Pub Date : 2004-10-24DOI: 10.1109/DASC.2004.1390839
A. Goossens
In previous research into UAV operator stations, the concept of integrated data presentation has been used to reduce the effort required to obtain and maintain level 2 situation awareness. With the resulting prototype, obtaining adequate level 3 situation awareness can still generate considerable workload. When using real-time extrapolation/ prediction to provide information regarding the ability to meet future time constraints, maintain separation and prevent threat incursions as a function of changes to the plan, the operator is relieved of many of the extrapolation tasks, and level 3 situation awareness can be achieved at a lower workload. This provides the possibility for more effective decision making in time-critical situations. To support the requirements definition of a future UAV operator station, the existing research prototype has been extended with functionality specifically intended to support level 3 situation awareness. This paper discusses the design rationale behind the functionality in more detail, provides an overview of the rating criteria and the rating method and presents the results from an evaluation by 31 subject matter experts.
{"title":"Development and evaluation of level 3 situation awareness support functions for a UAV operator station","authors":"A. Goossens","doi":"10.1109/DASC.2004.1390839","DOIUrl":"https://doi.org/10.1109/DASC.2004.1390839","url":null,"abstract":"In previous research into UAV operator stations, the concept of integrated data presentation has been used to reduce the effort required to obtain and maintain level 2 situation awareness. With the resulting prototype, obtaining adequate level 3 situation awareness can still generate considerable workload. When using real-time extrapolation/ prediction to provide information regarding the ability to meet future time constraints, maintain separation and prevent threat incursions as a function of changes to the plan, the operator is relieved of many of the extrapolation tasks, and level 3 situation awareness can be achieved at a lower workload. This provides the possibility for more effective decision making in time-critical situations. To support the requirements definition of a future UAV operator station, the existing research prototype has been extended with functionality specifically intended to support level 3 situation awareness. This paper discusses the design rationale behind the functionality in more detail, provides an overview of the rating criteria and the rating method and presents the results from an evaluation by 31 subject matter experts.","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125244566","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 : 2004-10-24DOI: 10.1109/DASC.2004.1391290
T. Rand, M. S. Eby
Airborne conflict management (ACM) is part of an air traffic safety and separation management concept wherein a degree of responsibility - sometimes total responsibility - for determining and executing maneuvers necessary to avoid conflicts with other traffic is assigned to the flight crew. The concept offers the promise of user-selected routing, improved safety, shorter flights, lowered flight costs, more efficient airspace utilization, and increased airspace capacity. The central and most crucial elements of ACM are the aircraft-based systems that provide pilots with the information needed to autonomously and safely maneuver within the airspace. The necessary information is awareness of a) existing conflicts, b) maneuvers that would create conflicts and c) maneuvers that can resolve conflicts. The ACM application is enabled by the automatic dependent surveillance-broadcast (ADS-B) reports of position, velocity, and other information. In Europe and in the U.S., government and private organizations have worked to advance the understanding, acceptance, and utilization of ACM technologies and practices. RTCA has published an ACM concept of operations document (RTCA Special Committee 186, 2003) and application description (RTCA Special Committee 186, 2000), Rockwell Collins has developed and tested the algorithms necessary to implement an ACM system. The three major components of the system are: conflict detection (CD) - algorithm that uses measures of a projected conflict's "severity", "stability", and "temporal proximity" in determining when to issue a CD alert; conflict prevention (CP) - mechanism that utilizes mathematical and numerical "conflict probes" to determine ground speeds, headings, altitudes, rates of climb, and bank angles that would conflict with the trajectories of other aircraft and conflict resolution (CR) - algorithms that use "repulsive force field"-like mechanisms to calculate conflict resolution guidance. This paper discusses each of these components, as developed and implemented by Rockwell Collins, in substantial detail.
