Pub Date : 2016-09-01DOI: 10.1109/DASC.2016.7778101
Yue Zhao, J. J. Zhu
An autonomous integrated Loss-of-Control (LOC) Prevention and Recovery (iLOCPR) system for UAVs is proposed with four operation modes: a nominal mode designed for 6 degree-of-freedom (DOF) trajectory tracking by trajectory linearization control; a LOC prevention mode designed by bandwidth adaptation augmentation to the baseline nominal controller for increasing the stability margin in the presence of LOC-prone flight conditions; a LOC arrest mode by reconfiguring the controller to recover and maintain healthy flight aerodynamic angles while temporarily giving up the trajectory tracking mission; a restoration mode to guide the vehicle back to the mission trajectory after successful LOC arrest. A supervisory discrete-event-driven automatic flight management system (AFMS) is designed to autonomously reconfigure the flight controller by coordinating and switching the control modes according to the real-time sensed flight conditions. A full comprehensive simulation entailing the nominal trajectory tracking, LOC prevention, LOC arrest and mission restoration is provided to demonstrate the effectiveness of modes switching and the performance of the iLOCPR system. The proposed framework can be further augmented for autonomous fault tolerance and collision avoidance in future development.
{"title":"An autonomous flight management system for prevention and recovery of unmanned aerial vehicle loss-of-control","authors":"Yue Zhao, J. J. Zhu","doi":"10.1109/DASC.2016.7778101","DOIUrl":"https://doi.org/10.1109/DASC.2016.7778101","url":null,"abstract":"An autonomous integrated Loss-of-Control (LOC) Prevention and Recovery (iLOCPR) system for UAVs is proposed with four operation modes: a nominal mode designed for 6 degree-of-freedom (DOF) trajectory tracking by trajectory linearization control; a LOC prevention mode designed by bandwidth adaptation augmentation to the baseline nominal controller for increasing the stability margin in the presence of LOC-prone flight conditions; a LOC arrest mode by reconfiguring the controller to recover and maintain healthy flight aerodynamic angles while temporarily giving up the trajectory tracking mission; a restoration mode to guide the vehicle back to the mission trajectory after successful LOC arrest. A supervisory discrete-event-driven automatic flight management system (AFMS) is designed to autonomously reconfigure the flight controller by coordinating and switching the control modes according to the real-time sensed flight conditions. A full comprehensive simulation entailing the nominal trajectory tracking, LOC prevention, LOC arrest and mission restoration is provided to demonstrate the effectiveness of modes switching and the performance of the iLOCPR system. The proposed framework can be further augmented for autonomous fault tolerance and collision avoidance in future development.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"65 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130019659","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 : 2016-09-01DOI: 10.1109/DASC.2016.7777981
Petr Petlach, M. Dub
The article deals with possibilities of utilization of modern industrial sensors for aircraft fuel quantity measurement. The purpose of the fuel quantity measurement in aircraft with either stationary or rotary wings is to provide information about the total amount of fuel and fuel variations under all aircraft attitudes and with all types of fuel. In aircraft technology, there are especially two basic methods of fuel quantity measurement used that are based on measurement of fuel level. Both methods are contact measurement methods and the fuel gauge is always in contact with fuel. The older, easier and cheaper method is based on float level sensors. Modern and more precise method is based on capacitance level sensors. The measured fuel level is then converted to volume or weight of the fuel and displayed on a fuel indicator in the cockpit. Both methods have some limitations and for that reason another fuel level measurement methods have been introduced onboard. Our practical experiments deal with possibilities of COTS ultrasonic sensors utilization for fuel gauging inside small aircraft fuel tank. Ultrasonic fuel level measurement is based on reflecting sound energy at an interface of liquid and air. Tested operating conditions include influence of aircraft attitude changes, mechanical forces changes and temperature changes on whole measuring systems. Fuel volume is also measured by reference capacitance fuel gauge during practical experiments. Experimental results lead to error quantification of COTS ultrasonic fluid level measurement and following technical measures to minimization of systematic errors.
