Pub Date : 2020-03-01DOI: 10.1109/AERO47225.2020.9172585
Cesare Guariniello, L. Mockus, A. Raz, D. DeLaurentis
System-of-Systems (SoS) are composed of large scale independent and complex heterogeneous systems which collaborate to create capabilities not achievable by a single system, for example air transportation system, satellite constellations, and space exploration architectures. To support architecting of aerospace SoS, in this work we present a methodology to accurately predict different aspects of performance for design/operation and SoS architecting, expanding previous work on intelligent architecting of aerospace SoS, by adding rigorous Uncertainty Quantification via Bayesian Neural Networks. A Bayesian Neural Network is a neural network with a-priori distribution on its weights. In addition to solving the overfit problem, which is common to traditional deep neural networks, Bayesian Neural Networks provide automated model pruning (or reduction of feature design space), that addresses a well-known dimensionality curse in the SoS domain. We enable SoS design/operation by using modeling and simulation, quantifying the uncertainty inherently present in SoS, and utilizing Artificial Intelligence and optimization techniques to design and operate the system so that its expected performance or behavior when the unexpected occurs (for example, a failure) still satisfies user requirements. Much of the research effort in the field of SoS has focused on the analysis of these complex entities, while there are still gaps in developing tools for automated synthesis and engineering of SoS that consider all the various aspects in this problem domain. In this expansion of the use of Artificial Intelligence towards automated design, these techniques are used not only to discover and employ features of interest in a complex design space, but also to assess how uncertainty can affect performance. This capability supports the automated design of robust architectures, that can effectively meet the user needs even in presence of uncertainty. The SoS design and evaluation methodology presented in this paper and demonstrated on a synthetic modular satellites problem starts from modeling and simulation, and design of experiments to explore the design space. The following step is deep learning, to develop a model which relates SoS architectural features with performance metrics. Uncertainty Quantification techniques are then applied to assess the performance metrics for different architectures. Once the most critical features that affect the SoS performance are identified, stochastic optimization of the SoS on a reduced design space can be performed to determine Pareto optimal features. The final step is determining if any additional design/operation measures need to be explored to further maximize the SoS performance.
{"title":"Towards Intelligent Architecting of Aerospace System-of-Systems: Part II","authors":"Cesare Guariniello, L. Mockus, A. Raz, D. DeLaurentis","doi":"10.1109/AERO47225.2020.9172585","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172585","url":null,"abstract":"System-of-Systems (SoS) are composed of large scale independent and complex heterogeneous systems which collaborate to create capabilities not achievable by a single system, for example air transportation system, satellite constellations, and space exploration architectures. To support architecting of aerospace SoS, in this work we present a methodology to accurately predict different aspects of performance for design/operation and SoS architecting, expanding previous work on intelligent architecting of aerospace SoS, by adding rigorous Uncertainty Quantification via Bayesian Neural Networks. A Bayesian Neural Network is a neural network with a-priori distribution on its weights. In addition to solving the overfit problem, which is common to traditional deep neural networks, Bayesian Neural Networks provide automated model pruning (or reduction of feature design space), that addresses a well-known dimensionality curse in the SoS domain. We enable SoS design/operation by using modeling and simulation, quantifying the uncertainty inherently present in SoS, and utilizing Artificial Intelligence and optimization techniques to design and operate the system so that its expected performance or behavior when the unexpected occurs (for example, a failure) still satisfies user requirements. Much of the research effort in the field of SoS has focused on the analysis of these complex entities, while there are still gaps in developing tools for automated synthesis and engineering of SoS that consider all the various aspects in this problem domain. In this expansion of the use of Artificial Intelligence towards automated design, these techniques are used not only to discover and employ features of interest in a complex design space, but also to assess how uncertainty can affect performance. This capability supports the automated design of robust architectures, that can effectively meet the user needs even in presence of uncertainty. The SoS design and evaluation methodology presented in this paper and demonstrated on a synthetic modular satellites problem starts from modeling and simulation, and design of experiments to explore the design space. The following step is deep learning, to develop a model which relates SoS architectural features with performance metrics. Uncertainty Quantification techniques are then applied to assess the performance metrics for different architectures. Once the most critical features that affect the SoS performance are identified, stochastic optimization of the SoS on a reduced design space can be performed to determine Pareto optimal features. The final step is determining if any additional design/operation measures need to be explored to further maximize the SoS performance.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"71 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":"124755346","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/AERO47225.2020.9172786
