Pub Date : 1995-11-05DOI: 10.1109/DASC.1995.482823
T. Brown, J. Donaldson
Cassini is a NASA/JPL spacecraft that is planned to be launched in 1997 for a 10.7 year mission (6.7 in transit, 4 in orbit) to the planet Saturn. This paper focuses on one subsystem on the spacecraft, the Command and Data Subsystem (CDS). Overviews are presented of the Cassini and CDS avionics and then the internal fault protection architecture for the subsystem is described. This description covers fault detections, error filtering, event activation rules, and response triggering for the following key subsystem regions: (1) Command and Data Electronics Assemblies, (2) 1553B Bus and Remote Terminal Communication Interface Units, (3) Remote Engineering Units, and (4) Solid State Recorders.
{"title":"Fault protection architecture for the command and data subsystem on the Cassini spacecraft","authors":"T. Brown, J. Donaldson","doi":"10.1109/DASC.1995.482823","DOIUrl":"https://doi.org/10.1109/DASC.1995.482823","url":null,"abstract":"Cassini is a NASA/JPL spacecraft that is planned to be launched in 1997 for a 10.7 year mission (6.7 in transit, 4 in orbit) to the planet Saturn. This paper focuses on one subsystem on the spacecraft, the Command and Data Subsystem (CDS). Overviews are presented of the Cassini and CDS avionics and then the internal fault protection architecture for the subsystem is described. This description covers fault detections, error filtering, event activation rules, and response triggering for the following key subsystem regions: (1) Command and Data Electronics Assemblies, (2) 1553B Bus and Remote Terminal Communication Interface Units, (3) Remote Engineering Units, and (4) Solid State Recorders.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126884033","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 : 1995-11-05DOI: 10.1109/DASC.1995.482826
L. Harrison, P. Saraceni
One of the functions of the FAA Technical Center's Digital Systems Validation program is to educate FAA certification engineers in new technologies. This paper introduces the topic, Complex Integrated Circuits, along with some of the certification risks associated with this technology. This work is a partial summary of a technical report prepared for the FAA Technical Center's Airport and Aircraft Safety R&D Branch, Flight Safety Research Section. This paper seeks to highlight some of the problems associated with complex digital hardware used in digital flight control and avionic systems.
{"title":"Reliability issues for design and test of complex integrated circuits [in avionic systems]","authors":"L. Harrison, P. Saraceni","doi":"10.1109/DASC.1995.482826","DOIUrl":"https://doi.org/10.1109/DASC.1995.482826","url":null,"abstract":"One of the functions of the FAA Technical Center's Digital Systems Validation program is to educate FAA certification engineers in new technologies. This paper introduces the topic, Complex Integrated Circuits, along with some of the certification risks associated with this technology. This work is a partial summary of a technical report prepared for the FAA Technical Center's Airport and Aircraft Safety R&D Branch, Flight Safety Research Section. This paper seeks to highlight some of the problems associated with complex digital hardware used in digital flight control and avionic systems.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126348841","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 : 1995-11-05DOI: 10.1109/DASC.1995.482913
H. Hoy, T. Lam
The US Army AFDD recently completed flight testing of a CH-47 helicopter to refine the handling qualities requirements for cargo-class rotorcraft. A self contained mobile laser tracking system and telemetry acquisition system was designed and configured to provide the requisite position tracking and telemetry acquisition. Real time tracking data correlated with aircraft acquired telemetry data was used to drive a real time display monitor. The purpose of this paper is to describe the design and capabilities of this computer graphics generated display developed specifically for the purposes of real-time flight test visualization.
