering system parameters of a military training aircraft","authors":"B. A. Nicolin, I. Nicolin","doi":"10.13111/2066-8201.2022.14.4.18","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.18","url":null,"abstract":"The mechanical-hydraulic steering system of a military training aircraft is a technical problem for specialized engineers and it must be investigated and solved in a scientific manner using theoretical knowledge, calculus programs such as Mathcad, and CAD applications for design such as CATIA V5 which allows the preservation of practical experience and favors its dissemination for future similar calculation. The scope of this calculus is to demonstrate that the active moment developed by the two hydraulic cylinders is always bigger than the resisting moment opposing the steering action of the nose landing gear wheel generated by the frictional forces between the wheel and the running way.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45823418","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 : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.9
T. P. PREM ANAND, K. Abishek, R. KRISHNA KAILASH, K. K. Nithiyanantham
Today's military missions require pre-emptive knowledge of hostile activities in and around the conflict zone. Using a multi rotor UAV for Reconnaissance has many disadvantages, such as cost, range, reduced maneuverability and much more. The main objective is to make the UAV completely autonomous, with the transmitter on standby. By entering the flight plan into the Ground Control System, the UAV will complete the assigned mission autonomously and will be guided by an operational flight plan wherein active waypoints are plotted in the GCS. The GCS can be linked to the Telemetry and the Global Positioning System to have a complete knowledge of the UAV location.
{"title":"Development and Automation of Fixed Wing UAV for Reconnaissance Mission with FPV Capability","authors":"T. P. PREM ANAND, K. Abishek, R. KRISHNA KAILASH, K. K. Nithiyanantham","doi":"10.13111/2066-8201.2022.14.4.9","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.9","url":null,"abstract":"Today's military missions require pre-emptive knowledge of hostile activities in and around the conflict zone. Using a multi rotor UAV for Reconnaissance has many disadvantages, such as cost, range, reduced maneuverability and much more. The main objective is to make the UAV completely autonomous, with the transmitter on standby. By entering the flight plan into the Ground Control System, the UAV will complete the assigned mission autonomously and will be guided by an operational flight plan wherein active waypoints are plotted in the GCS. The GCS can be linked to the Telemetry and the Global Positioning System to have a complete knowledge of the UAV location.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47758491","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 : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.20
Manuela Rusu, Ilinca Marin, Valentin Soare, S. Tonoiu, O. Blăjină
This article presents contractual requirements review as an element of a Quality Management System (SR EN 9100:2018 [1]), which requires the organization to conduct requirements reviews at various stages of the product realization lifecycle. Proper conduct of a review and management of requirements will enhance overall supply chain performance with regards to On-Time-On-Quality Delivery (OTOQD).
本文将合同需求评审作为质量管理体系(SR EN 9100:2018[1])的一个要素，要求组织在产品实现生命周期的各个阶段进行需求评审。对需求进行适当的评审和管理将提高供应链在准时、高质量交货方面的整体表现。
{"title":"Contractual Requirements Review and Management","authors":"Manuela Rusu, Ilinca Marin, Valentin Soare, S. Tonoiu, O. Blăjină","doi":"10.13111/2066-8201.2022.14.4.20","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.20","url":null,"abstract":"This article presents contractual requirements review as an element of a Quality Management System (SR EN 9100:2018 [1]), which requires the organization to conduct requirements reviews at various stages of the product realization lifecycle. Proper conduct of a review and management of requirements will enhance overall supply chain performance with regards to On-Time-On-Quality Delivery (OTOQD).","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47931264","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 : 2022-12-02DOI: 10.13111/2066-8201.2022.14.4.7
Z. Kutpanova, H. Temeltas, S. Kulmamirov
An unmanned aerial vehicle is a hardware and software complex with multi-purpose control. Unlike manned aviation, an unmanned aerial vehicle requires additional modules in its control system. These include the drone itself, the operator's workplace, software, data transmission lines and blocks necessary to fulfil the set flight objectives. The range of applications of unmanned aerial vehicles in the civil sector is not limited, but with the current state of the legal framework for the use of airspace, flight operations are somewhat difficult. The article formulates the main scientific position on the methodology of solving auxiliary tasks set in the work. The methodology specifies the main research stages, and it is a generalized methodological algorithm for the implementation of scientific research, which provides theoretical developments, field observations and simulation computer modelling. As a result of the study, it was found that the motion control systems of unmanned aerial vehicles are used for the process of their differentiation by the principle of complete external control, the advantages of which are considered in the work. For external control of divergence process of unmanned aerial vehicles, a method is considered for assessing the situation of convergence of unmanned aerial vehicles and choosing the manoeuvre of their difference using the area of dangerous courses, unmanned aerial vehicles approach, and it is possible to take into account the inertia of unmanned aerial vehicles when turning and the presence of navigational hazards that are in the manoeuvring area.
{"title":"Flight control and collision avoidance of three UAVs following each other","authors":"Z. Kutpanova, H. Temeltas, S. Kulmamirov","doi":"10.13111/2066-8201.2022.14.4.7","DOIUrl":"https://doi.org/10.13111/2066-8201.2022.14.4.7","url":null,"abstract":"An unmanned aerial vehicle is a hardware and software complex with multi-purpose control. Unlike manned aviation, an unmanned aerial vehicle requires additional modules in its control system. These include the drone itself, the operator's workplace, software, data transmission lines and blocks necessary to fulfil the set flight objectives. The range of applications of unmanned aerial vehicles in the civil sector is not limited, but with the current state of the legal framework for the use of airspace, flight operations are somewhat difficult. The article formulates the main scientific position on the methodology of solving auxiliary tasks set in the work. The methodology specifies the main research stages, and it is a generalized methodological algorithm for the implementation of scientific research, which provides theoretical developments, field observations and simulation computer modelling. As a result of the study, it was found that the motion control systems of unmanned aerial vehicles are used for the process of their differentiation by the principle of complete external control, the advantages of which are considered in the work. For external control of divergence process of unmanned aerial vehicles, a method is considered for assessing the situation of convergence of unmanned aerial vehicles and choosing the manoeuvre of their difference using the area of dangerous courses, unmanned aerial vehicles approach, and it is possible to take into account the inertia of unmanned aerial vehicles when turning and the presence of navigational hazards that are in the manoeuvring area.","PeriodicalId":37556,"journal":{"name":"INCAS Bulletin","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"2022-12-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"43406592","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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