R. Nikoukar, D. Copeland, Sean Sprouse, Matthew W. Cox, K. Kufahl
A Ka-band communication channel provides a high capacity link critical for deep space science data downlink. However, data transmissions over Ka-band are highly susceptible to weather conditions (such as wind, clouds, water vapor, etc.), In this work, we conduct a comprehensive statistical analysis based on the first year of Parker Solar Probe measurements to quantify weather effects on a Ka-band science data downlink. To this end, we compare the results of link models using Deep Space Network (DSN) aggregate annual and monthly statistics, and annual International Telecommunication Union (ITU) standards. Our results show a general agreement between monthly DSN and ITU models with a superior performance over annual DSN statistics. The Ka-band link models can match the observed carrier power to approximately 1 dB. However, the link models in general underestimate the symbol signal to noise ratio (SSNR). Furthermore, using ITU standards, we examined the use of local weather parameters such as mean air temperature, humidity, and barometric pressure to model atmospheric gaseous attenuation. We find an excellent agreement between the measured and modeled system noise temperature (SNT) based on atmospheric attenuation due to gas for clear days. For cloudy days, one needs to account for cloud contribution to atmospheric attenuation using total columnar content of liquid water. In terms of mission operations, the results of our statistical analyses provide the first steps toward ingesting short-term weather predictions into the link models which will allow for an increased data rates during tracks with favorable weather forecasts, and will ultimately enhance the overall data return of science data with little increase in the percentage of dropped frames.
{"title":"Quantifying Weather Effects on Ka-band Communication Links: A Parker Solar Probe Study","authors":"R. Nikoukar, D. Copeland, Sean Sprouse, Matthew W. Cox, K. Kufahl","doi":"10.1109/AERO47225.2020.9172786","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172786","url":null,"abstract":"A Ka-band communication channel provides a high capacity link critical for deep space science data downlink. However, data transmissions over Ka-band are highly susceptible to weather conditions (such as wind, clouds, water vapor, etc.), In this work, we conduct a comprehensive statistical analysis based on the first year of Parker Solar Probe measurements to quantify weather effects on a Ka-band science data downlink. To this end, we compare the results of link models using Deep Space Network (DSN) aggregate annual and monthly statistics, and annual International Telecommunication Union (ITU) standards. Our results show a general agreement between monthly DSN and ITU models with a superior performance over annual DSN statistics. The Ka-band link models can match the observed carrier power to approximately 1 dB. However, the link models in general underestimate the symbol signal to noise ratio (SSNR). Furthermore, using ITU standards, we examined the use of local weather parameters such as mean air temperature, humidity, and barometric pressure to model atmospheric gaseous attenuation. We find an excellent agreement between the measured and modeled system noise temperature (SNT) based on atmospheric attenuation due to gas for clear days. For cloudy days, one needs to account for cloud contribution to atmospheric attenuation using total columnar content of liquid water. In terms of mission operations, the results of our statistical analyses provide the first steps toward ingesting short-term weather predictions into the link models which will allow for an increased data rates during tracks with favorable weather forecasts, and will ultimately enhance the overall data return of science data with little increase in the percentage of dropped frames.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"78 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":"128514726","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/AERO47225.2020.9172283
Maj Michael LaSorda, J. Borky, R. Sega
The architecture selection process early in a major system acquisition is a critical step in determining the success of a program. There are recognized deficiencies that frequently occur in this step such as poor transparency into the final selection decision and excessive focus on lowest cost, which does not necessarily result in best value. This research investigates improvements to this process by integrating Model-Based Systems Engineering (MBSE) techniques; enforcing rigorous, quantitative evaluation metrics with a corresponding understanding of uncertainties; and eliciting stakeholder feedback in order to generate an architecture that is better optimized and trusted to provide improved value for the stakeholders. The proposed methodology presents a decision authority with an integrated assessment of architecture alternatives, to include expected performance evaluated against desired parameters with corresponding uncertainty distributions, and traceable to the concerns of the system's stakeholders. This thus enables a more informed and objective selection of the preferred alternative. We present a case study that analyzes the evaluation of a service-oriented architecture (SOA) providing satellite command and control with cyber security protections. This serves to define and demonstrate a new, more transparent and trusted architecture selection process, and the results show that it consistently achieves the desired improvements. Several excursions are also presented to show how rigorously capturing uncertainty could potentially lead to greater insights in architecture evaluation, which is a robust area for further investigation. The primary contribution of this research then is improved decision support to an architecture selection in the early phases of a system acquisition program.
