Pub Date : 2001-03-10DOI: 10.1109/AERO.2001.931222
D. Roberts
A modified SUU-25F/A dispenser pod system was evaluated for employment on the U.S. Navy F/A-18A Hornet fighter/attack aircraft. Testing had been conducted previously on the F/A-18A with a standard SUU-25F/A system, but was discontinued when the dispensed stores nearly collided with the horizontal stabilator. A modified system of two pods on the outboard wing station was designed to increase the separation clearance of the aft launched stores, below and outboard of the horizontal stabilator. Test methodology included a level flight build-up in airspeed with qualitative analysis of separation characteristics being conducted real-time using onboard telemetered video. The innovations implemented in this program enabled demonstration of store safe separation with a minimum number of test flights and store expenditures.
一种改进的SUU-25F/A分配吊舱系统被评估用于美国海军F/A- 18a大黄蜂战斗机/攻击机。先前在F/ a - 18a上使用标准的SUU-25F/ a系统进行了测试，但由于分配的支架几乎与水平稳定器相撞而中断。设计了一个由外翼站的两个吊舱组成的改进系统，以增加尾部发射的储存库、水平稳定器的下方和外侧的分离间隙。测试方法包括利用机载遥测视频对分离特性进行实时定性分析，并在空速上进行水平飞行。在该计划中实施的创新以最少的试飞次数和最少的存储支出实现了存储安全分离的演示。
{"title":"SUU-25F/A dispenser pod flight test program on the F/A-18A aircraft","authors":"D. Roberts","doi":"10.1109/AERO.2001.931222","DOIUrl":"https://doi.org/10.1109/AERO.2001.931222","url":null,"abstract":"A modified SUU-25F/A dispenser pod system was evaluated for employment on the U.S. Navy F/A-18A Hornet fighter/attack aircraft. Testing had been conducted previously on the F/A-18A with a standard SUU-25F/A system, but was discontinued when the dispensed stores nearly collided with the horizontal stabilator. A modified system of two pods on the outboard wing station was designed to increase the separation clearance of the aft launched stores, below and outboard of the horizontal stabilator. Test methodology included a level flight build-up in airspeed with qualitative analysis of separation characteristics being conducted real-time using onboard telemetered video. The innovations implemented in this program enabled demonstration of store safe separation with a minimum number of test flights and store expenditures.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121258927","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 : 2001-03-10DOI: 10.1109/AERO.2001.931405
P. Tappert, A. V. von Flotow, M. Mercadal
Blade tip sensors embedded into the engine case have been used for decades to measure blade tip clearance and blade vibration. Many sensing technologies have been used; capacitive, inductive, optical, microwave, infra-red, eddy-current, pressure and acoustic. These sensors generate data streams far greater than have been historically used in engine diagnostic units. Data streams of about 10,000 samples per second per sensor are about the minimum achievable, with some sensor front-ends delivering data streams of greater than 1Megasamples per second per sensor. In a PHM application, this data cannot be stored for later human analysis, but must be analyzed and discarded. This paper outlines autonomous algorithms for the real-time analysis of this data stream for PHM purposes. The application of these algorithms to several seeded fault tests is described. The need for a series of additional seeded fault tests is highlighted, for the purpose of maturing these algorithms prior to introduction into service.
