Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10115602
Stanley D. Straight, Kara O'Donnell, S. Herrin
The pace of innovation in the space community is accelerating. Even with limited resources and more complex, disaggregated missions on the horizon, the opportunity for technology development continues to grow exponentially. This gives an opportunity for the Space Force to accelerate the transformation of the overall architecture - which will require equally rapid technology transition from Research and Development (R&D) to production and operations. R&D organizations are often chartered to perform revolutionary research (as opposed to evolutionary research) meaning there isn't always the key advocate/warfighter or program for transition identified upfront. Unfortunately, this often results in the “technology transition valley of death” where innovative minimally mature systems aren't adopted into the future enterprise and those potential capabilities are lost. Successful transition of a new technology or new capability to acquisition and operations requires warfighter demand, building partnerships, and securing funding. In addition, other key enablers to rapid transition include rapid prototyping and development, ridesharing, and improved systems integrations processes. To bridge the valley of death, we'll need to rely on these enablers prove the “art of the possible” to potential stakeholders. This paper will address both successes and challenges of technology and capability transition from R&D organizations, using real-world examples of lessons learned. One such example is the ongoing evolution of the AFRL built EAGLE program to Space Systems Command Innovation and Prototyping Acquisition Delta's Long Duration Propulsive ESPA program, both of which are flown by the DoD Space Test Program. It will discuss the importance of not only looking at the systems engineering of the space vehicle, but system integration with ground systems and how other rideshare payloads play a critical role to the success of not just a single mission, but the collective missions that will build our future architecture.
{"title":"Experiences and Observations for Technology Transition in the USSF","authors":"Stanley D. Straight, Kara O'Donnell, S. Herrin","doi":"10.1109/AERO55745.2023.10115602","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115602","url":null,"abstract":"The pace of innovation in the space community is accelerating. Even with limited resources and more complex, disaggregated missions on the horizon, the opportunity for technology development continues to grow exponentially. This gives an opportunity for the Space Force to accelerate the transformation of the overall architecture - which will require equally rapid technology transition from Research and Development (R&D) to production and operations. R&D organizations are often chartered to perform revolutionary research (as opposed to evolutionary research) meaning there isn't always the key advocate/warfighter or program for transition identified upfront. Unfortunately, this often results in the “technology transition valley of death” where innovative minimally mature systems aren't adopted into the future enterprise and those potential capabilities are lost. Successful transition of a new technology or new capability to acquisition and operations requires warfighter demand, building partnerships, and securing funding. In addition, other key enablers to rapid transition include rapid prototyping and development, ridesharing, and improved systems integrations processes. To bridge the valley of death, we'll need to rely on these enablers prove the “art of the possible” to potential stakeholders. This paper will address both successes and challenges of technology and capability transition from R&D organizations, using real-world examples of lessons learned. One such example is the ongoing evolution of the AFRL built EAGLE program to Space Systems Command Innovation and Prototyping Acquisition Delta's Long Duration Propulsive ESPA program, both of which are flown by the DoD Space Test Program. It will discuss the importance of not only looking at the systems engineering of the space vehicle, but system integration with ground systems and how other rideshare payloads play a critical role to the success of not just a single mission, but the collective missions that will build our future architecture.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"22 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":"129156611","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/AERO55745.2023.10115734
Bettina Mrusek, Linda Weiland
The Kessler Effect was predicated on the notion that the addition of objects into orbit around the Earth could reach a tipping point in which space debris would become so condensed that it would restrict our ability to launch anything into orbit. While we are certainly not there yet, launch windows are an essential step in the mission planning process. The rise of constellations fueled by the recent commercialization of space further complicates this scenario and is a cause for concern among researchers and innovators alike. However, advances in technology, specifically, debris mitigation strategies, may prolong or even minimize the likelihood of the Kessler Effect becoming a reality. To examine this problem, current satellite launches were reviewed against debris mitigation strategies then compared to the total number of tracked debris and overall debris, as identified by the European Space Agency (ESA). Multiple linear regression models were used to illustrate the potential impact of additional satellite launches along with projected mitigation strategies on the total number of tracked debris in LEO and overall debris. The independent variable was the number of satellite launches to LEO less the percentage of these satellites that adhered to debris mitigation strategies as defined by the IADC. The dependent variables were the number of tracked debris in LEO and the number of overall debris. The time period for all data was 2010 through 2021. The results of the data analysis indicate that the addition of satellites in LEO does have a significant impact on tracked and overall debris levels, despite mitigation efforts. While the Kessler Theory has not occurred yet, the predictions made in the seminal study were based on a much smaller pool of debris compared to what exists today. Current debris mitigation strategies must be adhered to for new satellites, while effective debris removal opportunities must continue to be explored for existing orbital debris. Additional research that removes Starlink satellites from the sampled population may provide a more reliable view of the problem.
