Pub Date : 2020-03-01DOI: 10.1109/AERO47225.2020.9172553
D. Mohr, J. Doubleday
The NASA-ISRO Synthetic Aperture Radar (NISAR) mission is the first major collaboration between NASA and the Indian Space Research Organisation (ISRO), and will return an unprecedented amount of science data (~5,000 terabytes during its prime mission). From a mean altitude of ~750km, the Observatory will use two distinct bands of SAR to provide detailed insight into the evolution and state of Earth's crust, including the abatement of glaciers, ecosystem changes, and natural and man-made disasters, such as earthquakes, hurricanes, and oil spills. JPL will provide NISAR's L-band SAR, GPS receivers, a payload data system, solid state recorder, and a high-rate Ka-band telecom system. ISRO will provide the satellite bus and an S-band SAR. With both JPL and ISRO providing key flight components, NISAR operations will be inherently interactive. This, combined with the substantial geographic and time differences, brings a unique set of operational challenges. How should the project weigh each Center's responsibility for operation of their specific flight and ground components against the need for both JPL and ISRO to maintain situational awareness of the Observatory and Ground System? In preparation for launch in January 2022, the NISAR Mission System has worked to find the right balance between inter-Center collaboration and each Center's individual responsibilities. With the goal of minimizing the complexity of operational interfaces, NISAR must still perform – integrated long and short-term science planning, – coordinated commanding necessary to execute joint SAR observations, – coordinated commanding necessary to carry out all of the Ka-band downlinks, and – anomaly response and recovery. This paper describes NISAR's approach to addressing each of these challenges to joint operation of the Observatory.
{"title":"NISAR's Unique Challenges and Approach to Robust JPL/ISRO Joint Operations","authors":"D. Mohr, J. Doubleday","doi":"10.1109/AERO47225.2020.9172553","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172553","url":null,"abstract":"The NASA-ISRO Synthetic Aperture Radar (NISAR) mission is the first major collaboration between NASA and the Indian Space Research Organisation (ISRO), and will return an unprecedented amount of science data (~5,000 terabytes during its prime mission). From a mean altitude of ~750km, the Observatory will use two distinct bands of SAR to provide detailed insight into the evolution and state of Earth's crust, including the abatement of glaciers, ecosystem changes, and natural and man-made disasters, such as earthquakes, hurricanes, and oil spills. JPL will provide NISAR's L-band SAR, GPS receivers, a payload data system, solid state recorder, and a high-rate Ka-band telecom system. ISRO will provide the satellite bus and an S-band SAR. With both JPL and ISRO providing key flight components, NISAR operations will be inherently interactive. This, combined with the substantial geographic and time differences, brings a unique set of operational challenges. How should the project weigh each Center's responsibility for operation of their specific flight and ground components against the need for both JPL and ISRO to maintain situational awareness of the Observatory and Ground System? In preparation for launch in January 2022, the NISAR Mission System has worked to find the right balance between inter-Center collaboration and each Center's individual responsibilities. With the goal of minimizing the complexity of operational interfaces, NISAR must still perform – integrated long and short-term science planning, – coordinated commanding necessary to execute joint SAR observations, – coordinated commanding necessary to carry out all of the Ka-band downlinks, and – anomaly response and recovery. This paper describes NISAR's approach to addressing each of these challenges to joint operation of the Observatory.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"51 XV 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"127948690","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 : 2020-03-01DOI: 10.1109/AERO47225.2020.9172627
R. Vijayan, M. Bilal, K. Schilling
A systematic approach to modeling the relative motion of artificial satellites in the presence of perturbations is presented. The relative motion is described using relative position and velocities as states. The modeling here is restricted to low Earth orbit (LEO) satellites and therefore includes the differential J2 and drag effects. In this paper we expand on the modeling approach that makes use of the Reference Satellite Variables for the chief's orbit using simple Newtonian mechanics to systematically derive the exact nonlinear relative motion model with differential J2 and drag. These equations are exact for eccentric reference orbits as well as equatorial. This intuitive modeling approach shall establish a framework to incorporate other kinds of differential perturbations for higher fidelity models based on the significance of application. Simulation results of the developed nonlinear relative motion model show the effect of differential J2 and drag captured by the equations for a LEO leader-follower formation with large intersatellite distances. The propagation errors of the model are studied for varying initial conditions and reference orbits. A subsequent analysis gives further insight into how the model developed is particularly free from singularities in the special case of J2 and drag disturbances alone.
