Pub Date : 2017-06-08DOI: 10.1109/AERO.2017.7943817
R. Davidson, C. Bridges
Continual advancements in Earth Observation (EO) optical imager payloads has led to a significant increase in the volume of multispectral data generated onboard EO satellites. As a result, a growing onboard data bottleneck need to be alleviated. One technique commonly used is onboard image compression. However, the performance of traditional space qualified processors, such as radiation hardened FPGAs, are not able to meet current nor future onboard data processing requirements. Therefore, a new high capability hardware architecture is required. In previous work a new GPU accelerated scalable heterogeneous hardware architecture for onboard data processing was proposed. In this paper, two new CUDA GPU implementations of the state-of-the-art lossless multidimensional image compression algorithm CCSDS-123, are discussed. The first implementation is a generic CUDA implementation of the CCSDS-123 algorithm whilst the second is optimised specifically for multispectral EO imagery. Both implementations utilise image tiling to leverage an additional axis for algorithm parallelisation to increase processing throughput. The CUDA implementation and optimisation techniques deployed are discussed in the paper. In addition, compression ratio and throughput performance results are presented for each implementation. Further experimental studies into the relationships between algorithm user definable compression parameters, tile sizes, tile dimensions and the achieved compression ratio and throughput, were performed.
{"title":"GPU accelerated multispectral EO imagery optimised CCSDS-123 lossless compression implementation","authors":"R. Davidson, C. Bridges","doi":"10.1109/AERO.2017.7943817","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943817","url":null,"abstract":"Continual advancements in Earth Observation (EO) optical imager payloads has led to a significant increase in the volume of multispectral data generated onboard EO satellites. As a result, a growing onboard data bottleneck need to be alleviated. One technique commonly used is onboard image compression. However, the performance of traditional space qualified processors, such as radiation hardened FPGAs, are not able to meet current nor future onboard data processing requirements. Therefore, a new high capability hardware architecture is required. In previous work a new GPU accelerated scalable heterogeneous hardware architecture for onboard data processing was proposed. In this paper, two new CUDA GPU implementations of the state-of-the-art lossless multidimensional image compression algorithm CCSDS-123, are discussed. The first implementation is a generic CUDA implementation of the CCSDS-123 algorithm whilst the second is optimised specifically for multispectral EO imagery. Both implementations utilise image tiling to leverage an additional axis for algorithm parallelisation to increase processing throughput. The CUDA implementation and optimisation techniques deployed are discussed in the paper. In addition, compression ratio and throughput performance results are presented for each implementation. Further experimental studies into the relationships between algorithm user definable compression parameters, tile sizes, tile dimensions and the achieved compression ratio and throughput, were performed.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130286663","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 : 2017-06-08DOI: 10.1109/AERO.2017.7943706
S. Getty, J. Elsila, M. Balvin, W. Brinckerhoff, T. Cornish, Xiang Li, J. Ferrance, A. Grubisic, A. Southard
The Molecular Analyzer for Complex Refractory Organic-rich Surfaces, MACROS, is a novel instrument package being developed at NASA Goddard Space Flight Center. MACROS enables the in situ characterization of a sample's composition by coupling two powerful techniques into one compact instrument package: (1) laser desorption/ionization time-of-flight mass spectrometry (LDMS) for broad detection of inorganic mineral composition and non-volatile organics, and (2) liquid-phase extraction methods to gently isolate the soluble organic and inorganic fraction of a planetary powder for enrichment and detailed analysis by liquid chromatographic separation coupled to LDMS. The LDMS is capable of positive and negative ion detection, precision mass selection, and fragment analysis. Two modes are included for LDMS: single laser LDMS as the broad survey mode and two step laser mass spectrometry (L2MS). The liquid-phase extraction will be done in a newly designed extraction module (EM) prototype, providing selectivity in the analysis of a complex sample. For the sample collection, a diamond drill front end will be used to collect rock/icy powder. With all these components and capabilities together, MACROS offers a versatile analytical instrument for a mission targeting an icy moon, carbonaceous asteroid, or comet, to fully characterize the surface composition and advance our understanding of the chemical inventory present on that body.