机载冲突管理(ACM)是空中交通安全和分离管理概念的一部分，其中一定程度的责任-有时是全部责任-确定和执行必要的机动以避免与其他交通冲突分配给机组人员。该概念提供了用户选择路线、提高安全性、缩短飞行时间、降低飞行成本、提高空域利用率和增加空域容量的承诺。ACM的核心和最关键的要素是基于飞机的系统，它为飞行员提供在空域内自主和安全机动所需的信息。必要的信息是了解a)存在的冲突，b)可能产生冲突的操作，c)可以解决冲突的操作。ACM应用是通过ADS-B (automatic dependent surveillance-broadcast)广播报告位置、速度等信息来实现的。在欧洲和美国，政府和私人组织一直致力于促进对ACM技术和实践的理解、接受和利用。RTCA已经发布了ACM操作概念文档(RTCA Special Committee 186, 2003)和应用描述(RTCA Special Committee 186, 2000)，罗克韦尔柯林斯公司已经开发并测试了实现ACM系统所需的算法。该系统的三个主要组成部分是:冲突检测(CD)——一种算法，它使用预测冲突的“严重性”、“稳定性”和“时间接近性”来确定何时发出CD警报;冲突预防(CP)——利用数学和数值“冲突探测器”来确定地面速度、航向、高度、爬升率和与其他飞机轨迹相冲突的倾斜角度的机制;冲突解决(CR)——使用类似“斥力场”机制来计算冲突解决制导的算法。本文详细讨论了由罗克韦尔柯林斯公司开发和实现的每一个组件。
{"title":"Algorithms for airborne conflict detection, prevention, and resolution","authors":"T. Rand, M. S. Eby","doi":"10.1109/DASC.2004.1391290","DOIUrl":"https://doi.org/10.1109/DASC.2004.1391290","url":null,"abstract":"Airborne conflict management (ACM) is part of an air traffic safety and separation management concept wherein a degree of responsibility - sometimes total responsibility - for determining and executing maneuvers necessary to avoid conflicts with other traffic is assigned to the flight crew. The concept offers the promise of user-selected routing, improved safety, shorter flights, lowered flight costs, more efficient airspace utilization, and increased airspace capacity. The central and most crucial elements of ACM are the aircraft-based systems that provide pilots with the information needed to autonomously and safely maneuver within the airspace. The necessary information is awareness of a) existing conflicts, b) maneuvers that would create conflicts and c) maneuvers that can resolve conflicts. The ACM application is enabled by the automatic dependent surveillance-broadcast (ADS-B) reports of position, velocity, and other information. In Europe and in the U.S., government and private organizations have worked to advance the understanding, acceptance, and utilization of ACM technologies and practices. RTCA has published an ACM concept of operations document (RTCA Special Committee 186, 2003) and application description (RTCA Special Committee 186, 2000), Rockwell Collins has developed and tested the algorithms necessary to implement an ACM system. The three major components of the system are: conflict detection (CD) - algorithm that uses measures of a projected conflict's \"severity\", \"stability\", and \"temporal proximity\" in determining when to issue a CD alert; conflict prevention (CP) - mechanism that utilizes mathematical and numerical \"conflict probes\" to determine ground speeds, headings, altitudes, rates of climb, and bank angles that would conflict with the trajectories of other aircraft and conflict resolution (CR) - algorithms that use \"repulsive force field\"-like mechanisms to calculate conflict resolution guidance. This paper discusses each of these components, as developed and implemented by Rockwell Collins, in substantial detail.","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125414907","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 : 2004-10-24DOI: 10.1109/DASC.2004.1390783
S. Fischmeister, G. Menkhaus
Recent developments in embedded control systems promote the timed computation model following the principles of logical execution time (LET). Resulting control applications are time deterministic, value deterministic, and their properties may be subject to formal verification against a mathematical model of the control design. However, the timed computation model introduces inefficiencies to computation cycles. As the LET of a real-time control task requires being greater than its worst-case execution time and computed values are always propagated at the end of the LET, actuator updates are unnecessarily delayed. This makes the control cycle less responsive. In this paper, we present an approach that allows the definition of task sequences for a timed computation model implemented by the timing definition language (TDL). Task sequences help minimizing timing delays between sensor readings and actuator updates (e.g., in estimator-based control systems), managing startup and shutdown phases of control systems, and providing mechanisms for error-detection in fault-tolerant systems.