{"title":"Space Commercialization and the Rise of Constellations: The Resulting Impact on the Kessler Effect","authors":"Bettina Mrusek, Linda Weiland","doi":"10.1109/AERO55745.2023.10115734","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115734","url":null,"abstract":"The Kessler Effect was predicated on the notion that the addition of objects into orbit around the Earth could reach a tipping point in which space debris would become so condensed that it would restrict our ability to launch anything into orbit. While we are certainly not there yet, launch windows are an essential step in the mission planning process. The rise of constellations fueled by the recent commercialization of space further complicates this scenario and is a cause for concern among researchers and innovators alike. However, advances in technology, specifically, debris mitigation strategies, may prolong or even minimize the likelihood of the Kessler Effect becoming a reality. To examine this problem, current satellite launches were reviewed against debris mitigation strategies then compared to the total number of tracked debris and overall debris, as identified by the European Space Agency (ESA). Multiple linear regression models were used to illustrate the potential impact of additional satellite launches along with projected mitigation strategies on the total number of tracked debris in LEO and overall debris. The independent variable was the number of satellite launches to LEO less the percentage of these satellites that adhered to debris mitigation strategies as defined by the IADC. The dependent variables were the number of tracked debris in LEO and the number of overall debris. The time period for all data was 2010 through 2021. The results of the data analysis indicate that the addition of satellites in LEO does have a significant impact on tracked and overall debris levels, despite mitigation efforts. While the Kessler Theory has not occurred yet, the predictions made in the seminal study were based on a much smaller pool of debris compared to what exists today. Current debris mitigation strategies must be adhered to for new satellites, while effective debris removal opportunities must continue to be explored for existing orbital debris. Additional research that removes Starlink satellites from the sampled population may provide a more reliable view of the problem.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"1 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":"130591462","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/AERO55745.2023.10115905
R. Rogalin
Free space optical communication will increase data rates and science returns from deep space. The Optical to Orion (O2O) project will demonstrate these high-rate links on the Artemis-II mission, showcasing this technology for the first time on a crewed mission from cis-lunar space. This new paradigm of optical communication necessitates a re-evaluation of other core functionalities of remote spacecraft operation, including guidance, navigation and control. Existing RF-based ranging methods can exploit the structure of the communication signal in order to infer the range and range-rate of the spacecraft (known as synchronous two-way ranging), but optical communication utilizes a totally distinct communication signal format. The CCSDS is in the process of standardizing an optical-based method, which has its origins in the technique pioneered on the Lunar Laser Communication Demonstration (LLCD). A variant of this technique is used in O2O's Time of Flight (ToF) system, enabling highly accurate, real time ranging capabilities for the Artemis-II mission. In this paper we describe the ground signal processing implementation of O2O's synchronous two-way ranging scheme with centimeter-class accuracy. In contrast to the technique used in LLCD, the O2O Time of Flight system utilizes a hardware architecture based on a high dynamic-range Time to Digital Converter (TDC)-based receiver. We describe the architecture of the Time of Flight capture system, as well as the hardware and software necessary to extract range and range-rate information from the downlink and uplink signals. We also describe a novel calibration scheme that enables highly accurate compensation of the delays within the ground station without the explicit need to measure individual path lengths. We conclude the paper with simulation and experimental results validating the implementation.
