Pub Date : 2017-03-05DOI: 10.1109/AERO.2017.7943605
A. Donnellan, Joseph Green, A. Ansar, Joe Aletky, M. Glasscoe, Y. Ben‐Zion, R. Arrowsmith, S. DeLong
Large earthquakes cause billions of dollars in damage and extensive loss of life and property. Geodetic and topographic imaging provide measurements of transient and long-term crustal deformation needed to monitor fault zones and understand earthquakes. Earthquake-induced strain and rupture characteristics are expressed in topographic features imprinted on the landscapes of fault zones. Small UAVs provide an efficient and flexible means to collect multi-angle imagery to reconstruct fine scale fault zone topography and provide surrogate data to determine requirements for and to simulate future platforms for air- and space-based multi-angle imaging.
{"title":"Imaging of earthquake faults using small UAVs as a pathfinder for air and space observations","authors":"A. Donnellan, Joseph Green, A. Ansar, Joe Aletky, M. Glasscoe, Y. Ben‐Zion, R. Arrowsmith, S. DeLong","doi":"10.1109/AERO.2017.7943605","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943605","url":null,"abstract":"Large earthquakes cause billions of dollars in damage and extensive loss of life and property. Geodetic and topographic imaging provide measurements of transient and long-term crustal deformation needed to monitor fault zones and understand earthquakes. Earthquake-induced strain and rupture characteristics are expressed in topographic features imprinted on the landscapes of fault zones. Small UAVs provide an efficient and flexible means to collect multi-angle imagery to reconstruct fine scale fault zone topography and provide surrogate data to determine requirements for and to simulate future platforms for air- and space-based multi-angle imaging.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"35 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":"128389924","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943563
Cherice Moore, Randall Svetlik, Antony Williams
Long duration spaceflight has a negative effect on the human body, and exercise countermeasures are used onboard the International Space Station (ISS) to minimize bone and muscle loss, combatting these effects. Given the importance of these hardware systems to the health of the crew, this equipment must continue to be readily available. Designing spaceflight exercise hardware to meet high reliability and availability standards has proven to be challenging throughout the time the crewmembers have been living on ISS beginning in 2000. Furthermore, restoring operational capability after a failure is clearly time-critical, but can be problematic given the challenges of troubleshooting the problem from 220 miles away. Several best-practices have been leveraged in seeking to maximize availability of these exercise systems, including designing for robustness, implementing diagnostic instrumentation, relying on user feedback, and providing ample maintenance and sparing. These factors have enhanced the reliability of hardware systems, and therefore have contributed to keeping the crewmembers healthy upon return to Earth. This paper will review the failure history for three spaceflight exercise countermeasure systems identifying lessons learned that can help improve future systems. Specifically, the Treadmill with Vibration Isolation and Stabilization System (TVIS), Cycle Ergometer with Vibration Isolation and Stabilization System (CEVIS), and the Advanced Resistive Exercise Device (ARED) will be reviewed, analyzed, and conclusions identified so as to provide guidance for improving future exercise hardware designs. These lessons learned, paired with thorough testing, offer a path towards reduced system down-time.
{"title":"Designing for reliability and robustness in international space station exercise countermeasures systems","authors":"Cherice Moore, Randall Svetlik, Antony Williams","doi":"10.1109/AERO.2017.7943563","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943563","url":null,"abstract":"Long duration spaceflight has a negative effect on the human body, and exercise countermeasures are used onboard the International Space Station (ISS) to minimize bone and muscle loss, combatting these effects. Given the importance of these hardware systems to the health of the crew, this equipment must continue to be readily available. Designing spaceflight exercise hardware to meet high reliability and availability standards has proven to be challenging throughout the time the crewmembers have been living on ISS beginning in 2000. Furthermore, restoring operational capability after a failure is clearly time-critical, but can be problematic given the challenges of troubleshooting the problem from 220 miles away. Several best-practices have been leveraged in seeking to maximize availability of these exercise systems, including designing for robustness, implementing diagnostic instrumentation, relying on user feedback, and providing ample maintenance and sparing. These factors have enhanced the reliability of hardware systems, and therefore have contributed to keeping the crewmembers healthy upon return to Earth. This paper will review the failure history for three spaceflight exercise countermeasure systems identifying lessons learned that can help improve future systems. Specifically, the Treadmill with Vibration Isolation and Stabilization System (TVIS), Cycle Ergometer with Vibration Isolation and Stabilization System (CEVIS), and the Advanced Resistive Exercise Device (ARED) will be reviewed, analyzed, and conclusions identified so as to provide guidance for improving future exercise hardware designs. These lessons learned, paired with thorough testing, offer a path towards reduced system down-time.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"25 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125146183","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943637
J. C. Porcello
Communications systems can obtain substantial benefits from increased intelligence. Improvements to communications include increased spectral situational awareness, spectral optimization, and robust operation in dynamic and demanding communications environments. Furthermore, complex communication systems require a high degree of autonomous intelligence to optimize performance under such varying conditions. Machine Learning Algorithms provide a means to increase the intrinsic intelligence of wideband communication systems. This paper considers the use of Machine Learning Algorithms to increase the intelligence of communication systems. Specifically, the focus of this paper is to sense and learn the communication environment in real-time and optimize system parameters to maximize end-to-end performance. Communications systems have existing adaptive capabilities in many subsystems such as equalization. The focus in this paper is top level system intelligence by learning from the environment, and based on the system capabilities determine an optimal mode in the solution space in real-time. Furthermore, the goal of this paper is to consider implementation of Machine Learning Algorithms using FPGAs. Design data for implementing Machine Learning Algorithms using FPGAs is provided in the paper as well as reference circuits for implementation. Finally, an example implementation of a Machine Learning Algorithm for intelligent communications is provided based on implementation in a Xilinx UltraScale FPGA.
