Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10115925
A. Rupert, B. McGrath, J. C. Brill, Bruce J. P. Mortimer
For the past 25 years we have used traditional spatial orientation models together with flight data recordings to analyze and predict pilot orientation in aviation mishaps for which there is no apparent mechanical failure or in which spatial disorientation is suspected as a cause of the mishap. The model has been verified in rare mishaps where surviving aircrew have verified predicted perceptions and provided probable causation of several air transport mishaps for NTSB investigations especially dealing with the somatogravic illusions associated with go-around maneuvers. It was thought that helicopters did not have sufficient acceleration to produce the somatogravic illusion. There have been two recent interesting mishaps one which was clearly a somatogravic illusion (aircraft flight recorder data and cockpit voice recorder) and a second high profile mishap (Kobe Bryant) with almost identical flight path and similar degraded visual environment. These mishaps will be examined from the perspective of the recently revised perceptual model to show how the positive feedback nature of the somatogravic illusion can provide overwhelmingly compelling pitch-up sensations to the somatosensory and vestibular sensations even while the pilot is applying 40 plus degree nose down control inputs and looking at the orientation instrumentation. The recent model revisions also provide multisensory options with novel technologies to prevent this type of mishap. The revised and expanded model will assist our DoD safety centers, the FAA and the NTSB in the analysis of future mishaps. Furthermore, the model with all sensory systems now included provides indications of the best technology combinations to be implemented for future cockpits, especially as full automation is becoming more prevalent.
{"title":"Spatial Orientation Modeling: Expanding the Helicopter Envelope","authors":"A. Rupert, B. McGrath, J. C. Brill, Bruce J. P. Mortimer","doi":"10.1109/AERO55745.2023.10115925","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115925","url":null,"abstract":"For the past 25 years we have used traditional spatial orientation models together with flight data recordings to analyze and predict pilot orientation in aviation mishaps for which there is no apparent mechanical failure or in which spatial disorientation is suspected as a cause of the mishap. The model has been verified in rare mishaps where surviving aircrew have verified predicted perceptions and provided probable causation of several air transport mishaps for NTSB investigations especially dealing with the somatogravic illusions associated with go-around maneuvers. It was thought that helicopters did not have sufficient acceleration to produce the somatogravic illusion. There have been two recent interesting mishaps one which was clearly a somatogravic illusion (aircraft flight recorder data and cockpit voice recorder) and a second high profile mishap (Kobe Bryant) with almost identical flight path and similar degraded visual environment. These mishaps will be examined from the perspective of the recently revised perceptual model to show how the positive feedback nature of the somatogravic illusion can provide overwhelmingly compelling pitch-up sensations to the somatosensory and vestibular sensations even while the pilot is applying 40 plus degree nose down control inputs and looking at the orientation instrumentation. The recent model revisions also provide multisensory options with novel technologies to prevent this type of mishap. The revised and expanded model will assist our DoD safety centers, the FAA and the NTSB in the analysis of future mishaps. Furthermore, the model with all sensory systems now included provides indications of the best technology combinations to be implemented for future cockpits, especially as full automation is becoming more prevalent.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"248 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134146792","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115549
Li-Li Jiao, Li Zhou, Zhanxue Wang, Jing-wei Shi
In order to improve fighters' stealth ability and reach an integrated design of the outer fuselage and nozzle, a double serpentine nozzle can be scarfed at the tail according to the aircraft's skin. But the jet flow of the exhaust system is deflected when a nozzle is beveled, which makes the thrust line not completely coincide with the aircraft axis. Different degrees of thrust line cause corresponding deflection torque, which affects the aerodynamics layout of the aircraft and causes difficulties in aircraft control. In this paper, a double serpentine nozzle with bevel which consists of a first bend section, second bend section, and bevel section is taken as the baseline to study the influence of geometric parameters of the double serpentine nozzle with bevel on flow characteristics. Two parameters of the bevel section, angle, and length, were selected to research. Seven nozzles with different deflection angles of the bevel section were numerically simulated. Results show that the aerodynamic parameters of those nozzles are slightly different. The thrust line deflects in the same direction as the changed deflection direction of the bevel section, but the deflection amplitude of the thrust line is significantly smaller than the deflection amplitude of the bevel section. And when deflecting one direction (Y/Z) actively, the other direction (Z/Y) will have the opposite effect. The change of the bevel section deflection angle has a greater impact on the thrust line. Six nozzles with different lengths of the bevel section were selected. Numerical results show that as the length increases, the friction resistance of nozzles increases, and the loss increases. With the increase in the length of the bevel section, the angle between the thrust line and the vertical plane XY is gradually decreasing, so the thrust line deflects close to the bevel section axis. For the angle with the horizontal plane XZ, the thrust line deflects upward when the bevel section lengthens by 7%; then when the length of the bevel section continues to increase, the thrust line deflects downward. The average angle variation in each direction is about 0.1° when the length increases by 7%. In this paper, four flight conditions including subsonic and, supersonic jet conditions are studied. Flight conditions heavily influence the thrust line of the double serpentine nozzle with bevel.
