The Experts below are selected from a list of 7470 Experts worldwide ranked by ideXlab platform
R Brackett - One of the best experts on this subject based on the ideXlab platform.
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designing an open test software architecture featuring Lockheed Martin lm star spl reg case study
AUTOTESTCON, 2004Co-Authors: R Mcdonell, R BrackettAbstract:Nearly all of the automated test systems developed today are required to integrate with or at a minimum support the existing tests and test systems deployed in the depot and field. This involves supporting a wide range of tests developed in a variety of modern and legacy test development languages including LabWindows/CVI, LabVIEW, C/C++, Visual Basic, ATLAS, TCL, and HT-BASIC. The convergence of functionality across products and organizations for joint development and feature sets is also driving the movement towards highly reconfigurable test systems that are capable of adapting to multiple configurations. In addition, the convergence of products and functionality is also changing the development landscape to large contracts involving multiple suppliers working together to concurrently develop tests. Lastly, new test schemas, such as Automatic Test Markup Language (ATML), for defining test routines and results data in XML format are of growing concern to many test engineers regarding the integration of this technology among existing and new test systems. Each of these challenges emphasizes the need for an open test software architecture in next generation test systems that is capable of supporting tests developed in any test language, delivering a highly adaptable test architecture for multiple configurations, support for concurrent test development across multiple suppliers, and rapid insertion of new technologies such as ATML. This paper discusses the benefits of creating an open test software architecture and the latest test management software tools for designing an open test software architecture to meet each of these needs. The paper also features a case study of the recent Lockheed Martin Simulation, Training, & Support (LM STS) LM-STAR/spl reg/ open test software architecture designed for supporting military avionics, including the F-35 Joint Strike Fighter aircraft.
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Designing an open test software architecture featuring Lockheed Martin LM-STAR/spl reg/ case study
Proceedings AUTOTESTCON 2004., 1Co-Authors: R Mcdonell, R BrackettAbstract:Nearly all of the automated test systems developed today are required to integrate with or at a minimum support the existing tests and test systems deployed in the depot and field. This involves supporting a wide range of tests developed in a variety of modern and legacy test development languages including LabWindows/CVI, LabVIEW, C/C++, Visual Basic, ATLAS, TCL, and HT-BASIC. The convergence of functionality across products and organizations for joint development and feature sets is also driving the movement towards highly reconfigurable test systems that are capable of adapting to multiple configurations. In addition, the convergence of products and functionality is also changing the development landscape to large contracts involving multiple suppliers working together to concurrently develop tests. Lastly, new test schemas, such as Automatic Test Markup Language (ATML), for defining test routines and results data in XML format are of growing concern to many test engineers regarding the integration of this technology among existing and new test systems. Each of these challenges emphasizes the need for an open test software architecture in next generation test systems that is capable of supporting tests developed in any test language, delivering a highly adaptable test architecture for multiple configurations, support for concurrent test development across multiple suppliers, and rapid insertion of new technologies such as ATML. This paper discusses the benefits of creating an open test software architecture and the latest test management software tools for designing an open test software architecture to meet each of these needs. The paper also features a case study of the recent Lockheed Martin Simulation, Training, & Support (LM STS) LM-STAR/spl reg/ open test software architecture designed for supporting military avionics, including the F-35 Joint Strike Fighter aircraft.
