Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446754
A. Belz
Strategic technology roadmap exercises typically identify technology gaps and determine resource needs. In practice, closing the gaps is remarkably difficult. Internal development efforts sometimes flounder, and small businesses have experienced limited success in becoming vendors. Unfortunately, the financial crisis of 2008 has intensified the problem, forcing a shrinking venture capital industry to avoid aerospace technologies. Federal investment in small business technology development will likely increase, with no guarantee of improved returns. The need for effective technology transfer has grown as NASA's priorities have moved from commercializing internal development to introducing external innovations, but success seems elusive. On the other hand, many companies in the private sector excel at accelerating innovation. This document describes the funding environment for small businesses, identifies selected best practices in the private sector, and synthesizes them into recommendations for improved technology transfer from internal and external development sources.1 2
{"title":"Challenges in technology infusion: Adapting best practices from the private sector","authors":"A. Belz","doi":"10.1109/AERO.2010.5446754","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446754","url":null,"abstract":"Strategic technology roadmap exercises typically identify technology gaps and determine resource needs. In practice, closing the gaps is remarkably difficult. Internal development efforts sometimes flounder, and small businesses have experienced limited success in becoming vendors. Unfortunately, the financial crisis of 2008 has intensified the problem, forcing a shrinking venture capital industry to avoid aerospace technologies. Federal investment in small business technology development will likely increase, with no guarantee of improved returns. The need for effective technology transfer has grown as NASA's priorities have moved from commercializing internal development to introducing external innovations, but success seems elusive. On the other hand, many companies in the private sector excel at accelerating innovation. This document describes the funding environment for small businesses, identifies selected best practices in the private sector, and synthesizes them into recommendations for improved technology transfer from internal and external development sources.1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"48 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134132838","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446857
W. Marchant, M. Bester, Mark Lewis, B. Roberts
NuSTAR, a NASA Small Explorer mission, is a high-energy astrophysics observatory targeted for an early 2012 launch into a low-inclination, low-Earth orbit. The science instrument is a focusing X-ray telescope developed by Caltech. Mission operations are conducted at Space Sciences Laboratory at the University of California, Berkeley, and science operations at Caltech. Integrated software systems provided by the mission operations team support all phases of NuSTAR instrument and spacecraft development, observatory integration, and environmental testing. Required simulators, prototype modules, and flight and ground systems interfaces are introduced into the development and test environment early in the project to closely match to on-orbit operations. This test-like-you-fly philosophy demands foresight and disciplined development at the earliest stages of project, but reduces cost and risk throughout the project life cycle by streamlining workflows and preventing interface problems at later stages. It also provides an excellent training environment and essentially guarantees a smooth transition to on-orbit operations. This paper reports on the progress and first successes of the NuSTAR team with the taken approach. 1 2
{"title":"Using NuSTAR mission operations software for instrument and spacecraft development","authors":"W. Marchant, M. Bester, Mark Lewis, B. Roberts","doi":"10.1109/AERO.2010.5446857","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446857","url":null,"abstract":"NuSTAR, a NASA Small Explorer mission, is a high-energy astrophysics observatory targeted for an early 2012 launch into a low-inclination, low-Earth orbit. The science instrument is a focusing X-ray telescope developed by Caltech. Mission operations are conducted at Space Sciences Laboratory at the University of California, Berkeley, and science operations at Caltech. Integrated software systems provided by the mission operations team support all phases of NuSTAR instrument and spacecraft development, observatory integration, and environmental testing. Required simulators, prototype modules, and flight and ground systems interfaces are introduced into the development and test environment early in the project to closely match to on-orbit operations. This test-like-you-fly philosophy demands foresight and disciplined development at the earliest stages of project, but reduces cost and risk throughout the project life cycle by streamlining workflows and preventing interface problems at later stages. It also provides an excellent training environment and essentially guarantees a smooth transition to on-orbit operations. This paper reports on the progress and first successes of the NuSTAR team with the taken approach. 1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"38 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134310885","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446659
C. Webber, J. Holmes, M. Francis, R. Berger, A. Mantooth, A. Arthurs, Kimberly Cornett, J. Cressler
Developing complex mixed-signal System-in-Package (SiP) chip-sets or Systems-on-Chip (SoC) typically involves parallel analog and digital IC development, where verification engineers can expect to encounter disconnects between the design automation flows, user proficiencies, and IC release cycles. Verifying the SiP chip-set prior to manufacturing is the key milestone where these disconnects are resolved. Presented is a unique modeling, simulation and verification method which bridges these gaps much earlier in the design process. As an illustrative example the verification of a complex SiP for space applications is presented.12