{"title":"CH-47D computer graphics generated display monitor [for flight test visualization]","authors":"H. Hoy, T. Lam","doi":"10.1109/DASC.1995.482913","DOIUrl":"https://doi.org/10.1109/DASC.1995.482913","url":null,"abstract":"The US Army AFDD recently completed flight testing of a CH-47 helicopter to refine the handling qualities requirements for cargo-class rotorcraft. A self contained mobile laser tracking system and telemetry acquisition system was designed and configured to provide the requisite position tracking and telemetry acquisition. Real time tracking data correlated with aircraft acquired telemetry data was used to drive a real time display monitor. The purpose of this paper is to describe the design and capabilities of this computer graphics generated display developed specifically for the purposes of real-time flight test visualization.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122247113","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 : 1995-11-05DOI: 10.1109/DASC.1995.482800
L. Huffman, S. Bullock
The FAA has recently made a commitment to implement GPS Landing Systems as the primary IFR capability for all public use approach and landing systems. As an interim step, private use GPS Landing Systems have been authorized to advance the learning curve. A primary capability of a Local Area Augmentation System (LAAS) is the requirement to uplink differential correction data from a ground station to airborne users. Since this technology is relatively new and is rapidly changing, a robust data link is needed that can be easily modified and updated without investment risk to both the user and the supplier. Further, the ever increasing demand by airlines to drive initial investment cost down, reduce life cycle maintenance costs, and to realize operational savings through lower weight, power, and size results in identification of a 'Software Radio' being a logical architecture choice. E-Systems has implemented this technology in government applications and has successfully transitioned this technology to commercial applications such as the SCAT-I VHF Data Link using D8PSK modulation. This paper discusses the general concepts of a 'Software Radio' and then focuses on D8PSK digital modulation and demodulation techniques. Other potential modulations are briefly discussed along with a summary of performance demonstrations.
{"title":"Digital modulation and demodulation within E-systems differential GPS transmitter and receiver","authors":"L. Huffman, S. Bullock","doi":"10.1109/DASC.1995.482800","DOIUrl":"https://doi.org/10.1109/DASC.1995.482800","url":null,"abstract":"The FAA has recently made a commitment to implement GPS Landing Systems as the primary IFR capability for all public use approach and landing systems. As an interim step, private use GPS Landing Systems have been authorized to advance the learning curve. A primary capability of a Local Area Augmentation System (LAAS) is the requirement to uplink differential correction data from a ground station to airborne users. Since this technology is relatively new and is rapidly changing, a robust data link is needed that can be easily modified and updated without investment risk to both the user and the supplier. Further, the ever increasing demand by airlines to drive initial investment cost down, reduce life cycle maintenance costs, and to realize operational savings through lower weight, power, and size results in identification of a 'Software Radio' being a logical architecture choice. E-Systems has implemented this technology in government applications and has successfully transitioned this technology to commercial applications such as the SCAT-I VHF Data Link using D8PSK modulation. This paper discusses the general concepts of a 'Software Radio' and then focuses on D8PSK digital modulation and demodulation techniques. Other potential modulations are briefly discussed along with a summary of performance demonstrations.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126094702","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 : 1995-11-05DOI: 10.1109/DASC.1995.482920
E. Shalom
The Input Output Unit (IOU) for the Attitude and Articulation Subsystem (AACS) for the Cassini spacecraft uses an embedded microprocessor to format and interpret data packets sent over a bus with the electrical characteristics of MIL-STD-1553B. The IOU used available design and protocol elements when possible, and employed custom hardware and firmware elements when necessary. As a result, the hardware design of the IOU, including the design of a custom gate array, took place in a extremely short time. With extensive simulation and modeling of the design at both the chip and board level, design iterations were minimal, and there were no iterations of the gate array. The embedded microprocessor in the IOU provides great versatility and flexibility, and allowed the incorporation in many functions in firmware. For this reason, firmware design and verification were challenging linchpins of this effort. This I/O approach is a marked departure from approaches used on previous JPL spacecraft. It has resulted in significant changes in the interfaces of AACS peripherals and their integration at the subsystem level. Future trends are reinforcing this approach, with "smart" peripherals and instruments communicating over much higher bandwidth optical buses.