{"title":"Molecular analyzer for Complex Refractory Organic-rich Surfaces (MACROS)","authors":"S. Getty, J. Elsila, M. Balvin, W. Brinckerhoff, T. Cornish, Xiang Li, J. Ferrance, A. Grubisic, A. Southard","doi":"10.1109/AERO.2017.7943706","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943706","url":null,"abstract":"The Molecular Analyzer for Complex Refractory Organic-rich Surfaces, MACROS, is a novel instrument package being developed at NASA Goddard Space Flight Center. MACROS enables the in situ characterization of a sample's composition by coupling two powerful techniques into one compact instrument package: (1) laser desorption/ionization time-of-flight mass spectrometry (LDMS) for broad detection of inorganic mineral composition and non-volatile organics, and (2) liquid-phase extraction methods to gently isolate the soluble organic and inorganic fraction of a planetary powder for enrichment and detailed analysis by liquid chromatographic separation coupled to LDMS. The LDMS is capable of positive and negative ion detection, precision mass selection, and fragment analysis. Two modes are included for LDMS: single laser LDMS as the broad survey mode and two step laser mass spectrometry (L2MS). The liquid-phase extraction will be done in a newly designed extraction module (EM) prototype, providing selectivity in the analysis of a complex sample. For the sample collection, a diamond drill front end will be used to collect rock/icy powder. With all these components and capabilities together, MACROS offers a versatile analytical instrument for a mission targeting an icy moon, carbonaceous asteroid, or comet, to fully characterize the surface composition and advance our understanding of the chemical inventory present on that body.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"15 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122958802","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 : 2017-06-08DOI: 10.1109/AERO.2017.7943778
M. Bentum
Recent studies on extra solar planets (exoplanets) provide us with a new glimpse into the Milky Way's composition. Exoplanets appear to be very typical around Sunlike stars. Most of these exoplanets are observed via indirect measurements. If a direct radio observation of the exoplanet's signal was possible, new scientific information will help us in the search for Earth like planets. Magnetised exoplanets are expected to emit strongly at radio wavelengths, in the same way as magnetised planets in our own solar system. Direct radio observations of exoplanets, therefore, will give important additional information to science. It would confirm that the planet has a magnetic field and it will also put a limit on the magnetic field strength near the surface of the planet. The determination of circular polarisation would indicate the source of the magnetic hemisphere and would give limits on the plasma density in the magnetosphere. However, not a single exoplanet radio detection have been measured until now. There are two reasons for this: the weakness of the signal and the frequency range in which the signal will appear — very low frequencies. The only solution to detect these weak signals from exoplanets is to realise a space-based radio telescope. Space based ultra-long wavelength radio astronomy has recently gained interest. The need for large effective apertures spread over long ranges implies that advanced technologies are required, which is in reach at this moment. This together with the unexplored frequency band below 30 MHz makes these initiatives very interesting. A space or Lunar based low-frequency radio array would suffer significantly less from the limitations and hence would open up the last, virtually unexplored frequency domain in the electromagnetic spectrum. In this paper we will present the development of a space-based radio telescope for detection exoplanets in the ultra-long wavelength range. This includes a system concept, and the algorithms to be used as a direct exoplanet radio observatory.