{"title":"The Optical to Orion Time of Flight Ground Processing System","authors":"R. Rogalin","doi":"10.1109/AERO55745.2023.10115905","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115905","url":null,"abstract":"Free space optical communication will increase data rates and science returns from deep space. The Optical to Orion (O2O) project will demonstrate these high-rate links on the Artemis-II mission, showcasing this technology for the first time on a crewed mission from cis-lunar space. This new paradigm of optical communication necessitates a re-evaluation of other core functionalities of remote spacecraft operation, including guidance, navigation and control. Existing RF-based ranging methods can exploit the structure of the communication signal in order to infer the range and range-rate of the spacecraft (known as synchronous two-way ranging), but optical communication utilizes a totally distinct communication signal format. The CCSDS is in the process of standardizing an optical-based method, which has its origins in the technique pioneered on the Lunar Laser Communication Demonstration (LLCD). A variant of this technique is used in O2O's Time of Flight (ToF) system, enabling highly accurate, real time ranging capabilities for the Artemis-II mission. In this paper we describe the ground signal processing implementation of O2O's synchronous two-way ranging scheme with centimeter-class accuracy. In contrast to the technique used in LLCD, the O2O Time of Flight system utilizes a hardware architecture based on a high dynamic-range Time to Digital Converter (TDC)-based receiver. We describe the architecture of the Time of Flight capture system, as well as the hardware and software necessary to extract range and range-rate information from the downlink and uplink signals. We also describe a novel calibration scheme that enables highly accurate compensation of the delays within the ground station without the explicit need to measure individual path lengths. We conclude the paper with simulation and experimental results validating the implementation.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"69 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":"130721743","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/AERO55745.2023.10115642
Yeshua Noriega Long, Charles Lee, R. Gladden
The Next-Generation Mars Telecommunications Orbiters, a.k.a. Mars ComBirds, (MCB), are intended to serve as a deep-space relay hub that provides high-performance links to Earth at extreme data rates and to increase data return from a variety of Mars rovers, landers, aerobots, and science orbiters. As the current science orbiters used for relay are aging, the needs for these MCBs are becoming realistic, justified, and increasingly urgent. The message is further echoed when demands for Earth return data for next-decade missions to Mars, such as ExoMars, Mars Ice Mapper, Mars Sample Return, and future human exploration missions to the Red Planet, continue to increase. In addition, by communicating directly to these MCBs instead of Earth, communications systems for future science missions can be reduced. Thus, the costs can be lowered, or more science equipment can be added. Furthermore, MCBs' fields of view with Earth are much longer; therefore, an appropriate choice of orbits, a network of MCBs with cross-link capability can connect any users at Mars with Earth almost continuously. In this paper, we primarily provide a trade study on the design of the MCB orbits, which include the number of orbits, sizes, shapes, and orientations. Special attention is also given to a class of orbits that provides daily repeating ground tracks. These orbits can facilitate surface operations because they rise and set daily over a specific area at constant revisiting times. In addition, there is another class of orbits where a spacecraft would tug a science orbiter to a sun-sync Mars orbit and then raise its altitude and serve as a relay orbiter. More particularly, we will consider different orbit types such as (1) circular equatorial, (2) circular sun-sync, (3) Apoapsis at Constant time-of-day Critically Inclined (ACCI), (4) Apoapsis at Constant time-of-day Equatorial (ACE), and (5) SEP- Tugs. Mars surface users are assumed to be global and of any longitude and latitude. For users in orbit, we assume their orbital parameters similar to the typical low-Mars sun-sync orbits such as Mars Odyssey and Mars Reconnaissance orbiters. JPL-developed Telecom Orbit Analysis and Simulation Tool (TOAST) software is used to compute the contacts between the orbiters and users. The performance of these orbit constellations can be assessed through several metrics of interest, which include the maximum latitude, number of contacts per sol, contact duration, total contact time per sol, and maximum communication gap. Recommendations for the optimal orbital constellation choices (3-planar and coplanar variations) will be provided based on comparing the weighted means of each metric calculated at latitude-longitude coordinates during a simulation duration of 1 sol. The chosen orbits will then be further investigated in greater depth to weigh the pros and cons regarding a satellite's operational capabilities and limitations at that orbit.
