Pub Date : 2005-03-05DOI: 10.1109/AERO.2005.1559572
Dan L. Michaels, James F. Speed
Star trackers are traditionally a key component in spacecraft attitude control systems. Ball Aerospace has designed, developed and delivered the high accuracy star tracker (HAST). The HAST achieves 0.2 arcsec total error (1sigma) performance on each tracked star moving between 0.07 and 1.0 degrees/second. HAST maintains track on stars moving 0 to 4 degrees/second. Multiple star tracking further enhances the accuracy. This paper describes HAST and examines measured performance. Performance is assessed according to the three dominant error sources: 1) boresight alignment bias; 2) transit dependent bias; and 3) random measurement. The performance measurement techniques are described along with delivered product test results
{"title":"Ball Aerospace Star Tracker Achieves High Tracking Accuracy for a Moving Star Field","authors":"Dan L. Michaels, James F. Speed","doi":"10.1109/AERO.2005.1559572","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559572","url":null,"abstract":"Star trackers are traditionally a key component in spacecraft attitude control systems. Ball Aerospace has designed, developed and delivered the high accuracy star tracker (HAST). The HAST achieves 0.2 arcsec total error (1sigma) performance on each tracked star moving between 0.07 and 1.0 degrees/second. HAST maintains track on stars moving 0 to 4 degrees/second. Multiple star tracking further enhances the accuracy. This paper describes HAST and examines measured performance. Performance is assessed according to the three dominant error sources: 1) boresight alignment bias; 2) transit dependent bias; and 3) random measurement. The performance measurement techniques are described along with delivered product test results","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"89 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125118015","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 : 2005-03-05DOI: 10.1109/AERO.2005.1559634
R. Carvalho, D. Berrios, S. Wolfe, J. Williams
InvestigationOrganizer (IO) is a collaborative semantic Web application designed to support mishap investigations, and has been used for accidents ranging from those involving only minor property damage to the loss of the Space Shuttle Columbia. The development and use of IO in support of these investigations has provided significant lessons about the use of semantic Web technologies in real-world systems. IO is a data and knowledge repository for a wide range of mishap related information in which investigators meaningfully structure information and link together evidence, causal models, and investigation results. The types of knowledge that investigators can include in the repository are defined by its investigation ontology, a component of the system that expresses investigation concepts using a logical formalism. IO developers can dynamically alter this ontology without having to recompile the application. This paper describes the development of the investigation ontology for IO, focusing on its growth in response to user needs during the investigations, as well as efforts to control that growth
{"title":"Ontology Development and Evolution in the Accident Investigation Domain","authors":"R. Carvalho, D. Berrios, S. Wolfe, J. Williams","doi":"10.1109/AERO.2005.1559634","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559634","url":null,"abstract":"InvestigationOrganizer (IO) is a collaborative semantic Web application designed to support mishap investigations, and has been used for accidents ranging from those involving only minor property damage to the loss of the Space Shuttle Columbia. The development and use of IO in support of these investigations has provided significant lessons about the use of semantic Web technologies in real-world systems. IO is a data and knowledge repository for a wide range of mishap related information in which investigators meaningfully structure information and link together evidence, causal models, and investigation results. The types of knowledge that investigators can include in the repository are defined by its investigation ontology, a component of the system that expresses investigation concepts using a logical formalism. IO developers can dynamically alter this ontology without having to recompile the application. This paper describes the development of the investigation ontology for IO, focusing on its growth in response to user needs during the investigations, as well as efforts to control that growth","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"86 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126025946","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 : 2005-03-05DOI: 10.1109/AERO.2005.1559544
S. Baloch, T. Arslan, A. Stoica