{"title":"The search for exoplanets using ultra-long wavelength radio astronomy","authors":"M. Bentum","doi":"10.1109/AERO.2017.7943778","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943778","url":null,"abstract":"Recent studies on extra solar planets (exoplanets) provide us with a new glimpse into the Milky Way's composition. Exoplanets appear to be very typical around Sunlike stars. Most of these exoplanets are observed via indirect measurements. If a direct radio observation of the exoplanet's signal was possible, new scientific information will help us in the search for Earth like planets. Magnetised exoplanets are expected to emit strongly at radio wavelengths, in the same way as magnetised planets in our own solar system. Direct radio observations of exoplanets, therefore, will give important additional information to science. It would confirm that the planet has a magnetic field and it will also put a limit on the magnetic field strength near the surface of the planet. The determination of circular polarisation would indicate the source of the magnetic hemisphere and would give limits on the plasma density in the magnetosphere. However, not a single exoplanet radio detection have been measured until now. There are two reasons for this: the weakness of the signal and the frequency range in which the signal will appear — very low frequencies. The only solution to detect these weak signals from exoplanets is to realise a space-based radio telescope. Space based ultra-long wavelength radio astronomy has recently gained interest. The need for large effective apertures spread over long ranges implies that advanced technologies are required, which is in reach at this moment. This together with the unexplored frequency band below 30 MHz makes these initiatives very interesting. A space or Lunar based low-frequency radio array would suffer significantly less from the limitations and hence would open up the last, virtually unexplored frequency domain in the electromagnetic spectrum. In this paper we will present the development of a space-based radio telescope for detection exoplanets in the ultra-long wavelength range. This includes a system concept, and the algorithms to be used as a direct exoplanet radio observatory.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"6 5","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"120915624","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 : 2017-06-07DOI: 10.1109/AERO.2017.7943840
B. Allen, Catherine Borst, Scott Kidney, M. Mimovich, Chris Paavola, Timothy J. Pargett, P. Wilke, Christian Smith, K. Ishimura, Y. Takei, S. Yasuda
Inherently nonlinear vibration isolation systems offer compelling analytical performance advantages over their linear alternates. Verification testing followed by post-test correlation is essential to convincing otherwise conservative project management teams to adopt these technologies for their mission. This paper details a comprehensive test verification program developed and executed for a novel vibration isolation system developed for the Soft X-ray Spectrometer (SXS) onboard ASTRO-H (named Hitomi after launch). More specifically, the dual-stage / thermally conductive / nonlinear vibration isolation system developed for on-orbit amelioration of cryocooler-induced mechanical vibration, needed to undergo ground testing to demonstrate both on-orbit performance and launch induced response level rejection to protect sensitive payload temperature control components. The system, referred to as the VIS, realizes both small signal transmissibility at high frequency and small acceleration and displacement against vibration during launch and ground testing.
{"title":"Ground based test verification of a nonlinear vibration isolation system for cryocoolers of the Soft X-ray Spectrometer (SXS) onboard ASTRO-H (Hitomi)","authors":"B. Allen, Catherine Borst, Scott Kidney, M. Mimovich, Chris Paavola, Timothy J. Pargett, P. Wilke, Christian Smith, K. Ishimura, Y. Takei, S. Yasuda","doi":"10.1109/AERO.2017.7943840","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943840","url":null,"abstract":"Inherently nonlinear vibration isolation systems offer compelling analytical performance advantages over their linear alternates. Verification testing followed by post-test correlation is essential to convincing otherwise conservative project management teams to adopt these technologies for their mission. This paper details a comprehensive test verification program developed and executed for a novel vibration isolation system developed for the Soft X-ray Spectrometer (SXS) onboard ASTRO-H (named Hitomi after launch). More specifically, the dual-stage / thermally conductive / nonlinear vibration isolation system developed for on-orbit amelioration of cryocooler-induced mechanical vibration, needed to undergo ground testing to demonstrate both on-orbit performance and launch induced response level rejection to protect sensitive payload temperature control components. The system, referred to as the VIS, realizes both small signal transmissibility at high frequency and small acceleration and displacement against vibration during launch and ground testing.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-06-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130508341","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 : 2017-05-01DOI: 10.1109/AERO.2017.7943907
G. Kuperman, Bow-Nan Cheng
With the emergence of the Internet of Things, there is a renewed focus on multi-hop wireless networking to connect these systems of smart-devices. Many of the proposals to support this new networking paradigm continue to use the concept of routing: a path between users is formed via a series of point-to-point links. We believe that the characteristics of the wireless environment inherently make path-based routing unsuitable for wireless networking, and that new approaches need to be considered. In this paper, we examine the effectiveness of routing for reliably and efficiently delivering data in a wireless network. Specifically, we demonstrate that path-based routing (1) experiences high packet loss due to the inherently unreliable nature of control information, (2) is unable to ensure reliable message delivery in a lossy environment, and (3) incurs a high cost for route maintenance and repair. We compare path-based routing to newer “smart-flooding” protocols, and show that these alternative approaches provide better delivery at lower cost.