{"title":"Model-Based Systems Architecting with Decision Quantification for Cybersecurity, Cost, and Performance","authors":"Maj Michael LaSorda, J. Borky, R. Sega","doi":"10.1109/AERO47225.2020.9172283","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172283","url":null,"abstract":"The architecture selection process early in a major system acquisition is a critical step in determining the success of a program. There are recognized deficiencies that frequently occur in this step such as poor transparency into the final selection decision and excessive focus on lowest cost, which does not necessarily result in best value. This research investigates improvements to this process by integrating Model-Based Systems Engineering (MBSE) techniques; enforcing rigorous, quantitative evaluation metrics with a corresponding understanding of uncertainties; and eliciting stakeholder feedback in order to generate an architecture that is better optimized and trusted to provide improved value for the stakeholders. The proposed methodology presents a decision authority with an integrated assessment of architecture alternatives, to include expected performance evaluated against desired parameters with corresponding uncertainty distributions, and traceable to the concerns of the system's stakeholders. This thus enables a more informed and objective selection of the preferred alternative. We present a case study that analyzes the evaluation of a service-oriented architecture (SOA) providing satellite command and control with cyber security protections. This serves to define and demonstrate a new, more transparent and trusted architecture selection process, and the results show that it consistently achieves the desired improvements. Several excursions are also presented to show how rigorously capturing uncertainty could potentially lead to greater insights in architecture evaluation, which is a robust area for further investigation. The primary contribution of this research then is improved decision support to an architecture selection in the early phases of a system acquisition program.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"63 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":"128520932","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/AERO47225.2020.9172666
Evan Graser, Sean P. McGill, A. Rankin, A. Bielawiec
The Mars Science Laboratory (MSL) Curiosity rover experienced increasing wheel damage beginning in October 2013. While the wheels were designed to operate with considerable damage, the rate at which damage was occurring was unexpected and raised concerns regarding wheel life expectancy. As of Sol 2555 (10-14-19), there are two broken grousers on the left middle wheel, and one broken grouser on the right middle wheel. One possible scenario, albeit remote, is that enough grousers break on a wheel such that unconstrained portions of the wheel could contact the cable running from the rover motor controller assembly to the wheel's drive actuator. If the cable to a drive actuator is damaged, that wheel may no longer respond to commands. To make progress towards a navigation goal position, that wheel would need to be dragged. To mitigate the risk of damaging a cable running to a wheels drive actuator, the unconstrained portion of a wheel could be strategically shed by performing driving maneuvers on an immovable rock. What would remain after wheel shedding is a rimmed wheel (the outer 1/3 of the wheel). We studied the feasibility of remotely commanding the rover to perform the shed maneuver on one of its front wheels. To inform whether or not to shed the wheels, we tested the performance of driving on one or more rimmed wheels in flight. This led to a two-month test campaign in the Jet Propulsion Laboratory (JPL) Mars Yard using the Scarecrow testbed rover. Driving and steering performance was characterized on a variety of terrain types and slopes in a worst-case rimmed wheeled configuration. Test results indicate that if wheel shedding could be successfully executed in flight, Curiosity could continue to drive indefinitely on rimmed wheels.