{"title":"Nonlinear dynamic modeling of satellite relative motion with differential $pmb{J}_{2}$ and drag","authors":"R. Vijayan, M. Bilal, K. Schilling","doi":"10.1109/AERO47225.2020.9172627","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172627","url":null,"abstract":"A systematic approach to modeling the relative motion of artificial satellites in the presence of perturbations is presented. The relative motion is described using relative position and velocities as states. The modeling here is restricted to low Earth orbit (LEO) satellites and therefore includes the differential J2 and drag effects. In this paper we expand on the modeling approach that makes use of the Reference Satellite Variables for the chief's orbit using simple Newtonian mechanics to systematically derive the exact nonlinear relative motion model with differential J2 and drag. These equations are exact for eccentric reference orbits as well as equatorial. This intuitive modeling approach shall establish a framework to incorporate other kinds of differential perturbations for higher fidelity models based on the significance of application. Simulation results of the developed nonlinear relative motion model show the effect of differential J2 and drag captured by the equations for a LEO leader-follower formation with large intersatellite distances. The propagation errors of the model are studied for varying initial conditions and reference orbits. A subsequent analysis gives further insight into how the model developed is particularly free from singularities in the special case of J2 and drag disturbances alone.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"465 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123253835","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 : 2020-03-01DOI: 10.1109/AERO47225.2020.9172811
J. Thangavelautham, A. Chandra, Erik Jensen
There is growing interest in expanding beyond space exploration and pursuing the dream of living and working in space. The next critical step towards living and working in space requires kick-starting a space economy. One important challenge with this space-economy is ensuring the ready supply and low-cost availability of raw materials. The escape delta-v of 11.2 km/s from Earth makes transportation of materials from Earth very costly. Transporting materials from the Moon takes 2.4 km/s and from Mars 5.0 km/s. Based on these factors, the Moon and Mars can become colonies to export material into this space economy. One critical question is what are the resources required to sustain a space economy? Water has been identified as a critical resource both to sustain human-life but also for use in propulsion, attitude-control, power, thermal storage and radiation protection systems. Water may be obtained off-world through In-Situ Resource Utilization (ISRU) in the course of human or robotic space exploration. The Moon is also rich in iron, titanium and silicon. Based upon these important findings, we plan on developing an energy model to determine the feasibility of developing a mining base on the Moon. This mining base mines and principally exports water, titanium and steel. The moon has been selected, as there are significant reserves of water known to exists at the permanently shadowed crater regions and there are significant sources of titanium and iron throughout the Moon's surface. Our designs for a mining base utilize renewable energy sources namely photovoltaics and solar-thermal concentrators to provide power to construct the base, keep it operational and export water and other resources using a Mass Driver. However, the site where large quantities of water are present lack sunlight and hence the water needs to be transported using rail from the southern region to base located at mid latitude. Using the energy model developed, we will determine the energy per Earth-day to export 100 tons each of water, titanium and low-grade steel into Lunar escape velocity and to the Earth-Moon Lagrange points. Our study of water and metal mining on the Moon found the key to keeping the mining base efficient is to make it robotic. Teams of robots (consisting of 300 infrastructure robots) would be used to construct the entire base using locally available resources and fully operate the base. This would decrease energy needs by 15-folds. Furthermore, the base can be built 15-times faster using robotics and 3D printing. This shows that automation and robotics is the key to making such a base technologically feasible. The Moon is a lot closer to Earth than Mars and the prospect of having a greater impact on the space economy cannot be stressed. Our study intends to determine the cost-benefit analysis of lunar resource mining.