{"title":"Characterizing deficiencies of path-based routing for wireless multi-hop networks","authors":"G. Kuperman, Bow-Nan Cheng","doi":"10.1109/AERO.2017.7943907","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943907","url":null,"abstract":"With the emergence of the Internet of Things, there is a renewed focus on multi-hop wireless networking to connect these systems of smart-devices. Many of the proposals to support this new networking paradigm continue to use the concept of routing: a path between users is formed via a series of point-to-point links. We believe that the characteristics of the wireless environment inherently make path-based routing unsuitable for wireless networking, and that new approaches need to be considered. In this paper, we examine the effectiveness of routing for reliably and efficiently delivering data in a wireless network. Specifically, we demonstrate that path-based routing (1) experiences high packet loss due to the inherently unreliable nature of control information, (2) is unable to ensure reliable message delivery in a lossy environment, and (3) incurs a high cost for route maintenance and repair. We compare path-based routing to newer “smart-flooding” protocols, and show that these alternative approaches provide better delivery at lower cost.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-05-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129157246","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 : 2017-03-10DOI: 10.1109/AERO.2017.7943583
Tara P. Polsgrove, H. Thomas, Walter Stephens, Tim Collins, M. Rucker, M. Gernhardt, Mathew R. Zwack, Patrick Dees
The total ascent vehicle mass drives performance requirements for the Mars descent systems and the Earth to Mars transportation elements. Minimizing Mars Ascent Vehicle (MAV) mass is a priority and minimizing the crew cabin size and mass is one way to do that. Human missions to Mars may utilize several small cabins where crew members could live for days up to a couple of weeks. A common crew cabin design that can perform in each of these applications is desired and could reduce the overall mission cost. However, for the MAV, the crew cabin size and mass can have a large impact on vehicle design and performance. This paper explores the sensitivities to trajectory, propulsion, crew cabin size and the benefits and impacts of using a common crew cabin design for the MAV. Results of these trades will be presented along with mass and performance estimates for the selected design.
{"title":"Human Mars ascent vehicle configuration and performance sensitivities","authors":"Tara P. Polsgrove, H. Thomas, Walter Stephens, Tim Collins, M. Rucker, M. Gernhardt, Mathew R. Zwack, Patrick Dees","doi":"10.1109/AERO.2017.7943583","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943583","url":null,"abstract":"The total ascent vehicle mass drives performance requirements for the Mars descent systems and the Earth to Mars transportation elements. Minimizing Mars Ascent Vehicle (MAV) mass is a priority and minimizing the crew cabin size and mass is one way to do that. Human missions to Mars may utilize several small cabins where crew members could live for days up to a couple of weeks. A common crew cabin design that can perform in each of these applications is desired and could reduce the overall mission cost. However, for the MAV, the crew cabin size and mass can have a large impact on vehicle design and performance. This paper explores the sensitivities to trajectory, propulsion, crew cabin size and the benefits and impacts of using a common crew cabin design for the MAV. Results of these trades will be presented along with mass and performance estimates for the selected design.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"66 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"117316501","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 : 2017-03-09DOI: 10.1109/AERO.2017.7943823
D. Seal
As a follow-on to the Technical Capability Assessment Team, in 2015 NASA began seven Agency-wide efforts to seek out opportunities to improve the effectiveness of NASA operations. One of these technical teams is the Mission Operations Planning team, charged with increasing interactions and efficiency for planning of mission activities. That team is chaired by the author with representatives from eight other centers across the Agency. As the strategic architects for the vision of agency-wide ops planning, the team has identified a number of new initiatives and techniques to improve planning, including: breaking down walls within centers which obstruct multi-mission planning; breaking down walls agency-wide which obstruct the sharing of ops planning lessons and capabilities; strengthening the community of practice of ops planning capability developers; establishing best practices for a variety of types of ops planning; defining standards for activity plans and timelines, and plan inputs; and recommending the presence of “multi-mission operations champions” within each center to implement these recommendations into the next decade.
