Pub Date : 2013-03-12DOI: 10.1109/MAES.2013.6477865
Dayton L. Jones
The Square Kilometer Array will be the premier facility for radio astronomy during several decades, starting around 2020. It will provide orders-of-magnitude increases in sensitivity and field of view, allowing a wide range of fundamental science questions to be answered. However, a number of key technology areas need further development to meet the demanding performance and cost goals of the SKA. These include wide-bandwidth feeds and low noise amplifiers, very low power digital signal processing, real time interference detection and excision, software to handle massive data rates and volumes, and low-cost operations. Developing solutions for each of these areas will require industry expertise and experience. 1 2
{"title":"Technology challenges for the Square Kilometer Array","authors":"Dayton L. Jones","doi":"10.1109/MAES.2013.6477865","DOIUrl":"https://doi.org/10.1109/MAES.2013.6477865","url":null,"abstract":"The Square Kilometer Array will be the premier facility for radio astronomy during several decades, starting around 2020. It will provide orders-of-magnitude increases in sensitivity and field of view, allowing a wide range of fundamental science questions to be answered. However, a number of key technology areas need further development to meet the demanding performance and cost goals of the SKA. These include wide-bandwidth feeds and low noise amplifiers, very low power digital signal processing, real time interference detection and excision, software to handle massive data rates and volumes, and low-cost operations. Developing solutions for each of these areas will require industry expertise and experience. 1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2013-03-12","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121618140","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 : 2011-12-01DOI: 10.1109/MAES.2011.6138395
R. Terrile
This paper explores impediments to innovation in aerospace and suggests how successful pathways from other industries can be adopted to facilitate greater innovation. Because of its nature, space exploration would seem to be a ripe field of technical innovation. However, engineering can also be a frustratingly conservative endeavor when the realities of cost and risk are included. Impediments like the “find the fault” engineering culture, the treatment of technical risk as almost always evaluated in terms of negative impact, the difficult to account for expansive Moore's Law growth when making predictions, and the stove-piped structural organization of most large aerospace companies and federally funded research laboratories tend to inhibit cross-cutting technical innovation. One successful example of a multi-use cross cutting application that can scale with Moore's Law is the Evolutionary Computational Methods (ECM) technique developed at the Jet Propulsion Lab for automated spectral retrieval. Future innovations like computational engineering and automated design optimization can potentially redefine space exploration, but will require learning lessons from successful innovators.12
{"title":"Pathways and challenges to innovation in aerospace","authors":"R. Terrile","doi":"10.1109/MAES.2011.6138395","DOIUrl":"https://doi.org/10.1109/MAES.2011.6138395","url":null,"abstract":"This paper explores impediments to innovation in aerospace and suggests how successful pathways from other industries can be adopted to facilitate greater innovation. Because of its nature, space exploration would seem to be a ripe field of technical innovation. However, engineering can also be a frustratingly conservative endeavor when the realities of cost and risk are included. Impediments like the “find the fault” engineering culture, the treatment of technical risk as almost always evaluated in terms of negative impact, the difficult to account for expansive Moore's Law growth when making predictions, and the stove-piped structural organization of most large aerospace companies and federally funded research laboratories tend to inhibit cross-cutting technical innovation. One successful example of a multi-use cross cutting application that can scale with Moore's Law is the Evolutionary Computational Methods (ECM) technique developed at the Jet Propulsion Lab for automated spectral retrieval. Future innovations like computational engineering and automated design optimization can potentially redefine space exploration, but will require learning lessons from successful innovators.12","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"450 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2011-12-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115277825","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 : 2010-06-17DOI: 10.1109/MAES.2010.5486535
Brenda K. Wetzel
The Space Department at the Johns Hopkins University Applied Physics Laboratory (APL) launched a formal mentoring program in 2007.1 While a mentoring program existed previously, it was not widely utilized and eventually lost support. The new program was designed to focus on the staff members' needs and desires for career growth and an opportunity for those skilled with years of expertise in the space domain to share their wisdom and gain a new perspective. Especially in an era where budgets are constrained, mentoring is a cost effective method to ensure continuity of knowledge and enthusiasm in staff. This paper discusses the motivations for starting the program, the hurdles involved, and the benefits derived during the first few years of APL's new Space Department mentoring program. The paper includes the design details of the program, as well as successes and lessons learned to date.2
{"title":"Mentoring: A key to longevity in Space","authors":"Brenda K. Wetzel","doi":"10.1109/MAES.2010.5486535","DOIUrl":"https://doi.org/10.1109/MAES.2010.5486535","url":null,"abstract":"The Space Department at the Johns Hopkins University Applied Physics Laboratory (APL) launched a formal mentoring program in 2007.1 While a mentoring program existed previously, it was not widely utilized and eventually lost support. The new program was designed to focus on the staff members' needs and desires for career growth and an opportunity for those skilled with years of expertise in the space domain to share their wisdom and gain a new perspective. Especially in an era where budgets are constrained, mentoring is a cost effective method to ensure continuity of knowledge and enthusiasm in staff. This paper discusses the motivations for starting the program, the hurdles involved, and the benefits derived during the first few years of APL's new Space Department mentoring program. The paper includes the design details of the program, as well as successes and lessons learned to date.2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"195 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-06-17","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115643162","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 : 2010-04-15DOI: 10.1109/AERO.2010.5446788
A. Khwaja, J. E. Urban
RealSpec is a declarative and executable specification language for specifying real-time and concurrent software systems based on the dataflow computation model.