{"title":"Possibilities of COTS ultrasonic fuel quantity measurement","authors":"Petr Petlach, M. Dub","doi":"10.1109/DASC.2016.7777981","DOIUrl":"https://doi.org/10.1109/DASC.2016.7777981","url":null,"abstract":"The article deals with possibilities of utilization of modern industrial sensors for aircraft fuel quantity measurement. The purpose of the fuel quantity measurement in aircraft with either stationary or rotary wings is to provide information about the total amount of fuel and fuel variations under all aircraft attitudes and with all types of fuel. In aircraft technology, there are especially two basic methods of fuel quantity measurement used that are based on measurement of fuel level. Both methods are contact measurement methods and the fuel gauge is always in contact with fuel. The older, easier and cheaper method is based on float level sensors. Modern and more precise method is based on capacitance level sensors. The measured fuel level is then converted to volume or weight of the fuel and displayed on a fuel indicator in the cockpit. Both methods have some limitations and for that reason another fuel level measurement methods have been introduced onboard. Our practical experiments deal with possibilities of COTS ultrasonic sensors utilization for fuel gauging inside small aircraft fuel tank. Ultrasonic fuel level measurement is based on reflecting sound energy at an interface of liquid and air. Tested operating conditions include influence of aircraft attitude changes, mechanical forces changes and temperature changes on whole measuring systems. Fuel volume is also measured by reference capacitance fuel gauge during practical experiments. Experimental results lead to error quantification of COTS ultrasonic fluid level measurement and following technical measures to minimization of systematic errors.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"134 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116354034","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 : 2016-09-01DOI: 10.1109/DASC.2016.7777959
Michael P. Owen, Mykel J. Kochenderfer
The ACAS Xu program has developed both a horizontal and vertical collision avoidance logic to enable unmanned aircraft to avoid manned aircraft. Each logic supports a variety of surveillance sources and is individually capable of providing a significant safety benefit. This paper proposes a logic selection function that can effectively arbitrate between the horizontal and vertical logics to achieve an overall safety benefit without requiring the use of simultaneous horizontal and vertical maneuvers. Monte Carlo simulations show that the logic selection function can provide a performance benefit for a variety of surveillance sources.
{"title":"Dynamic logic selection for unmanned aircraft separation","authors":"Michael P. Owen, Mykel J. Kochenderfer","doi":"10.1109/DASC.2016.7777959","DOIUrl":"https://doi.org/10.1109/DASC.2016.7777959","url":null,"abstract":"The ACAS Xu program has developed both a horizontal and vertical collision avoidance logic to enable unmanned aircraft to avoid manned aircraft. Each logic supports a variety of surveillance sources and is individually capable of providing a significant safety benefit. This paper proposes a logic selection function that can effectively arbitrate between the horizontal and vertical logics to achieve an overall safety benefit without requiring the use of simultaneous horizontal and vertical maneuvers. Monte Carlo simulations show that the logic selection function can provide a performance benefit for a variety of surveillance sources.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"55 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133767764","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 : 2016-09-01DOI: 10.1109/DASC.2016.7778086
R. Schreiber, J. Bajer
The paper is aimed at the determination and verification of system parameters, that can be achieved with the utilization of commonly available RTL-SDR software defined receiver in TDOA based system intended for position determination of the small-UAS. The paper describes a way of performing practical experiments, measurement setup and properties of the signal used. Experimental results lead to the specification of potentially achievable accuracy and resolution of time difference of arrival measurement.