{"title":"Designing and implementing Machine Learning Algorithms for advanced communications using FPGAs","authors":"J. C. Porcello","doi":"10.1109/AERO.2017.7943637","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943637","url":null,"abstract":"Communications systems can obtain substantial benefits from increased intelligence. Improvements to communications include increased spectral situational awareness, spectral optimization, and robust operation in dynamic and demanding communications environments. Furthermore, complex communication systems require a high degree of autonomous intelligence to optimize performance under such varying conditions. Machine Learning Algorithms provide a means to increase the intrinsic intelligence of wideband communication systems. This paper considers the use of Machine Learning Algorithms to increase the intelligence of communication systems. Specifically, the focus of this paper is to sense and learn the communication environment in real-time and optimize system parameters to maximize end-to-end performance. Communications systems have existing adaptive capabilities in many subsystems such as equalization. The focus in this paper is top level system intelligence by learning from the environment, and based on the system capabilities determine an optimal mode in the solution space in real-time. Furthermore, the goal of this paper is to consider implementation of Machine Learning Algorithms using FPGAs. Design data for implementing Machine Learning Algorithms using FPGAs is provided in the paper as well as reference circuits for implementation. Finally, an example implementation of a Machine Learning Algorithm for intelligent communications is provided based on implementation in a Xilinx UltraScale FPGA.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"127 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116151403","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943612
Peter Sullivan, Michael Bernas, E. Liggett, M. Eastwood, R. Green
Imaging spectroscopy places high demands upon detector performance. The dynamic range, linearity, and sensitivity must be maintained at high frame rates, and artifacts must be minimized across large focal plane array (FPA) formats. In this contribution, we discuss the Teledyne CHROMA HgCdTe FPA in the context of imaging spectrometer applications. The FPA was characterized in a laboratory thermal-vacuum chamber that allowed the read noise, dark current, well capacity, linearity, and crosstalk to be measured. Results are presented across a range of operating temperatures and pixel clock rates. Additionally, the outcomes of radiation testing to 100 krad TID are discussed. The results of these characterizations are critical to the designs and performance predictions of future imaging spectrometers utilizing the HgCdTe CHROMA FPA.