P. E. Bradley - One of the best experts on this subject based on the ideXlab platform.
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off state conductance measurements of the nist Lockheed Martin miniature pulse tube flight cryocooler laboratory vs space
Advances in cryogenic engineering, 2002Co-Authors: D. R. Ladner, R. Radebaugh, P. E. BradleyAbstract:A two-stage miniature pulse tube (PT) cryocooler, designed for a Space Shuttle flight demonstration, was built and tested at Lockheed Martin Astronautics (LMA) and at the NIST Boulder Lab. The Miniature PT Flight Cryocooler (MPTFC) was designed to provide 0.15 W of cooling at 80 K with heat rejection at 275 K. It was developed as the smallest cryocooler of its kind for the purpose of demonstrating launch survivability and thermal performance in a zero-g environment. The flight version was fabricated as a Getaway Special (GAS) Payload. Although on-orbit cooling performance was not demonstrated because of failed primary batteries, the first off-state PT thermal conductance measurements in zero-g were conducted successfully using the secondary battery system. The data acquisition system and all flight diagnostic sensors performed nominally to provide 15 hours of zero-g warm-up data. The results of the cold head thermal conductance measurements both in zero-g aboard STS-90 and in the laboratory environment are compared to a thermal model for the two-stage PT, detailed in a separate presentation.
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Design and Test of the NIST/Lockheed Martin Miniature Pulse Tube Flight Cryocooler
Cryocoolers 11, 2002Co-Authors: P. E. Bradley, R. Radebaugh, J. H. Xiao, D. R. LadnerAbstract:A two-stage miniature pulse tube (PT) cryocooler, designed for a Space Shuttle flight demonstration, was built and tested at Lockheed Martin Astronautics (LMA) at Denver, CO and the NIST Boulder Laboratory. The Miniature PT Flight Cryocooler (MPTFC) was designed to provide 0.15 W of cooling at 80 K with heat rejection at 275 K. It was developed as the smallest cryocooler of its kind for the purpose of demonstrating launch survivability and thermal performance in a zero-g environment. A prototype laboratory version was first built and tested to provide information on component sizing and flow rates for comparison to numerical models. The flight version was then fabricated as a Getaway Special (GAS) Payload. Cost containment and manned flight safety constraints limited the extent of the MPTFC development to achieve performance optimization. Nonetheless, it reached 87 K driven by a commercially available tactical compressor with a swept volume of 0.75 cc. The on-orbit cooling performance was not demonstrated because of low battery voltage resulting from failed primary batteries. The first off-state PT thermal conductance measurements were successful, however, and the MPTFC also demonstrated the robustness of PT cryocoolers by surviving pro-launch vibration testing, shipping, and the launch and landing of STS-90 with no measurable performance degradation.
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design and test of the nist Lockheed Martin miniature pulse tube flight cryocooler
2002Co-Authors: P. E. Bradley, R. Radebaugh, J. H. Xiao, D. R. LadnerAbstract:A two-stage miniature pulse tube (PT) cryocooler, designed for a Space Shuttle flight demonstration, was built and tested at Lockheed Martin Astronautics (LMA) at Denver, CO and the NIST Boulder Laboratory. The Miniature PT Flight Cryocooler (MPTFC) was designed to provide 0.15 W of cooling at 80 K with heat rejection at 275 K. It was developed as the smallest cryocooler of its kind for the purpose of demonstrating launch survivability and thermal performance in a zero-g environment. A prototype laboratory version was first built and tested to provide information on component sizing and flow rates for comparison to numerical models. The flight version was then fabricated as a Getaway Special (GAS) Payload. Cost containment and manned flight safety constraints limited the extent of the MPTFC development to achieve performance optimization. Nonetheless, it reached 87 K driven by a commercially available tactical compressor with a swept volume of 0.75 cc. The on-orbit cooling performance was not demonstrated because of low battery voltage resulting from failed primary batteries. The first off-state PT thermal conductance measurements were successful, however, and the MPTFC also demonstrated the robustness of PT cryocoolers by surviving pro-launch vibration testing, shipping, and the launch and landing of STS-90 with no measurable performance degradation.