{"title":"On the Orbit Constellation Assessment for the Next-Generation Mars Telecommunications Orbiters","authors":"Yeshua Noriega Long, Charles Lee, R. Gladden","doi":"10.1109/AERO55745.2023.10115642","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115642","url":null,"abstract":"The Next-Generation Mars Telecommunications Orbiters, a.k.a. Mars ComBirds, (MCB), are intended to serve as a deep-space relay hub that provides high-performance links to Earth at extreme data rates and to increase data return from a variety of Mars rovers, landers, aerobots, and science orbiters. As the current science orbiters used for relay are aging, the needs for these MCBs are becoming realistic, justified, and increasingly urgent. The message is further echoed when demands for Earth return data for next-decade missions to Mars, such as ExoMars, Mars Ice Mapper, Mars Sample Return, and future human exploration missions to the Red Planet, continue to increase. In addition, by communicating directly to these MCBs instead of Earth, communications systems for future science missions can be reduced. Thus, the costs can be lowered, or more science equipment can be added. Furthermore, MCBs' fields of view with Earth are much longer; therefore, an appropriate choice of orbits, a network of MCBs with cross-link capability can connect any users at Mars with Earth almost continuously. In this paper, we primarily provide a trade study on the design of the MCB orbits, which include the number of orbits, sizes, shapes, and orientations. Special attention is also given to a class of orbits that provides daily repeating ground tracks. These orbits can facilitate surface operations because they rise and set daily over a specific area at constant revisiting times. In addition, there is another class of orbits where a spacecraft would tug a science orbiter to a sun-sync Mars orbit and then raise its altitude and serve as a relay orbiter. More particularly, we will consider different orbit types such as (1) circular equatorial, (2) circular sun-sync, (3) Apoapsis at Constant time-of-day Critically Inclined (ACCI), (4) Apoapsis at Constant time-of-day Equatorial (ACE), and (5) SEP- Tugs. Mars surface users are assumed to be global and of any longitude and latitude. For users in orbit, we assume their orbital parameters similar to the typical low-Mars sun-sync orbits such as Mars Odyssey and Mars Reconnaissance orbiters. JPL-developed Telecom Orbit Analysis and Simulation Tool (TOAST) software is used to compute the contacts between the orbiters and users. The performance of these orbit constellations can be assessed through several metrics of interest, which include the maximum latitude, number of contacts per sol, contact duration, total contact time per sol, and maximum communication gap. Recommendations for the optimal orbital constellation choices (3-planar and coplanar variations) will be provided based on comparing the weighted means of each metric calculated at latitude-longitude coordinates during a simulation duration of 1 sol. The chosen orbits will then be further investigated in greater depth to weigh the pros and cons regarding a satellite's operational capabilities and limitations at that orbit.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"25 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":"130479197","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/AERO55745.2023.10115676
Saptarshi Bandyopadhyay, R. Amini, Robert Miller, S. Bhaskaran, Rodney L. Anderson, S. Hernandez, M. Haynes, P. Adell, Carol A. Raymond, L. Fesq
In this paper, we present a novel integrated simulation tool that models science yield and mission resources as a function of science payload, mission and system design, spacecraft behavior and modes, and target uncertainties. This provides a comprehensive and self-consistent approach to multi-spacecraft mission formulation around small bodies. We demonstrate this tool for the case of a notional three-spacecraft mission to the near-Earth asteroid Apophis, which will flyby Earth in 2029.