{"title":"Influence of Bevel Section on Flow Characteristics of Double Serpentine Nozzle with Bevel","authors":"Li-Li Jiao, Li Zhou, Zhanxue Wang, Jing-wei Shi","doi":"10.1109/AERO55745.2023.10115549","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115549","url":null,"abstract":"In order to improve fighters' stealth ability and reach an integrated design of the outer fuselage and nozzle, a double serpentine nozzle can be scarfed at the tail according to the aircraft's skin. But the jet flow of the exhaust system is deflected when a nozzle is beveled, which makes the thrust line not completely coincide with the aircraft axis. Different degrees of thrust line cause corresponding deflection torque, which affects the aerodynamics layout of the aircraft and causes difficulties in aircraft control. In this paper, a double serpentine nozzle with bevel which consists of a first bend section, second bend section, and bevel section is taken as the baseline to study the influence of geometric parameters of the double serpentine nozzle with bevel on flow characteristics. Two parameters of the bevel section, angle, and length, were selected to research. Seven nozzles with different deflection angles of the bevel section were numerically simulated. Results show that the aerodynamic parameters of those nozzles are slightly different. The thrust line deflects in the same direction as the changed deflection direction of the bevel section, but the deflection amplitude of the thrust line is significantly smaller than the deflection amplitude of the bevel section. And when deflecting one direction (Y/Z) actively, the other direction (Z/Y) will have the opposite effect. The change of the bevel section deflection angle has a greater impact on the thrust line. Six nozzles with different lengths of the bevel section were selected. Numerical results show that as the length increases, the friction resistance of nozzles increases, and the loss increases. With the increase in the length of the bevel section, the angle between the thrust line and the vertical plane XY is gradually decreasing, so the thrust line deflects close to the bevel section axis. For the angle with the horizontal plane XZ, the thrust line deflects upward when the bevel section lengthens by 7%; then when the length of the bevel section continues to increase, the thrust line deflects downward. The average angle variation in each direction is about 0.1° when the length increases by 7%. In this paper, four flight conditions including subsonic and, supersonic jet conditions are studied. Flight conditions heavily influence the thrust line of the double serpentine nozzle with bevel.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131534365","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115747
Yuki Matsumoto, Ryo Nakamura, Toshinori Ikenaga, S. Ueda
JAXA is considering the HTV-X for Gateway (HTV-XG) to supply materials to Gateway. As a transition orbit from Earth to the Near Rectilinear Halo Orbit (NRHO) where Gateway will stay, the Hohmann transit orbit using a lunar flyby is being considered in the nominal case. The three major maneuvers in this orbit are the Trans-Lunar Injection (TLI), Powered Lunar Swing-By (PLSB), and NRHO Injection (NRHOI). Recovery trajectories for TLI failure have been studied, but recovery trajectories for NRHOI and PLSB maneuvers have not been studied yet. Therefore, this paper focuses on recovery trajectory planning in case of NRHOI or PLSB failure.