{"title":"Rimmed Wheel Performance on the Mars Science Laboratory Scarecrow Rover","authors":"Evan Graser, Sean P. McGill, A. Rankin, A. Bielawiec","doi":"10.1109/AERO47225.2020.9172666","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172666","url":null,"abstract":"The Mars Science Laboratory (MSL) Curiosity rover experienced increasing wheel damage beginning in October 2013. While the wheels were designed to operate with considerable damage, the rate at which damage was occurring was unexpected and raised concerns regarding wheel life expectancy. As of Sol 2555 (10-14-19), there are two broken grousers on the left middle wheel, and one broken grouser on the right middle wheel. One possible scenario, albeit remote, is that enough grousers break on a wheel such that unconstrained portions of the wheel could contact the cable running from the rover motor controller assembly to the wheel's drive actuator. If the cable to a drive actuator is damaged, that wheel may no longer respond to commands. To make progress towards a navigation goal position, that wheel would need to be dragged. To mitigate the risk of damaging a cable running to a wheels drive actuator, the unconstrained portion of a wheel could be strategically shed by performing driving maneuvers on an immovable rock. What would remain after wheel shedding is a rimmed wheel (the outer 1/3 of the wheel). We studied the feasibility of remotely commanding the rover to perform the shed maneuver on one of its front wheels. To inform whether or not to shed the wheels, we tested the performance of driving on one or more rimmed wheels in flight. This led to a two-month test campaign in the Jet Propulsion Laboratory (JPL) Mars Yard using the Scarecrow testbed rover. Driving and steering performance was characterized on a variety of terrain types and slopes in a worst-case rimmed wheeled configuration. Test results indicate that if wheel shedding could be successfully executed in flight, Curiosity could continue to drive indefinitely on rimmed wheels.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"1 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":"128672559","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/AERO47225.2020.9172670
S. Mortazavi, S. Mortazavi, L. Sihver
During manned space missions, humans will be accompanied by microorganisms. This prompts us to study the characteristics of bacteria grown in space [1]. It has been shown that a pre-exposure to low levels of either ionizing or non-ionizing radiation can make microorganisms more resistant not only to high doses of ionizing radiation but to any factor that threatens their survival (e.g. antibiotics) [2], [3]. This phenomenon that is called “adaptive response” (i.e. increased resistance in living organisms pre-exposed to a low level stressor such as a low dose of ionizing radiation) [4] significantly increases the risk of serious infections in deep space missions. It's worth noting that both animal and human data confirm the disruption of the immune system during spaceflight [5]. In addition, the virulence of bacteria can also be increased significantly in space [4], hence this kind of adaptive response which increases the resistance of bacteria can endanger the astronauts' lives in space. On the other hand, A NASA report notes that as astronauts' cells will be exposed to multiple protons before being traversed by HZE particles, they can show adaptive responses. Given this consideration, it would be realistic to expect co-radioadaptation of astronauts' microbiome and their body in a deep space journey to Mars and beyond. The complexity of these phenomena and current uncertainties, which highlight the need for further studies before any long-term manned mission, will be discussed in this paper.
{"title":"Radioadaptation of Astronauts' Microbiome and Bodies in a Deep Space Mission to Mars and Beyond","authors":"S. Mortazavi, S. Mortazavi, L. Sihver","doi":"10.1109/AERO47225.2020.9172670","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172670","url":null,"abstract":"During manned space missions, humans will be accompanied by microorganisms. This prompts us to study the characteristics of bacteria grown in space [1]. It has been shown that a pre-exposure to low levels of either ionizing or non-ionizing radiation can make microorganisms more resistant not only to high doses of ionizing radiation but to any factor that threatens their survival (e.g. antibiotics) [2], [3]. This phenomenon that is called “adaptive response” (i.e. increased resistance in living organisms pre-exposed to a low level stressor such as a low dose of ionizing radiation) [4] significantly increases the risk of serious infections in deep space missions. It's worth noting that both animal and human data confirm the disruption of the immune system during spaceflight [5]. In addition, the virulence of bacteria can also be increased significantly in space [4], hence this kind of adaptive response which increases the resistance of bacteria can endanger the astronauts' lives in space. On the other hand, A NASA report notes that as astronauts' cells will be exposed to multiple protons before being traversed by HZE particles, they can show adaptive responses. Given this consideration, it would be realistic to expect co-radioadaptation of astronauts' microbiome and their body in a deep space journey to Mars and beyond. The complexity of these phenomena and current uncertainties, which highlight the need for further studies before any long-term manned mission, will be discussed in this paper.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"38 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":"127253668","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/AERO47225.2020.9172325