{"title":"Integrated Science and Engineering Simulation Environment for Formation Flying Mission around Small Body","authors":"Saptarshi Bandyopadhyay, R. Amini, Robert Miller, S. Bhaskaran, Rodney L. Anderson, S. Hernandez, M. Haynes, P. Adell, Carol A. Raymond, L. Fesq","doi":"10.1109/AERO55745.2023.10115676","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115676","url":null,"abstract":"In this paper, we present a novel integrated simulation tool that models science yield and mission resources as a function of science payload, mission and system design, spacecraft behavior and modes, and target uncertainties. This provides a comprehensive and self-consistent approach to multi-spacecraft mission formulation around small bodies. We demonstrate this tool for the case of a notional three-spacecraft mission to the near-Earth asteroid Apophis, which will flyby Earth in 2029.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"612 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":"131425912","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/AERO55745.2023.10115719
Todd H. Treichel
Light emitting diodes (LED) are semiconductors that convert electrical energy into light and are used by commercial markets to replace traditional fluorescent and incandescent lighting technologies. Advantages of transitioning to LED technologies in spacecraft are reduced mass, reduced occupied volume, reduced power, improved color control, longer operating life, and lower cost associated with power consumption and disposal. This research provides evidence that selected commercial LEDs used in a solid-state design are capable of meeting NASA and DOD environmental test requirements supported by additional analysis for human factors in search of adverse effects, such as fatigue, eyestrain, and headaches in astronauts. Reliability and human factors are both essential for long term missions where crew habitation relies solely on artificial light sources. In an effort to advance the technology readiness level (TRL) for human spacecraft lighting, a randomized block experimental design for evaluating human factor effects using soft white light, emitted from two different prototype LED designs and a Sylvania fluorescent general luminaire assembly (GLA) representing heritage lighting designed for the International Space Station (ISS). There was no statistical evidence to support claims that the LED technology involved in this research failed for reliability, caused fatigue, eyestrain and/or headache in humans. Based on these research findings, a down-selection was made for full implementation of a solid-state LED design that once flight released by Sierra Space, underwent a human factor confirmation trial in support of earlier results.
{"title":"Human Factor Evaluation of LED General Luminaire Assemblies for Spacecraft Lighting","authors":"Todd H. Treichel","doi":"10.1109/AERO55745.2023.10115719","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115719","url":null,"abstract":"Light emitting diodes (LED) are semiconductors that convert electrical energy into light and are used by commercial markets to replace traditional fluorescent and incandescent lighting technologies. Advantages of transitioning to LED technologies in spacecraft are reduced mass, reduced occupied volume, reduced power, improved color control, longer operating life, and lower cost associated with power consumption and disposal. This research provides evidence that selected commercial LEDs used in a solid-state design are capable of meeting NASA and DOD environmental test requirements supported by additional analysis for human factors in search of adverse effects, such as fatigue, eyestrain, and headaches in astronauts. Reliability and human factors are both essential for long term missions where crew habitation relies solely on artificial light sources. In an effort to advance the technology readiness level (TRL) for human spacecraft lighting, a randomized block experimental design for evaluating human factor effects using soft white light, emitted from two different prototype LED designs and a Sylvania fluorescent general luminaire assembly (GLA) representing heritage lighting designed for the International Space Station (ISS). There was no statistical evidence to support claims that the LED technology involved in this research failed for reliability, caused fatigue, eyestrain and/or headache in humans. Based on these research findings, a down-selection was made for full implementation of a solid-state LED design that once flight released by Sierra Space, underwent a human factor confirmation trial in support of earlier results.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"38 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":"125431181","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/AERO55745.2023.10115922
Casey J. Clark, J. D. Smith, Andrew J. Nick, Victoria Ortega, A. Kennett, R. P. Dillon, B. Buckles
The Space Environment Dynamometer (SED) chamber was designed to conduct research in cryobotics; an area of study that focuses on robotic systems and rotating machinery operating in extreme cold environments including Earth, low Earth orbit, Mars, Moon, asteroids, Solar orbit, planetary orbit, or those encountered during travel among these destinations. The test chamber incorporates a modular dynamometer, consisting of a variety of brakes, torque sensors and motors to be easily interchanged between tests. Each test employs a unique test profile that incorporates different setpoints of applied torques and velocities for a given period or number of revolutions. The modularity of the dynamometer setup allows for any combination of motor, gearbox to be tested. This chamber is one of a kind and resides at the Swamp Works facility within the Granular Mechanics and Regolith Operations laboratory (GMRO) at NASA Kennedy Space Center. Other cold chambers exist, however they are project specific and do not simultaneously output real time torque, temperature and efficiency data. The modularity of this extreme cold environment test chamber, coupled with the custom software and instrumentation, makes it one of a kind. The chamber is capable of stabilizing cryogenic temperatures and pressures