RealSpec是一种声明性和可执行的规范语言，用于指定基于数据流计算模型的实时和并发软件系统。
{"title":"Preciseness for predictability with the RealSpec real-time executable specification language","authors":"A. Khwaja, J. E. Urban","doi":"10.1109/AERO.2010.5446788","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446788","url":null,"abstract":"RealSpec is a declarative and executable specification language for specifying real-time and concurrent software systems based on the dataflow computation model.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-04-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124852968","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 : 2010-04-15DOI: 10.1109/AERO.2010.5446731
R. Schlanbusch, R. Kristiansen, P. J. Nicklasson
Due to the parametrization of the attitude for closed loop rigid body systems we either encounter an inherent geometric singularity using Euler representation, or obtain dual equilibrium points using the unit quaternion. In order to save energy during attitude maneuvers the choice of equilibrium point and thus rotational direction is imperative for quaternion feedback systems. Normally the shortest rotation is preferred, but in this paper we present schemes where both initial attitude and angular velocity are considered for choosing the preferable rotational direction for a rigid body, thus taking advantage of the initial angular velocity. The solution is based on a set of simple rules where two initial parameters are analyzed and the sign of the solution decides which rotational direction is preferable. The check is not computationally consuming, and may therefore be implemented on i.e. a spacecraft where computational resources are limited. When the preferable equilibrium is chosen, it is kept throughout the maneuver. A tracking controller is derived, resulting in uniform asymptotic stability for both equilibrium points, and the performance of our results are shown through a large number of simulations using randomized initial values.
{"title":"On choosing quaternion equilibrium point in attitude stabilization","authors":"R. Schlanbusch, R. Kristiansen, P. J. Nicklasson","doi":"10.1109/AERO.2010.5446731","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446731","url":null,"abstract":"Due to the parametrization of the attitude for closed loop rigid body systems we either encounter an inherent geometric singularity using Euler representation, or obtain dual equilibrium points using the unit quaternion. In order to save energy during attitude maneuvers the choice of equilibrium point and thus rotational direction is imperative for quaternion feedback systems. Normally the shortest rotation is preferred, but in this paper we present schemes where both initial attitude and angular velocity are considered for choosing the preferable rotational direction for a rigid body, thus taking advantage of the initial angular velocity. The solution is based on a set of simple rules where two initial parameters are analyzed and the sign of the solution decides which rotational direction is preferable. The check is not computationally consuming, and may therefore be implemented on i.e. a spacecraft where computational resources are limited. When the preferable equilibrium is chosen, it is kept throughout the maneuver. A tracking controller is derived, resulting in uniform asymptotic stability for both equilibrium points, and the performance of our results are shown through a large number of simulations using randomized initial values.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"71 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-04-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121878488","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 : 2010-04-15DOI: 10.1109/AERO.2010.5446993
G. Meirion-Griffith, M. Spenko
A critical component of remote terrestrial and planetary exploration is understanding how terrain properties affect rover mobility. Bekker theory has long been used successfully in this regard for the analysis of large vehicles. In recent years, the semi-empirical formulae contained within Bekker theory have also been applied to small UGVs. Bekker himself noted, however, that his formulae offer significantly less accurate predictions for vehicles with wheel diameters and normal loading lower than 50 cm and 45 N, respectively. This has been shown to lead to errors in the prediction of tractive performance. The results of this paper show that Bekker theory yields under-estimates of small wheel sinkage and resistances. The consequences of such errors are severe, as they could potentially lead to unexpected rover immobilization. With increasing numbers of small UGVs being used in planetary, research and military roles, it is crucial to investigate the source of these errors. This paper details an empirical approach to characterizing small vehicle wheel sinkage and its impact on vehicle-terrain models.