{"title":"Autonomous PHM with blade-tip-sensors: algorithms and seeded fault experience","authors":"P. Tappert, A. V. von Flotow, M. Mercadal","doi":"10.1109/AERO.2001.931405","DOIUrl":"https://doi.org/10.1109/AERO.2001.931405","url":null,"abstract":"Blade tip sensors embedded into the engine case have been used for decades to measure blade tip clearance and blade vibration. Many sensing technologies have been used; capacitive, inductive, optical, microwave, infra-red, eddy-current, pressure and acoustic. These sensors generate data streams far greater than have been historically used in engine diagnostic units. Data streams of about 10,000 samples per second per sensor are about the minimum achievable, with some sensor front-ends delivering data streams of greater than 1Megasamples per second per sensor. In a PHM application, this data cannot be stored for later human analysis, but must be analyzed and discarded. This paper outlines autonomous algorithms for the real-time analysis of this data stream for PHM purposes. The application of these algorithms to several seeded fault tests is described. The need for a series of additional seeded fault tests is highlighted, for the purpose of maturing these algorithms prior to introduction into service.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124064598","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 : 2001-03-10DOI: 10.1109/AERO.2001.931299
S. Mandutianu, F. Hadaegh, P. Elliot
Concerns use of spacecraft as autonomous coordinated teams. Generalized reasoning capability offered by advanced distributed software technology and AI can cope with unexpected events and uncertainty, and so close the loop of perception, decision and eventually deliberation. The team members play interchangeable roles and negotiate about the task. We present a multi-agent system to provide a high degree of autonomy and support for coordination among team members. We use JPL formation flying mission initial architectures as benchmark. Our target is to avoid inconsistencies/disagreements between two or more participants in a collaborative context, increase the system's fault tolerance in cases such as loss of a member while the system still operates reliably. We address cooperation between collaborating independent autonomous agents. In a top-down organization agents are coordinated hierarchically, where the agents at the top of the hierarchy make the majority of the intelligent group decisions. In a more structured but still hierarchical organization, lower-level agents exercise more intelligence. A lower-level agent can advance a plan for the others to follow, and a higher-rank agent decides on the best plans. Although more rigid, the centralized intelligence organization allows for less communication among agents, so is more straightforward to implement. The decentralized approach requires more communication, but the intelligence is truly distributed, which makes for a more flexible, adaptive and efficient organization.
{"title":"Multi-agent system for formation flying missions","authors":"S. Mandutianu, F. Hadaegh, P. Elliot","doi":"10.1109/AERO.2001.931299","DOIUrl":"https://doi.org/10.1109/AERO.2001.931299","url":null,"abstract":"Concerns use of spacecraft as autonomous coordinated teams. Generalized reasoning capability offered by advanced distributed software technology and AI can cope with unexpected events and uncertainty, and so close the loop of perception, decision and eventually deliberation. The team members play interchangeable roles and negotiate about the task. We present a multi-agent system to provide a high degree of autonomy and support for coordination among team members. We use JPL formation flying mission initial architectures as benchmark. Our target is to avoid inconsistencies/disagreements between two or more participants in a collaborative context, increase the system's fault tolerance in cases such as loss of a member while the system still operates reliably. We address cooperation between collaborating independent autonomous agents. In a top-down organization agents are coordinated hierarchically, where the agents at the top of the hierarchy make the majority of the intelligent group decisions. In a more structured but still hierarchical organization, lower-level agents exercise more intelligence. A lower-level agent can advance a plan for the others to follow, and a higher-rank agent decides on the best plans. Although more rigid, the centralized intelligence organization allows for less communication among agents, so is more straightforward to implement. The decentralized approach requires more communication, but the intelligence is truly distributed, which makes for a more flexible, adaptive and efficient organization.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127720524","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 : 2001-03-10DOI: 10.1109/AERO.2001.931417
M. Connally, T. Kuiper
The Deep Space Mission System, (DSMS) Science Operations Concept describes the vision for facilitating the use of the DSMS, particularly the Deep Space Network (DSN) for direct science observations in the areas of radio astronomy, planetary radar, radio science and VLBI. scientific research is inherently an innovative activity; the "surprising result" is the best possible outcome. This operations concept establishes a framework that allows scientists to make full use of the DSMS's science capabilities by providing the amount and type of collaboration from DSMS science personnel appropriate to each observation program.