to commensurate moon environments. Tests have successfully been conducted on motors and gearboxes for various cryogenic temperature set points, torques, and angular velocities. Relevant internal temperatures of the test article and chamber were recorded using a variety of temperature sensors. The temperature setpoints, on the motors and gearboxes tested, were stabilized by using PID gain scheduling of the PWM signal for the various heaters. The heat removal for the motor was provided by creating a thermally conductive path from a cryohead directly to the test article using copper straps. A variety of strainwave gears (SWGs), also known as Harmonic drives, planetary gear systems and DC motor actuator configurations have been tested in the chamber. The experiments performed were for various projects including Bulk Metallic Glass Gears (BMGG), Volatiles Investigating Polar Exploration Rover (VIPER), In-Situ Resource Utilization Pilot Excavator (IPEX). Various upgrades have been made to the extreme cold environment test chamber for the use of cryobotic research. These upgrades greatly increased the autonomous capabilities of the test set up by providing redundancies in the hardware and software. The redundancies were primarily added to protect the integrity of the cryohead. A new strapping and insulation method was performed to create the thermal conductive path from the actuators to the cryohead. The software was upgraded to include temperature setpoint control, further increasing the autonomous capabilities of the test. This paper goes into detail regarding the upgrades made to the extreme cold environment test chamber, as well as highlights the results from a COLDArm accepta
{"title":"Experimental Capabilities and Achievements of the Space Environment Dynamometer (SED)","authors":"Casey J. Clark, J. D. Smith, Andrew J. Nick, Victoria Ortega, A. Kennett, R. P. Dillon, B. Buckles","doi":"10.1109/AERO55745.2023.10115922","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115922","url":null,"abstract":"The Space Environment Dynamometer (SED) chamber was designed to conduct research in cryobotics; an area of study that focuses on robotic systems and rotating machinery operating in extreme cold environments including Earth, low Earth orbit, Mars, Moon, asteroids, Solar orbit, planetary orbit, or those encountered during travel among these destinations. The test chamber incorporates a modular dynamometer, consisting of a variety of brakes, torque sensors and motors to be easily interchanged between tests. Each test employs a unique test profile that incorporates different setpoints of applied torques and velocities for a given period or number of revolutions. The modularity of the dynamometer setup allows for any combination of motor, gearbox to be tested. This chamber is one of a kind and resides at the Swamp Works facility within the Granular Mechanics and Regolith Operations laboratory (GMRO) at NASA Kennedy Space Center. Other cold chambers exist, however they are project specific and do not simultaneously output real time torque, temperature and efficiency data. The modularity of this extreme cold environment test chamber, coupled with the custom software and instrumentation, makes it one of a kind. The chamber is capable of stabilizing cryogenic temperatures and pressures to commensurate moon environments. Tests have successfully been conducted on motors and gearboxes for various cryogenic temperature set points, torques, and angular velocities. Relevant internal temperatures of the test article and chamber were recorded using a variety of temperature sensors. The temperature setpoints, on the motors and gearboxes tested, were stabilized by using PID gain scheduling of the PWM signal for the various heaters. The heat removal for the motor was provided by creating a thermally conductive path from a cryohead directly to the test article using copper straps. A variety of strainwave gears (SWGs), also known as Harmonic drives, planetary gear systems and DC motor actuator configurations have been tested in the chamber. The experiments performed were for various projects including Bulk Metallic Glass Gears (BMGG), Volatiles Investigating Polar Exploration Rover (VIPER), In-Situ Resource Utilization Pilot Excavator (IPEX). Various upgrades have been made to the extreme cold environment test chamber for the use of cryobotic research. These upgrades greatly increased the autonomous capabilities of the test set up by providing redundancies in the hardware and software. The redundancies were primarily added to protect the integrity of the cryohead. A new strapping and insulation method was performed to create the thermal conductive path from the actuators to the cryohead. The software was upgraded to include temperature setpoint control, further increasing the autonomous capabilities of the test. This paper goes into detail regarding the upgrades made to the extreme cold environment test chamber, as well as highlights the results from a COLDArm accepta","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"1 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":"125500019","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/AERO55745.2023.10115684
K. Benmeziane, P. Fabiani, S. Herbin, J. Lacaille, E. Ledinot
A general recommendation from the French office for aeronautical and space standardization (BNAE) is being drawn up by experts from Onera, Thales, Dassault and Safran, with the collaboration of Airbus, MBDA and ADP, the main French aeronautical companies. This document is based on mathematical and statistical elements which are reintroduced within a system and software development process considering the specificities of algorithms based on learning methods from data sets or data generators. For each activity in this development process, whether it is data capitalization or the use of artificial intelligence, risks are identified, and mitigation methods proposed. A few application cases are included in the document to illustrate the particularities of certain types of algorithms. Methods of estimation, classification, categorization or even reinforcement learning are mentioned. This paper gives a summary in English of the general recommendation.