{"title":"Software defined radio based receiver for TDOA positioning system","authors":"R. Schreiber, J. Bajer","doi":"10.1109/DASC.2016.7778086","DOIUrl":"https://doi.org/10.1109/DASC.2016.7778086","url":null,"abstract":"The paper is aimed at the determination and verification of system parameters, that can be achieved with the utilization of commonly available RTL-SDR software defined receiver in TDOA based system intended for position determination of the small-UAS. The paper describes a way of performing practical experiments, measurement setup and properties of the signal used. Experimental results lead to the specification of potentially achievable accuracy and resolution of time difference of arrival measurement.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130491415","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 : 2016-09-01DOI: 10.1109/DASC.2016.7778111
A. Zeitler, T. Hanti, Sebastian Hiergeist, A. Schwierz
The move from a purely remotely piloted aerial system (RPAS) via air vehicles using automated systems up to a fully autonomous platform is a way that is being followed today. Using automatic take-off and/or landing (ATOL) or waypoint flying, the path towards more complex technologies for RPAS control is clear. Inserting such new technologies into an aerial platform requires extensive testing from an early project phase. Due to the complex nature of environment-related system inputs combined with highly complex algorithms, a pure ground testing will never be able to stimulate those new developments properly. At this point flying testbeds will be used as test vehicles for new equipment operating under real conditions. This paper describes the conceptional design and hardware realization of the datalink system of such a RPAS technology demonstrator testbed for autonomous concepts in the sub-150kg class. Designed light enough to respect certification limitations, this small scale RPAS shall be able to carry realistic avionics hardware undergoing testing in real environment for use as a cheap and flexible testbed. Driven by the concept of flight operations within a dedicated test range and pushed by flight safety a reliable communication system had to be designed to assure a secure conduction and surveillance of the flight, while still being able to interact with the experiments onboard.
{"title":"A communication system approach for a small scale RPAS demonstrator","authors":"A. Zeitler, T. Hanti, Sebastian Hiergeist, A. Schwierz","doi":"10.1109/DASC.2016.7778111","DOIUrl":"https://doi.org/10.1109/DASC.2016.7778111","url":null,"abstract":"The move from a purely remotely piloted aerial system (RPAS) via air vehicles using automated systems up to a fully autonomous platform is a way that is being followed today. Using automatic take-off and/or landing (ATOL) or waypoint flying, the path towards more complex technologies for RPAS control is clear. Inserting such new technologies into an aerial platform requires extensive testing from an early project phase. Due to the complex nature of environment-related system inputs combined with highly complex algorithms, a pure ground testing will never be able to stimulate those new developments properly. At this point flying testbeds will be used as test vehicles for new equipment operating under real conditions. This paper describes the conceptional design and hardware realization of the datalink system of such a RPAS technology demonstrator testbed for autonomous concepts in the sub-150kg class. Designed light enough to respect certification limitations, this small scale RPAS shall be able to carry realistic avionics hardware undergoing testing in real environment for use as a cheap and flexible testbed. Driven by the concept of flight operations within a dedicated test range and pushed by flight safety a reliable communication system had to be designed to assure a secure conduction and surveillance of the flight, while still being able to interact with the experiments onboard.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130614906","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 : 2016-09-01DOI: 10.1109/DASC.2016.7777945
Lu Ma, Chao Zhang
With the incoming of the new era of 5G mobile communications and Internet of Things (IoT), the aeronautical communications for aircraft, Air-to-Ground (A/G) communications and Air-to-Air (A/A) communications, confronts with new challenges of high safety, large transmission capacity, low latency, high elasticity, and synthetic service providing etc. In this paper, the new requirement and challenges of future aeronautical communications are reviewed. Moreover, the future aeronautical communications architecture is envisioned and the typical wareforms recommended for 5G are deeply analyzed. Finally, the transition from the current aeronautical datalinks is prospectively discussed.