{"title":"The input output unit for the attitude and articulation control subsystem on the Cassini spacecraft","authors":"E. Shalom","doi":"10.1109/DASC.1995.482920","DOIUrl":"https://doi.org/10.1109/DASC.1995.482920","url":null,"abstract":"The Input Output Unit (IOU) for the Attitude and Articulation Subsystem (AACS) for the Cassini spacecraft uses an embedded microprocessor to format and interpret data packets sent over a bus with the electrical characteristics of MIL-STD-1553B. The IOU used available design and protocol elements when possible, and employed custom hardware and firmware elements when necessary. As a result, the hardware design of the IOU, including the design of a custom gate array, took place in a extremely short time. With extensive simulation and modeling of the design at both the chip and board level, design iterations were minimal, and there were no iterations of the gate array. The embedded microprocessor in the IOU provides great versatility and flexibility, and allowed the incorporation in many functions in firmware. For this reason, firmware design and verification were challenging linchpins of this effort. This I/O approach is a marked departure from approaches used on previous JPL spacecraft. It has resulted in significant changes in the interfaces of AACS peripherals and their integration at the subsystem level. Future trends are reinforcing this approach, with \"smart\" peripherals and instruments communicating over much higher bandwidth optical buses.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"77 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116679971","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 : 1995-11-05DOI: 10.1109/DASC.1995.482922
P. Babcock
The Space Station Freedom was comprised of "utility" systems, such as power generation and distribution, thermal management, and data processing, and "user" systems such as communication and tracking; propulsion, payload support, and guidance, navigation, and control. These systems are required to work together to provide various station functions. To protect the lives onboard and the investment in the station, the systems and their connectivity had to be designed to continue to support critical functions after any single fault for early assembly stages, and after any two faults for later stages. Of these critical functions, attitude control was the most global, incorporating equipment from nearly all major systems. The challenge was to develop an architecture, or integration, of these systems that would achieve the specified level of fault tolerant attitude control and operate, autonomously, for the three-month unmanned periods during the assembly process. Additionally, this architecture had to maintain the desired utility of the station for each stage of the assembly process. This paper discusses the approach developed for integrating these systems such that the fault tolerance requirements were met for all stages of assembly. Some of the key integration issues will be examined and the role of analysis tools will be described. The resultant design was a highly channelized one, and the reasons and the benefits of this design will be explored. The final design was accepted by the Space Station Control Board as the design baseline in July, 1992.
{"title":"Channelization: the two-fault tolerant attitude control function for the Space Station Freedom","authors":"P. Babcock","doi":"10.1109/DASC.1995.482922","DOIUrl":"https://doi.org/10.1109/DASC.1995.482922","url":null,"abstract":"The Space Station Freedom was comprised of \"utility\" systems, such as power generation and distribution, thermal management, and data processing, and \"user\" systems such as communication and tracking; propulsion, payload support, and guidance, navigation, and control. These systems are required to work together to provide various station functions. To protect the lives onboard and the investment in the station, the systems and their connectivity had to be designed to continue to support critical functions after any single fault for early assembly stages, and after any two faults for later stages. Of these critical functions, attitude control was the most global, incorporating equipment from nearly all major systems. The challenge was to develop an architecture, or integration, of these systems that would achieve the specified level of fault tolerant attitude control and operate, autonomously, for the three-month unmanned periods during the assembly process. Additionally, this architecture had to maintain the desired utility of the station for each stage of the assembly process. This paper discusses the approach developed for integrating these systems such that the fault tolerance requirements were met for all stages of assembly. Some of the key integration issues will be examined and the role of analysis tools will be described. The resultant design was a highly channelized one, and the reasons and the benefits of this design will be explored. The final design was accepted by the Space Station Control Board as the design baseline in July, 1992.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127933632","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 : 1995-11-05DOI: 10.1109/DASC.1995.482833
J. Heckathorn, J. Lala, J. Prizant, L. Silver
This paper discusses the system analysis and design aspects of the Global Positioning System Operational Control System (OCS) remote site modernization study. Requirements analysis for a mission-critical legacy system poses a unique set of challenges such as undocumented requirements, a continually evolving system, variances between documented requirements and the system as implemented, an unrecorded repository of knowledge in designers and operators of the system, and so on. The paper discusses how these challenges were recognized and overcome. The system architecture designed to meet these requirements also had to meet the broader goals of OCS modernization including an open system architecture, increased dependability, expandability and flexibility. The paper describes key features as well as the design rationale of the architecture selected to meet these requirements.