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Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10115531
Georges Labrèche, Cesar Guzman Alvarez
The SaaSyML app developed for the OPS-SAT spacecraft provides open access to on-board Machine Learning (ML) capabilities that an experimenter can interact with via RESTful Application Programming Interface (API) endpoints. The app's architecture follows the successes of Software as a Service (SaaS) in modern Web-based software engineering and implements the “as-a-Service” model, thus introducing the concept of Satellite Platform as a Service (SPaaS). An experimenter app on-board OPS-SAT can subscribe to SaaSyML's training data feed and pull measurement, telemetry, and housekeeping data from any of the spacecraft's instruments or its on-board software datapool. The ML features provided by the SaaSyML app cover both training and prediction operations. The Java Statistical Analysis Tool (JSAT) open-source java library for ML is used thus unlocking access to over 100 training algorithms on-board a flying mission. Past experiments have successfully implemented ML on-board OPS-SAT but have yet to offer any comprehensive re-usability. SaaSyML's service-oriented approach spares the experimenters the complexities of having to implement their own data provisioning and ML solutions so that they can focus instead on expanding the field of experimentation and use-cases for applied ML in space. A further novelty is also introduced with a plugin design for an software extension mechanism that allows experimenters to inject custom code to address ML needs specific to their experiments (e.g. calculating target labels/classes during supervised learning training operations). SaaSyML is developed using the Eclipse Vert.x event-driven application toolkit that runs on the Java Virtual Machine (JVM). This design choice introduces event-driven software engineering and practical use of the spacecraft dual-core payload computer and Linux environment. SaaSyML is a reference in embracing and leveraging multi-threaded and multi-core software design for space applications. This translates to non-blocking ML training and prediction operations running in parallel while multiple experimenter apps interact with the service. SaaSyML demonstrates how a more capable space-grade processor enables a paradigm shift towards developing more sophisticated client facing space software with reduced development complexity, effort, and cost.
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Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10115898
B. Bradley, Brandon Burns, J. Dooley, J. Feldman, Winston Jackson, Jeremy L. Pecharich, A. Rettura, Andres Rivera, N. Shougarian, J. Stehly, Erisa Stilley, Stephen Watson
Jupiter's icy moon Europa is a prime target in our exploration of potentially habitable worlds beyond Earth. The combination of a subsurface liquid water layer in contact with a rocky seafloor may yield an ocean rich in the elements and energy needed for the emergence of life, and for potentially sustaining life through time. Europa may hold the clues to one of NASA's long-standing quests - to determine whether or not we are alone in the universe. The Europa Clipper mission will characterize Europa's habitability as the first step in the search for potential life at the Jovian moon by conducting approximately four dozen flybys. While the Clipper project is entering into the heart of its testing and validation program, some critical updates have been in work to ensure mission success. This paper will summarize changes to the mission plan and science measurement requirements from the mission's System Integration Review (SIR) baseline. It will outline the Verification and Validation (V&V) approach and how key technical challenges like power management in the presence of extreme changes in temperature and illumination, and science robustness in the presence of spacecraft and instrument faults and cyber-security are being addressed. Since SIR, Europa Clipper's Propulsion Module has arrived at JPL along with the Plasma Instrument for Magnetic Sounding (PIMS), Europa Ultraviolet Spectrograph (Europa-UVS), Europa Thermal Emission Imaging System (E-THEMIS). Europa Imaging System (EIS) Wide Angle Camera (WAC), Surface Dust Analyzer (SUDA) and boxes from the GNC, Avionics, Propulsion, Power and Thermal subsystems. Some science requirements have been relaxed while the mission plan has been updated to improve robustness and increase the number of data collection opportunities per flyby. Gaining confidence that such a large, complex spacecraft will operate as intended in the extreme temperature and