Marlin Ballard, A. Baker, R. Peak, Selçuk Cimtalay, M. Blackburn, D. Mavris
One major benefit offered by MBSE is the ability to formalize interactions between subsystems in the design process. This formalization eases the transfer of information between parties. The process of government acquisition is likewise characterized by information transfer: diverse requirements must be altered and tracked between the requesting, responding, and evaluating parties. Thus, it is a natural extension of MBSE is to apply it to the acquisition process. This paper demonstrates a set of tools and patterns developed during a surrogate simulation of an MBSE-enabled Request for Proposal between NAVAIR and a responding contractor. In particular, the tools presented were developed from the NAVAIR Systems Model viewpoint. This paper covers four tools developed in this surrogate pilot. The first analyzes the problem of requirement generation. While standards such as the OMG SysML are being adopted by MBSE practitioners, the model literacy of all stakeholders is unlikely and may never be fully guaranteed. Document generation tools, such as OpenMBEE have been developed for SysML software, which enable presentation of descriptive information about the model. This paper demonstrates modeling patterns and a tool that translates information from native-model form into a text-based format. The second and third tools presented assist in the acquirer's source selection process. Making use of the patterns which generate the text requirements above, Evaluation and Estimation Models are presented, which can act directly on contractors' responses. The Evaluation Model assists the verification process by ensuring numerical requirements are satisfied. The Estimation Model compares the contractors' claimed values with historically expected values, to assist directing the source selection experts' focus of examination. The fourth tool presented offers a method of extracting historical traceability for model elements. This aids the acquisition process by enabling digital signoff at any stage of the acquisition process. These four tools were applied in the surrogate acquisition process for a notional UAV, and a description of this case study is presented.
{"title":"Facilitating the Transition to Model-Based Acquisition","authors":"Marlin Ballard, A. Baker, R. Peak, Selçuk Cimtalay, M. Blackburn, D. Mavris","doi":"10.1109/AERO47225.2020.9172325","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172325","url":null,"abstract":"One major benefit offered by MBSE is the ability to formalize interactions between subsystems in the design process. This formalization eases the transfer of information between parties. The process of government acquisition is likewise characterized by information transfer: diverse requirements must be altered and tracked between the requesting, responding, and evaluating parties. Thus, it is a natural extension of MBSE is to apply it to the acquisition process. This paper demonstrates a set of tools and patterns developed during a surrogate simulation of an MBSE-enabled Request for Proposal between NAVAIR and a responding contractor. In particular, the tools presented were developed from the NAVAIR Systems Model viewpoint. This paper covers four tools developed in this surrogate pilot. The first analyzes the problem of requirement generation. While standards such as the OMG SysML are being adopted by MBSE practitioners, the model literacy of all stakeholders is unlikely and may never be fully guaranteed. Document generation tools, such as OpenMBEE have been developed for SysML software, which enable presentation of descriptive information about the model. This paper demonstrates modeling patterns and a tool that translates information from native-model form into a text-based format. The second and third tools presented assist in the acquirer's source selection process. Making use of the patterns which generate the text requirements above, Evaluation and Estimation Models are presented, which can act directly on contractors' responses. The Evaluation Model assists the verification process by ensuring numerical requirements are satisfied. The Estimation Model compares the contractors' claimed values with historically expected values, to assist directing the source selection experts' focus of examination. The fourth tool presented offers a method of extracting historical traceability for model elements. This aids the acquisition process by enabling digital signoff at any stage of the acquisition process. These four tools were applied in the surrogate acquisition process for a notional UAV, and a description of this case study is presented.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"146 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":"127512202","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/AERO47225.2020.9172607
B. Donahue
The NASA Space Launch Systems (SLS) outstanding capabilities for launching heavy, large diameter payloads will enable robust lunar architectures where the Near Rectilinear Halo Orbit (NRHO) is used as an aggregation node for lander and Orion elements. SLS capabilities and production status is discussed, as is the new large Exploration Upper Stage, currently in development, which will optimize the SLS Core and Booster Stages. A simplified lunar architecture is presented that takes advantage of the SLS launch capabilities. An overview of lander engine options is given and a propulsion trade study is performed and conclusions are drawn.