{"title":"Task sequencing for optimizing the computation cycle in a timed computation model","authors":"S. Fischmeister, G. Menkhaus","doi":"10.1109/DASC.2004.1390783","DOIUrl":"https://doi.org/10.1109/DASC.2004.1390783","url":null,"abstract":"Recent developments in embedded control systems promote the timed computation model following the principles of logical execution time (LET). Resulting control applications are time deterministic, value deterministic, and their properties may be subject to formal verification against a mathematical model of the control design. However, the timed computation model introduces inefficiencies to computation cycles. As the LET of a real-time control task requires being greater than its worst-case execution time and computed values are always propagated at the end of the LET, actuator updates are unnecessarily delayed. This makes the control cycle less responsive. In this paper, we present an approach that allows the definition of task sequences for a timed computation model implemented by the timing definition language (TDL). Task sequences help minimizing timing delays between sensor readings and actuator updates (e.g., in estimator-based control systems), managing startup and shutdown phases of control systems, and providing mechanisms for error-detection in fault-tolerant systems.","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130250867","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 : 2004-10-24DOI: 10.1109/DASC.2004.1390758
M. Luo
We propose a multivariate trending for aircraft fault detection. Multivariate trending generate fault indicators using output sensor data, is one of black-box approach. We use convex polygon for the computation of a rough shape or extent of the normal data set. Quickhull algorithm is used for the hull finding because it is simpler and uses less memory. It is assumed that the normal data points are in general position, so that their convex hull is a simple complex. We represent a d-dimensional convex hull by its vertices and (d-1)-dimensional faces. From multivariate trend analysis, if we find the measurements have the tendency to leave the convex polygon, this measurement can be labeled as a fault. If a new point is above all hyperplane of the convex hull, it is outside the convex polygon.
{"title":"Multivariate fault detection with convex hull","authors":"M. Luo","doi":"10.1109/DASC.2004.1390758","DOIUrl":"https://doi.org/10.1109/DASC.2004.1390758","url":null,"abstract":"We propose a multivariate trending for aircraft fault detection. Multivariate trending generate fault indicators using output sensor data, is one of black-box approach. We use convex polygon for the computation of a rough shape or extent of the normal data set. Quickhull algorithm is used for the hull finding because it is simpler and uses less memory. It is assumed that the normal data points are in general position, so that their convex hull is a simple complex. We represent a d-dimensional convex hull by its vertices and (d-1)-dimensional faces. From multivariate trend analysis, if we find the measurements have the tendency to leave the convex polygon, this measurement can be labeled as a fault. If a new point is above all hyperplane of the convex hull, it is outside the convex polygon.","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"5 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129041749","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 : 2004-10-24DOI: 10.1109/DASC.2004.1390842
Youngchul Bae
In this paper, we propose a method to target searching method that has unstable limit cycles in a chaos trajectory surface. We assume all targets in the chaos trajectory surface have a Van der Pol equation with a stable limit cycle. When a chaos robot meets the target in the Lorenz equation, Hamilton and hyper-chaos equation trajectory, the target absorbs the robot. We also show computer simulation results of Lorenz equation, Hamilton and hyper-chaos equation trajectories with one or more Van der Pol as a target. We proposed and verified the results of the method to make the embedding chaotic mobile robot to searching target with the chaotic trajectory in any plane. It searched the target, when it meets or closes to the target.
{"title":"Target searching method in the chaotic mobile robot","authors":"Youngchul Bae","doi":"10.1109/DASC.2004.1390842","DOIUrl":"https://doi.org/10.1109/DASC.2004.1390842","url":null,"abstract":"In this paper, we propose a method to target searching method that has unstable limit cycles in a chaos trajectory surface. We assume all targets in the chaos trajectory surface have a Van der Pol equation with a stable limit cycle. When a chaos robot meets the target in the Lorenz equation, Hamilton and hyper-chaos equation trajectory, the target absorbs the robot. We also show computer simulation results of Lorenz equation, Hamilton and hyper-chaos equation trajectories with one or more Van der Pol as a target. We proposed and verified the results of the method to make the embedding chaotic mobile robot to searching target with the chaotic trajectory in any plane. It searched the target, when it meets or closes to the target.","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129421527","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 : 2004-10-24DOI: 10.1109/DASC.2004.1391310
D. Allerton, A.J. Clare
A millimetric radar imaging sensor can project a forward-looking view in a head-up display (HUD) to provide enhanced vision in the final stages of an approach, particularly in conditions of very low visibility. Although this increases situational awareness for the flight crew, the image quality is poor and there is no direct measure of system integrity. This paper describes a synthetic vision system using real-time image feature extraction to detect the runway in the image. This information is combined with knowledge of the aircraft position and attitude to provide flight guidance cues and to monitor the aircraft flight path. In the initial phase of the approach, GPS measurements are used to align the inertial reference system. During the final stages of an approach, inertial reference measurements are combined with imaging data to locate the vertices of the runway. Sensor fusion methods are used to provide flight guidance cues in the HUD and to determine system integrity measurements of the imaging system. A synthetic vision system overlays the computed runway position on the cluttered radar image and displays essential flight data. The paper outlines a radar model of the sensor, which runs on a PC-based visual system. This model has been used to provide a realistic real-time radar image during development of the tracking algorithms. The inertial reference system and the tracking system are also modeled and combined in an extended Kalman filter to provide flight guidance and to give timely warning of system failures to the flight crew. The paper describes the sensor fusion method developed for failure detection and provides examples of low visibility approaches flown in a flight simulator, to demonstrate the effectiveness of these techniques.