radiation environments is accomplished through a combination of piecewise system level testing, and modeling where testing is not possible. Solar array power management in the presence of extreme temperature variation, from the inner solar system to seeing first light after the cold soaks of up to nine-hour Jupiter eclipses, has been improved to address the dynamic current-voltage (IV) curve behavior. Probabilistic risk assessments are regularly used to understand how changes in science observation schedule, science measurement requirements, and expected frequency of interruptions due to radiation and other causes affect robustness of the mission as a whole to achieve its intended science. In the cyber-security realm, increasing threats and vulnerability concerns have necessitated higher levels of protective actions by sponsoring agencies and projects. The Clipper project has implemented new cybersecurity requirements from NASA and other government agencies to protect project assets, and has been actively engaged with institutional efforts to standardize the set of
{"title":"Europa Clipper Mission: Road from System Integration Review to Launch","authors":"B. Bradley, Brandon Burns, J. Dooley, J. Feldman, Winston Jackson, Jeremy L. Pecharich, A. Rettura, Andres Rivera, N. Shougarian, J. Stehly, Erisa Stilley, Stephen Watson","doi":"10.1109/AERO55745.2023.10115898","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115898","url":null,"abstract":"Jupiter's icy moon Europa is a prime target in our exploration of potentially habitable worlds beyond Earth. The combination of a subsurface liquid water layer in contact with a rocky seafloor may yield an ocean rich in the elements and energy needed for the emergence of life, and for potentially sustaining life through time. Europa may hold the clues to one of NASA's long-standing quests - to determine whether or not we are alone in the universe. The Europa Clipper mission will characterize Europa's habitability as the first step in the search for potential life at the Jovian moon by conducting approximately four dozen flybys. While the Clipper project is entering into the heart of its testing and validation program, some critical updates have been in work to ensure mission success. This paper will summarize changes to the mission plan and science measurement requirements from the mission's System Integration Review (SIR) baseline. It will outline the Verification and Validation (V&V) approach and how key technical challenges like power management in the presence of extreme changes in temperature and illumination, and science robustness in the presence of spacecraft and instrument faults and cyber-security are being addressed. Since SIR, Europa Clipper's Propulsion Module has arrived at JPL along with the Plasma Instrument for Magnetic Sounding (PIMS), Europa Ultraviolet Spectrograph (Europa-UVS), Europa Thermal Emission Imaging System (E-THEMIS). Europa Imaging System (EIS) Wide Angle Camera (WAC), Surface Dust Analyzer (SUDA) and boxes from the GNC, Avionics, Propulsion, Power and Thermal subsystems. Some science requirements have been relaxed while the mission plan has been updated to improve robustness and increase the number of data collection opportunities per flyby. Gaining confidence that such a large, complex spacecraft will operate as intended in the extreme temperature and radiation environments is accomplished through a combination of piecewise system level testing, and modeling where testing is not possible. Solar array power management in the presence of extreme temperature variation, from the inner solar system to seeing first light after the cold soaks of up to nine-hour Jupiter eclipses, has been improved to address the dynamic current-voltage (IV) curve behavior. Probabilistic risk assessments are regularly used to understand how changes in science observation schedule, science measurement requirements, and expected frequency of interruptions due to radiation and other causes affect robustness of the mission as a whole to achieve its intended science. In the cyber-security realm, increasing threats and vulnerability concerns have necessitated higher levels of protective actions by sponsoring agencies and projects. The Clipper project has implemented new cybersecurity requirements from NASA and other government agencies to protect project assets, and has been actively engaged with institutional efforts to standardize the set of ","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"41 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":"122280667","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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