{"title":"Crewed Lunar Missions and Architectures Enabled by the NASA Space Launch System","authors":"B. Donahue","doi":"10.1109/AERO47225.2020.9172607","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172607","url":null,"abstract":"The NASA Space Launch Systems (SLS) outstanding capabilities for launching heavy, large diameter payloads will enable robust lunar architectures where the Near Rectilinear Halo Orbit (NRHO) is used as an aggregation node for lander and Orion elements. SLS capabilities and production status is discussed, as is the new large Exploration Upper Stage, currently in development, which will optimize the SLS Core and Booster Stages. A simplified lunar architecture is presented that takes advantage of the SLS launch capabilities. An overview of lander engine options is given and a propulsion trade study is performed and conclusions are drawn.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"150 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":"131846503","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/AERO47225.2020.9172535
Shenghao Jiang, Macheng Shen
Consider a scenario where multiple Unmanned Aerial Vehicles (UAVs) autonomously collaborate with each other to explore an unknown environment where GPS is not available. A visual fiducial marker with known geometry is fixed on each UAV to provide relative localization between any pair of UAVs. Nevertheless, the UAV s need to plan their motion to ensure that the marker always appears in camera's field-of-view so that they can be localized. Such requirement limits the trajectory space of UAVs when they are exploring the environment. To solve this issue, our first technical contribution is an innovative multi-UAV spatial closed-loop coordination mechanism, which provides guaranteed relative localization wherever they are in the unknown and texture-less environment. The coordination, however, requires that the environment satisfy line-of-sight (LOS) constraints, and therefore necessities the division of the global environment into different subareas such that LOS constraints are met within each subarea. Our second contribution is a novel temporal-spatial pose graph to register different subareas into one global environment accurately. Finally, we present an iterative strategy to simultaneously maximize the volume of exploration space and minimize the localization error under the line-of-sight (LOS) constraints. Comparison with STOA visual localization techniques in simulated unknown environment demonstrates that our method is robust, accurate and independent of the environment.
{"title":"Localization - guaranteed navigation in GPS-denied environment via multi-UAV closed-loop coordination","authors":"Shenghao Jiang, Macheng Shen","doi":"10.1109/AERO47225.2020.9172535","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172535","url":null,"abstract":"Consider a scenario where multiple Unmanned Aerial Vehicles (UAVs) autonomously collaborate with each other to explore an unknown environment where GPS is not available. A visual fiducial marker with known geometry is fixed on each UAV to provide relative localization between any pair of UAVs. Nevertheless, the UAV s need to plan their motion to ensure that the marker always appears in camera's field-of-view so that they can be localized. Such requirement limits the trajectory space of UAVs when they are exploring the environment. To solve this issue, our first technical contribution is an innovative multi-UAV spatial closed-loop coordination mechanism, which provides guaranteed relative localization wherever they are in the unknown and texture-less environment. The coordination, however, requires that the environment satisfy line-of-sight (LOS) constraints, and therefore necessities the division of the global environment into different subareas such that LOS constraints are met within each subarea. Our second contribution is a novel temporal-spatial pose graph to register different subareas into one global environment accurately. Finally, we present an iterative strategy to simultaneously maximize the volume of exploration space and minimize the localization error under the line-of-sight (LOS) constraints. Comparison with STOA visual localization techniques in simulated unknown environment demonstrates that our method is robust, accurate and independent of the environment.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"3 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":"132174963","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/AERO47225.2020.9172298
Shintaro Hashimoto, Daichi Hirano, N. Ishihama
Before space debris can be removed efficiently, its 6-DoF poses (positions and attitudes) need to be estimated accurately from observed images with high resolution. Further, if the debris is axisymmetric, such as the remains of a multistage rocket, or if part of the debris cannot be seen due to optical conditions, it is considerably more difficult to estimate its parameters. If some parameters cannot be estimated for some reason, all parameters may be affected because each parameter in Euler angle and quaternion has an interdependency and the solution will not be determined uniquely. This research proposes methods that obtain the solution by decomposing the quaternion into the direction and rotation based on the forward direction so that direction and rotation parameters can be estimated independently. Moreover, this research was able to adaptively improve accuracy based on a threshold of uncertainty by adding an uncertainty value to each parameter. When the estimated parameters likely having error values that exceed 2% based on uncertainty value are deleted, estimated error of parameter $x, y, z$ (position), $n_{x}, n_{y},n_{z}$ and $theta_{z}$ (attitude) were 1.25%, 1.35%, 3.76%, 2.27%, 2.64%, 3.06%, and 18.32% respectively.