{"title":"Recovery Orbit Search Scheme for Major Maneuver Failure in NRHO Transfer Orbit Using Lunar Flyby","authors":"Yuki Matsumoto, Ryo Nakamura, Toshinori Ikenaga, S. Ueda","doi":"10.1109/AERO55745.2023.10115747","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115747","url":null,"abstract":"JAXA is considering the HTV-X for Gateway (HTV-XG) to supply materials to Gateway. As a transition orbit from Earth to the Near Rectilinear Halo Orbit (NRHO) where Gateway will stay, the Hohmann transit orbit using a lunar flyby is being considered in the nominal case. The three major maneuvers in this orbit are the Trans-Lunar Injection (TLI), Powered Lunar Swing-By (PLSB), and NRHO Injection (NRHOI). Recovery trajectories for TLI failure have been studied, but recovery trajectories for NRHOI and PLSB maneuvers have not been studied yet. Therefore, this paper focuses on recovery trajectory planning in case of NRHOI or PLSB failure.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134340135","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115814
Sebastian-Sven Olzem, Babak Salamat, Thomas Kienast, T. A. Drouven, Elsbacher Gerhard
The objective of this paper is to present a basic preliminary design tool that aims to elaborate on flight mechanical properties of a generic aircraft (e.g. parametrization of different configurations). The proposed framework utilizes either a given set of aerodynamic coefficients or calculates them according to the “blade-theory” by geometrical data. Then, the possible flight envelope of the given aircraft can be computed to evaluate the performance for a trimmed flight state. The modelled airframe can be analysed via the evolution of forces and moments acting on the center of mass to further elaborate on the expected performance. It is also meant to be a tool for testing localization, state estimation and control algorithms. Numerical results are reported for a generic delta-wing plus V-tail fighter configuration.
{"title":"Aircraft Conceptualization and Analysis by Flight Simulation","authors":"Sebastian-Sven Olzem, Babak Salamat, Thomas Kienast, T. A. Drouven, Elsbacher Gerhard","doi":"10.1109/AERO55745.2023.10115814","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115814","url":null,"abstract":"The objective of this paper is to present a basic preliminary design tool that aims to elaborate on flight mechanical properties of a generic aircraft (e.g. parametrization of different configurations). The proposed framework utilizes either a given set of aerodynamic coefficients or calculates them according to the “blade-theory” by geometrical data. Then, the possible flight envelope of the given aircraft can be computed to evaluate the performance for a trimmed flight state. The modelled airframe can be analysed via the evolution of forces and moments acting on the center of mass to further elaborate on the expected performance. It is also meant to be a tool for testing localization, state estimation and control algorithms. Numerical results are reported for a generic delta-wing plus V-tail fighter configuration.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131903876","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115758
Lisa Watson-Morgan, Lakiesha V. Hawkins, Lemuel Carpenter, L. Gagliano, Laura Means, T. Percy, T. Polsgrove, Joseph Vermette, Christopher P. Zavrel
For more than a decade, efforts have been ongoing at NASA's Marshall Space Flight Center (MSFC) in Huntsville, Alabama, to land humans and large, human-rated cargo on planetary bodies like the Moon and Mars. This work continues today under the Center's Landers Program (LP) office. Recognizing MSFC's heritage, NASA stood up the Human Landing System program at the Center in August 2019 to be responsible for spacecrafts that will land the next American astronauts on the Moon under Artemis. With work well underway for the historic Artemis III mission to land the first woman and first person of color on the lunar surface through the Appendix H Option A contract with SpaceX, LP is focused on the development of landers that will support the Agency's long-term Artemis efforts at the Moon and NASA's future at Mars. In March 2022, NASA announced its plan to solicit a second industry provider in addition to SpaceX to develop and demonstrate a lander that meets the program's extended set of requirements for missions beyond Artemis III. Under the umbrella of Sustaining Lunar Development, these requirements will meet NASA's needs for recurring, long-term access to the lunar surface, such as accommodating an increased crew size and delivering more mass to the surface. Additionally, NASA plans to leverage crewed lander development activities to procure and certify the design of landers capable of human-class cargo delivery. This paper will examine how the Landers Program office at MSFC is bridging from the initial demonstration phase of development for the Human Landing System program to the Sustaining Lunar Development phase and feeding forward to Mars. The requirements and lines of effort for landing humans and human class cargo will be discussed, as well as near-term and future milestones for the program.