{"title":"Sensor fusion methods for synthetic vision systems","authors":"D. Allerton, A.J. Clare","doi":"10.1109/DASC.2004.1391310","DOIUrl":"https://doi.org/10.1109/DASC.2004.1391310","url":null,"abstract":"A millimetric radar imaging sensor can project a forward-looking view in a head-up display (HUD) to provide enhanced vision in the final stages of an approach, particularly in conditions of very low visibility. Although this increases situational awareness for the flight crew, the image quality is poor and there is no direct measure of system integrity. This paper describes a synthetic vision system using real-time image feature extraction to detect the runway in the image. This information is combined with knowledge of the aircraft position and attitude to provide flight guidance cues and to monitor the aircraft flight path. In the initial phase of the approach, GPS measurements are used to align the inertial reference system. During the final stages of an approach, inertial reference measurements are combined with imaging data to locate the vertices of the runway. Sensor fusion methods are used to provide flight guidance cues in the HUD and to determine system integrity measurements of the imaging system. A synthetic vision system overlays the computed runway position on the cluttered radar image and displays essential flight data. The paper outlines a radar model of the sensor, which runs on a PC-based visual system. This model has been used to provide a realistic real-time radar image during development of the tracking algorithms. The inertial reference system and the tracking system are also modeled and combined in an extended Kalman filter to provide flight guidance and to give timely warning of system failures to the flight crew. The paper describes the sensor fusion method developed for failure detection and provides examples of low visibility approaches flown in a flight simulator, to demonstrate the effectiveness of these techniques.","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129722145","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 : 2004-10-24DOI: 10.1109/DASC.2004.1390809
T. Smith, C. Uri
The benefits of modified condition/decision coverage (MC/DC) in development of safety critical software are well recognized. Use of commercial-off-the-shelf (COTS) software is encouraged, and vendors of COTS software have expressed interest in developing a standard interface to assist in carrying out functions needed for the safety critical domain. A useful analogy can be drawn between a complex integrated circuit, with millions more storage locations and logic gates inside than pins on its interface, and an executable version of software, with many more variables and logical statements inside than are directly visible on its interface description. IEEE has developed an interface standard for testing package integrated circuits (that is, the tests are conducted through the interface pins), called boundary-scan. An analogous interface specification for software modules has been proposed in a COTS software forum, initially by Therese Smith and continued by Dr. Gregory Eakman of Pathfinder Solutions, who has completed scholarly work in this area. The FAA is advancing the technology used to support interface metadata. Net-centric architecture increases both the visibility of the metadata repository and the level of automation used to interact with the metadata. Given that the software vendors are pursuing a strategy for testability, there is interest at FAA in whether the testability is useful, and if so, in expanding the metadata to be maintained in a proposed "FAA interface management system" to include interface data used for testing.