{"title":"Event driven mixed signal modeling techniques for System-in-Package functional verification","authors":"C. Webber, J. Holmes, M. Francis, R. Berger, A. Mantooth, A. Arthurs, Kimberly Cornett, J. Cressler","doi":"10.1109/AERO.2010.5446659","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446659","url":null,"abstract":"Developing complex mixed-signal System-in-Package (SiP) chip-sets or Systems-on-Chip (SoC) typically involves parallel analog and digital IC development, where verification engineers can expect to encounter disconnects between the design automation flows, user proficiencies, and IC release cycles. Verifying the SiP chip-set prior to manufacturing is the key milestone where these disconnects are resolved. Presented is a unique modeling, simulation and verification method which bridges these gaps much earlier in the design process. As an illustrative example the verification of a complex SiP for space applications is presented.12","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134390822","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446748
G. Bianchi, G. Aglietti, G. Richardson
Due to their high strength to weight ratio and stiffness to weight ratio the use of honeycomb panels is particularly attractive in spacecraft structures. Honeycomb panels are often used in secondary satellite structures such as equipment platforms and solar arrays, but they can also be used as part of the primary structure of a satellite. Indeed honeycomb panel assemblies can be, and are, used to produce efficient and cost-effective primary structures. These types of structures have been used for some time for numerous satellites; however, their development still poses some challenges ranging from the structural performance of the panels themselves to the problem of connecting them to other panels or structural elements. These challenges are faced each time a new satellite is being developed adding cost to the design process. Furthermore, often due to strict timescales in the development process, some of the uncertainties which naturally arise from these challenges cannot always be completely addressed. To compensate for this, conservative design approaches often need to be taken with the ultimate effect of lowering the efficiency of the structure's final design. To meet these challenges and provide a better knowledge base for future satellite development projects a number of research activities have been, and are still, under way at the University of Southampton. The aim of this paper is to describe these research activities and present the key results. 1 2
{"title":"Development of efficient and cost-effective spacecraft structures based on honeycomb panel assemblies","authors":"G. Bianchi, G. Aglietti, G. Richardson","doi":"10.1109/AERO.2010.5446748","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446748","url":null,"abstract":"Due to their high strength to weight ratio and stiffness to weight ratio the use of honeycomb panels is particularly attractive in spacecraft structures. Honeycomb panels are often used in secondary satellite structures such as equipment platforms and solar arrays, but they can also be used as part of the primary structure of a satellite. Indeed honeycomb panel assemblies can be, and are, used to produce efficient and cost-effective primary structures. These types of structures have been used for some time for numerous satellites; however, their development still poses some challenges ranging from the structural performance of the panels themselves to the problem of connecting them to other panels or structural elements. These challenges are faced each time a new satellite is being developed adding cost to the design process. Furthermore, often due to strict timescales in the development process, some of the uncertainties which naturally arise from these challenges cannot always be completely addressed. To compensate for this, conservative design approaches often need to be taken with the ultimate effect of lowering the efficiency of the structure's final design. To meet these challenges and provide a better knowledge base for future satellite development projects a number of research activities have been, and are still, under way at the University of Southampton. The aim of this paper is to describe these research activities and present the key results. 1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"50 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134379646","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446674
Wei Li, Jiuqiang Han
Topology change is the main factor which is affecting the network life time of Wireless Sensor Network applications. In normal WSNs with stationary nodes, the topology change is often caused by node failure which is due to energy depletion. However, in the mobile Wireless Senor Network, the main reason of the topology change is caused by the node movement. Sensor nodes in the network may move in any patterns, and different mobility patterns have various influences on the network life time. In this paper, through extensive simulations on different routing protocols with different mobility patterns, we evaluated the impact first, and then analyzed the reasons, in the end we proposed a dynamic parameters optimization method for the mobile Wireless Sensor Network.12
{"title":"Dynamic Wireless Sensor Network parameters optimization adapting different node mobility","authors":"Wei Li, Jiuqiang Han","doi":"10.1109/AERO.2010.5446674","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446674","url":null,"abstract":"Topology change is the main factor which is affecting the network life time of Wireless Sensor Network applications. In normal WSNs with stationary nodes, the topology change is often caused by node failure which is due to energy depletion. However, in the mobile Wireless Senor Network, the main reason of the topology change is caused by the node movement. Sensor nodes in the network may move in any patterns, and different mobility patterns have various influences on the network life time. In this paper, through extensive simulations on different routing protocols with different mobility patterns, we evaluated the impact first, and then analyzed the reasons, in the end we proposed a dynamic parameters optimization method for the mobile Wireless Sensor Network.12","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132034048","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446715
T. Ellis, Jason D. Schmidt
Adaptive optics (AO) systems on airborne platforms must be able to sense fields degraded by strong turbulence such as that associated with long horizontal propagation paths. The self-referencing interferometer (SRI) is a wavefront sensor that has been shown to be insensitive to scintillation. However, the limitations of the SRI have not been fully examined for extended beacons, which may have an angular extent larger than the isoplanatic angle of the atmosphere. This work presents results of computer simulations that examine the open-loop performance of an SRI wavefront sensor using an extended beacon and compares this performance with that of a Shack-Hartmann wavefront sensor.
