Pub Date : 1995-11-05DOI: 10.1109/DASC.1995.482822
M. Peterson, L. Nguyen, D.V. Edleman, J.F. Coffel
A process has been developed to improve upon the existing "Clean Aircraft" concept as currently defined by FAA guidelines for airline operations. The new "Safe Wing" concept works with existing airline programs for operations in icing conditions. It adds a contamination detection and classification system to the current procedural system. This addition improves overall system safety while eliminating burdensome checks, reducing delays and saving deicing/anti-icing fluid costs. By eliminating unnecessary deicings, if also reduces the environmental impact of using excessive deicing fluid. The HALO contamination detection system is comprised of ultrasonic sensors, processing electronics and a cockpit display. This multisensor system automatically and continuously monitors critical wing areas. The ultrasonic sensors provide area coverage and sensitivity to a variety of contaminants. These sensors are integrated into a HALO system design based on correlating contamination roughness, location and extent with aerodynamic performance. The HALO system development passed a major milestone with an in-service evaluation on a Northwest MD-80 during the 1994-95 winter season. This evaluation was designed to show technology viability in the demanding environment of airline winter operations. The single-sensor evaluation system showed a correct classification rate of greater than 95 percent and sensitivity to a variety of contaminants. A multi-sensor, broad coverage prototype system will be tested in the 1995-96 winter season.
{"title":"The HALO system-applying the \"safe wing\" concept to airline operations in ground icing conditions","authors":"M. Peterson, L. Nguyen, D.V. Edleman, J.F. Coffel","doi":"10.1109/DASC.1995.482822","DOIUrl":"https://doi.org/10.1109/DASC.1995.482822","url":null,"abstract":"A process has been developed to improve upon the existing \"Clean Aircraft\" concept as currently defined by FAA guidelines for airline operations. The new \"Safe Wing\" concept works with existing airline programs for operations in icing conditions. It adds a contamination detection and classification system to the current procedural system. This addition improves overall system safety while eliminating burdensome checks, reducing delays and saving deicing/anti-icing fluid costs. By eliminating unnecessary deicings, if also reduces the environmental impact of using excessive deicing fluid. The HALO contamination detection system is comprised of ultrasonic sensors, processing electronics and a cockpit display. This multisensor system automatically and continuously monitors critical wing areas. The ultrasonic sensors provide area coverage and sensitivity to a variety of contaminants. These sensors are integrated into a HALO system design based on correlating contamination roughness, location and extent with aerodynamic performance. The HALO system development passed a major milestone with an in-service evaluation on a Northwest MD-80 during the 1994-95 winter season. This evaluation was designed to show technology viability in the demanding environment of airline winter operations. The single-sensor evaluation system showed a correct classification rate of greater than 95 percent and sensitivity to a variety of contaminants. A multi-sensor, broad coverage prototype system will be tested in the 1995-96 winter season.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"57 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":"127698355","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.1995.482827
Melville D. Mcintyre, C. Gossett
The Boeing Commercial Airplane Group has certified an all-new, integrated Fault Tolerant Air Data and Inertial Reference System (FT-ADIRS) on its 777 airliner. The FT-ADIRS consists of the Fault Tolerant Air Data and Inertial Reference Unit (FT-ADIRU), the Secondary Attitude and Air Data Reference Unit (SAARU), and six Air Data Modules (ADMs). New processes for the design, verification, and validation of the system were developed. The FT-ADIRS redundancy management and system performance were validated using a unique process whereby flight-recorded sensor data were replayed through actual production units. Faults were inserted in a Monte Carlo fashion to demonstrate the ability of the inertial navigation and air data functions to isolate and survive sensor faults in real-time.