{"title":"GPS ground antenna and monitor station upgrades: system analysis and design","authors":"J. Heckathorn, J. Lala, J. Prizant, L. Silver","doi":"10.1109/DASC.1995.482833","DOIUrl":"https://doi.org/10.1109/DASC.1995.482833","url":null,"abstract":"This paper discusses the system analysis and design aspects of the Global Positioning System Operational Control System (OCS) remote site modernization study. Requirements analysis for a mission-critical legacy system poses a unique set of challenges such as undocumented requirements, a continually evolving system, variances between documented requirements and the system as implemented, an unrecorded repository of knowledge in designers and operators of the system, and so on. The paper discusses how these challenges were recognized and overcome. The system architecture designed to meet these requirements also had to meet the broader goals of OCS modernization including an open system architecture, increased dependability, expandability and flexibility. The paper describes key features as well as the design rationale of the architecture selected to meet these requirements.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"41 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121785957","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 : 1995-11-05DOI: 10.1109/DASC.1995.482817
J. Soderberg
The Lockheed Martin T-BIRD II Avionic System incorporates a modular federated processor configuration interconnected by commercially available software and industry standard data buses. This suite, used on the Lockheed Martin entry into the Joint Primary Air Training System (JPATS) competition, represents a complete departure from the single source electronic flight instrument systems (EFIS) avionics suites used on similar aircraft. Instead, we chose each component for the optimum performance, availability, supportability, training effectiveness, acquisition and life cycle costs. The modularity and standardization available in today's avionics allowed us to integrate diverse instruments easily. This paper describes the system and its development and some of the advantages of this approach to avionics acquisition.
{"title":"T-bird II training system avionics","authors":"J. Soderberg","doi":"10.1109/DASC.1995.482817","DOIUrl":"https://doi.org/10.1109/DASC.1995.482817","url":null,"abstract":"The Lockheed Martin T-BIRD II Avionic System incorporates a modular federated processor configuration interconnected by commercially available software and industry standard data buses. This suite, used on the Lockheed Martin entry into the Joint Primary Air Training System (JPATS) competition, represents a complete departure from the single source electronic flight instrument systems (EFIS) avionics suites used on similar aircraft. Instead, we chose each component for the optimum performance, availability, supportability, training effectiveness, acquisition and life cycle costs. The modularity and standardization available in today's avionics allowed us to integrate diverse instruments easily. This paper describes the system and its development and some of the advantages of this approach to avionics acquisition.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130230047","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 : 1995-11-05DOI: 10.1109/DASC.1995.482832
L. Burkhardt, J. Heckathorn, J. Lala, L. Silver
This paper discusses the software aspects of the Global Positioning System (GPS) remote site modernization study, specifically, the software requirements analysis. At the beginning of the software requirements analysis phase, a qualitative trade-off study was performed to determine if a structured analysis or an object-oriented analysis (OOA) approach would be followed. The latter was chosen because it offers a number of advantages over the life-cycle of a software development project. This paper outlines these advantages. In conjunction with this methodology study, a study of Computer-aided Software Engineering (CASE) tools was performed to ascertain if available software requirements analysis and design tools would aid the software development process, in general, and requirements analysis, in particular. The results of this study are also summarized in this paper. The paper also discusses the experiences of Draper Laboratory software engineers in using OOA to perform software requirements analysis for a large software project (over 100,000 lines of Ada source code estimated), and how this approach was followed while specifying requirements using the Software Requirements Specification Data Item Description (DID) that accompanies DOD-STD-2167A.