{"title":"NASA's current initiative to improve operations planning","authors":"D. Seal","doi":"10.1109/AERO.2017.7943823","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943823","url":null,"abstract":"As a follow-on to the Technical Capability Assessment Team, in 2015 NASA began seven Agency-wide efforts to seek out opportunities to improve the effectiveness of NASA operations. One of these technical teams is the Mission Operations Planning team, charged with increasing interactions and efficiency for planning of mission activities. That team is chaired by the author with representatives from eight other centers across the Agency. As the strategic architects for the vision of agency-wide ops planning, the team has identified a number of new initiatives and techniques to improve planning, including: breaking down walls within centers which obstruct multi-mission planning; breaking down walls agency-wide which obstruct the sharing of ops planning lessons and capabilities; strengthening the community of practice of ops planning capability developers; establishing best practices for a variety of types of ops planning; defining standards for activity plans and timelines, and plan inputs; and recommending the presence of “multi-mission operations champions” within each center to implement these recommendations into the next decade.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"131 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124882897","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 : 2017-03-06DOI: 10.1109/AERO.2017.7943937
J. Burt, D. Steinfeld
The National Aeronautics and Space Administration (NASA) Goddard's Rideshare Office estimates that between 2013 and 2022, NASA launches of primary satellites will have left unused more than 20,371 kilograms of excess capacity. This equates to hundreds of millions of dollars in launch-vehicle costs going unutilized. To fill this void with a standard CubeSat or SmallSat spacecraft platform, which when required to be more reliable, still will cost in the neighborhood of $1M a kilogram, making it prohibitively expensive. A newly proposed solution, which NASA is pursuing, is called the Capsulation Satellite or CapSat. CapSat is a modularized, pressurized, thermally controlled spacecraft designed to host ruggedized commercially available instrumentation in a terrestriallike environment on orbit. Using a technique that is under review for a patent, CapSat actively manages internal air temperatures in a manner similar to a household thermostat. This gives CapSat high-thermal stability, which, in turn, provides component longevity. CapSat was specifically designed to take advantage of the United States Air Force (USAF) Rideshare Program and the Evolved Expendable Launch Vehicle Secondary Payload Adaptor, or ESPA ring. The ESPA ring comes in two sizes: standard and Grande. CapSat primarily will take advantage of the ESPA Grande to provide a 300-kilogram payload capability per attachment point, with up to four attachment points per ring. This approach combines a high-mass capability with a proven Rideshare mechanical interface and secondary payload management infrastructure. Opportunities for ESPA-based co-manifests are continuing to expand. The CapSat program is currently funded to design and build a limited prototype and perform thermal-vacuum testing. CapSat is currently in the concept/study phase for both single missions and constellation of earth- and space-observing missions. One of these studies includes land imaging using state-of-the-art advanced infrared detector technology. This paper will report on the current status of the CapSat hardware design, testing, and results as well as any openly available advanced concept study results. The CapSat solution is intended to be a game-changing paradigm shift. CapSat will repurpose currently available, already-proven technology to reduce spaceflight hardware costs to less than $50,000 per kilogram.