{"title":"The Boeing 777 Fault Tolerant Air Data and Inertial Reference System-a new venture in working together","authors":"Melville D. Mcintyre, C. Gossett","doi":"10.1109/DASC.1995.482827","DOIUrl":"https://doi.org/10.1109/DASC.1995.482827","url":null,"abstract":"The Boeing Commercial Airplane Group has certified an all-new, integrated Fault Tolerant Air Data and Inertial Reference System (FT-ADIRS) on its 777 airliner. The FT-ADIRS consists of the Fault Tolerant Air Data and Inertial Reference Unit (FT-ADIRU), the Secondary Attitude and Air Data Reference Unit (SAARU), and six Air Data Modules (ADMs). New processes for the design, verification, and validation of the system were developed. The FT-ADIRS redundancy management and system performance were validated using a unique process whereby flight-recorded sensor data were replayed through actual production units. Faults were inserted in a Monte Carlo fashion to demonstrate the ability of the inertial navigation and air data functions to isolate and survive sensor faults in real-time.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"54 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":"121363813","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.1995.482816
J. Ozols
Future tactical aircraft avionics processing systems development will be significantly different than in the past. Requirements growth will plateau. Processing device performance parameters will grow exponentially. Processing systems will continue to decrease in size. System complexity and bandwidth will increasingly reside within the processing devices themselves. All this will have significant implications for avionics system architectures and interconnect structures. And, as a consequence, the system architecture can be implemented in a relatively simple network based on COTS serial interconnects.
{"title":"Avionics processing system trends and implications","authors":"J. Ozols","doi":"10.1109/DASC.1995.482816","DOIUrl":"https://doi.org/10.1109/DASC.1995.482816","url":null,"abstract":"Future tactical aircraft avionics processing systems development will be significantly different than in the past. Requirements growth will plateau. Processing device performance parameters will grow exponentially. Processing systems will continue to decrease in size. System complexity and bandwidth will increasingly reside within the processing devices themselves. All this will have significant implications for avionics system architectures and interconnect structures. And, as a consequence, the system architecture can be implemented in a relatively simple network based on COTS serial interconnects.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"10 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":"116888021","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.1995.482929
M. Gries
This paper will describe the systems engineering process used in developing the 777 Autopilot Flight Director System (AFDS). It will include discussions regarding requirements capture, requirements allocation to hardware and software, system architecture considerations (including the architectural impact of safety requirements), change management, requirements and verification traceability, and requirements based verification. Additionally, the organizational structure employed and its interaction with the systems engineering process will also be reviewed. Finally, the results from a recent joint (Boeing and Collins) lessons learned exercise will be summarized.
{"title":"Systems engineering for the 777 Autopilot Flight Director System","authors":"M. Gries","doi":"10.1109/DASC.1995.482929","DOIUrl":"https://doi.org/10.1109/DASC.1995.482929","url":null,"abstract":"This paper will describe the systems engineering process used in developing the 777 Autopilot Flight Director System (AFDS). It will include discussions regarding requirements capture, requirements allocation to hardware and software, system architecture considerations (including the architectural impact of safety requirements), change management, requirements and verification traceability, and requirements based verification. Additionally, the organizational structure employed and its interaction with the systems engineering process will also be reviewed. Finally, the results from a recent joint (Boeing and Collins) lessons learned exercise will be summarized.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"67 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":"115807463","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.1995.482926
R. Hess
This paper discusses the development and i m pl em en t a t i o n component - o ri e n t e d environment for systems development, known as the ADVISETM product suite. The ADVISETM product suite is composed of a combination of computer hardware, software, and electrical interfaces intended to support the specification, design, integration, and test of air vehicle systems. of a The ADVISETM system contains a library of system components (pumps, valves, control computers, etc.) which the user treats as building blocks. The user configures the components to represent a system. The user can elect to simulate, emulate, or stimulate any or all these components. The flexibility of the component-oriented approach for systems development provides many advantages for managing complex systems development.