New systematic single error correcting codes-based circuits are introduced for random access memories, with ultimate minimal encoding/decoding complexity, low power and high performance. These new, codes-based circuits can be used in combinational circuits and in on-chip random access memories of reconfigurable architectures with high performance and ultimate minimum decoding/encoding complexity. Due to the overhead of parity check bits associated with the error-correcting-codes, there has always been a demand for an efficient and compact code for small memories in terms of data width. The proposed codes give improved performance even for small memories over the other codes. Area and power comparisons have been performed to benchmark the performance index of our codes. The code-centric circuits offer significant advantages over existing error correcting codes-based circuits in the literature in terms of lower size, power and cost which make them suitable for wider range of applications such as those targeting space. The paper describes the new efficient code and associated circuits for its implementation
{"title":"Efficient Error Correcting Codes for On-Chip DRAM Applications for Space Missions","authors":"S. Baloch, T. Arslan, A. Stoica","doi":"10.1109/AERO.2005.1559544","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559544","url":null,"abstract":"New systematic single error correcting codes-based circuits are introduced for random access memories, with ultimate minimal encoding/decoding complexity, low power and high performance. These new, codes-based circuits can be used in combinational circuits and in on-chip random access memories of reconfigurable architectures with high performance and ultimate minimum decoding/encoding complexity. Due to the overhead of parity check bits associated with the error-correcting-codes, there has always been a demand for an efficient and compact code for small memories in terms of data width. The proposed codes give improved performance even for small memories over the other codes. Area and power comparisons have been performed to benchmark the performance index of our codes. The code-centric circuits offer significant advantages over existing error correcting codes-based circuits in the literature in terms of lower size, power and cost which make them suitable for wider range of applications such as those targeting space. The paper describes the new efficient code and associated circuits for its implementation","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"136 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123252725","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 : 2005-03-05DOI: 10.1109/AERO.2005.1559700
Y. Macheret, Philipp Koehn, D. Sparrow
Achieving high reliability is one of the major objectives in the development of the future combat system (FCS) family of military vehicles. The proposed solution to achieve this objective is a prognostics-based approach characterized by a capability to monitor the status of mission-critical components and forecast the future state of the FCS system. In this paper, two approaches for achieving and maintaining high operational availability of military systems are analyzed and compared: overhaul and prognostics asset management strategies. It is shown that the prognostics approach leads to improved operational availability by anticipating failure and reducing administrative and logistics delays. In addition, the prognostics capability allows intelligent maintenance that is, replacing only those parts whose remaining lifetime reached the critical value. In this case, the improved operational availability is achieved at a significantly lower cost (number of spares) compared to that of the overhaul maintenance strategy. The prognostics approach also leads to a reduced risk of failure during the upcoming missions, since it allows field commanders to select only those platforms whose remaining life exceeds the duration of the upcoming mission
{"title":"Improving reliability and operational availability of military systems","authors":"Y. Macheret, Philipp Koehn, D. Sparrow","doi":"10.1109/AERO.2005.1559700","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559700","url":null,"abstract":"Achieving high reliability is one of the major objectives in the development of the future combat system (FCS) family of military vehicles. The proposed solution to achieve this objective is a prognostics-based approach characterized by a capability to monitor the status of mission-critical components and forecast the future state of the FCS system. In this paper, two approaches for achieving and maintaining high operational availability of military systems are analyzed and compared: overhaul and prognostics asset management strategies. It is shown that the prognostics approach leads to improved operational availability by anticipating failure and reducing administrative and logistics delays. In addition, the prognostics capability allows intelligent maintenance that is, replacing only those parts whose remaining lifetime reached the critical value. In this case, the improved operational availability is achieved at a significantly lower cost (number of spares) compared to that of the overhaul maintenance strategy. The prognostics approach also leads to a reduced risk of failure during the upcoming missions, since it allows field commanders to select only those platforms whose remaining life exceeds the duration of the upcoming mission","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125348771","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 : 2005-03-05DOI: 10.1109/AERO.2005.1559539
J. Ramos, D. Brenner, G. Galica, C. Walter