{"title":"Capsulation satellite or CapSat: A low-cost, reliable, rapid-response spacecraft platform","authors":"J. Burt, D. Steinfeld","doi":"10.1109/AERO.2017.7943937","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943937","url":null,"abstract":"The National Aeronautics and Space Administration (NASA) Goddard's Rideshare Office estimates that between 2013 and 2022, NASA launches of primary satellites will have left unused more than 20,371 kilograms of excess capacity. This equates to hundreds of millions of dollars in launch-vehicle costs going unutilized. To fill this void with a standard CubeSat or SmallSat spacecraft platform, which when required to be more reliable, still will cost in the neighborhood of $1M a kilogram, making it prohibitively expensive. A newly proposed solution, which NASA is pursuing, is called the Capsulation Satellite or CapSat. CapSat is a modularized, pressurized, thermally controlled spacecraft designed to host ruggedized commercially available instrumentation in a terrestriallike environment on orbit. Using a technique that is under review for a patent, CapSat actively manages internal air temperatures in a manner similar to a household thermostat. This gives CapSat high-thermal stability, which, in turn, provides component longevity. CapSat was specifically designed to take advantage of the United States Air Force (USAF) Rideshare Program and the Evolved Expendable Launch Vehicle Secondary Payload Adaptor, or ESPA ring. The ESPA ring comes in two sizes: standard and Grande. CapSat primarily will take advantage of the ESPA Grande to provide a 300-kilogram payload capability per attachment point, with up to four attachment points per ring. This approach combines a high-mass capability with a proven Rideshare mechanical interface and secondary payload management infrastructure. Opportunities for ESPA-based co-manifests are continuing to expand. The CapSat program is currently funded to design and build a limited prototype and perform thermal-vacuum testing. CapSat is currently in the concept/study phase for both single missions and constellation of earth- and space-observing missions. One of these studies includes land imaging using state-of-the-art advanced infrared detector technology. This paper will report on the current status of the CapSat hardware design, testing, and results as well as any openly available advanced concept study results. The CapSat solution is intended to be a game-changing paradigm shift. CapSat will repurpose currently available, already-proven technology to reduce spaceflight hardware costs to less than $50,000 per kilogram.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125896411","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 : 2017-03-05DOI: 10.1109/AERO.2017.7943609
M. Deans, J. Márquez, T. Cohen, Matthew J. Miller, I. Deliz, S. Hillenius, J. Hoffman, Y. J. Lee, D. Lees, J. Norheim, D. Lim
In June of 2016, the Biologic Analog Science Associated with Lava Terrains (BASALT) research project conducted its first field deployment, which we call BASALT-1. BASALT-1 consisted of a science-driven field campaign in a volcanic field in Idaho as a simulated human mission to Mars. Scientists and mission operators were provided a suite of ground software tools that we refer to collectively as Minerva to carry out their work. Minerva provides capabilities for traverse planning and route optimization, timeline generation and display, procedure management, execution monitoring, data archiving, visualization, and search. This paper describes the Minerva architecture, constituent components, use cases, and some preliminary findings from the BASALT-1 campaign.
{"title":"Minerva: User-centered science operations software capability for future human exploration","authors":"M. Deans, J. Márquez, T. Cohen, Matthew J. Miller, I. Deliz, S. Hillenius, J. Hoffman, Y. J. Lee, D. Lees, J. Norheim, D. Lim","doi":"10.1109/AERO.2017.7943609","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943609","url":null,"abstract":"In June of 2016, the Biologic Analog Science Associated with Lava Terrains (BASALT) research project conducted its first field deployment, which we call BASALT-1. BASALT-1 consisted of a science-driven field campaign in a volcanic field in Idaho as a simulated human mission to Mars. Scientists and mission operators were provided a suite of ground software tools that we refer to collectively as Minerva to carry out their work. Minerva provides capabilities for traverse planning and route optimization, timeline generation and display, procedure management, execution monitoring, data archiving, visualization, and search. This paper describes the Minerva architecture, constituent components, use cases, and some preliminary findings from the BASALT-1 campaign.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129905270","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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