{"title":"Wavefront sensor performance in strong turbulence with an extended beacon","authors":"T. Ellis, Jason D. Schmidt","doi":"10.1109/AERO.2010.5446715","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446715","url":null,"abstract":"Adaptive optics (AO) systems on airborne platforms must be able to sense fields degraded by strong turbulence such as that associated with long horizontal propagation paths. The self-referencing interferometer (SRI) is a wavefront sensor that has been shown to be insensitive to scintillation. However, the limitations of the SRI have not been fully examined for extended beacons, which may have an angular extent larger than the isoplanatic angle of the atmosphere. This work presents results of computer simulations that examine the open-loop performance of an SRI wavefront sensor using an extended beacon and compares this performance with that of a Shack-Hartmann wavefront sensor.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"220 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133999034","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446833
M. Azam, S. Ghoshal, S. Dixit, M. Pecht
A major issue in system health forecasting emanates from the necessity of transforming instantaneous (fast time scale) health condition and/or performance related observations into slow time-scale estimates. Slow time-scale transformation refers to aggregation of information from observations within a time interval, and assigning a representative state or symbol to the whole interval. The sequence of such symbols can be used to track and forecast system performance/health condition in a reliable way. Symbolic time series analysis (STSA) that employs an entropy maximization approach towards observation partitioning and symbol assignment has been proven quite useful for this purpose. This paper presents an STSA based approach for forecasting performance/health conditions of complex electronic systems using outlier removal and information fusion based pre-processing, and non-linear dynamic Markov model-based post-processing schemes. The dynamic Markov model computes the probability of observing a word that is present in symbolic time series. The probability of transition from one state to another is estimated by traversing through the symbolic series transition probabilities. Thereby, a discrete state transition model is obtained that can serve as the estimator of a system's behavior (in terms of health or performance) over time. An advantage of Markov model is that it extends naturally to forecast the performance/health states and estimates the Remaining Useful Life (RUL). Under this work, a STSA-based forecasting scheme was developed and validated on a set of automotive GPS1,2.
{"title":"Symbolic time series analysis based health condition forecasting in complex electronic systems","authors":"M. Azam, S. Ghoshal, S. Dixit, M. Pecht","doi":"10.1109/AERO.2010.5446833","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446833","url":null,"abstract":"A major issue in system health forecasting emanates from the necessity of transforming instantaneous (fast time scale) health condition and/or performance related observations into slow time-scale estimates. Slow time-scale transformation refers to aggregation of information from observations within a time interval, and assigning a representative state or symbol to the whole interval. The sequence of such symbols can be used to track and forecast system performance/health condition in a reliable way. Symbolic time series analysis (STSA) that employs an entropy maximization approach towards observation partitioning and symbol assignment has been proven quite useful for this purpose. This paper presents an STSA based approach for forecasting performance/health conditions of complex electronic systems using outlier removal and information fusion based pre-processing, and non-linear dynamic Markov model-based post-processing schemes. The dynamic Markov model computes the probability of observing a word that is present in symbolic time series. The probability of transition from one state to another is estimated by traversing through the symbolic series transition probabilities. Thereby, a discrete state transition model is obtained that can serve as the estimator of a system's behavior (in terms of health or performance) over time. An advantage of Markov model is that it extends naturally to forecast the performance/health states and estimates the Remaining Useful Life (RUL). Under this work, a STSA-based forecasting scheme was developed and validated on a set of automotive GPS1,2.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"31 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114060005","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446807
E. Pastor, Marc Solé, Juan López, P. Royo, C. Barrado
This work introduces a flexible and reusable architecture designed to facilitate the development of remote sensing applications. Based on it, we are developing a helicopter system, called Red-Eye, devoted to the detection, control and analysis of wild land forest fires in the Mediterranean area. The design of the proposed system is composed of five main components. Each component will work collaboratively to constitute a platform of high added value. The general architecture designed for wildfire monitoring is being tailored for two relevant objectives within the particular Mediterranean scenario: tactical day/night fire front evolution, and post-fire hot-spot detection.