{"title":"Autonomous Robot Teams for Lunar Mining Base Construction and Operation","authors":"J. Thangavelautham, A. Chandra, Erik Jensen","doi":"10.1109/AERO47225.2020.9172811","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172811","url":null,"abstract":"There is growing interest in expanding beyond space exploration and pursuing the dream of living and working in space. The next critical step towards living and working in space requires kick-starting a space economy. One important challenge with this space-economy is ensuring the ready supply and low-cost availability of raw materials. The escape delta-v of 11.2 km/s from Earth makes transportation of materials from Earth very costly. Transporting materials from the Moon takes 2.4 km/s and from Mars 5.0 km/s. Based on these factors, the Moon and Mars can become colonies to export material into this space economy. One critical question is what are the resources required to sustain a space economy? Water has been identified as a critical resource both to sustain human-life but also for use in propulsion, attitude-control, power, thermal storage and radiation protection systems. Water may be obtained off-world through In-Situ Resource Utilization (ISRU) in the course of human or robotic space exploration. The Moon is also rich in iron, titanium and silicon. Based upon these important findings, we plan on developing an energy model to determine the feasibility of developing a mining base on the Moon. This mining base mines and principally exports water, titanium and steel. The moon has been selected, as there are significant reserves of water known to exists at the permanently shadowed crater regions and there are significant sources of titanium and iron throughout the Moon's surface. Our designs for a mining base utilize renewable energy sources namely photovoltaics and solar-thermal concentrators to provide power to construct the base, keep it operational and export water and other resources using a Mass Driver. However, the site where large quantities of water are present lack sunlight and hence the water needs to be transported using rail from the southern region to base located at mid latitude. Using the energy model developed, we will determine the energy per Earth-day to export 100 tons each of water, titanium and low-grade steel into Lunar escape velocity and to the Earth-Moon Lagrange points. Our study of water and metal mining on the Moon found the key to keeping the mining base efficient is to make it robotic. Teams of robots (consisting of 300 infrastructure robots) would be used to construct the entire base using locally available resources and fully operate the base. This would decrease energy needs by 15-folds. Furthermore, the base can be built 15-times faster using robotics and 3D printing. This shows that automation and robotics is the key to making such a base technologically feasible. The Moon is a lot closer to Earth than Mars and the prospect of having a greater impact on the space economy cannot be stressed. Our study intends to determine the cost-benefit analysis of lunar resource mining.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"30 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116119818","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 : 2020-03-01DOI: 10.1109/AERO47225.2020.9172569
Jay L. Gao
This paper describes a Markovian queueing network model of multiple access communication that captures considerations for both spacecraft operations and data transmissions duty cycle. Several performance metrics were presented to measure bandwidth efficiency and latency from both the communications and operations perspectives. Leveraging the mathematical framework derived from Jackson queueing theory, we demonstrate the use of this model by applying it to notional relay networks envisioned for Mars, Lunar, and Earth environments and analyzing the performance between frequency and code division multiple access approaches. We conclude this paper with discussions on the modeling results and the pros and cons of our model.
{"title":"A Markovian Queueing Model of Multiple Access Communications in Space","authors":"Jay L. Gao","doi":"10.1109/AERO47225.2020.9172569","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172569","url":null,"abstract":"This paper describes a Markovian queueing network model of multiple access communication that captures considerations for both spacecraft operations and data transmissions duty cycle. Several performance metrics were presented to measure bandwidth efficiency and latency from both the communications and operations perspectives. Leveraging the mathematical framework derived from Jackson queueing theory, we demonstrate the use of this model by applying it to notional relay networks envisioned for Mars, Lunar, and Earth environments and analyzing the performance between frequency and code division multiple access approaches. We conclude this paper with discussions on the modeling results and the pros and cons of our model.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121650662","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 : 2020-03-01DOI: 10.1109/AERO47225.2020.9172344
Markus Guerster, J. Grotz, P. Belobaba, E. Crawley, B. Cameron
In this paper we propose a Revenue Management framework for satcom operators and show with a proof-of-concept simulation that predicts a significant gain in revenues. New satellite operators, highly variable demand for data, digital payloads, and new phased array technologies are likely to remake the current satcom landscape. One of the challenges operators old and new will face is how to manage demand and capacity. Airlines faced a similar situation with deregulation in the 1970s - their response with tiered pricing and seat inventory control to allocate capacity (known as Revenue Management), which may offer lessons for the satcom market. The satcom industry shares many characteristics with the airline industry, such as inflexible capacity, low marginal sales cost, perishable inventory, heterogenous customers, and variable and uncertain demand. Generally, those characteristics favor the implementation of a Revenue Management system. However, the details of how Revenue Management can be used by satcom operators still need to be explored, which is the focus of this paper.