{"title":"Characterization of the Teledyne CHROMA HgCdTe detector for imaging spectrometers","authors":"Peter Sullivan, Michael Bernas, E. Liggett, M. Eastwood, R. Green","doi":"10.1109/AERO.2017.7943612","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943612","url":null,"abstract":"Imaging spectroscopy places high demands upon detector performance. The dynamic range, linearity, and sensitivity must be maintained at high frame rates, and artifacts must be minimized across large focal plane array (FPA) formats. In this contribution, we discuss the Teledyne CHROMA HgCdTe FPA in the context of imaging spectrometer applications. The FPA was characterized in a laboratory thermal-vacuum chamber that allowed the read noise, dark current, well capacity, linearity, and crosstalk to be measured. Results are presented across a range of operating temperatures and pixel clock rates. Additionally, the outcomes of radiation testing to 100 krad TID are discussed. The results of these characterizations are critical to the designs and performance predictions of future imaging spectrometers utilizing the HgCdTe CHROMA FPA.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"3 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122039437","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943873
J. Marshall, R. Ferguson, David Matthes, Lisa Assadzadeh
This paper describes some of the initial steps BAE Systems' space electronics group is taking to become familiar with an MBSE tool and apply it to our current onboard hardware development projects as we shape the best ways to apply these to a product oriented multi-tiered set of spacecraft electronic items: silicon circuits, IP cores, components, modules, boxes and systems with their associated firmware, gateware and software and test equipment.1
{"title":"Transitioning model based systems engineering to onboard spacecraft electronics","authors":"J. Marshall, R. Ferguson, David Matthes, Lisa Assadzadeh","doi":"10.1109/AERO.2017.7943873","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943873","url":null,"abstract":"This paper describes some of the initial steps BAE Systems' space electronics group is taking to become familiar with an MBSE tool and apply it to our current onboard hardware development projects as we shape the best ways to apply these to a product oriented multi-tiered set of spacecraft electronic items: silicon circuits, IP cores, components, modules, boxes and systems with their associated firmware, gateware and software and test equipment.1","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123985788","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943780
Erick J. Sturm
During the final five orbits of Cassini's mission, the spacecraft will get closer to Saturn than it has ever been. These five orbits were designed to be as deep in the atmosphere as Cassini could safely fly; however, recent occultation data of Saturn's atmosphere suggest that it is contracting. Given this contraction, the primary concern during these orbits has shifted from spacecraft health and safety to loss of science value. This paper explores a scenario for modifying the Cassini spacecraft's trajectory, during these final orbits, such that it dips deeper into Saturn's atmosphere. This scenario describes the method for in-situ detection of Saturn's atmospheric state, the locations and sizes of maneuvers that would reduce the final periapsis altitudes, the effects of such maneuvers on the remaining trajectory, and the risks involved. The result is that a periapsis-lowering, “pop-down” maneuver is feasible during Cassini's final orbits. Risk to the spacecraft is minimized by using the attitude control thrusters as density detectors during the first three atmospheric transits of the final five orbits. Should these transits reveal sufficiently low density and should sufficient propellant remain, then the Cassini project will consider performing the maneuver.
{"title":"Diving deeper: Exploring the feasibility of lowering Cassini's final orbits","authors":"Erick J. Sturm","doi":"10.1109/AERO.2017.7943780","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943780","url":null,"abstract":"During the final five orbits of Cassini's mission, the spacecraft will get closer to Saturn than it has ever been. These five orbits were designed to be as deep in the atmosphere as Cassini could safely fly; however, recent occultation data of Saturn's atmosphere suggest that it is contracting. Given this contraction, the primary concern during these orbits has shifted from spacecraft health and safety to loss of science value. This paper explores a scenario for modifying the Cassini spacecraft's trajectory, during these final orbits, such that it dips deeper into Saturn's atmosphere. This scenario describes the method for in-situ detection of Saturn's atmospheric state, the locations and sizes of maneuvers that would reduce the final periapsis altitudes, the effects of such maneuvers on the remaining trajectory, and the risks involved. The result is that a periapsis-lowering, “pop-down” maneuver is feasible during Cassini's final orbits. Risk to the spacecraft is minimized by using the attitude control thrusters as density detectors during the first three atmospheric transits of the final five orbits. Should these transits reveal sufficiently low density and should sufficient propellant remain, then the Cassini project will consider performing the maneuver.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"88 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123354521","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943884
Shannon T. Brown, P. Focardi, A. Kitiyakara, F. Maiwald, L. Milligan, O. Montes, S. Padmanabhan, R. Redick, D. Russel, V. Bach, P. Walkemeyer
The Compact Ocean Wind Vector Radiometer (COWVR) is new type of conical microwave sensor ideal for small satellite implementation. This paper provides an overview of the COWVR sensor, mission and provides perspectives for the future of this technology to enable low-cost sustainable passive microwave observations into the next decade.
{"title":"The COWVR Mission: Demonstrating the capability of a new generation of small satellite weather sensors","authors":"Shannon T. Brown, P. Focardi, A. Kitiyakara, F. Maiwald, L. Milligan, O. Montes, S. Padmanabhan, R. Redick, D. Russel, V. Bach, P. Walkemeyer","doi":"10.1109/AERO.2017.7943884","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943884","url":null,"abstract":"The Compact Ocean Wind Vector Radiometer (COWVR) is new type of conical microwave sensor ideal for small satellite implementation. This paper provides an overview of the COWVR sensor, mission and provides perspectives for the future of this technology to enable low-cost sustainable passive microwave observations into the next decade.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121863661","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943690
C. A. Pascucci, Michael Szmuk, Behçet Açikmese
This paper addresses the control allocation problem for an over-actuated system with a nonlinear relation between the control inputs and the realized force and torque vectors. Specifically, we consider a multi-engine rocket example where the attained force and torque vectors are nonlinear functions of the thrust magnitudes and engine gimbal angles. Since the system is over-actuated, the surface defining this nonlinear relationship represents a non-unique map between the control variables and the resultant force and torque vectors. In this work, our goal is to command the actuators to produce desired force and torque vectors with minimal actuator reconfiguration effort, subject to actuator dynamics and constraints (e.g. slew-rates, maximum gimbal angles). In achieving this objective, the control space is traversed in a way that preserves the force and torque impulse requested from the control allocator, thus ensuring that the transient motion of the actuators produces the desired change in linear and angular momentum. With our problem formulation, we are able to express the original problem as a convex optimal control problem, which can then be solved onboard and in real-time by taking advantage of modern convex solvers. The advantages of our method are manyfold, providing a systematic method for solving the control allocation problem, enabling a wider flight envelope, and reducing actuator fatigue.
