Pub Date : 1996-10-27DOI: 10.1109/DASC.1996.559144
Patrick Feighery, Timothy Hanson, Thomas Lehman, Alexander Mondrus, Dallas Scott, Theodore Signore, Ralph Smith, George Uhl
The Aeronautical Telecommunication Network (ATN) is being defined within the International Civil Aviation Organization (ICAO) as a digital data communications network for the aeronautical community. ATN routers will link the diverse networks and technologies within the aeronautical environment into an internetwork. The routers provide intelligence to select the best communications path for each pair of users. Mobile routing is the key element that makes ATN unique from most networks. Mobile routing allows a ground system to communicate to an aircraft, without interruption, as it flies in and out of coverage of various air/ground subnetworks. The Center for Advanced Aviation Systems Development (CAASD) developed the Aeronautical Communication Engineering Testbed (ACET) to evaluate the ATN for the US Federal Aviation Administration.
{"title":"The Aeronautical Telecommunications Network (ATN) testbed","authors":"Patrick Feighery, Timothy Hanson, Thomas Lehman, Alexander Mondrus, Dallas Scott, Theodore Signore, Ralph Smith, George Uhl","doi":"10.1109/DASC.1996.559144","DOIUrl":"https://doi.org/10.1109/DASC.1996.559144","url":null,"abstract":"The Aeronautical Telecommunication Network (ATN) is being defined within the International Civil Aviation Organization (ICAO) as a digital data communications network for the aeronautical community. ATN routers will link the diverse networks and technologies within the aeronautical environment into an internetwork. The routers provide intelligence to select the best communications path for each pair of users. Mobile routing is the key element that makes ATN unique from most networks. Mobile routing allows a ground system to communicate to an aircraft, without interruption, as it flies in and out of coverage of various air/ground subnetworks. The Center for Advanced Aviation Systems Development (CAASD) developed the Aeronautical Communication Engineering Testbed (ACET) to evaluate the ATN for the US Federal Aviation Administration.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133548159","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 : 1996-10-27DOI: 10.1109/DASC.1996.559199
K. Dudley
In support of NASA's fly-by-light/power-by-wire (FBL/PBW) program, a series of flight tests were conducted by NASA Langley Research Center in February, 1995. The NASA Boeing 757 was flown past known RF transmitters to measure both external and internal radiated fields. The aircraft was instrumented with strategically located sensors for acquiring data on shielding effectiveness and internal coupling. The data are intended to support computational and statistical modeling codes used to predict internal field levels of an electromagnetic environment (EME) on an aircraft. The hardware, instrumentation, and sensors, forged the basis of the data acquisition system. The configuration of the hardware provided for accurate measurements of the electromagnetic environment during flight. The system operated at several specified frequencies and modulation schemes. Internal and external EME data were recorded by the acquisition equipment and additional flight parameters were acquired from the aircraft's flight data bus. This paper describes the flight instrumentation system on board the aircraft and concentrates on the hardware components employed during the EME flight test. Measurement instrumentation, sensors, and aircraft configurations, are illustrated and discussed. Particular attention is given to design, operation, and use of the hardware. The actualized flight test scenarios are discussed to give broader scope of the experiment, design requirements and philosophy are examined to highlight the quality and the limitations of the system, and flight data is presented as a representative sample of experiment results.