{"title":"Revenue Management for Communication Satellite Operators - Opportunities and Challenges","authors":"Markus Guerster, J. Grotz, P. Belobaba, E. Crawley, B. Cameron","doi":"10.1109/AERO47225.2020.9172344","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172344","url":null,"abstract":"In this paper we propose a Revenue Management framework for satcom operators and show with a proof-of-concept simulation that predicts a significant gain in revenues. New satellite operators, highly variable demand for data, digital payloads, and new phased array technologies are likely to remake the current satcom landscape. One of the challenges operators old and new will face is how to manage demand and capacity. Airlines faced a similar situation with deregulation in the 1970s - their response with tiered pricing and seat inventory control to allocate capacity (known as Revenue Management), which may offer lessons for the satcom market. The satcom industry shares many characteristics with the airline industry, such as inflexible capacity, low marginal sales cost, perishable inventory, heterogenous customers, and variable and uncertain demand. Generally, those characteristics favor the implementation of a Revenue Management system. However, the details of how Revenue Management can be used by satcom operators still need to be explored, which is the focus of this paper.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121819709","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 : 2020-03-01DOI: 10.1109/AERO47225.2020.9172733
T. Cwik, M. Kozlov, Richard T. French, A. Shapiro, Edward Sewall
This paper describes a 3-year accelerator pilot program with the objective of enabling or enhancing future science missions at the Jet Propulsion Laboratory (JPL) through infusion of commercial technologies from early stage companies. Success criteria for Year 1 that will support a decision to proceed to the second year are described. The pilot is funded by a consortium from government and industry. Techstars, a leading corporate accelerator operator, supported by Starburst Aerospace, manages the program. The program accelerates growth of ten early stage companies through seed investment, mentorship, networking, agile processes, and investor pitch development. The startups have not received prior significant investment but have core teams and some discriminating characteristics; e.g., a product with traction or a compelling technology with commercial potential. The pilot provides a pathway for maturing necessary relationships to ultimately infuse those technologies. The pilot is a pathfinder for JPL as well as future efforts sponsored by the National Aeronautics and Space Administration (NASA). The pilot meets the spirit of NASA's strategic objective to align partnerships with NASA missions and programs, increasing efficiency and effectiveness. The challenges JPL faces in developing partnerships with startups, in particular cultural barriers and minimal experience with the entrepreneurial sector are acknowledged. A set of specific success criteria that act as leading indicators of infusion are used to assess the efficacy of the pilot across two major categories: content and culture. A range of value propositions are discussed as well. Pre-program elements are described; these include formulation, identification of technical sub-themes, marketing and communications, recruiting, candidate review and selection, due diligence, and conflict of interest. Key roles including mentors, program management, and partner liaisons are detailed. The actual program takes place over 13 weeks in Los Angeles, with weekly objectives and key results tracked as a group to build relationships and opportunities across the class. During the first month, the companies receive product/market fit analysis, customer discovery, technical mentoring, hiring support, investor introductions, go-to-market strategy assistance, and market understanding. In the second month, the companies meet potential customers and push forward commercial opportunities. In the final month, the companies work closely with program management to develop a compelling story while pushing commercial deals and building traction as well as collaborations with consortium sponsors. At program end, each company works to secure at least one major partnership. Longer-term post-program activities lead to infusion of technologies into future missions. Other ongoing activities for class and consortium members are described. Over 300 applications to the accelerator pilot were begun with a high level of credible, ap