The application of commercial-off-the-shelf (COTS) processing components in operational space missions with optimal performance and efficiency requires a system-level approach. Of primary concern is the need to handle the inherent susceptibility of COTS components to single event upsets (SEUs). Honeywell in conjunction with Physical Sciences Incorporated, and WW Technology Group has developed a new paradigm for fault tolerant COTS based onboard computing. The paradigm is called "environmentally adaptive fault tolerant computing" (EAFTC.) EAFTC combines a set of innovative technologies to enable efficient use of high performance COTS processors, in the harsh space environment, while maintaining the required system availability
{"title":"Environmentally Adaptive Fault Tolerant Computing (EAFTC)","authors":"J. Ramos, D. Brenner, G. Galica, C. Walter","doi":"10.1109/AERO.2005.1559539","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559539","url":null,"abstract":"The application of commercial-off-the-shelf (COTS) processing components in operational space missions with optimal performance and efficiency requires a system-level approach. Of primary concern is the need to handle the inherent susceptibility of COTS components to single event upsets (SEUs). Honeywell in conjunction with Physical Sciences Incorporated, and WW Technology Group has developed a new paradigm for fault tolerant COTS based onboard computing. The paradigm is called \"environmentally adaptive fault tolerant computing\" (EAFTC.) EAFTC combines a set of innovative technologies to enable efficient use of high performance COTS processors, in the harsh space environment, while maintaining the required system availability","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126737843","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 : 2005-03-05DOI: 10.1109/AERO.2005.1559398
D. Srinivasan, R. Wallis, D. Royster, J. Bruzzi, P. Malouf, K. B. Fielhauer
The MESSENGER spacecraft uses an X-band (8.4-GHz) phased array for high-rate downlink communications to meet mission data requirements yet still survive the extreme environment at the planet Mercury. To survive the solar intensity at the planet, the MESSENGER spacecraft uses a sunshade that must remain Sun-pointed; this restricts pointing of the spacecraft. The use of two phased-array antennas alleviates the need for a gimbaled high-gain dish. The RF signal is routed through on-board solid-state power amplifiers that control the phases of the signals fed to the phased arrays, thereby pointing without the need for any moving parts while maintaining a Sun-pointed attitude. Each phased array is composed of eight slotted waveguide sticks. This paper describes a method for a real-time, fast verification of the steering of the phased array during any phase of spacecraft-level testing (including thermal-vacuum) without the need to free radiate, which is specifically critical to a spacecraft during integration and test. This newly developed and implemented approach does not require near-field probing, in-line couplers, or extra flight mates and de-mates. Once the antennas are integrated onto the spacecraft, schedule constraints force the need for very quick verification methods. The technique described herein quickly samples the phase of the signal at each array element and, in conjunction with subsystem-level measurements, mathematically calculates the radiated antenna pattern. The phases within each array element are measured using innovative loop couplers that may simply be removed once testing is complete. These phases are combined using specifically designed software to calculate the far-field radiated pattern to verify pointing.
{"title":"Spacecraft-level testing and verification of an X-band phased array","authors":"D. Srinivasan, R. Wallis, D. Royster, J. Bruzzi, P. Malouf, K. B. Fielhauer","doi":"10.1109/AERO.2005.1559398","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559398","url":null,"abstract":"The MESSENGER spacecraft uses an X-band (8.4-GHz) phased array for high-rate downlink communications to meet mission data requirements yet still survive the extreme environment at the planet Mercury. To survive the solar intensity at the planet, the MESSENGER spacecraft uses a sunshade that must remain Sun-pointed; this restricts pointing of the spacecraft. The use of two phased-array antennas alleviates the need for a gimbaled high-gain dish. The RF signal is routed through on-board solid-state power amplifiers that control the phases of the signals fed to the phased arrays, thereby pointing without the need for any moving parts while maintaining a Sun-pointed attitude. Each phased array is composed of eight slotted waveguide sticks. This paper describes a method for a real-time, fast verification of the steering of the phased array during any phase of spacecraft-level testing (including thermal-vacuum) without the need to free radiate, which is specifically critical to a spacecraft during integration and test. This newly developed and implemented approach does not require near-field probing, in-line couplers, or extra flight mates and de-mates. Once the antennas are integrated onto the spacecraft, schedule constraints force the need for very quick verification methods. The technique described herein quickly samples the phase of the signal at each array element and, in conjunction with subsystem-level measurements, mathematically calculates the radiated antenna pattern. The phases within each array element are measured using innovative loop couplers that may simply be removed once testing is complete. These phases are combined using specifically designed software to calculate the far-field radiated pattern to verify pointing.","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116458888","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 : 2005-03-05DOI: 10.1109/AERO.2005.1559432