{"title":"A description of the hardware element of the NASA EME flight tests","authors":"K. Dudley","doi":"10.1109/DASC.1996.559199","DOIUrl":"https://doi.org/10.1109/DASC.1996.559199","url":null,"abstract":"In support of NASA's fly-by-light/power-by-wire (FBL/PBW) program, a series of flight tests were conducted by NASA Langley Research Center in February, 1995. The NASA Boeing 757 was flown past known RF transmitters to measure both external and internal radiated fields. The aircraft was instrumented with strategically located sensors for acquiring data on shielding effectiveness and internal coupling. The data are intended to support computational and statistical modeling codes used to predict internal field levels of an electromagnetic environment (EME) on an aircraft. The hardware, instrumentation, and sensors, forged the basis of the data acquisition system. The configuration of the hardware provided for accurate measurements of the electromagnetic environment during flight. The system operated at several specified frequencies and modulation schemes. Internal and external EME data were recorded by the acquisition equipment and additional flight parameters were acquired from the aircraft's flight data bus. This paper describes the flight instrumentation system on board the aircraft and concentrates on the hardware components employed during the EME flight test. Measurement instrumentation, sensors, and aircraft configurations, are illustrated and discussed. Particular attention is given to design, operation, and use of the hardware. The actualized flight test scenarios are discussed to give broader scope of the experiment, design requirements and philosophy are examined to highlight the quality and the limitations of the system, and flight data is presented as a representative sample of experiment results.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116651019","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 : 1996-10-27DOI: 10.1109/DASC.1996.559143
N. Gustavsson
At its tenth Air Navigation Conference (1991), the ICAO endorsed the so-called Communication, Navigation, Surveillance/Air Traffic Management concept, CNS/ATM. This concept envisages the use of data link communications, satellite navigation and automatic dependent surveillance (ADS). The Swedish Civil Aviation Administration (SCAA) has been involved in the technical and operational development of an integrated CNS/ATM since 1990. The system concept is based on the use of GNSS and a time synchronised VHF data link (VDL Mode 4/STDMA). The system is intended to support all elements of CNS. This paper discusses the requirements for an integrated CNS system. It also gives an overview of the VDL mode 4/STDMA system as well as description of on-going trials and standardisation effort within ICAO.
{"title":"VDL Mode 4/STDMA-a CNS data link","authors":"N. Gustavsson","doi":"10.1109/DASC.1996.559143","DOIUrl":"https://doi.org/10.1109/DASC.1996.559143","url":null,"abstract":"At its tenth Air Navigation Conference (1991), the ICAO endorsed the so-called Communication, Navigation, Surveillance/Air Traffic Management concept, CNS/ATM. This concept envisages the use of data link communications, satellite navigation and automatic dependent surveillance (ADS). The Swedish Civil Aviation Administration (SCAA) has been involved in the technical and operational development of an integrated CNS/ATM since 1990. The system concept is based on the use of GNSS and a time synchronised VHF data link (VDL Mode 4/STDMA). The system is intended to support all elements of CNS. This paper discusses the requirements for an integrated CNS system. It also gives an overview of the VDL mode 4/STDMA system as well as description of on-going trials and standardisation effort within ICAO.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121980741","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 : 1996-10-27DOI: 10.1109/DASC.1996.559201
M. Sievers
Dependability is defined as the trustworthiness of a system such that: reliance may be justifiably placed on the service it delivers and; the system has the ability to provide required service whenever that service is needed. The service delivered by a system is its behavior as perceived by its user(s); a user is another system (human or physical) that interacts with the dependable system. This paper will provide a discussion of fault-tolerance design and validation concepts for achieving high levels of dependability. Although fault-tolerance is most effective when designed into a system from the beginning, this paper will also consider approaches that can be effective in improving the dependability of systems developed from commercial off-the-shelf products.
{"title":"Fault-tolerance: a methodology for implementing highly dependable systems","authors":"M. Sievers","doi":"10.1109/DASC.1996.559201","DOIUrl":"https://doi.org/10.1109/DASC.1996.559201","url":null,"abstract":"Dependability is defined as the trustworthiness of a system such that: reliance may be justifiably placed on the service it delivers and; the system has the ability to provide required service whenever that service is needed. The service delivered by a system is its behavior as perceived by its user(s); a user is another system (human or physical) that interacts with the dependable system. This paper will provide a discussion of fault-tolerance design and validation concepts for achieving high levels of dependability. Although fault-tolerance is most effective when designed into a system from the beginning, this paper will also consider approaches that can be effective in improving the dependability of systems developed from commercial off-the-shelf products.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128834444","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 : 1996-10-27DOI: 10.1109/DASC.1996.559176
G. Freyer, M. Hatfield, M. Slocum
In order to design, assess, and certify the performance of avionics systems, among other parameters, one must be able to characterize the radiative environment in which the system will operate. The intrinsic variability of the problem of characterizing the electromagnetic environment in aircraft cavities suggests the desirability of an approach which could statistically bound the environment in terms of a small number of quantifiable parameters. Within the past few years both theory and experimental data have become available which suggests that for some aspects of the problem, a statistical bounding technique is feasible. The technique applies to complex, multi-moded cavities. This paper reviews pertinent aspects of the statistical theory and its predictions concerning aircraft cavity environments. The paper presents cavity electromagnetic environment data from two large transport and two commuter aircraft. Data from both external and internal emitters are presented.