{"title":"DSMS Science Operations Concept","authors":"M. Connally, T. Kuiper","doi":"10.1109/AERO.2001.931417","DOIUrl":"https://doi.org/10.1109/AERO.2001.931417","url":null,"abstract":"The Deep Space Mission System, (DSMS) Science Operations Concept describes the vision for facilitating the use of the DSMS, particularly the Deep Space Network (DSN) for direct science observations in the areas of radio astronomy, planetary radar, radio science and VLBI. scientific research is inherently an innovative activity; the \"surprising result\" is the best possible outcome. This operations concept establishes a framework that allows scientists to make full use of the DSMS's science capabilities by providing the amount and type of collaboration from DSMS science personnel appropriate to each observation program.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"49 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126424406","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 : 2001-03-10DOI: 10.1109/AERO.2001.931734
J. Owens, M. Johnson
Small missions can play a large role in future robotic space exploration. While these missions cannot accomplish the vast scope of science objectives achieved by large missions such as Mars Sample Return or Cassini, they offer opportunities to explore smaller, but pertinent, science goals for significantly reduced total mission cost. The Jet Propulsion Laboratory's Advanced Projects Design Team (Team X) has conducted several mission studies to explore the feasibility of scientifically significant small interplanetary missions. These mission studies encompassed various targets (Mars, Earth's Moon, Venus, the Sun) using several scientific payloads (radar, imagers, radiometers). These missions can also perform other functions such as probe/balloon delivery or communications relay for landed missions. The studies considered a range of secondary payload launch vehicle options. This paper will highlight the results from these studies and discuss how the concurrent engineering environment of Team X lends itself to pre-phase A concept investigations.
{"title":"Interplanetary small mission studies","authors":"J. Owens, M. Johnson","doi":"10.1109/AERO.2001.931734","DOIUrl":"https://doi.org/10.1109/AERO.2001.931734","url":null,"abstract":"Small missions can play a large role in future robotic space exploration. While these missions cannot accomplish the vast scope of science objectives achieved by large missions such as Mars Sample Return or Cassini, they offer opportunities to explore smaller, but pertinent, science goals for significantly reduced total mission cost. The Jet Propulsion Laboratory's Advanced Projects Design Team (Team X) has conducted several mission studies to explore the feasibility of scientifically significant small interplanetary missions. These mission studies encompassed various targets (Mars, Earth's Moon, Venus, the Sun) using several scientific payloads (radar, imagers, radiometers). These missions can also perform other functions such as probe/balloon delivery or communications relay for landed missions. The studies considered a range of secondary payload launch vehicle options. This paper will highlight the results from these studies and discuss how the concurrent engineering environment of Team X lends itself to pre-phase A concept investigations.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128027152","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 : 2001-03-10DOI: 10.1109/AERO.2001.931461
S. Larson, R. Beer
The Tropospheric Emission Spectrometer (TES) will provide the first three-dimensional (latitude/longitude and altitude) measurements of tropospheric ozone and related species. The scientific objectives of the TES project are discussed, and an overview of the experiment and mission plan are presented. An overview of the design of the ground system is provided as context to a description of how some of the unique challenges posed by the development of the TES ground system were addressed. The solutions described include: concurrent engineering of flight and ground systems, use of CASE tools in software development, use of workstations clusters to meet computational requirements, and the development of a project-specific framework.
{"title":"Overview of the Tropospheric Emission Spectrometer ground system","authors":"S. Larson, R. Beer","doi":"10.1109/AERO.2001.931461","DOIUrl":"https://doi.org/10.1109/AERO.2001.931461","url":null,"abstract":"The Tropospheric Emission Spectrometer (TES) will provide the first three-dimensional (latitude/longitude and altitude) measurements of tropospheric ozone and related species. The scientific objectives of the TES project are discussed, and an overview of the experiment and mission plan are presented. An overview of the design of the ground system is provided as context to a description of how some of the unique challenges posed by the development of the TES ground system were addressed. The solutions described include: concurrent engineering of flight and ground systems, use of CASE tools in software development, use of workstations clusters to meet computational requirements, and the development of a project-specific framework.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"50 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121690566","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 : 2001-03-10DOI: 10.1109/AERO.2001.931697
M. Reinhart, J. R. Jensen, J.M. Cloeren, C. Deboy, K. B. Fielhauer, R. Schulze
This paper provides a detailed description of the radio communications system developed for the Comet Nucleus Tour (CONTOUR) Project. The communications system embodies a delicate balance of minimizing cost while providing the high performance needed to support a deep-space science mission. CONTOUR employs a transceiver-based X-band system instead of traditional deep-space transponders. For navigation, we have a conventional ranging channel and employ a novel Doppler frequency measurement technique. A reference oscillator with low phase noise is included to allow narrow bandwidth downlink carrier tracking at the ground stations. The antenna system is a combination of high- and low-gain antennas to support high-data-rate science returns and low-data-rate emergency operations. As CONTOUR is spin stabilized for most of the mission, including emergency operations, all antennas have been designed to provide continuous coverage around 360/spl deg/ of spacecraft rotation.