S. Horan, G. Deivasigamani
The design of a protocol for satellite cluster link establishment and management that accounts for link corruption, node failures, and node re-establishment is presented in this paper. This protocol will need to manage the traffic flow between nodes in the satellite cluster, adjust routing tables due to node motion, allow for sub-networks in the cluster, and similar activities. This protocol development is in its initial stages. Preliminary results with eight nodes demonstrate its operations and potential problems that may arise when significant numbers of channel errors are present
{"title":"Design of a fault-tolerant satellite cluster link establishment protocol","authors":"S. Horan, G. Deivasigamani","doi":"10.1109/AERO.2005.1559432","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559432","url":null,"abstract":"The design of a protocol for satellite cluster link establishment and management that accounts for link corruption, node failures, and node re-establishment is presented in this paper. This protocol will need to manage the traffic flow between nodes in the satellite cluster, adjust routing tables due to node motion, allow for sub-networks in the cluster, and similar activities. This protocol development is in its initial stages. Preliminary results with eight nodes demonstrate its operations and potential problems that may arise when significant numbers of channel errors are present","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"228 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116541576","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 : 2005-03-05DOI: 10.1109/AERO.2005.1559460
Y. Krikorian, D. Emmons, J. McVey
An analysis and results are presented in this paper for the amount of usage and communications cost of the deep space network (DSN) for a Mars manned flyby mission. A survey of communication needs of past manned space missions was conducted, including those for the moon, International Space Station (ISS), and Space Shuttle. A Mars flyby trajectory was created in order to analyze the dynamic communication link between the spacecraft and the DSN. Based on the data throughput requirements obtained, a trade space of spacecraft telecommunication systems is presented. DSN usage (in numbers of hours) for the 34 m and 70 m antennas is tabulated. Finally, a trade study of cost for the DSN aperture fee for the Mars manned flyby mission is computed
{"title":"Communication coverage and cost of the deep space network for a Mars manned flyby mission","authors":"Y. Krikorian, D. Emmons, J. McVey","doi":"10.1109/AERO.2005.1559460","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559460","url":null,"abstract":"An analysis and results are presented in this paper for the amount of usage and communications cost of the deep space network (DSN) for a Mars manned flyby mission. A survey of communication needs of past manned space missions was conducted, including those for the moon, International Space Station (ISS), and Space Shuttle. A Mars flyby trajectory was created in order to analyze the dynamic communication link between the spacecraft and the DSN. Based on the data throughput requirements obtained, a trade space of spacecraft telecommunication systems is presented. DSN usage (in numbers of hours) for the 34 m and 70 m antennas is tabulated. Finally, a trade study of cost for the DSN aperture fee for the Mars manned flyby mission is computed","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114169963","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 : 2005-03-05DOI: 10.1109/AERO.2005.1559402
C. McCarroll, Raytheon
Microwave distribution systems for phased array antennas are always being optimized for compactness and higher performance. Hard wired corporate feeds are usually the implementation of choice because design information is well understood. However, compromises in system size, weight and performance are usually made as a trade for ease of design. Spatial near-field feed networks on the other hand have the potential of higher compactness and performance but are much harder to implement because their design information is not as well understood. This paper presents an example near-field spatial feed using a horn antenna feeding a three horn array. The demonstration is used to validate a near-field antenna array sampling technique developed for the purpose of designing near-field spatial feeds. The work includes the full 3D electromagnetic modeling of the feed, the optimization of the feed and finally the experimental testing of the feed. The modeled versus measured data presented will show that compact high performance spatial near-field feeds can be accurately modeled and implemented for specific feed requirements.