{"title":"Characterization of the electromagnetic environment in aircraft cavities excited by internal and external sources","authors":"G. Freyer, M. Hatfield, M. Slocum","doi":"10.1109/DASC.1996.559176","DOIUrl":"https://doi.org/10.1109/DASC.1996.559176","url":null,"abstract":"In order to design, assess, and certify the performance of avionics systems, among other parameters, one must be able to characterize the radiative environment in which the system will operate. The intrinsic variability of the problem of characterizing the electromagnetic environment in aircraft cavities suggests the desirability of an approach which could statistically bound the environment in terms of a small number of quantifiable parameters. Within the past few years both theory and experimental data have become available which suggests that for some aspects of the problem, a statistical bounding technique is feasible. The technique applies to complex, multi-moded cavities. This paper reviews pertinent aspects of the statistical theory and its predictions concerning aircraft cavity environments. The paper presents cavity electromagnetic environment data from two large transport and two commuter aircraft. Data from both external and internal emitters are presented.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129773709","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 : 1996-10-27DOI: 10.1109/DASC.1996.559142
I. Ray
The International Civil Aviation Organization (ICAO) is developing a Communication, Navigation, and Surveillance/Air Traffic Management system (CNS/ATM) to provide advanced data link services between aircraft and ground hosts. These services will be provided over the Aeronautical Telecommunications Network (ATN) infrastructure, which is yet to be fully implemented. In the interim, the FANS 1 (Future Air Navigation System) program was developed, which offers valuable intermediate data link services over the existing ACARS network as a first step toward a full CNS/ATM system. Of paramount importance in both systems is the robustness of the Air Traffic Services (ATS) message transfer integrity. This paper describes and documents the ATS message integrity across the interim FANS 1 system, and its logical extension to the end state CNS/ATM environment. We will show that the interim system offers robust message integrity, assuring very low (and very acceptable) undetected error rates for ATS messages. It is shown that the FANS 1 implementation benefits from an end-to-end CRC, augmented by multiple levels of subnetwork CRCs to achieve this high-level of integrity. This robustness is further augmented by other error detection processes used in the FANS 1 Flight Management System (FMS). In this paper, the worst case probability of undetected errors for the interim system, considering multiple CRC's across each subnetwork, is calculated. Additional error detection mechanisms used in airborne ATS end systems are also considered. Finally, these concepts are expanded to encompass the enhanced error detection processes for future CNS/ATM applications over the ATN.
{"title":"Robust message integrity for FANS 1 and CNS/ATM","authors":"I. Ray","doi":"10.1109/DASC.1996.559142","DOIUrl":"https://doi.org/10.1109/DASC.1996.559142","url":null,"abstract":"The International Civil Aviation Organization (ICAO) is developing a Communication, Navigation, and Surveillance/Air Traffic Management system (CNS/ATM) to provide advanced data link services between aircraft and ground hosts. These services will be provided over the Aeronautical Telecommunications Network (ATN) infrastructure, which is yet to be fully implemented. In the interim, the FANS 1 (Future Air Navigation System) program was developed, which offers valuable intermediate data link services over the existing ACARS network as a first step toward a full CNS/ATM system. Of paramount importance in both systems is the robustness of the Air Traffic Services (ATS) message transfer integrity. This paper describes and documents the ATS message integrity across the interim FANS 1 system, and its logical extension to the end state CNS/ATM environment. We will show that the interim system offers robust message integrity, assuring very low (and very acceptable) undetected error rates for ATS messages. It is shown that the FANS 1 implementation benefits from an end-to-end CRC, augmented by multiple levels of subnetwork CRCs to achieve this high-level of integrity. This robustness is further augmented by other error detection processes used in the FANS 1 Flight Management System (FMS). In this paper, the worst case probability of undetected errors for the interim system, considering multiple CRC's across each subnetwork, is calculated. Additional error detection mechanisms used in airborne ATS end systems are also considered. Finally, these concepts are expanded to encompass the enhanced error detection processes for future CNS/ATM applications over the ATN.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126351854","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 : 1996-10-27DOI: 10.1109/DASC.1996.559132
W. Gifford
This paper describes a method to obtain structural coverage using a combination of structural coverage attained through Requirement-Based Testing (RBT) and Analysis. This method sets a specific coverage level that must be obtained through RBT alone for each element. The remaining code, not structurally covered, is then analyzed using a number of criteria. This combination of testing and analysis provides the structural coverage, which is part of the requirement-based formal verification test results.