{"title":"The CONTOUR radio communications system","authors":"M. Reinhart, J. R. Jensen, J.M. Cloeren, C. Deboy, K. B. Fielhauer, R. Schulze","doi":"10.1109/AERO.2001.931697","DOIUrl":"https://doi.org/10.1109/AERO.2001.931697","url":null,"abstract":"This paper provides a detailed description of the radio communications system developed for the Comet Nucleus Tour (CONTOUR) Project. The communications system embodies a delicate balance of minimizing cost while providing the high performance needed to support a deep-space science mission. CONTOUR employs a transceiver-based X-band system instead of traditional deep-space transponders. For navigation, we have a conventional ranging channel and employ a novel Doppler frequency measurement technique. A reference oscillator with low phase noise is included to allow narrow bandwidth downlink carrier tracking at the ground stations. The antenna system is a combination of high- and low-gain antennas to support high-data-rate science returns and low-data-rate emergency operations. As CONTOUR is spin stabilized for most of the mission, including emergency operations, all antennas have been designed to provide continuous coverage around 360/spl deg/ of spacecraft rotation.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"86 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121773339","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 : 2001-03-10DOI: 10.1109/AERO.2001.931196
N. Haddad, R. Berger, R.D. Brown
The advent of broadband space communication has accelerated the need for high density, high performance, low power radiation hardened technology. A 0.25 /spl mu/m CMOS radiation enhanced ASIC library was developed and demonstrated. The library is compatible with state-of-the-art radiation tolerant commercial foundry fabrication and offers a significant advancement over the latest radiation hardened technology now in production. The Library supports 70 ps delay, 0.02 /spl mu/W/Gate/MHz power consumption and up to 7M gate/chip density, and achieves an upset rate of <1E-10 upset/bit/day in the 90% geosynchronous environment. The technology is latch-up immune and supports a total dose of >200 Krad (Si) in the natural space environment.
宽带空间通信的出现加速了对高密度、高性能、低功耗抗辐射技术的需求。研制并演示了0.25 /spl μ m CMOS辐射增强专用集成电路库。该库与最先进的耐辐射商业铸造制造兼容，并提供了目前生产中最新的辐射硬化技术的重大进步。该库支持70 ps延迟，0.02 /spl mu/W/Gate/MHz功耗和高达7M的栅极/芯片密度，在自然空间环境下实现200 Krad (Si)的扰流率。
{"title":"Low power 0.25 /spl mu/m ASIC technology for space applications","authors":"N. Haddad, R. Berger, R.D. Brown","doi":"10.1109/AERO.2001.931196","DOIUrl":"https://doi.org/10.1109/AERO.2001.931196","url":null,"abstract":"The advent of broadband space communication has accelerated the need for high density, high performance, low power radiation hardened technology. A 0.25 /spl mu/m CMOS radiation enhanced ASIC library was developed and demonstrated. The library is compatible with state-of-the-art radiation tolerant commercial foundry fabrication and offers a significant advancement over the latest radiation hardened technology now in production. The Library supports 70 ps delay, 0.02 /spl mu/W/Gate/MHz power consumption and up to 7M gate/chip density, and achieves an upset rate of <1E-10 upset/bit/day in the 90% geosynchronous environment. The technology is latch-up immune and supports a total dose of >200 Krad (Si) in the natural space environment.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":" 796","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131978201","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 : 2001-03-10DOI: 10.1109/AERO.2001.931364
R. Oishi
The Aeronautical Telecommunication Network (ATN) is designed to carry air traffic control (ATC) communications. The ATN is based on the Open Systems Interconnect (OSI) architecture which affords flexibility for data communications between end systems. The ATN was created by the International Civil Aviation Organization (ICAO) and, when implemented, will provide basic point-to-point communications with performance appropriate for ATC applications. Applications which provide digital equivalents of current voice services are the initial application targets of the ATN. It is becoming clear, however, that future air traffic management applications will not only rely increasingly on data communications but will require new or modified ATN capabilities. This paper will review the basic architecture of the ATN, examine the communications requirements of some current and future air traffic management applications, and suggest areas for expansion of ATN capabilities.