{"title":"Space Startup Accelerator Pilot","authors":"T. Cwik, M. Kozlov, Richard T. French, A. Shapiro, Edward Sewall","doi":"10.1109/AERO47225.2020.9172733","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172733","url":null,"abstract":"This paper describes a 3-year accelerator pilot program with the objective of enabling or enhancing future science missions at the Jet Propulsion Laboratory (JPL) through infusion of commercial technologies from early stage companies. Success criteria for Year 1 that will support a decision to proceed to the second year are described. The pilot is funded by a consortium from government and industry. Techstars, a leading corporate accelerator operator, supported by Starburst Aerospace, manages the program. The program accelerates growth of ten early stage companies through seed investment, mentorship, networking, agile processes, and investor pitch development. The startups have not received prior significant investment but have core teams and some discriminating characteristics; e.g., a product with traction or a compelling technology with commercial potential. The pilot provides a pathway for maturing necessary relationships to ultimately infuse those technologies. The pilot is a pathfinder for JPL as well as future efforts sponsored by the National Aeronautics and Space Administration (NASA). The pilot meets the spirit of NASA's strategic objective to align partnerships with NASA missions and programs, increasing efficiency and effectiveness. The challenges JPL faces in developing partnerships with startups, in particular cultural barriers and minimal experience with the entrepreneurial sector are acknowledged. A set of specific success criteria that act as leading indicators of infusion are used to assess the efficacy of the pilot across two major categories: content and culture. A range of value propositions are discussed as well. Pre-program elements are described; these include formulation, identification of technical sub-themes, marketing and communications, recruiting, candidate review and selection, due diligence, and conflict of interest. Key roles including mentors, program management, and partner liaisons are detailed. The actual program takes place over 13 weeks in Los Angeles, with weekly objectives and key results tracked as a group to build relationships and opportunities across the class. During the first month, the companies receive product/market fit analysis, customer discovery, technical mentoring, hiring support, investor introductions, go-to-market strategy assistance, and market understanding. In the second month, the companies meet potential customers and push forward commercial opportunities. In the final month, the companies work closely with program management to develop a compelling story while pushing commercial deals and building traction as well as collaborations with consortium sponsors. At program end, each company works to secure at least one major partnership. Longer-term post-program activities lead to infusion of technologies into future missions. Other ongoing activities for class and consortium members are described. Over 300 applications to the accelerator pilot were begun with a high level of credible, ap","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123879971","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 : 2020-03-01DOI: 10.1109/AERO47225.2020.9172284
M. Levedahl, J. D. Glass
The global nearest pattern (GNP) approach to data association is closely related to the global nearest neighbor (GNN) problem, and both require that a cost of non-assignment of tracks be established. The existing theory for GNN can be reasonably applied to GNP problems, but adjustments are required to optimally account for bias estimation and uncertainty in GNP. These adjustments are presented along with Monte Carlo analysis showing the achieved performance is nearly optimal.
{"title":"Optimal Non-Assignment Costs for the GNP Problem","authors":"M. Levedahl, J. D. Glass","doi":"10.1109/AERO47225.2020.9172284","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172284","url":null,"abstract":"The global nearest pattern (GNP) approach to data association is closely related to the global nearest neighbor (GNN) problem, and both require that a cost of non-assignment of tracks be established. The existing theory for GNN can be reasonably applied to GNP problems, but adjustments are required to optimally account for bias estimation and uncertainty in GNP. These adjustments are presented along with Monte Carlo analysis showing the achieved performance is nearly optimal.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"119 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114252355","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 : 2020-03-01DOI: 10.1109/AERO47225.2020.9172517
K. M. Han, J. Yang-Scharlotta, Mohammad Ashjitou, D. Costanzo, D. Giovinazzo, Mohammad Morjarradi
This work investigates the electrical performance of a high speed general purpose operation amplifier, OPA2356, operating under cryogenic temperature -180°C. Evidence of cryogenic-induced instability of OPA2356 was experimentally observed and repeated using different hardware setups — a subtle increase in OPA2356's Isupply current variations after extended -180°C cold dwell for 24 hours. The monitored Isupply current revealed increased random fluctuation of Isupply, characterized by its standard deviation σ, as compared to its initial room temperature current (σ25C-initial). This is exemplified by ~2σ 25C-initial at −180°C/24hrs and ~1.8σ 25C-initial at 25°C/post-cold. This work also suggests using the static supply current (Isupply), also commonly known as DC quiescent current, of the analog chip as a good monitor of analog chip's instability operating under cryogenic conditions. This is demonstrated using another hardware setup where the OPA2356 was implemented as a unity-gain amplifier. We also found that increasing voltage headroom by maximizing the allowable VDD in analog chips will enable proper cryogenic operation of analog chips, which can be a critical trade-off for a space electronic system to consider between long term reliability and operating window.