{"title":"GPS ground antenna and monitor station upgrades: software requirements analysis","authors":"L. Burkhardt, J. Heckathorn, J. Lala, L. Silver","doi":"10.1109/DASC.1995.482832","DOIUrl":"https://doi.org/10.1109/DASC.1995.482832","url":null,"abstract":"This paper discusses the software aspects of the Global Positioning System (GPS) remote site modernization study, specifically, the software requirements analysis. At the beginning of the software requirements analysis phase, a qualitative trade-off study was performed to determine if a structured analysis or an object-oriented analysis (OOA) approach would be followed. The latter was chosen because it offers a number of advantages over the life-cycle of a software development project. This paper outlines these advantages. In conjunction with this methodology study, a study of Computer-aided Software Engineering (CASE) tools was performed to ascertain if available software requirements analysis and design tools would aid the software development process, in general, and requirements analysis, in particular. The results of this study are also summarized in this paper. The paper also discusses the experiences of Draper Laboratory software engineers in using OOA to perform software requirements analysis for a large software project (over 100,000 lines of Ada source code estimated), and how this approach was followed while specifying requirements using the Software Requirements Specification Data Item Description (DID) that accompanies DOD-STD-2167A.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121636700","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 : 1995-11-05DOI: 10.1109/DASC.1995.482819
R. P. Stead, G.P. Gambarani, D. Tillotson
In response to United States (U.S.) law mandating installation, by December 31, 1993, of TCAS IT on all air carrier aircraft with more than thirty passenger seats operating in U.S. Airspace, the first in-service flight of a certified TCAS II production unit occurred in June 1990. Currently, worldwide installations of TCAS IT in air carrier and business aircraft are estimated at over 7,000 units. Total accumulated flight operations exceed 50 million hours, with over 1.5 million additional hours accumulated each month. This paper provides a status update on the TCAS Transition Program (TTP) which was established to monitor the operational performance and assist with the introduction of TCAS II avionics into the National Airspace System (NAS). The update is provided by means of a qualitative performance comparison between the software logic initially fielded (Version 6.02) and the latest version (Version 6.04A) developed to address various flight performance dynamics and interface issues between TCAS and the air traffic control (ATC) system. This latest software logic has been in operation in all TCAS II-equipped aircraft since January 1, 1995.
{"title":"Traffic Alert and Collision Avoidance System (TCAS) transition program (TTP): a status update","authors":"R. P. Stead, G.P. Gambarani, D. Tillotson","doi":"10.1109/DASC.1995.482819","DOIUrl":"https://doi.org/10.1109/DASC.1995.482819","url":null,"abstract":"In response to United States (U.S.) law mandating installation, by December 31, 1993, of TCAS IT on all air carrier aircraft with more than thirty passenger seats operating in U.S. Airspace, the first in-service flight of a certified TCAS II production unit occurred in June 1990. Currently, worldwide installations of TCAS IT in air carrier and business aircraft are estimated at over 7,000 units. Total accumulated flight operations exceed 50 million hours, with over 1.5 million additional hours accumulated each month. This paper provides a status update on the TCAS Transition Program (TTP) which was established to monitor the operational performance and assist with the introduction of TCAS II avionics into the National Airspace System (NAS). The update is provided by means of a qualitative performance comparison between the software logic initially fielded (Version 6.02) and the latest version (Version 6.04A) developed to address various flight performance dynamics and interface issues between TCAS and the air traffic control (ATC) system. This latest software logic has been in operation in all TCAS II-equipped aircraft since January 1, 1995.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"1995-11-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134138411","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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