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Off-state conductance measurements of the NIST/Lockheed Martin miniature pulse tube flight cryocooler: Laboratory vs. Space
AIP Conference Proceedings, 2002Co-Authors: D. R. Ladner, R. Radebaugh, P. E. BradleyAbstract:A two-stage miniature pulse tube (PT) cryocooler, designed for a Space Shuttle flight demonstration, was built and tested at Lockheed Martin Astronautics (LMA) and at the NIST Boulder Lab. The Miniature PT Flight Cryocooler (MPTFC) was designed to provide 0.15 W of cooling at 80 K with heat rejection at 275 K. It was developed as the smallest cryocooler of its kind for the purpose of demonstrating launch survivability and thermal performance in a zero-g environment. The flight version was fabricated as a Getaway Special (GAS) Payload. Although on-orbit cooling performance was not demonstrated because of failed primary batteries, the first off-state PT thermal conductance measurements in zero-g were conducted successfully using the secondary battery system. The data acquisition system and all flight diagnostic sensors performed nominally to provide 15 hours of zero-g warm-up data. The results of the cold head thermal conductance measurements both in zero-g aboard STS-90 and in the laboratory environment are compared to a thermal model for the two-stage PT, detailed in a separate presentation.
D. R. Ladner - One of the best experts on this subject based on the ideXlab platform.
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off state conductance measurements of the nist Lockheed Martin miniature pulse tube flight cryocooler laboratory vs space
Advances in cryogenic engineering, 2002Co-Authors: D. R. Ladner, R. Radebaugh, P. E. BradleyAbstract:A two-stage miniature pulse tube (PT) cryocooler, designed for a Space Shuttle flight demonstration, was built and tested at Lockheed Martin Astronautics (LMA) and at the NIST Boulder Lab. The Miniature PT Flight Cryocooler (MPTFC) was designed to provide 0.15 W of cooling at 80 K with heat rejection at 275 K. It was developed as the smallest cryocooler of its kind for the purpose of demonstrating launch survivability and thermal performance in a zero-g environment. The flight version was fabricated as a Getaway Special (GAS) Payload. Although on-orbit cooling performance was not demonstrated because of failed primary batteries, the first off-state PT thermal conductance measurements in zero-g were conducted successfully using the secondary battery system. The data acquisition system and all flight diagnostic sensors performed nominally to provide 15 hours of zero-g warm-up data. The results of the cold head thermal conductance measurements both in zero-g aboard STS-90 and in the laboratory environment are compared to a thermal model for the two-stage PT, detailed in a separate presentation.
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Design and Test of the NIST/Lockheed Martin Miniature Pulse Tube Flight Cryocooler
Cryocoolers 11, 2002Co-Authors: P. E. Bradley, R. Radebaugh, J. H. Xiao, D. R. LadnerAbstract:A two-stage miniature pulse tube (PT) cryocooler, designed for a Space Shuttle flight demonstration, was built and tested at Lockheed Martin Astronautics (LMA) at Denver, CO and the NIST Boulder Laboratory. The Miniature PT Flight Cryocooler (MPTFC) was designed to provide 0.15 W of cooling at 80 K with heat rejection at 275 K. It was developed as the smallest cryocooler of its kind for the purpose of demonstrating launch survivability and thermal performance in a zero-g environment. A prototype laboratory version was first built and tested to provide information on component sizing and flow rates for comparison to numerical models. The flight version was then fabricated as a Getaway Special (GAS) Payload. Cost containment and manned flight safety constraints limited the extent of the MPTFC development to achieve performance optimization. Nonetheless, it reached 87 K driven by a commercially available tactical compressor with a swept volume of 0.75 cc. The on-orbit cooling performance was not demonstrated because of low battery voltage resulting from failed primary batteries. The first off-state PT thermal conductance measurements were successful, however, and the MPTFC also demonstrated the robustness of PT cryocoolers by surviving pro-launch vibration testing, shipping, and the launch and landing of STS-90 with no measurable performance degradation.