{"title":"An empirical study of the terramechanics of small unmanned ground vehicles","authors":"G. Meirion-Griffith, M. Spenko","doi":"10.1109/AERO.2010.5446993","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446993","url":null,"abstract":"A critical component of remote terrestrial and planetary exploration is understanding how terrain properties affect rover mobility. Bekker theory has long been used successfully in this regard for the analysis of large vehicles. In recent years, the semi-empirical formulae contained within Bekker theory have also been applied to small UGVs. Bekker himself noted, however, that his formulae offer significantly less accurate predictions for vehicles with wheel diameters and normal loading lower than 50 cm and 45 N, respectively. This has been shown to lead to errors in the prediction of tractive performance. The results of this paper show that Bekker theory yields under-estimates of small wheel sinkage and resistances. The consequences of such errors are severe, as they could potentially lead to unexpected rover immobilization. With increasing numbers of small UGVs being used in planetary, research and military roles, it is crucial to investigate the source of these errors. This paper details an empirical approach to characterizing small vehicle wheel sinkage and its impact on vehicle-terrain models.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-04-15","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134117522","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446924
G. Mayhew
Normal design practice is to decouple the design of applications using a network from the design of the network itself. Designers optimize network performance by only focusing on network transport layer mechanisms for robustness (connectivity), efficiency (throughput), & speed of service (latency). Applications offer loads to the network and rely on the QoS function in the network to prioritize the traffic flows. By contrast, network centric operations focus on application layer features like situation awareness and synchronization to enhance force effectiveness. Therefore, in contrast to enterprise networks in which QoS processes messages based on fixed priorities by data type, in mission orientated MANET, QoS must be a cooperative function between application and network resource management that uses dynamic priority allocation derived from task priorities established by commanders within echelon hierarchies1,2.
{"title":"Dynamic message prioritization in tactical wireless MANET","authors":"G. Mayhew","doi":"10.1109/AERO.2010.5446924","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446924","url":null,"abstract":"Normal design practice is to decouple the design of applications using a network from the design of the network itself. Designers optimize network performance by only focusing on network transport layer mechanisms for robustness (connectivity), efficiency (throughput), & speed of service (latency). Applications offer loads to the network and rely on the QoS function in the network to prioritize the traffic flows. By contrast, network centric operations focus on application layer features like situation awareness and synchronization to enhance force effectiveness. Therefore, in contrast to enterprise networks in which QoS processes messages based on fixed priorities by data type, in mission orientated MANET, QoS must be a cooperative function between application and network resource management that uses dynamic priority allocation derived from task priorities established by commanders within echelon hierarchies1,2.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"64 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114963575","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446777
T. E. Strand, J. Ennis
Significant research was performed to understand the requirements and potential risks of operating a tiltrotor in the austere environment. 1 2 This test specifically addressed performing Short Takeoff and Landing (STOL) operations at up to 70 knots on semi and unprepared runways. A multi-phase test was planned for over a year and a half. Despite detailed preparation and multiple build up conditions, the nose gear collapsed in an unidentified sink hole at the final test location. Post analysis data showed that the nose gear failed as predicted, with loads exceeding existing load limits, however the soil bearing capacity did not meet test requirements. This collapse brought many safety “lessons learned”. This paper addresses the methodology, test results, and lessons learned of testing in unfamiliar and unpredictable conditions.
{"title":"V-22 osprey unprepared surface short takeoff and landing evaluation","authors":"T. E. Strand, J. Ennis","doi":"10.1109/AERO.2010.5446777","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446777","url":null,"abstract":"Significant research was performed to understand the requirements and potential risks of operating a tiltrotor in the austere environment. 1 2 This test specifically addressed performing Short Takeoff and Landing (STOL) operations at up to 70 knots on semi and unprepared runways. A multi-phase test was planned for over a year and a half. Despite detailed preparation and multiple build up conditions, the nose gear collapsed in an unidentified sink hole at the final test location. Post analysis data showed that the nose gear failed as predicted, with loads exceeding existing load limits, however the soil bearing capacity did not meet test requirements. This collapse brought many safety “lessons learned”. This paper addresses the methodology, test results, and lessons learned of testing in unfamiliar and unpredictable conditions.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114967052","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446713
Major Daniel Burtz