{"title":"Structural coverage analysis method","authors":"W. Gifford","doi":"10.1109/DASC.1996.559132","DOIUrl":"https://doi.org/10.1109/DASC.1996.559132","url":null,"abstract":"This paper describes a method to obtain structural coverage using a combination of structural coverage attained through Requirement-Based Testing (RBT) and Analysis. This method sets a specific coverage level that must be obtained through RBT alone for each element. The remaining code, not structurally covered, is then analyzed using a number of criteria. This combination of testing and analysis provides the structural coverage, which is part of the requirement-based formal verification test results.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121380094","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 : 1996-10-27DOI: 10.1109/DASC.1996.559140
A. Warren
This paper aims to develop an operational concept and requirements for initial en route Free Flight using a simulation model of the Cleveland Air Route Traffic Control Center. The results of simulation studies of proposed implementation concepts are summarised and infrastructure requirements to transition from the current ATC system to mature Free Flight are specified. The transition path to Free Flight envisioned in this paper assumes an orderly development of technologies based on requirements derived from these studies. The purpose of this paper is to present a methodology and initial results in deriving airborne and ground-based requirements for cooperative development of the future Air Traffic Control system.
{"title":"A methodology and initial results specifying requirements for Free Flight transitions","authors":"A. Warren","doi":"10.1109/DASC.1996.559140","DOIUrl":"https://doi.org/10.1109/DASC.1996.559140","url":null,"abstract":"This paper aims to develop an operational concept and requirements for initial en route Free Flight using a simulation model of the Cleveland Air Route Traffic Control Center. The results of simulation studies of proposed implementation concepts are summarised and infrastructure requirements to transition from the current ATC system to mature Free Flight are specified. The transition path to Free Flight envisioned in this paper assumes an orderly development of technologies based on requirements derived from these studies. The purpose of this paper is to present a methodology and initial results in deriving airborne and ground-based requirements for cooperative development of the future Air Traffic Control system.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124210936","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 : 1996-10-27DOI: 10.1109/DASC.1996.559171
E. Ulbrich
This paper describes the author's personal view of the near term future of avionics technology. It forecasts an ultimate consolidation of today's systems into a super-system matched to the natural requirements of future pilots.
{"title":"The coming avionics utility","authors":"E. Ulbrich","doi":"10.1109/DASC.1996.559171","DOIUrl":"https://doi.org/10.1109/DASC.1996.559171","url":null,"abstract":"This paper describes the author's personal view of the near term future of avionics technology. It forecasts an ultimate consolidation of today's systems into a super-system matched to the natural requirements of future pilots.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132353684","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 : 1996-10-27DOI: 10.1109/DASC.1996.559146
M. Doss, K. Liebel, S. Lee, K. Calcagni, R. Crum
An overview of the recent work in migrating the Integrated Modular Avionics (IMA) architecture to space is presented. IMA is a candidate avionics architecture for space vehicles. The IMA was originally developed for the Boeing 777 program; since the IMA's successful implementation on the 777 program, significant progress has been made on the space IMA. This migration has focused on three areas: the architecture of a space IMA, a rapid prototyping laboratory, and development testing of space IMA components.
{"title":"Migration of Integrated Modular Avionics to space","authors":"M. Doss, K. Liebel, S. Lee, K. Calcagni, R. Crum","doi":"10.1109/DASC.1996.559146","DOIUrl":"https://doi.org/10.1109/DASC.1996.559146","url":null,"abstract":"An overview of the recent work in migrating the Integrated Modular Avionics (IMA) architecture to space is presented. IMA is a candidate avionics architecture for space vehicles. The IMA was originally developed for the Boeing 777 program; since the IMA's successful implementation on the 777 program, significant progress has been made on the space IMA. This migration has focused on three areas: the architecture of a space IMA, a rapid prototyping laboratory, and development testing of space IMA components.","PeriodicalId":332554,"journal":{"name":"15th DASC. AIAA/IEEE Digital Avionics Systems Conference","volume":null,"pages":null},"PeriodicalIF":0.0,"publicationDate":"1996-10-27","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122622053","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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