{"title":"5G wareforms design for aeronautical communications","authors":"Lu Ma, Chao Zhang","doi":"10.1109/DASC.2016.7777945","DOIUrl":"https://doi.org/10.1109/DASC.2016.7777945","url":null,"abstract":"With the incoming of the new era of 5G mobile communications and Internet of Things (IoT), the aeronautical communications for aircraft, Air-to-Ground (A/G) communications and Air-to-Air (A/A) communications, confronts with new challenges of high safety, large transmission capacity, low latency, high elasticity, and synthetic service providing etc. In this paper, the new requirement and challenges of future aeronautical communications are reviewed. Moreover, the future aeronautical communications architecture is envisioned and the typical wareforms recommended for 5G are deeply analyzed. Finally, the transition from the current aeronautical datalinks is prospectively discussed.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"78 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116682381","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 : 2016-09-01DOI: 10.1109/DASC.2016.7777963
Ryan Gardner, D. Genin, Raymond McDowell, C. Rouff, Anshu Saksena, Aurora C. Schmidt
We present a probabilistic model checking approach for evaluating the safety and operational suitability of the Airborne Collision Avoidance System X (ACAS X). This system issues advisories to pilots when the risk of mid-air collision is imminent, and is expected to be equipped on all large, piloted aircraft in the future. We developed an approach to efficiently compute the probabilities of generically specified events and the most likely sequences of states leading to those events within a discrete-time Markov chain model of aircraft flight and ACAS X. The probabilities and sequences are computed for all states in the model. Events of interest include near mid-air collisions (NMACs) and undesirable sequences of advisories that affect operational suitability. We have validated numerous observations of the model with higher-fidelity simulations of the full system. This analysis has revealed several characteristics of ACAS X's behavior.
{"title":"Probabilistic model checking of the next-generation airborne collision avoidance system","authors":"Ryan Gardner, D. Genin, Raymond McDowell, C. Rouff, Anshu Saksena, Aurora C. Schmidt","doi":"10.1109/DASC.2016.7777963","DOIUrl":"https://doi.org/10.1109/DASC.2016.7777963","url":null,"abstract":"We present a probabilistic model checking approach for evaluating the safety and operational suitability of the Airborne Collision Avoidance System X (ACAS X). This system issues advisories to pilots when the risk of mid-air collision is imminent, and is expected to be equipped on all large, piloted aircraft in the future. We developed an approach to efficiently compute the probabilities of generically specified events and the most likely sequences of states leading to those events within a discrete-time Markov chain model of aircraft flight and ACAS X. The probabilities and sequences are computed for all states in the model. Events of interest include near mid-air collisions (NMACs) and undesirable sequences of advisories that affect operational suitability. We have validated numerous observations of the model with higher-fidelity simulations of the full system. This analysis has revealed several characteristics of ACAS X's behavior.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129380046","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 : 2016-09-01DOI: 10.1109/DASC.2016.7777987
Sarah D'Souza, A. Ishihara, Ben E. Nikaido, Hashmatullah Hasseeb
Managing trajectory separation of unmanned aircraft is critical to ensuring accessibility, efficiency, and safety in low altitude airspace. The concept of a geo-fence has emerged as a way to manage trajectory separation. A geo-fence consists of distance buffers that enclose individual trajectories to identify a `keep-in' region and/or enclose areas that identify `keep-out' regions. The `keep-in' geo-fence size can be defined as a static number or calculated as a function of vehicle performance characteristics, state of the airspace, weather, and other unforeseen events such as emergency or disaster response. Given that the fleet of Unmanned Aircraft Systems (UAS) operating in low altitude airspace will be numerous and non-homogeneous, calculating a `keep-in' geo-fence will need to balance operational safety and efficiency. A recently tested UAS Traffic Management (UTM) prototype used a geo-fence size of 30 meters, horizontally and vertically, for every operation submitted. The goal of this work is to determine the feasibility of a generalized, simple algorithm that calculates geo-fence sizes as a function of vehicle performance and potential wind disturbances. The resulting geo-fence size could be smaller or larger because the vehicle performance in the presence of wind is considered, thus leading to trajectory separation that is safe and efficient. In this paper, two simplified methods were developed to determine the feasibility of calculating a geo-fence as a function of vehicle parameters and wind information. The first method calculates the geo-fence using basic vehicle parameters and wind sensor data in a set of algebraic-geometric equations. The second method models a generic PID control system that uses a simplified set of equations of motion for the plant and uses gain scheduling to account for wind disturbances. It was found that the Algebraic-Geometric Geo-fence Algorithm provides geo-fence sizes of approximately 15 meters horizontally and 5 meters vertically, which is much smaller than the UTM static value of 30 meters. In the PID Controller Geo-fence Algorithm it was found that the geo-fence size is further reduced to less than 5 meters, horizontally and vertically. These results reveal that implementing geo-fence calculations provide UTM with the ability to schedule and separate operations based on geofences that are dynamic to vehicle capability and environment, which is more efficient than using a single static geo-fence.