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design and test of the nist Lockheed Martin miniature pulse tube flight cryocooler
2002Co-Authors: P. E. Bradley, R. Radebaugh, J. H. Xiao, D. R. LadnerAbstract:A two-stage miniature pulse tube (PT) cryocooler, designed for a Space Shuttle flight demonstration, was built and tested at Lockheed Martin Astronautics (LMA) at Denver, CO and the NIST Boulder Laboratory. The Miniature PT Flight Cryocooler (MPTFC) was designed to provide 0.15 W of cooling at 80 K with heat rejection at 275 K. It was developed as the smallest cryocooler of its kind for the purpose of demonstrating launch survivability and thermal performance in a zero-g environment. A prototype laboratory version was first built and tested to provide information on component sizing and flow rates for comparison to numerical models. The flight version was then fabricated as a Getaway Special (GAS) Payload. Cost containment and manned flight safety constraints limited the extent of the MPTFC development to achieve performance optimization. Nonetheless, it reached 87 K driven by a commercially available tactical compressor with a swept volume of 0.75 cc. The on-orbit cooling performance was not demonstrated because of low battery voltage resulting from failed primary batteries. The first off-state PT thermal conductance measurements were successful, however, and the MPTFC also demonstrated the robustness of PT cryocoolers by surviving pro-launch vibration testing, shipping, and the launch and landing of STS-90 with no measurable performance degradation.
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Off-state conductance measurements of the NIST/Lockheed Martin miniature pulse tube flight cryocooler: Laboratory vs. Space
AIP Conference Proceedings, 2002Co-Authors: D. R. Ladner, R. Radebaugh, P. E. BradleyAbstract:A two-stage miniature pulse tube (PT) cryocooler, designed for a Space Shuttle flight demonstration, was built and tested at Lockheed Martin Astronautics (LMA) and at the NIST Boulder Lab. The Miniature PT Flight Cryocooler (MPTFC) was designed to provide 0.15 W of cooling at 80 K with heat rejection at 275 K. It was developed as the smallest cryocooler of its kind for the purpose of demonstrating launch survivability and thermal performance in a zero-g environment. The flight version was fabricated as a Getaway Special (GAS) Payload. Although on-orbit cooling performance was not demonstrated because of failed primary batteries, the first off-state PT thermal conductance measurements in zero-g were conducted successfully using the secondary battery system. The data acquisition system and all flight diagnostic sensors performed nominally to provide 15 hours of zero-g warm-up data. The results of the cold head thermal conductance measurements both in zero-g aboard STS-90 and in the laboratory environment are compared to a thermal model for the two-stage PT, detailed in a separate presentation.
R Mcdonell - One of the best experts on this subject based on the ideXlab platform.
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designing an open test software architecture featuring Lockheed Martin lm star spl reg case study
AUTOTESTCON, 2004Co-Authors: R Mcdonell, R BrackettAbstract:Nearly all of the automated test systems developed today are required to integrate with or at a minimum support the existing tests and test systems deployed in the depot and field. This involves supporting a wide range of tests developed in a variety of modern and legacy test development languages including LabWindows/CVI, LabVIEW, C/C++, Visual Basic, ATLAS, TCL, and HT-BASIC. The convergence of functionality across products and organizations for joint development and feature sets is also driving the movement towards highly reconfigurable test systems that are capable of adapting to multiple configurations. In addition, the convergence of products and functionality is also changing the development landscape to large contracts involving multiple suppliers working together to concurrently develop tests. Lastly, new test schemas, such as Automatic Test Markup Language (ATML), for defining test routines and results data in XML format are of growing concern to many test engineers regarding the integration of this technology among existing and new test systems. Each of these challenges emphasizes the need for an open test software architecture in next generation test systems that is capable of supporting tests developed in any test language, delivering a highly adaptable test architecture for multiple configurations, support for concurrent test development across multiple suppliers, and rapid insertion of new technologies such as ATML. This paper discusses the benefits of creating an open test software architecture and the latest test management software tools for designing an open test software architecture to meet each of these needs. The paper also features a case study of the recent Lockheed Martin Simulation, Training, & Support (LM STS) LM-STAR/spl reg/ open test software architecture designed for supporting military avionics, including the F-35 Joint Strike Fighter aircraft.