{"title":"Cryogenic Temperature Induced Instability of 200MHz CMOS Operational Amplifier","authors":"K. M. Han, J. Yang-Scharlotta, Mohammad Ashjitou, D. Costanzo, D. Giovinazzo, Mohammad Morjarradi","doi":"10.1109/AERO47225.2020.9172517","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172517","url":null,"abstract":"This work investigates the electrical performance of a high speed general purpose operation amplifier, OPA2356, operating under cryogenic temperature -180°C. Evidence of cryogenic-induced instability of OPA2356 was experimentally observed and repeated using different hardware setups — a subtle increase in OPA2356's Isupply current variations after extended -180°C cold dwell for 24 hours. The monitored Isupply current revealed increased random fluctuation of Isupply, characterized by its standard deviation σ, as compared to its initial room temperature current (σ25C-initial). This is exemplified by ~2σ 25C-initial at −180°C/24hrs and ~1.8σ 25C-initial at 25°C/post-cold. This work also suggests using the static supply current (Isupply), also commonly known as DC quiescent current, of the analog chip as a good monitor of analog chip's instability operating under cryogenic conditions. This is demonstrated using another hardware setup where the OPA2356 was implemented as a unity-gain amplifier. We also found that increasing voltage headroom by maximizing the allowable VDD in analog chips will enable proper cryogenic operation of analog chips, which can be a critical trade-off for a space electronic system to consider between long term reliability and operating window.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125290784","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 : 2020-03-01DOI: 10.1109/AERO47225.2020.9172751
Jennifer R. Amador, W. K. Thompson, J. Mindock, Michelle Urbina, K. McGuire, L. Boley, Hector L. Chavez, Tatyana Y. Rakalina, Esther Lee, Travis B. Mosher, Sarah Lumpkins, E. Kerstman, K. Lehnhardt
The NASA Human Research Program's (HRP) Exploration Medical Capability (ExMC) Element is utilizing a Model Based Systems Engineering (MBSE) approach to enhance the development of systems engineering products that will be used to advance medical system designs for exploration missions beyond Low Earth Orbit. In support of future missions, the team is capturing content such as system behaviors, functional decompositions, architecture, system requirements and interfaces, and recommendations for clinical capabilities and resources in Systems Modeling Language (SysML) models. As these products mature, SysML models provide a way for ExMC to capture relationships among the various products, which includes supporting more integrated and multi-faceted views of future medical systems. In addition to using SysML models, HRP and ExMC are developing supplementary tools to support two key functions: 1) prioritizing current and future research activities for exploration missions in an objective manner; and 2) enabling risk-informed and evidence-based trade space analysis for future space vehicles, missions, and systems. This paper will discuss the long-term HRP and ExMC vision for the larger ecosystem of tools, which include dynamic Probabilistic Risk Assessment (PRA) capabilities, additional SysML models, a database of system component options, and data visualizations. It also includes a review of an initial Pilot Project focused on enabling medical system trade studies utilizing data that is coordinated across tools for consistent outputs (e.g., mission risk metrics that are associated with medical system mass values and medical conditions addressed). This first Pilot Project demonstrated successful operating procedures and integration across tools. Finally, the paper will also cover a second Pilot Project that utilizes tool enhancements such as medical system optimization capabilities, post-processing, and visualization of generated data for subject matter expert review, and increased integration amongst the tools themselves.