{"title":"Future applications and the Aeronautical Telecommunication Network","authors":"R. Oishi","doi":"10.1109/AERO.2001.931364","DOIUrl":"https://doi.org/10.1109/AERO.2001.931364","url":null,"abstract":"The Aeronautical Telecommunication Network (ATN) is designed to carry air traffic control (ATC) communications. The ATN is based on the Open Systems Interconnect (OSI) architecture which affords flexibility for data communications between end systems. The ATN was created by the International Civil Aviation Organization (ICAO) and, when implemented, will provide basic point-to-point communications with performance appropriate for ATC applications. Applications which provide digital equivalents of current voice services are the initial application targets of the ATN. It is becoming clear, however, that future air traffic management applications will not only rely increasingly on data communications but will require new or modified ATN capabilities. This paper will review the basic architecture of the ATN, examine the communications requirements of some current and future air traffic management applications, and suggest areas for expansion of ATN capabilities.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130009969","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 : 2001-03-10DOI: 10.1109/AERO.2001.931421
Meemong Lee, R. Weidner, Wenwen Lu
The Virtual Mission project led by the Mission Simulation and Instrument Modeling Group at JPL has been playing an active role in the NASA-wide information technology infusion programs, such as, Information System Technology, Next-Generation Infrastructure Technology, and Intelligent Synthesis Environment. The goal of the Virtual Mission project is to enable automated design space exploration, progressive design optimization, and lifecycle-wide design validation to ensure mission success. Design-based mission operation has been a major part of the research effort in order to establish system-wide as well as lifecycle-wide impact analysis as an integral part of the mission design process. The design-based mission operation is approached by implementing Virtual Mission Lifecycle (VML), modeling and simulation tools and system engineering processes for building a virtual mission system that can perform a realistic mission operation during the design phase of a mission. As in the real mission lifecycle convention, the VML is composed of design, development, integration and test, and operation phases. This paper describes the four phases of the VML addressing a major challenge per phase, mission model framework, virtual prototyping, agent-based mission system integration, and virtual mission operation.
{"title":"Design-based mission operation","authors":"Meemong Lee, R. Weidner, Wenwen Lu","doi":"10.1109/AERO.2001.931421","DOIUrl":"https://doi.org/10.1109/AERO.2001.931421","url":null,"abstract":"The Virtual Mission project led by the Mission Simulation and Instrument Modeling Group at JPL has been playing an active role in the NASA-wide information technology infusion programs, such as, Information System Technology, Next-Generation Infrastructure Technology, and Intelligent Synthesis Environment. The goal of the Virtual Mission project is to enable automated design space exploration, progressive design optimization, and lifecycle-wide design validation to ensure mission success. Design-based mission operation has been a major part of the research effort in order to establish system-wide as well as lifecycle-wide impact analysis as an integral part of the mission design process. The design-based mission operation is approached by implementing Virtual Mission Lifecycle (VML), modeling and simulation tools and system engineering processes for building a virtual mission system that can perform a realistic mission operation during the design phase of a mission. As in the real mission lifecycle convention, the VML is composed of design, development, integration and test, and operation phases. This paper describes the four phases of the VML addressing a major challenge per phase, mission model framework, virtual prototyping, agent-based mission system integration, and virtual mission operation.","PeriodicalId":329225,"journal":{"name":"2001 IEEE Aerospace Conference Proceedings (Cat. No.01TH8542)","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2001-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130245001","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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