Future space telescopes will contain lightweight, flexible, segmented mirrors. Traditional control approaches for mirror alignment and shape control may be inadequate due to flexibilities and low natural frequencies. Using adaptive optics for space telescopes presents a possible solution. This research proposes H∞ robust control techniques for these types of systems. An H∞ controller is synthesized for a complex analytical model. This was accomplished with a new technique for model reduction using Zernike polynomials. The H∞ design process used was validated on a simpler adaptive optics testbed. The experimental verification also showed that the robust control techniques outperformed the classical control techniques in the presence of disturbances. The results are a Zernike polynomial method for model reduction, robust controller synthesis for a complex adaptive optics analytical model, and experimental verification on an AO testbed. Although the robust control design is more complex, it provides improved performance in the presence of uncertainty in the disturbances and modeling.12
{"title":"Robust control techniques for adaptive optic space telescopes","authors":"Major Daniel Burtz","doi":"10.1109/AERO.2010.5446713","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446713","url":null,"abstract":"Future space telescopes will contain lightweight, flexible, segmented mirrors. Traditional control approaches for mirror alignment and shape control may be inadequate due to flexibilities and low natural frequencies. Using adaptive optics for space telescopes presents a possible solution. This research proposes H∞ robust control techniques for these types of systems. An H∞ controller is synthesized for a complex analytical model. This was accomplished with a new technique for model reduction using Zernike polynomials. The H∞ design process used was validated on a simpler adaptive optics testbed. The experimental verification also showed that the robust control techniques outperformed the classical control techniques in the presence of disturbances. The results are a Zernike polynomial method for model reduction, robust controller synthesis for a complex adaptive optics analytical model, and experimental verification on an AO testbed. Although the robust control design is more complex, it provides improved performance in the presence of uncertainty in the disturbances and modeling.12","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"41 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121819324","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446780
S. Luongo, F. Corraro, U. Ciniglio, V. Di Vito, A. Moccia
This paper presents an innovative 3D analytical algorithm for the resolution of the pair-wise non-cooperative collision avoidance problem between aircrafts. The proposed algorithm addresses the above described problem by using an innovative approach, based on the consideration of a cylindrical safety bubble, and it is able to obtain an optimal three-dimensional analytical solution for this problem. This novel approach allows different minimum separations on the vertical and horizontal planes with respect to the nominal trajectory to be achieved, so minimizing the impact of the collision avoidance maneuver on surrounding traffic. Moreover, the algorithm has the very interesting feature that it does not require the solution of any non deterministic and/or iterative problem, resulting suitable for real-time applications. This is due to the capability of the algorithm to find a closed form solution for the kinematic optimization problem here considered. The solution of the collision avoidance problem requires the simultaneous change of all control variables (speed module, track and slope angles), aiming to assure the required safety level and, at the same time, to minimize aircraft deviation from the nominal trajectory. This system is mainly developed for unmanned aircraft vehicles, where high levels of autonomy (i.e. the avoidance maneuver is autonomously executed by a standard autopilot) are required, but it can also be used, as aid to pilots, in manned commercial aircrafts. The effectiveness of the algorithm is evaluated by means of numerical simulations, where suitable conflict scenarios, taking into account aircraft dynamics and on-board sensors errors and limitations, are considered. Scenarios where both aircrafts are equipped with the proposed collision avoidance algorithm or where both aircrafts are subjected to Visual Flight Rules are also considered. 1 2
{"title":"A novel 3D analytical algorithm for autonomous collision avoidance considering cylindrical safety bubble","authors":"S. Luongo, F. Corraro, U. Ciniglio, V. Di Vito, A. Moccia","doi":"10.1109/AERO.2010.5446780","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446780","url":null,"abstract":"This paper presents an innovative 3D analytical algorithm for the resolution of the pair-wise non-cooperative collision avoidance problem between aircrafts. The proposed algorithm addresses the above described problem by using an innovative approach, based on the consideration of a cylindrical safety bubble, and it is able to obtain an optimal three-dimensional analytical solution for this problem. This novel approach allows different minimum separations on the vertical and horizontal planes with respect to the nominal trajectory to be achieved, so minimizing the impact of the collision avoidance maneuver on surrounding traffic. Moreover, the algorithm has the very interesting feature that it does not require the solution of any non deterministic and/or iterative problem, resulting suitable for real-time applications. This is due to the capability of the algorithm to find a closed form solution for the kinematic optimization problem here considered. The solution of the collision avoidance problem requires the simultaneous change of all control variables (speed module, track and slope angles), aiming to assure the required safety level and, at the same time, to minimize aircraft deviation from the nominal trajectory. This system is mainly developed for unmanned aircraft vehicles, where high levels of autonomy (i.e. the avoidance maneuver is autonomously executed by a standard autopilot) are required, but it can also be used, as aid to pilots, in manned commercial aircrafts. The effectiveness of the algorithm is evaluated by means of numerical simulations, where suitable conflict scenarios, taking into account aircraft dynamics and on-board sensors errors and limitations, are considered. Scenarios where both aircrafts are equipped with the proposed collision avoidance algorithm or where both aircrafts are subjected to Visual Flight Rules are also considered. 1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124894695","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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