{"title":"Landing Humans and Human-Class Cargo on the Moon and Mars","authors":"Lisa Watson-Morgan, Lakiesha V. Hawkins, Lemuel Carpenter, L. Gagliano, Laura Means, T. Percy, T. Polsgrove, Joseph Vermette, Christopher P. Zavrel","doi":"10.1109/AERO55745.2023.10115758","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115758","url":null,"abstract":"For more than a decade, efforts have been ongoing at NASA's Marshall Space Flight Center (MSFC) in Huntsville, Alabama, to land humans and large, human-rated cargo on planetary bodies like the Moon and Mars. This work continues today under the Center's Landers Program (LP) office. Recognizing MSFC's heritage, NASA stood up the Human Landing System program at the Center in August 2019 to be responsible for spacecrafts that will land the next American astronauts on the Moon under Artemis. With work well underway for the historic Artemis III mission to land the first woman and first person of color on the lunar surface through the Appendix H Option A contract with SpaceX, LP is focused on the development of landers that will support the Agency's long-term Artemis efforts at the Moon and NASA's future at Mars. In March 2022, NASA announced its plan to solicit a second industry provider in addition to SpaceX to develop and demonstrate a lander that meets the program's extended set of requirements for missions beyond Artemis III. Under the umbrella of Sustaining Lunar Development, these requirements will meet NASA's needs for recurring, long-term access to the lunar surface, such as accommodating an increased crew size and delivering more mass to the surface. Additionally, NASA plans to leverage crewed lander development activities to procure and certify the design of landers capable of human-class cargo delivery. This paper will examine how the Landers Program office at MSFC is bridging from the initial demonstration phase of development for the Human Landing System program to the Sustaining Lunar Development phase and feeding forward to Mars. The requirements and lines of effort for landing humans and human class cargo will be discussed, as well as near-term and future milestones for the program.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133874807","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115778
A. Connell, Matthew F. Hurst
The flight software for the Mars Perseverance Rover is capable of autonomous onboard scheduling. The goal of this capability is to reduce spacecraft idle time and unnecessary heating to leave more resources for science observations. Enabling this first-of-its-kind onboard scheduling requires tight coordination between the Mission Operations team, ground software, and flight software. This paper will focus on the ground software tools that have been created or enhanced by the Mars 2020 mission in support of autonomous onboard scheduling. The following challenges were encountered: automating the creation of planning constraints to reduce tedious and error-prone manual work, while providing enough flexibility for the team to handle unique scenarios; providing visibility to allow the Operations team to build trust in a variable execution system in a way that is digestible within a tight planning timeline; using flight software simulation to validate the files that will be sent to the spacecraft in a realistic manner, even though we cannot truly predict what will happen on the rover; after plan execution on the rover, analyzing the data returned from the spacecraft to understand what did happen, and using that information to predict initial conditions for the next planning cycle.