{"title":"6-DoF Pose Estimation for Axisymmetric Objects Using Deep Learning with Uncertainty","authors":"Shintaro Hashimoto, Daichi Hirano, N. Ishihama","doi":"10.1109/AERO47225.2020.9172298","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172298","url":null,"abstract":"Before space debris can be removed efficiently, its 6-DoF poses (positions and attitudes) need to be estimated accurately from observed images with high resolution. Further, if the debris is axisymmetric, such as the remains of a multistage rocket, or if part of the debris cannot be seen due to optical conditions, it is considerably more difficult to estimate its parameters. If some parameters cannot be estimated for some reason, all parameters may be affected because each parameter in Euler angle and quaternion has an interdependency and the solution will not be determined uniquely. This research proposes methods that obtain the solution by decomposing the quaternion into the direction and rotation based on the forward direction so that direction and rotation parameters can be estimated independently. Moreover, this research was able to adaptively improve accuracy based on a threshold of uncertainty by adding an uncertainty value to each parameter. When the estimated parameters likely having error values that exceed 2% based on uncertainty value are deleted, estimated error of parameter $x, y, z$ (position), $n_{x}, n_{y},n_{z}$ and $theta_{z}$ (attitude) were 1.25%, 1.35%, 3.76%, 2.27%, 2.64%, 3.06%, and 18.32% respectively.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"1 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":"130802527","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/AERO47225.2020.9172645
A. Papenfuss, Fabian Reuschling, J. Jakobi, T. Rambau, E. Michaelsen, N. Scherer-Negenborn
The research project INVIDEON evaluated requirements, technical solutions and the benefit of fusing visible (VIS) and infra-red (IR) spectrum camera streams into a single panorama video stream. In this paper, the design process for developing a usable and accepted fusion is described. As both sensors have strengthens and weaknesses, INVIDEON proposes a fused panorama optimized out of both sensors to be presented to the ATC officer (ATCO). This paper gives an overview of the project and reports results of acceptance and usability of the INVIDEON solution. The process of supporting the definition of requirements by means of rapid prototyping and taking a user-centered approach is described. Main findings of requirements for fusing VIS and IR camera data for remote tower operations are highlighted and set into context with the air traffic controller's tasks. A specific fusion approach was developed within the project and evaluated by means of recorded IR and VIS data. For evaluation, a testbed was set up at a regional airport and data representing different visibility conditions were selected out of 70 days data recordings. Five air traffic controllers participated in the final evaluation. Subjective data on perceived usability, situational awareness and trust in automation was assessed. Furthermore, qualitative data on HMI design and optimization potential from debriefings and comments was collected and clustered.
{"title":"Designing a fusion of visible and infra-red camera streams for remote tower operations","authors":"A. Papenfuss, Fabian Reuschling, J. Jakobi, T. Rambau, E. Michaelsen, N. Scherer-Negenborn","doi":"10.1109/AERO47225.2020.9172645","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172645","url":null,"abstract":"The research project INVIDEON evaluated requirements, technical solutions and the benefit of fusing visible (VIS) and infra-red (IR) spectrum camera streams into a single panorama video stream. In this paper, the design process for developing a usable and accepted fusion is described. As both sensors have strengthens and weaknesses, INVIDEON proposes a fused panorama optimized out of both sensors to be presented to the ATC officer (ATCO). This paper gives an overview of the project and reports results of acceptance and usability of the INVIDEON solution. The process of supporting the definition of requirements by means of rapid prototyping and taking a user-centered approach is described. Main findings of requirements for fusing VIS and IR camera data for remote tower operations are highlighted and set into context with the air traffic controller's tasks. A specific fusion approach was developed within the project and evaluated by means of recorded IR and VIS data. For evaluation, a testbed was set up at a regional airport and data representing different visibility conditions were selected out of 70 days data recordings. Five air traffic controllers participated in the final evaluation. Subjective data on perceived usability, situational awareness and trust in automation was assessed. Furthermore, qualitative data on HMI design and optimization potential from debriefings and comments was collected and clustered.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"24 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":"130907477","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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