{"title":"A COMPONENT-ORIENTED ENVIRONMENT FOR SYSTEMS DEVELOPMENT","authors":"R. Hess","doi":"10.1109/DASC.1995.482926","DOIUrl":"https://doi.org/10.1109/DASC.1995.482926","url":null,"abstract":"This paper discusses the development and i m pl em en t a t i o n component - o ri e n t e d environment for systems development, known as the ADVISETM product suite. The ADVISETM product suite is composed of a combination of computer hardware, software, and electrical interfaces intended to support the specification, design, integration, and test of air vehicle systems. of a The ADVISETM system contains a library of system components (pumps, valves, control computers, etc.) which the user treats as building blocks. The user configures the components to represent a system. The user can elect to simulate, emulate, or stimulate any or all these components. The flexibility of the component-oriented approach for systems development provides many advantages for managing complex systems development.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"38 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":"126889807","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.1995.482842
K. Nerius
A typical SEM module consists of two Circuit Card Assemblies (CCAs). Electronics contained on the CCAs achieve unparalleled circuit densities by using Application Specific Integrated Circuits (ASICs) with gate counts in excess of 100,000 gates and Multi-Chip Modules ( M C M s ) . The two CCAs mount back to back on a common heat sink and interconnect to the backplane through a single multi-pin connector. Each backplane connector type contains over 300 pins and has provisions for fiber. optic, RF (co-axial) and analog interconnects. Module cooling i s through convection from the rail edges or by forcing liquid through a hollow cored heat sink.
{"title":"SEM PACKAGING OF ADVANCED MODULAR AVIONICS","authors":"K. Nerius","doi":"10.1109/DASC.1995.482842","DOIUrl":"https://doi.org/10.1109/DASC.1995.482842","url":null,"abstract":"A typical SEM module consists of two Circuit Card Assemblies (CCAs). Electronics contained on the CCAs achieve unparalleled circuit densities by using Application Specific Integrated Circuits (ASICs) with gate counts in excess of 100,000 gates and Multi-Chip Modules ( M C M s ) . The two CCAs mount back to back on a common heat sink and interconnect to the backplane through a single multi-pin connector. Each backplane connector type contains over 300 pins and has provisions for fiber. optic, RF (co-axial) and analog interconnects. Module cooling i s through convection from the rail edges or by forcing liquid through a hollow cored heat sink.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"31 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":"116600072","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.1995.482916
R.M. Kobee, M. Schrank, A. Anderson, G.W. Boyce
In support of a software support decision, MITRE has created a risk-based analysis approach to determine the most appropriate organization to maintain the fielded software. The approach for the risk analysis consisted of defining the risk categories and developing a supporting risk assessment questionnaire. Questions created for this risk assessment were divided into three risk areas: product, program, and organizational. The answers to these questions supported the risk, technical, and cost assessments. Criteria were established to determine the significance of the answers to the risk related questions. Based on the scoring, it can be determined whether the risk was high, medium, or low for each area and recommendations can be formulated and presented.
{"title":"A risk-based approach for the evaluation on software maintenance options for militarized avionics","authors":"R.M. Kobee, M. Schrank, A. Anderson, G.W. Boyce","doi":"10.1109/DASC.1995.482916","DOIUrl":"https://doi.org/10.1109/DASC.1995.482916","url":null,"abstract":"In support of a software support decision, MITRE has created a risk-based analysis approach to determine the most appropriate organization to maintain the fielded software. The approach for the risk analysis consisted of defining the risk categories and developing a supporting risk assessment questionnaire. Questions created for this risk assessment were divided into three risk areas: product, program, and organizational. The answers to these questions supported the risk, technical, and cost assessments. Criteria were established to determine the significance of the answers to the risk related questions. Based on the scoring, it can be determined whether the risk was high, medium, or low for each area and recommendations can be formulated and presented.","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":"133837506","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.1995.482939
D. Small, K. Kerns
Free flight concepts call for integrating advanced avionics and ground automation into new operational procedures. The concepts unavoidably raise human factors issues. Significant opportunities exist for leveraging applicable human performance data and principles from past research on avionics, automation, and system design to inform decisions and trade-offs at the front end of free flight development. Examples in this paper show how past research results can expedite the implementation of free flight by giving partial answers to newly raised issues and aiding the efficient resolution of remaining questions.