{"title":"Ground Software to Support Autonomous Onboard Scheduling for Mars Perseverance Rover","authors":"A. Connell, Matthew F. Hurst","doi":"10.1109/AERO55745.2023.10115778","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115778","url":null,"abstract":"The flight software for the Mars Perseverance Rover is capable of autonomous onboard scheduling. The goal of this capability is to reduce spacecraft idle time and unnecessary heating to leave more resources for science observations. Enabling this first-of-its-kind onboard scheduling requires tight coordination between the Mission Operations team, ground software, and flight software. This paper will focus on the ground software tools that have been created or enhanced by the Mars 2020 mission in support of autonomous onboard scheduling. The following challenges were encountered: automating the creation of planning constraints to reduce tedious and error-prone manual work, while providing enough flexibility for the team to handle unique scenarios; providing visibility to allow the Operations team to build trust in a variable execution system in a way that is digestible within a tight planning timeline; using flight software simulation to validate the files that will be sent to the spacecraft in a realistic manner, even though we cannot truly predict what will happen on the rover; after plan execution on the rover, analyzing the data returned from the spacecraft to understand what did happen, and using that information to predict initial conditions for the next planning cycle.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"9 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133828634","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115569
Rachel Misbin, A. George
Hardware-in-the-loop testing is a popular, economi-cal way to test and validate flight software systems for small satellites compared to testing on flight hardware. Further cost savings can be achieved by replacing the hardware in these systems with functionally equivalent emulations (some-times termed “emulation-in-the-loop”). This work aims to better inform system-level small satellite flight software test design through a study of the tradeoffs between hardware-in-the-loop and emulation-in-the-loop systems. In this work, two systems are presented-one featuring hardware, the other featuring emulation-which are used to evaluate the advantages and disadvantages of a traditional hardware-in-the-loop testbed compared to an emulation-in-the-loop testbed. Two demon-strations are performed on these two testbeds: (1) a large-scale spacecraft cluster demonstration, which seeks to show how hardware and emulation perform at scale; and (2) an image processing demonstration, which seeks to show how hardware and emulation differ for more compute-intensive applications. The hardware-in-the-loop testbed is composed of an instance of NASA's core Flight System (cFS) running on the ARM Cortex-A9 processor of a Zynq-7020 System-on-Chip (SoC) interfaced with NASA Goddard's open-source 42 spacecraft simulator to create a closed-loop system. The emulation-in-the-loop testbed is identical but with the ARM processor emulated instead. Emulation-in-the-loop systems offer portability, cost savings, and improved scalability over hardware-in-the-loop systems but at the cost of system accuracy and increased complexity. In the case of flight software for small satellites, the inherent reduced accuracy of emulation-in-the-loop can prove acceptable in light of the significant cost savings, the reduction in depen-dence on hardware early in development, and the reduction of wear on hardware. In addition to the two emulation-based and hardware-based demonstrations, a comprehensive view of the benefits and drawbacks of QEMU-based emulation as a replacement for traditional hardware is presented for the case of in-the-loop simulation of flight software.
{"title":"QEMU-Based Emulation-in-the-Loop for the Simulation of Small Satellite Flight Software","authors":"Rachel Misbin, A. George","doi":"10.1109/AERO55745.2023.10115569","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115569","url":null,"abstract":"Hardware-in-the-loop testing is a popular, economi-cal way to test and validate flight software systems for small satellites compared to testing on flight hardware. Further cost savings can be achieved by replacing the hardware in these systems with functionally equivalent emulations (some-times termed “emulation-in-the-loop”). This work aims to better inform system-level small satellite flight software test design through a study of the tradeoffs between hardware-in-the-loop and emulation-in-the-loop systems. In this work, two systems are presented-one featuring hardware, the other featuring emulation-which are used to evaluate the advantages and disadvantages of a traditional hardware-in-the-loop testbed compared to an emulation-in-the-loop testbed. Two demon-strations are performed on these two testbeds: (1) a large-scale spacecraft cluster demonstration, which seeks to show how hardware and emulation perform at scale; and (2) an image processing demonstration, which seeks to show how hardware and emulation differ for more compute-intensive applications. The hardware-in-the-loop testbed is composed of an instance of NASA's core Flight System (cFS) running on the ARM Cortex-A9 processor of a Zynq-7020 System-on-Chip (SoC) interfaced with NASA Goddard's open-source 42 spacecraft simulator to create a closed-loop system. The emulation-in-the-loop testbed is identical but with the ARM processor emulated instead. Emulation-in-the-loop systems offer portability, cost savings, and improved scalability over hardware-in-the-loop systems but at the cost of system accuracy and increased complexity. In the case of flight software for small satellites, the inherent reduced accuracy of emulation-in-the-loop can prove acceptable in light of the significant cost savings, the reduction in depen-dence on hardware early in development, and the reduction of wear on hardware. In addition to the two emulation-based and hardware-based demonstrations, a comprehensive view of the benefits and drawbacks of QEMU-based emulation as a replacement for traditional hardware is presented for the case of in-the-loop simulation of flight software.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"66 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133013525","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10115714