{"title":"IEEE scan-like interface for air traffic control software testing","authors":"T. Smith, C. Uri","doi":"10.1109/DASC.2004.1390809","DOIUrl":"https://doi.org/10.1109/DASC.2004.1390809","url":null,"abstract":"The benefits of modified condition/decision coverage (MC/DC) in development of safety critical software are well recognized. Use of commercial-off-the-shelf (COTS) software is encouraged, and vendors of COTS software have expressed interest in developing a standard interface to assist in carrying out functions needed for the safety critical domain. A useful analogy can be drawn between a complex integrated circuit, with millions more storage locations and logic gates inside than pins on its interface, and an executable version of software, with many more variables and logical statements inside than are directly visible on its interface description. IEEE has developed an interface standard for testing package integrated circuits (that is, the tests are conducted through the interface pins), called boundary-scan. An analogous interface specification for software modules has been proposed in a COTS software forum, initially by Therese Smith and continued by Dr. Gregory Eakman of Pathfinder Solutions, who has completed scholarly work in this area. The FAA is advancing the technology used to support interface metadata. Net-centric architecture increases both the visibility of the metadata repository and the level of automation used to interact with the metadata. Given that the software vendors are pursuing a strategy for testability, there is interest at FAA in whether the testability is useful, and if so, in expanding the metadata to be maintained in a proposed \"FAA interface management system\" to include interface data used for testing.","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"37 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126550415","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 : 2004-10-24DOI: 10.1109/DASC.2004.1390756
Ravi Mukkamala, R. Ramesh, N. Agarwal, M. Bandagadde, S. Myadam
In most engineering disciplines, systems are designed by reusing existing components that have been used in other systems. It is certainly worthwhile to make use of existing architectures available as a whole or in part in the large space of designs instead of rebuilding the whole architecture. In collaboration with NASA Langley Research Center, we have been developing methods to reuse existing architectures for health and usage monitoring (HUMS) of aerospace structures. We discuss some of the key reuse techniques, which can be used to reuse existing available architectures in the design space. The primary contribution of This work is an iterative process model for employing reuse technique in a complex engineering system.
{"title":"Reusability: a technique for the design of HUMS architectures","authors":"Ravi Mukkamala, R. Ramesh, N. Agarwal, M. Bandagadde, S. Myadam","doi":"10.1109/DASC.2004.1390756","DOIUrl":"https://doi.org/10.1109/DASC.2004.1390756","url":null,"abstract":"In most engineering disciplines, systems are designed by reusing existing components that have been used in other systems. It is certainly worthwhile to make use of existing architectures available as a whole or in part in the large space of designs instead of rebuilding the whole architecture. In collaboration with NASA Langley Research Center, we have been developing methods to reuse existing architectures for health and usage monitoring (HUMS) of aerospace structures. We discuss some of the key reuse techniques, which can be used to reuse existing available architectures in the design space. The primary contribution of This work is an iterative process model for employing reuse technique in a complex engineering system.","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"201 ","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120970698","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 : 2004-10-24DOI: 10.1109/DASC.2004.1390737
Wen-Chi Lu, F. Mora-Camino, K. Achaibou
With the sustained increase of air traffic, the demand for new maneuvering capabilities of transport aircrafts is getting more important in order to tackle traffic saturated conditions. In this communication, a new guidance control structure is proposed to perform trajectory tracking through smooth manoeuvers. The design approach is based first on a differential flatness property of aircraft guidance dynamics which is displayed in This work and then on the use of neural networks to invert the guidance dynamics in order to generate directives to the autopilot. To compensate the effect of modeling errors and of other disturbances, an adaptive control approach is adopted to perform the maneuvers.
{"title":"A new flight guidance approach based on differential flatness","authors":"Wen-Chi Lu, F. Mora-Camino, K. Achaibou","doi":"10.1109/DASC.2004.1390737","DOIUrl":"https://doi.org/10.1109/DASC.2004.1390737","url":null,"abstract":"With the sustained increase of air traffic, the demand for new maneuvering capabilities of transport aircrafts is getting more important in order to tackle traffic saturated conditions. In this communication, a new guidance control structure is proposed to perform trajectory tracking through smooth manoeuvers. The design approach is based first on a differential flatness property of aircraft guidance dynamics which is displayed in This work and then on the use of neural networks to invert the guidance dynamics in order to generate directives to the autopilot. To compensate the effect of modeling errors and of other disturbances, an adaptive control approach is adopted to perform the maneuvers.","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"49 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121182856","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 : 2004-10-24DOI: 10.1109/DASC.2004.1390752
W. Larsen
{"title":"Aircraft health monitoring for maintenance management - [Not available for publication]","authors":"W. Larsen","doi":"10.1109/DASC.2004.1390752","DOIUrl":"https://doi.org/10.1109/DASC.2004.1390752","url":null,"abstract":"","PeriodicalId":422463,"journal":{"name":"The 23rd Digital Avionics Systems Conference (IEEE Cat. No.04CH37576)","volume":"15 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2004-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124487699","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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