{"title":"Optimal control allocation for a multi-engine overactuated spacecraft","authors":"C. A. Pascucci, Michael Szmuk, Behçet Açikmese","doi":"10.1109/AERO.2017.7943690","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943690","url":null,"abstract":"This paper addresses the control allocation problem for an over-actuated system with a nonlinear relation between the control inputs and the realized force and torque vectors. Specifically, we consider a multi-engine rocket example where the attained force and torque vectors are nonlinear functions of the thrust magnitudes and engine gimbal angles. Since the system is over-actuated, the surface defining this nonlinear relationship represents a non-unique map between the control variables and the resultant force and torque vectors. In this work, our goal is to command the actuators to produce desired force and torque vectors with minimal actuator reconfiguration effort, subject to actuator dynamics and constraints (e.g. slew-rates, maximum gimbal angles). In achieving this objective, the control space is traversed in a way that preserves the force and torque impulse requested from the control allocator, thus ensuring that the transient motion of the actuators produces the desired change in linear and angular momentum. With our problem formulation, we are able to express the original problem as a convex optimal control problem, which can then be solved onboard and in real-time by taking advantage of modern convex solvers. The advantages of our method are manyfold, providing a systematic method for solving the control allocation problem, enabling a wider flight envelope, and reducing actuator fatigue.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"103 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122015097","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943570
K. Beaton, S. Chappell, A. Abercromby, Matthew J. Miller, S. Nawotniak, S. Hughes, A. Brady, D. Lim
The Biologic Analog Science Associated with Lava Terrains (BASALT) project is a multi-year program dedicated to iteratively develop, implement, and evaluate concepts of operations (ConOps) and supporting capabilities intended to enable and enhance human scientific exploration of Mars. This paper describes the planning, execution, and initial results from the first field deployment, referred to as BASALT-1, which consisted of a series of ten simulated extravehicular activities on volcanic flows in Idaho's Craters of the Moon National Monument and Preserve. The ConOps and capabilities deployed and tested during BASALT-1 were based on previous NASA trade studies and analog testing. Our primary research question was whether those ConOps and capabilities work acceptably when performing real (non-simulated) biological and geological scientific exploration under four different Mars-to-Earth communication conditions: 5 and 15 min one-way light time communication latencies and low (0.512 Mb/s uplink, 1.54 Mb/s downlink) and high (5.0 Mb/s uplink, 10.0 Mb/s downlink) bandwidth conditions, which represent two alternative technical communication capabilities currently proposed for future human exploration missions. The synthesized results, based on objective and subjective measures, from BASALT-1 established preliminary findings that the baseline ConOp, software systems, and communication protocols were scientifically and operationally acceptable with minor improvements desired by the “Mars” extravehicular and intravehicular crewmembers. However, unacceptable components of the ConOps and required improvements were identified by the “Earth” Mission Support Center. These data provide a basis for guiding and prioritizing capability development for future BASALT deployments and, ultimately, future human exploration missions.