{"title":"Feasibility of varying geo-fence around an unmanned aircraft operation based on vehicle performance and wind","authors":"Sarah D'Souza, A. Ishihara, Ben E. Nikaido, Hashmatullah Hasseeb","doi":"10.1109/DASC.2016.7777987","DOIUrl":"https://doi.org/10.1109/DASC.2016.7777987","url":null,"abstract":"Managing trajectory separation of unmanned aircraft is critical to ensuring accessibility, efficiency, and safety in low altitude airspace. The concept of a geo-fence has emerged as a way to manage trajectory separation. A geo-fence consists of distance buffers that enclose individual trajectories to identify a `keep-in' region and/or enclose areas that identify `keep-out' regions. The `keep-in' geo-fence size can be defined as a static number or calculated as a function of vehicle performance characteristics, state of the airspace, weather, and other unforeseen events such as emergency or disaster response. Given that the fleet of Unmanned Aircraft Systems (UAS) operating in low altitude airspace will be numerous and non-homogeneous, calculating a `keep-in' geo-fence will need to balance operational safety and efficiency. A recently tested UAS Traffic Management (UTM) prototype used a geo-fence size of 30 meters, horizontally and vertically, for every operation submitted. The goal of this work is to determine the feasibility of a generalized, simple algorithm that calculates geo-fence sizes as a function of vehicle performance and potential wind disturbances. The resulting geo-fence size could be smaller or larger because the vehicle performance in the presence of wind is considered, thus leading to trajectory separation that is safe and efficient. In this paper, two simplified methods were developed to determine the feasibility of calculating a geo-fence as a function of vehicle parameters and wind information. The first method calculates the geo-fence using basic vehicle parameters and wind sensor data in a set of algebraic-geometric equations. The second method models a generic PID control system that uses a simplified set of equations of motion for the plant and uses gain scheduling to account for wind disturbances. It was found that the Algebraic-Geometric Geo-fence Algorithm provides geo-fence sizes of approximately 15 meters horizontally and 5 meters vertically, which is much smaller than the UTM static value of 30 meters. In the PID Controller Geo-fence Algorithm it was found that the geo-fence size is further reduced to less than 5 meters, horizontally and vertically. These results reveal that implementing geo-fence calculations provide UTM with the ability to schedule and separate operations based on geofences that are dynamic to vehicle capability and environment, which is more efficient than using a single static geo-fence.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115426085","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 : 2016-09-01DOI: 10.1109/DASC.2016.7778094
T. Etherington, L. Kramer, R. Bailey, Kellie D. Kennedy, C. Stephens
Accident statistics cite the flight crew as a causal factor in over 60% of accidents involving transport category airplanes. Yet, a well-trained and well-qualified pilot is acknowledged as the critical center point of aircraft systems safety and an integral safety component of the entire commercial aviation system. No data currently exists that quantifies the contribution of the flight crew in this role. Neither does data exist for how often the flight crew handles non-normal procedures or system failures on a daily basis in the National Airspace System. A pilot-in-the-loop high fidelity motion simulation study was conducted by the NASA Langley Research Center in partnership with the Federal Aviation Administration (FAA) to evaluate the pilot's contribution to flight safety during normal flight and in response to aircraft system failures. Eighteen crews flew various normal and non-normal procedures over a two-day period and their actions were recorded in response to failures. To quantify the human's contribution, crew complement was used as the experiment independent variable in a between-subjects design. Pilot actions and performance when one of the flight crew was impaired were also recorded for comparison against the nominal two-crew operations. This paper details a portion of the results of this study.