P. Wurz, T. Bandy, P. Mandli, Simon Studer, Sebastien Havoz, Matthias Blaukovitsch, Benoit Gabriel Plet, M. Tulej, D. Piazza, Peter Keresztes Schmidt, Sven Riedo, A. Riedo
We are developing laser-based mass spectrometry (LIMS) for the in situ investigation of the chemical and mineralogical composition of the lunar regolith. The current development of our LIMS instrument is for an application on a robotic mission within the Artemis CLPS program of NASA. The CLPS lander will be placed in the south polar region. The LIMS system consists of a time-of-flight mass analyzer (TOF-MS), a laser system (LSS) providing nano-second laser pulses focused to um spots on the sample surface, electronics (ELU) for operating the LIMS system, and a sample handling system (SHS). The TOF-MS, LSS, and ELU are according to our established design presented earlier. The SHS is specially designed for the CLPS lander to collect regolith grains from the lunar surface in the vicinity of the lander. The SHS design foresees rotating steel brushes that free regolith grains from the surface into ballistic trajectories. A conveyor belt collects these grains, which is electrically biased to improve its collection efficiency. Adjusting the speed of the brushes and the voltage on the conveyor belt allow to optimize the collection efficiency of the grains. The conveyor belt transports the grains to the entrance of the mass analyzer where grain by grain analysis will be performed. The main scientific objective for the LIMS instrument is the geochemical analysis of the lunar regolith, by the analysis of individual regolith grains and assessing their mineralogical diversity. In addition, this investigation will also address technical aspects of sampling a planetary surface at or near a landed spacecraft, i.e., the effect the plume of the retrorockets has on the regolith underneath the lander. Of particular interest is the chemical contamination of the surface by the spent fuel, and the amount of removal grains by the gas drag.
{"title":"In Situ Lunar Regolith Analysis by Laser-Based Mass Spectrometry","authors":"P. Wurz, T. Bandy, P. Mandli, Simon Studer, Sebastien Havoz, Matthias Blaukovitsch, Benoit Gabriel Plet, M. Tulej, D. Piazza, Peter Keresztes Schmidt, Sven Riedo, A. Riedo","doi":"10.1109/AERO55745.2023.10115714","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115714","url":null,"abstract":"We are developing laser-based mass spectrometry (LIMS) for the in situ investigation of the chemical and mineralogical composition of the lunar regolith. The current development of our LIMS instrument is for an application on a robotic mission within the Artemis CLPS program of NASA. The CLPS lander will be placed in the south polar region. The LIMS system consists of a time-of-flight mass analyzer (TOF-MS), a laser system (LSS) providing nano-second laser pulses focused to um spots on the sample surface, electronics (ELU) for operating the LIMS system, and a sample handling system (SHS). The TOF-MS, LSS, and ELU are according to our established design presented earlier. The SHS is specially designed for the CLPS lander to collect regolith grains from the lunar surface in the vicinity of the lander. The SHS design foresees rotating steel brushes that free regolith grains from the surface into ballistic trajectories. A conveyor belt collects these grains, which is electrically biased to improve its collection efficiency. Adjusting the speed of the brushes and the voltage on the conveyor belt allow to optimize the collection efficiency of the grains. The conveyor belt transports the grains to the entrance of the mass analyzer where grain by grain analysis will be performed. The main scientific objective for the LIMS instrument is the geochemical analysis of the lunar regolith, by the analysis of individual regolith grains and assessing their mineralogical diversity. In addition, this investigation will also address technical aspects of sampling a planetary surface at or near a landed spacecraft, i.e., the effect the plume of the retrorockets has on the regolith underneath the lander. Of particular interest is the chemical contamination of the surface by the spent fuel, and the amount of removal grains by the gas drag.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"116 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121112541","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 : 2023-03-04DOI: 10.1109/AERO55745.2023.10116016
R. Killough, M. Beasley, Alan Henry, C. Deforest, J. Redfern, William Wells, Keith G. W. Smith, G. Laurent, Sarah Gibson, R. Colaninno
The Polarimeter to UNify the Corona and Heliosphere (PUNCH) mission comprises a constellation of four micro-satellites that will produce 3D images of the solar wind by imaging the faint traces of sunlight reflected from free electrons in the solar corona and solar wind. Three of the PUNCH observatories host a Wide Field Imager (WFI) instrument each, and one hosts a Narrow Field Imager (NFI). The mission is funded by the NASA Explorers Program. This paper highlights some of the design decisions that went into enabling what has been described as an elegant design, enabling a common spacecraft as well as significant commonality in instrument components for the four PUNCH observatories hosting three very different instruments. The design approach minimized risk while enabling big science in the context of a Small Explorer mission budget. Although well into flight development and fabrication, PUNCH was recently transitioned from a prime mission to a rideshare mission for deployment from a secondary payload adaptor. We briefly discuss some of the challenges encountered to-date in this transition, assumptions that had to be made, and impact to the mission schedule.