{"title":"Extravehicular activity operations concepts under communication latency and bandwidth constraints","authors":"K. Beaton, S. Chappell, A. Abercromby, Matthew J. Miller, S. Nawotniak, S. Hughes, A. Brady, D. Lim","doi":"10.1109/AERO.2017.7943570","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943570","url":null,"abstract":"The Biologic Analog Science Associated with Lava Terrains (BASALT) project is a multi-year program dedicated to iteratively develop, implement, and evaluate concepts of operations (ConOps) and supporting capabilities intended to enable and enhance human scientific exploration of Mars. This paper describes the planning, execution, and initial results from the first field deployment, referred to as BASALT-1, which consisted of a series of ten simulated extravehicular activities on volcanic flows in Idaho's Craters of the Moon National Monument and Preserve. The ConOps and capabilities deployed and tested during BASALT-1 were based on previous NASA trade studies and analog testing. Our primary research question was whether those ConOps and capabilities work acceptably when performing real (non-simulated) biological and geological scientific exploration under four different Mars-to-Earth communication conditions: 5 and 15 min one-way light time communication latencies and low (0.512 Mb/s uplink, 1.54 Mb/s downlink) and high (5.0 Mb/s uplink, 10.0 Mb/s downlink) bandwidth conditions, which represent two alternative technical communication capabilities currently proposed for future human exploration missions. The synthesized results, based on objective and subjective measures, from BASALT-1 established preliminary findings that the baseline ConOp, software systems, and communication protocols were scientifically and operationally acceptable with minor improvements desired by the “Mars” extravehicular and intravehicular crewmembers. However, unacceptable components of the ConOps and required improvements were identified by the “Earth” Mission Support Center. These data provide a basis for guiding and prioritizing capability development for future BASALT deployments and, ultimately, future human exploration missions.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134499298","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943911
S. Hoffman, Alida D. Andrews, B. Joosten, K. Watts
In an on-going effort to make human Mars missions more affordable and sustainable, NASA continues to investigate the innovative leveraging of technological advances in conjunction with the use of accessible Martian resources directly applicable to these missions. One of the resources with the broadest utility for human missions is water. Many past studies of human Mars missions assumed a complete lack of water derivable from local sources. However, recent advances in our understanding of the Martian environment provides growing evidence that Mars may be more “water rich” than previously suspected. This is based on data indicating that substantial quantities of water are mixed with surface regolith, bound in minerals located at or near the surface, and buried in large glacier-like forms. This paper describes an assessment of what could be done in a “water rich” human Mars mission scenario. A description of what is meant by “water rich” in this context is provided, including a quantification of the water that would be used by crews in this scenario. The different types of potential feedstock that could be used to generate these quantities of water are described, drawing on the most recently available assessments of data being returned from Mars. This paper specifically focuses on sources that appear to be buried quantities of water ice. (An assessment of other potential feedstock materials is documented in another paper.) Technologies and processes currently used in terrestrial Polar Regions are reviewed. One process with a long history of use on Earth and with potential application on Mars — the Rodriguez Well — is described and results of an analysis simulating the performance of such a well on Mars are presented. These results indicate that a Rodriguez Well capable of producing the quantities of water identified for a “water rich” human mission are within the capabilities assumed to be available on the Martian surface, as envisioned in other comparable Evolvable Mars Campaign assessments. The paper concludes by capturing additional findings and describing additional simulations and tests that should be conducted to better characterize the performance of the identified terrestrial technologies for accessing subsurface ice, as well as the Rodriguez Well, under Mars environmental conditions.
{"title":"A water rich mars surface mission scenario","authors":"S. Hoffman, Alida D. Andrews, B. Joosten, K. Watts","doi":"10.1109/AERO.2017.7943911","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943911","url":null,"abstract":"In an on-going effort to make human Mars missions more affordable and sustainable, NASA continues to investigate the innovative leveraging of technological advances in conjunction with the use of accessible Martian resources directly applicable to these missions. One of the resources with the broadest utility for human missions is water. Many past studies of human Mars missions assumed a complete lack of water derivable from local sources. However, recent advances in our understanding of the Martian environment provides growing evidence that Mars may be more “water rich” than previously suspected. This is based on data indicating that substantial quantities of water are mixed with surface regolith, bound in minerals located at or near the surface, and buried in large glacier-like forms. This paper describes an assessment of what could be done in a “water rich” human Mars mission scenario. A description of what is meant by “water rich” in this context is provided, including a quantification of the water that would be used by crews in this scenario. The different types of potential feedstock that could be used to generate these quantities of water are described, drawing on the most recently available assessments of data being returned from Mars. This paper specifically focuses on sources that appear to be buried quantities of water ice. (An assessment of other potential feedstock materials is documented in another paper.) Technologies and processes currently used in terrestrial Polar Regions are reviewed. One process with a long history of use on Earth and with potential application on Mars — the Rodriguez Well — is described and results of an analysis simulating the performance of such a well on Mars are presented. These results indicate that a Rodriguez Well capable of producing the quantities of water identified for a “water rich” human mission are within the capabilities assumed to be available on the Martian surface, as envisioned in other comparable Evolvable Mars Campaign assessments. The paper concludes by capturing additional findings and describing additional simulations and tests that should be conducted to better characterize the performance of the identified terrestrial technologies for accessing subsurface ice, as well as the Rodriguez Well, under Mars environmental conditions.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"112 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115892712","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：