{"title":"Quantifying pilot contribution to flight safety for normal and non-normal airline operations","authors":"T. Etherington, L. Kramer, R. Bailey, Kellie D. Kennedy, C. Stephens","doi":"10.1109/DASC.2016.7778094","DOIUrl":"https://doi.org/10.1109/DASC.2016.7778094","url":null,"abstract":"Accident statistics cite the flight crew as a causal factor in over 60% of accidents involving transport category airplanes. Yet, a well-trained and well-qualified pilot is acknowledged as the critical center point of aircraft systems safety and an integral safety component of the entire commercial aviation system. No data currently exists that quantifies the contribution of the flight crew in this role. Neither does data exist for how often the flight crew handles non-normal procedures or system failures on a daily basis in the National Airspace System. A pilot-in-the-loop high fidelity motion simulation study was conducted by the NASA Langley Research Center in partnership with the Federal Aviation Administration (FAA) to evaluate the pilot's contribution to flight safety during normal flight and in response to aircraft system failures. Eighteen crews flew various normal and non-normal procedures over a two-day period and their actions were recorded in response to failures. To quantify the human's contribution, crew complement was used as the experiment independent variable in a between-subjects design. Pilot actions and performance when one of the flight crew was impaired were also recorded for comparison against the nominal two-crew operations. This paper details a portion of the results of this study.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"51 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114174664","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 : 2016-09-01DOI: 10.1109/DASC.2016.7778031
S. Cheon, S. Ha, Y. Moon
In this paper, a hardware-in-the loop simulation (HILS) platform is presented for verifying the image-based object tracking method adopted in the small Unmanned Aerial Vehicle (sUAV). The platform is constructed by image processing module, scene generation module, and flight control module. In the image processing module, the motion of target object is measured by using the speeded-up robust features (SURF) algorithm and the feature matching technique. And then, control command is provided to allow the target object to be tracked by sUAV automatically. The JMAVSIM software developed by PX4 dev-team is used in the proposed platform to simulate the flight of sUAV and provide virtual scene and flight data. Pixhawk based on PX4 firmware which is a popular flight control computer is used as flight control module in the proposed platform. Experimental results show that the object tracking method based on sUAV is effectively tested and evaluated in the proposed HILS platform.
{"title":"Hardware-in-the-loop simulation platform for image-based object tracking method using small UAV","authors":"S. Cheon, S. Ha, Y. Moon","doi":"10.1109/DASC.2016.7778031","DOIUrl":"https://doi.org/10.1109/DASC.2016.7778031","url":null,"abstract":"In this paper, a hardware-in-the loop simulation (HILS) platform is presented for verifying the image-based object tracking method adopted in the small Unmanned Aerial Vehicle (sUAV). The platform is constructed by image processing module, scene generation module, and flight control module. In the image processing module, the motion of target object is measured by using the speeded-up robust features (SURF) algorithm and the feature matching technique. And then, control command is provided to allow the target object to be tracked by sUAV automatically. The JMAVSIM software developed by PX4 dev-team is used in the proposed platform to simulate the flight of sUAV and provide virtual scene and flight data. Pixhawk based on PX4 firmware which is a popular flight control computer is used as flight control module in the proposed platform. Experimental results show that the object tracking method based on sUAV is effectively tested and evaluated in the proposed HILS platform.","PeriodicalId":340472,"journal":{"name":"2016 IEEE/AIAA 35th Digital Avionics Systems Conference (DASC)","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2016-09-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116280693","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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