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Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10115968
R. Allen, Y. Rachlin, J. Ruprecht, Sean Loughran, J. Varey, H. Viggh
This paper introduces a collection of non-cooperative game environments that are intended to spur development and act as proving grounds for autonomous and AI decision-makers in the orbital domain. SpaceGym comprises two distinct suites of game environments: OrbitDefender2D (OD2D) and the Ker-bal Space Program Differential Games suite (KSPDG). OrbitDe-fender2D consists of discrete, chess-like, two-player gridworld games. OD2D game mechanics are loosely based on orbital motion and players compete to maintain control of orbital slots. The KSPDG suite consists of multi-agent pursuit-evasion differential games constructed within the Kerbal Space Program (KSP) game engine. In comparison to the very limited set of comparable environments in the existing literature, KSPDG represents a much more configurable, extensible, and higher-fidelity aerospace environment suite that leverages a mature game engine to incorporate physics models for phenomenon such as collision mechanics, kinematic chains for deformable bodies, atmospheric drag, variable-mass propulsion, solar irradiance, and thermal models. Both the discrete and differential game suites are built with standardized input/output interfaces based on OpenAI Gym and PettingZoo specifications. This standardization enables-but does not enforce-the use of rein-forcement learning agents within the SpaceGym environments. As a comparison point for future research, we provide baseline agents that employ techniques of model predictive control, numerical differential game solvers, and reinforcement learning-along with their respective performance metrics-for a subset of the SpaceGym environments. The SpaceGym software libraries can be found at https://github.com/mit-II/spacegym-od2d and https://github.com/mit-II/spacegym-kspdg.
本文介绍了一系列非合作游戏环境，旨在刺激开发，并作为轨道领域自主和人工智能决策者的试验场。SpaceGym包含两个不同的游戏环境套件:OrbitDefender2D (OD2D)和Ker-bal Space Program Differential Games套件(KSPDG)。《OrbitDe-fender2D》是一款类似国际象棋的双人网格世界游戏。OD2D游戏机制基于轨道运动，玩家通过竞争来保持对轨道槽的控制。KSPDG套件由在Kerbal空间计划(KSP)游戏引擎中构建的多智能体追击-逃避微分博弈组成。与现有文献中非常有限的可比环境相比，KSPDG代表了一个更具可配置性、可扩展性和更高保真度的航空航天环境套件，它利用成熟的游戏引擎将碰撞力学、可变形物体的运动链、大气阻力、变质量推进、太阳辐照度和热模型等现象的物理模型结合起来。离散和差分游戏套件都是基于OpenAI Gym和PettingZoo规范的标准化输入/输出接口构建的。这种标准化支持(但不强制)在SpaceGym环境中使用强化学习代理。作为未来研究的比较点，我们为SpaceGym环境的一个子集提供了采用模型预测控制、数值微分博弈求解器和强化学习技术的基线代理，以及它们各自的性能指标。SpaceGym软件库可以在https://github.com/mit-II/spacegym-od2d和https://github.com/mit-II/spacegym-kspdg上找到。
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