{"title":"An evaluation of near-field spatial feeds for phased array antennas","authors":"C. McCarroll, Raytheon","doi":"10.1109/AERO.2005.1559402","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559402","url":null,"abstract":"Microwave distribution systems for phased array antennas are always being optimized for compactness and higher performance. Hard wired corporate feeds are usually the implementation of choice because design information is well understood. However, compromises in system size, weight and performance are usually made as a trade for ease of design. Spatial near-field feed networks on the other hand have the potential of higher compactness and performance but are much harder to implement because their design information is not as well understood. This paper presents an example near-field spatial feed using a horn antenna feeding a three horn array. The demonstration is used to validate a near-field antenna array sampling technique developed for the purpose of designing near-field spatial feeds. The work includes the full 3D electromagnetic modeling of the feed, the optimization of the feed and finally the experimental testing of the feed. The modeled versus measured data presented will show that compact high performance spatial near-field feeds can be accurately modeled and implemented for specific feed requirements.","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"115 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114400819","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 : 2005-03-05DOI: 10.1109/AERO.2005.1559696
W. Kahle, J. Miller
There is a body of evidence, and a group of advocates, supporting the need for integrated system health management for space exploration systems. The advocates include operators responsible for complex and inherently risky decisions, and the technologists working in the domain of health management and looking for application for their products. Others in the decision loops take the view that health management is too expensive, or represents a technology paradigm shift that is not warranted. Within NASA, there have been two groups of technical experts studying this situation. Collectively, they have generated data supporting the view that health management systems have a positive impact on system safety, mission assurance and life cycle cost control. One of these groups is led by Bill Kahle and other NASA project managers, who have managed and/or proposed "technology risk reduction" demonstrations to increase the traditional technology readiness level (TRL) of health management processes and technologies. The experiments and demonstrations produce data needed for more ambitious health management technology applications. Well funded and successful within the constraints of the approved programs and projects, these demonstrations nevertheless have had limited success persuading decision makers, managers and designers of new and proposed programs to incorporate system-level health management technologies. The other group is led by Jim Miller and supported the NASA space architect's CRAI (capabilities, requirements, analyses, and integration) efforts by developing a capabilities breakdown structure (CBS) for the domain of IAHM&C (integrated avionics, health management, and controls). The CBS identifies the critical capabilities, provides definitions and metrics by which the effectiveness of these capabilities may be measured, and assessed the state of the art of these capabilities against a set of hypothetical scenarios (architectures) put forth for implementing the new exploration initiative. In the aggregate, the two groups define a comprehensive view that is required to accommodate and support the annual funding profile that program managers deal with continually, and which typically tends to obscure health management progress. Notwithstanding fiscal variability, funding health management piecemeal can still result in specific, quantifiable, and practical value to the overall health management goals. This paper provides insight into the thought processes and conclusions of these teams and reflects the thoroughness and specificity of the recommended investment areas and investment strategies. The authors propose that NASA need not make the total investment in these technologies since there is a considerable need and commensurate investment in the defense and private industry. The paper does not recommend a specific set of technologies for specific exploration application scenarios since these scenarios have not yet been fully developed. The paper do
{"title":"The practical value of health management in space exploration systems","authors":"W. Kahle, J. Miller","doi":"10.1109/AERO.2005.1559696","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559696","url":null,"abstract":"There is a body of evidence, and a group of advocates, supporting the need for integrated system health management for space exploration systems. The advocates include operators responsible for complex and inherently risky decisions, and the technologists working in the domain of health management and looking for application for their products. Others in the decision loops take the view that health management is too expensive, or represents a technology paradigm shift that is not warranted. Within NASA, there have been two groups of technical experts studying this situation. Collectively, they have generated data supporting the view that health management systems have a positive impact on system safety, mission assurance and life cycle cost control. One of these groups is led by Bill Kahle and other NASA project managers, who have managed and/or proposed \"technology risk reduction\" demonstrations to increase the traditional technology readiness level (TRL) of health management processes and technologies. The experiments and demonstrations produce data needed for more ambitious health management technology applications. Well funded and successful within the constraints of the approved programs and projects, these demonstrations nevertheless have had limited success persuading decision makers, managers and designers of new and proposed programs to incorporate system-level health management technologies. The other group is led by Jim Miller and supported the NASA space architect's CRAI (capabilities, requirements, analyses, and integration) efforts by developing a capabilities breakdown structure (CBS) for the domain of IAHM&C (integrated avionics, health management, and controls). The CBS identifies the critical capabilities, provides definitions and metrics by which the effectiveness of these capabilities may be measured, and assessed the state of the art of these capabilities against a set of hypothetical scenarios (architectures) put forth for implementing the new exploration initiative. In the aggregate, the two groups define a comprehensive view that is required to accommodate and support the annual funding profile that program managers deal with continually, and which typically tends to obscure health management progress. Notwithstanding fiscal variability, funding health management piecemeal can still result in specific, quantifiable, and practical value to the overall health management goals. This paper provides insight into the thought processes and conclusions of these teams and reflects the thoroughness and specificity of the recommended investment areas and investment strategies. The authors propose that NASA need not make the total investment in these technologies since there is a considerable need and commensurate investment in the defense and private industry. The paper does not recommend a specific set of technologies for specific exploration application scenarios since these scenarios have not yet been fully developed. The paper do","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121878051","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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