{"title":"Enabling Space Exploration Medical System Development Using a Tool Ecosystem","authors":"Jennifer R. Amador, W. K. Thompson, J. Mindock, Michelle Urbina, K. McGuire, L. Boley, Hector L. Chavez, Tatyana Y. Rakalina, Esther Lee, Travis B. Mosher, Sarah Lumpkins, E. Kerstman, K. Lehnhardt","doi":"10.1109/AERO47225.2020.9172751","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172751","url":null,"abstract":"The NASA Human Research Program's (HRP) Exploration Medical Capability (ExMC) Element is utilizing a Model Based Systems Engineering (MBSE) approach to enhance the development of systems engineering products that will be used to advance medical system designs for exploration missions beyond Low Earth Orbit. In support of future missions, the team is capturing content such as system behaviors, functional decompositions, architecture, system requirements and interfaces, and recommendations for clinical capabilities and resources in Systems Modeling Language (SysML) models. As these products mature, SysML models provide a way for ExMC to capture relationships among the various products, which includes supporting more integrated and multi-faceted views of future medical systems. In addition to using SysML models, HRP and ExMC are developing supplementary tools to support two key functions: 1) prioritizing current and future research activities for exploration missions in an objective manner; and 2) enabling risk-informed and evidence-based trade space analysis for future space vehicles, missions, and systems. This paper will discuss the long-term HRP and ExMC vision for the larger ecosystem of tools, which include dynamic Probabilistic Risk Assessment (PRA) capabilities, additional SysML models, a database of system component options, and data visualizations. It also includes a review of an initial Pilot Project focused on enabling medical system trade studies utilizing data that is coordinated across tools for consistent outputs (e.g., mission risk metrics that are associated with medical system mass values and medical conditions addressed). This first Pilot Project demonstrated successful operating procedures and integration across tools. Finally, the paper will also cover a second Pilot Project that utilizes tool enhancements such as medical system optimization capabilities, post-processing, and visualization of generated data for subject matter expert review, and increased integration amongst the tools themselves.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"51 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122630254","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 : 2020-03-01DOI: 10.1109/AERO47225.2020.9172564
Prashant Kumar, S. Sonkar, A. K. Ghosh, Deepu Philip
A Powered Paraglider, also known as Paramotor, has a ram-air inflated canopy in the shape of an aerofoil from which a payload, commonly called as Gondola, housing both propulsion system and control mechanism is suspended. It can lift heavy loads, is quick to setup for rapid launch, and is compact and light-weight, thereby making it ideal for military operations like tactical surveillance and cargo deployment. Paramotors are suitable for scenarios where stable and low speed flying capabilities are necessary. This paper presents a software architecture for guidance and control of light weight small scale Paramotors. For heading and altitude tracking, the system uses feedback compensated control laws. First, linear models are derived that describe both the Paramotor's longitudinal and lateral dynamics. Then, a six degree-of-freedom model is used to describe dynamics, weight, aerodynamic forces on payload and parafoil, aerodynamic moments, effect of apparent forces and moments, moments generated on the centre of mass by the forces exerted at the payload and parafoil. Then system identification based on simplified linear lateral and longitudinal models is used. These simplified linear models are used for designing control laws using classical frequency domain techniques. MATLAB/Simulink was used to simulate the performance of the proposed Paramotor controllers. It was found that the described approach is robust enough for designing control strategies to maintain stability in event of disturbances.
{"title":"Dynamic Waypoint Navigation and Control of Light Weight Powered Paraglider","authors":"Prashant Kumar, S. Sonkar, A. K. Ghosh, Deepu Philip","doi":"10.1109/AERO47225.2020.9172564","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172564","url":null,"abstract":"A Powered Paraglider, also known as Paramotor, has a ram-air inflated canopy in the shape of an aerofoil from which a payload, commonly called as Gondola, housing both propulsion system and control mechanism is suspended. It can lift heavy loads, is quick to setup for rapid launch, and is compact and light-weight, thereby making it ideal for military operations like tactical surveillance and cargo deployment. Paramotors are suitable for scenarios where stable and low speed flying capabilities are necessary. This paper presents a software architecture for guidance and control of light weight small scale Paramotors. For heading and altitude tracking, the system uses feedback compensated control laws. First, linear models are derived that describe both the Paramotor's longitudinal and lateral dynamics. Then, a six degree-of-freedom model is used to describe dynamics, weight, aerodynamic forces on payload and parafoil, aerodynamic moments, effect of apparent forces and moments, moments generated on the centre of mass by the forces exerted at the payload and parafoil. Then system identification based on simplified linear lateral and longitudinal models is used. These simplified linear models are used for designing control laws using classical frequency domain techniques. MATLAB/Simulink was used to simulate the performance of the proposed Paramotor controllers. It was found that the described approach is robust enough for designing control strategies to maintain stability in event of disturbances.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131397709","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}