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Designing an open test software architecture featuring Lockheed Martin LM-STAR/spl reg/ case study
Proceedings AUTOTESTCON 2004., 1Co-Authors: R Mcdonell, R BrackettAbstract:Nearly all of the automated test systems developed today are required to integrate with or at a minimum support the existing tests and test systems deployed in the depot and field. This involves supporting a wide range of tests developed in a variety of modern and legacy test development languages including LabWindows/CVI, LabVIEW, C/C++, Visual Basic, ATLAS, TCL, and HT-BASIC. The convergence of functionality across products and organizations for joint development and feature sets is also driving the movement towards highly reconfigurable test systems that are capable of adapting to multiple configurations. In addition, the convergence of products and functionality is also changing the development landscape to large contracts involving multiple suppliers working together to concurrently develop tests. Lastly, new test schemas, such as Automatic Test Markup Language (ATML), for defining test routines and results data in XML format are of growing concern to many test engineers regarding the integration of this technology among existing and new test systems. Each of these challenges emphasizes the need for an open test software architecture in next generation test systems that is capable of supporting tests developed in any test language, delivering a highly adaptable test architecture for multiple configurations, support for concurrent test development across multiple suppliers, and rapid insertion of new technologies such as ATML. This paper discusses the benefits of creating an open test software architecture and the latest test management software tools for designing an open test software architecture to meet each of these needs. The paper also features a case study of the recent Lockheed Martin Simulation, Training, & Support (LM STS) LM-STAR/spl reg/ open test software architecture designed for supporting military avionics, including the F-35 Joint Strike Fighter aircraft.
P Wallis - One of the best experts on this subject based on the ideXlab platform.
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design fabrication of the Lockheed Martin solar cell demonstration experiment for the iss forward technology solar cell experiment ii
Photovoltaic Specialists Conference, 2009Co-Authors: S. Gasner, M. Tresemer, S. Billets, D. Bhatt, P WallisAbstract:The Naval Research Labs (NRL) has been funded for the second Forward Solar Cell Technology Experiment (FTSCE). As part of a risk reduction effort for future programs, Lockheed Martin Space Systems Company (LMSSC) fabricated a flight experiment for FTSCE II. The experiment consists of two coupons. The first coupon has UTJ and BTJM solar cells from Spectrolab and Emcore respectively. The second coupon has Spectrolab's next generation XTJ solar cell and Emcore's next generation ZTJM solar cell. In addition to getting AM0 electrical data and solar cell flight experience in low earth orbit for these solar cells, another objective of the experiment is to validate atomic oxygen protection designs for the solar cell and substrate. The coupons have been fabricated and delivered to NRL. The FTSCE II package will be mounted on the International Space Station in November 2009 and is expected to be in orbit approximately one year.
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Design & fabrication of the Lockheed Martin solar cell demonstration experiment for the ISS Forward Technology Solar Cell Experiment II
2009 34th IEEE Photovoltaic Specialists Conference (PVSC), 2009Co-Authors: S. Gasner, M. Tresemer, S. Billets, D. Bhatt, P WallisAbstract:The Naval Research Labs (NRL) has been funded for the second Forward Solar Cell Technology Experiment (FTSCE). As part of a risk reduction effort for future programs, Lockheed Martin Space Systems Company (LMSSC) fabricated a flight experiment for FTSCE II. The experiment consists of two coupons. The first coupon has UTJ and BTJM solar cells from Spectrolab and Emcore respectively. The second coupon has Spectrolab's next generation XTJ solar cell and Emcore's next generation ZTJM solar cell. In addition to getting AM0 electrical data and solar cell flight experience in low earth orbit for these solar cells, another objective of the experiment is to validate atomic oxygen protection designs for the solar cell and substrate. The coupons have been fabricated and delivered to NRL. The FTSCE II package will be mounted on the International Space Station in November 2009 and is expected to be in orbit approximately one year.