{"title":"OPPORTUNITIES FOR RAPID INTEGRATION OF HUMAN FACTORS IN DEVELOPING A FREE FLIGHT CAPABILITY","authors":"D. Small, K. Kerns","doi":"10.1109/DASC.1995.482939","DOIUrl":"https://doi.org/10.1109/DASC.1995.482939","url":null,"abstract":"Free flight concepts call for integrating advanced avionics and ground automation into new operational procedures. The concepts unavoidably raise human factors issues. Significant opportunities exist for leveraging applicable human performance data and principles from past research on avionics, automation, and system design to inform decisions and trade-offs at the front end of free flight development. Examples in this paper show how past research results can expedite the implementation of free flight by giving partial answers to newly raised issues and aiding the efficient resolution of remaining questions.","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":"130991817","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.1995.482810
B. Morrison, M. N. Robillard
Raytheon has developed and is certifying fault-tolerant low-cost distributed Control-By-Light technology for use in the next generation of civil, regional, and general aviation aircraft. Distributed control-by-light holds significant promise when applied to complex sensor/actuator systems such as aircraft controls. The CBL system replaces mechanical, hydraulic and electrical controls presently used to monitor, control and display flight, engine, and utility functions, and has substantial weight, cost, safety, and performance advantages over today's mechanical and fly-by-wire techniques. This paper describes the system concepts, configuration, and flight test program conducted with Raytheon Aircraft Company, and outlines the formal certification program now underway.
{"title":"Flight test and certification plans for low-cost distributed control-by-light systems","authors":"B. Morrison, M. N. Robillard","doi":"10.1109/DASC.1995.482810","DOIUrl":"https://doi.org/10.1109/DASC.1995.482810","url":null,"abstract":"Raytheon has developed and is certifying fault-tolerant low-cost distributed Control-By-Light technology for use in the next generation of civil, regional, and general aviation aircraft. Distributed control-by-light holds significant promise when applied to complex sensor/actuator systems such as aircraft controls. The CBL system replaces mechanical, hydraulic and electrical controls presently used to monitor, control and display flight, engine, and utility functions, and has substantial weight, cost, safety, and performance advantages over today's mechanical and fly-by-wire techniques. This paper describes the system concepts, configuration, and flight test program conducted with Raytheon Aircraft Company, and outlines the formal certification program now underway.","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":"129837489","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.1995.482932
G. Fuller, Andrew J. Poggio
An in-depth review of electromagnetic aircraft coupling models and recent experimental results from 1984 to 1995 provides a systematic approach for conducting HIRF certification. This approach uses models developed by NIST and LLNL to characterize the internal HIRF environment of an aircraft. Recent measurements on 707, 757, and GA/business aircraft conducted by NSWC, NIST, LLNL, and AF Phillips Labs suggest ways to reduce the dimensions of the test space. The principle dimension of this approach is frequency. Analysis is used to predict the expected fields in each of three frequency regimes where the coupling phenomena are unique. Analysis and spot testing can be used to eliminate or reduce the required testing in each of these ranges. Considerable savings in test time, complexity and costs can be achieved by collapsing the remaining dimensions of power density and illumination. Specifically, equivalent internal illumination by much lower power sources can be substituted for high powered external illumination. The number and choices of polarization and required aspect angles can be reduced as well using this approach.
{"title":"A fresh look: a more economic approach to HIRF certification","authors":"G. Fuller, Andrew J. Poggio","doi":"10.1109/DASC.1995.482932","DOIUrl":"https://doi.org/10.1109/DASC.1995.482932","url":null,"abstract":"An in-depth review of electromagnetic aircraft coupling models and recent experimental results from 1984 to 1995 provides a systematic approach for conducting HIRF certification. This approach uses models developed by NIST and LLNL to characterize the internal HIRF environment of an aircraft. Recent measurements on 707, 757, and GA/business aircraft conducted by NSWC, NIST, LLNL, and AF Phillips Labs suggest ways to reduce the dimensions of the test space. The principle dimension of this approach is frequency. Analysis is used to predict the expected fields in each of three frequency regimes where the coupling phenomena are unique. Analysis and spot testing can be used to eliminate or reduce the required testing in each of these ranges. Considerable savings in test time, complexity and costs can be achieved by collapsing the remaining dimensions of power density and illumination. Specifically, equivalent internal illumination by much lower power sources can be substituted for high powered external illumination. The number and choices of polarization and required aspect angles can be reduced as well using this approach.","PeriodicalId":125963,"journal":{"name":"Proceedings of 14th Digital Avionics Systems Conference","volume":"115 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":"132367030","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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