{"title":"Helicopter-based wildfire monitoring system software architecture","authors":"E. Pastor, Marc Solé, Juan López, P. Royo, C. Barrado","doi":"10.1109/AERO.2010.5446807","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446807","url":null,"abstract":"This work introduces a flexible and reusable architecture designed to facilitate the development of remote sensing applications. Based on it, we are developing a helicopter system, called Red-Eye, devoted to the detection, control and analysis of wild land forest fires in the Mediterranean area. The design of the proposed system is composed of five main components. Each component will work collaboratively to constitute a platform of high added value. The general architecture designed for wildfire monitoring is being tailored for two relevant objectives within the particular Mediterranean scenario: tactical day/night fire front evolution, and post-fire hot-spot detection.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"28 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122056068","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446846
Ruwan P. Somawardhana, J. Millard
The Cassini spacecraft has performed its four year Prime Mission at Saturn and is currently in orbit at Saturn performing a two year extended mission. 12Its main engine nozzles are susceptible to impact damage from micrometeoroids and on-orbit dust. The spacecraft has an articulating device known as the Main Engine Assembly (MEA) cover which can close and shield the main engines from these threats. The cover opens to allow for main engine burns that are necessary to maintain the trajectory. Periodically updated analyses of potential on-orbit dust hazard threats have resulted in the need to continue to use the MEA cover beyond its intended use and beyond its design life. This paper provides a detailed Systems-level overview of the flight management of the MEA cover device and its flight performance to date.
{"title":"Cassini Main Engine Assembly cover flight management and performance","authors":"Ruwan P. Somawardhana, J. Millard","doi":"10.1109/AERO.2010.5446846","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446846","url":null,"abstract":"The Cassini spacecraft has performed its four year Prime Mission at Saturn and is currently in orbit at Saturn performing a two year extended mission. 12Its main engine nozzles are susceptible to impact damage from micrometeoroids and on-orbit dust. The spacecraft has an articulating device known as the Main Engine Assembly (MEA) cover which can close and shield the main engines from these threats. The cover opens to allow for main engine burns that are necessary to maintain the trajectory. Periodically updated analyses of potential on-orbit dust hazard threats have resulted in the need to continue to use the MEA cover beyond its intended use and beyond its design life. This paper provides a detailed Systems-level overview of the flight management of the MEA cover device and its flight performance to date.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"112 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117198444","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446809
P. Feiler
Safety-critical systems have become increasingly software reliant and the current development process of “build, then integrate” has become unaffordable.1,2 This paper examines two major contributors to today's exponential growth in cost: system-level faults that are not discovered until late in the development process; and multiple truths of analysis results when predicting system properties through model-based analysis and validating them against system implementations. We discuss the root causes of such system-level problems, and an architecture-centric model-based analysis approach of different operational quality aspects from an architecture model. A key technology is the SAE Architecture Analysis & Design Language (AADL) standard for embedded software-reliant system. It supports a single source approach to analysis of operational qualities such as responsiveness, safety-criticality, security, and reliability through model annotations. The paper concludes with a summary of an industrial case study that demonstrates the feasibility of this approach.
{"title":"Model-based validation of safety-critical embedded systems","authors":"P. Feiler","doi":"10.1109/AERO.2010.5446809","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446809","url":null,"abstract":"Safety-critical systems have become increasingly software reliant and the current development process of “build, then integrate” has become unaffordable.1,2 This paper examines two major contributors to today's exponential growth in cost: system-level faults that are not discovered until late in the development process; and multiple truths of analysis results when predicting system properties through model-based analysis and validating them against system implementations. We discuss the root causes of such system-level problems, and an architecture-centric model-based analysis approach of different operational quality aspects from an architecture model. A key technology is the SAE Architecture Analysis & Design Language (AADL) standard for embedded software-reliant system. It supports a single source approach to analysis of operational qualities such as responsiveness, safety-criticality, security, and reliability through model annotations. The paper concludes with a summary of an industrial case study that demonstrates the feasibility of this approach.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114940893","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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