Pub Date : 2020-03-01DOI: 10.1109/AERO47225.2020.9172648
A. Mahran, Ramy Samy
The efficiency of Ka-band Satellite communication is very susceptible to several weather conditions. Error patterns of the Ka-band satellite channels under various weather conditions (clear/cloudy, rain and thundershower) indicate that errors neither happen separately at random nor in well-defined bursts, but a mixed manner. Therefore, designing codes that can correct random and burst errors simultaneously are highly desired. In this work, we introduce a configuration of a CCSDS rate compatible product code that includes both the CCSDS-recommended Reed-Solomon codes and the extended Hamming code. The proposed scheme not only achieves almost the same error performance of the CCSDS-recommended Reed-Solomon Convolutional concatenated codes but also has minimal decoding effort and memory requirement. Moreover, an analysis of the different weather conditions in the Ka-band for satellite communication will be introduced.
{"title":"CCSDS Rate-Compatible Product Code for Ka-Band Satellite Communications","authors":"A. Mahran, Ramy Samy","doi":"10.1109/AERO47225.2020.9172648","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172648","url":null,"abstract":"The efficiency of Ka-band Satellite communication is very susceptible to several weather conditions. Error patterns of the Ka-band satellite channels under various weather conditions (clear/cloudy, rain and thundershower) indicate that errors neither happen separately at random nor in well-defined bursts, but a mixed manner. Therefore, designing codes that can correct random and burst errors simultaneously are highly desired. In this work, we introduce a configuration of a CCSDS rate compatible product code that includes both the CCSDS-recommended Reed-Solomon codes and the extended Hamming code. The proposed scheme not only achieves almost the same error performance of the CCSDS-recommended Reed-Solomon Convolutional concatenated codes but also has minimal decoding effort and memory requirement. Moreover, an analysis of the different weather conditions in the Ka-band for satellite communication will be introduced.","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":"128988182","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/AERO47225.2020.9172745
E. Shao, Joshua L. Anderson, Vanessa Mechem, Danny Tran, Jacqueline Ryan, R. Valencia, D. Keymeulen, E. Liggett, Michael Bernas, M. Klimesh, Simon Shin, D. Dolman
The emergent technology of Multi-Processor System-on-Chip (MPSoC) devices promises lighter, smaller, cheaper, more capable and reliable space electronic systems that could help to unveil some of the secrets in our universe. This paper describes the automation and the integration of hardware/software co-verification tools (LiveCheckHSI) for the Xilinx Zynq-based SoC and UltraScale MPSoC avionics system that have been developed at the Jet Propulsion Laboratory (JPL) for Next-Generation Imaging Spectrometers (NGIS). The flight NGIS avionics acquires and compresses images in real-time, in addition to reporting telemetry and programming the spectrometer, focus step motor, and heaters. This paper describes the new development of LiveCheckHSI: comprising a data visualization tool, as well as command and telemetry software. In addition, the deployment of LiveCheckHSI to flight avionics is described. The heavy reliance on the ability to discern instrument behavior in real time for displaying data transmitted by an imaging spectrometer led to the development of LiveView, a co-verification tool that executes real-time data processing and visualization on hyperspectral imaging data. This paper documents progress on current LiveView development, including the implementation of features that allow LiveView to be compiled without a CameraLink driver installed, enable the dragging and dropping of files into LiveView, and enable subframe sampling rates in the fast Fourier transform widget. Furthermore, this paper details the Qt-based p2serialcmds GUI and its development, which includes enhancements to the remote recording and automated test scripting capabilities. The p2serialcmds GUI serves as a comprehensive user interface for interacting with the LiveView software, NGIS, and supporting devices, and its development, which includes enhancements on the recording and scripting abilities and implementations of new features. This paper also describes the integration of the Qt-based LiveView application and the Qt-based p2serialcmds GUI onto the MPSoC. This installation was made possible by building the Yocto Linux operating system (OS) onto the MPSoC, which thereby enabled C++ applications such as the Qt framework, LiveView, and p2serialcmds to be compiled and run on the device.
{"title":"LiveView and P2serialcmds Co-Verification Software for NGIS and Embedded MPSoC Instrument Avionics","authors":"E. Shao, Joshua L. Anderson, Vanessa Mechem, Danny Tran, Jacqueline Ryan, R. Valencia, D. Keymeulen, E. Liggett, Michael Bernas, M. Klimesh, Simon Shin, D. Dolman","doi":"10.1109/AERO47225.2020.9172745","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172745","url":null,"abstract":"The emergent technology of Multi-Processor System-on-Chip (MPSoC) devices promises lighter, smaller, cheaper, more capable and reliable space electronic systems that could help to unveil some of the secrets in our universe. This paper describes the automation and the integration of hardware/software co-verification tools (LiveCheckHSI) for the Xilinx Zynq-based SoC and UltraScale MPSoC avionics system that have been developed at the Jet Propulsion Laboratory (JPL) for Next-Generation Imaging Spectrometers (NGIS). The flight NGIS avionics acquires and compresses images in real-time, in addition to reporting telemetry and programming the spectrometer, focus step motor, and heaters. This paper describes the new development of LiveCheckHSI: comprising a data visualization tool, as well as command and telemetry software. In addition, the deployment of LiveCheckHSI to flight avionics is described. The heavy reliance on the ability to discern instrument behavior in real time for displaying data transmitted by an imaging spectrometer led to the development of LiveView, a co-verification tool that executes real-time data processing and visualization on hyperspectral imaging data. This paper documents progress on current LiveView development, including the implementation of features that allow LiveView to be compiled without a CameraLink driver installed, enable the dragging and dropping of files into LiveView, and enable subframe sampling rates in the fast Fourier transform widget. Furthermore, this paper details the Qt-based p2serialcmds GUI and its development, which includes enhancements to the remote recording and automated test scripting capabilities. The p2serialcmds GUI serves as a comprehensive user interface for interacting with the LiveView software, NGIS, and supporting devices, and its development, which includes enhancements on the recording and scripting abilities and implementations of new features. This paper also describes the integration of the Qt-based LiveView application and the Qt-based p2serialcmds GUI onto the MPSoC. This installation was made possible by building the Yocto Linux operating system (OS) onto the MPSoC, which thereby enabled C++ applications such as the Qt framework, LiveView, and p2serialcmds to be compiled and run on the device.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126690270","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/AERO47225.2020.9172781
M. Müller, S. Stoneman, Ingo von Bargen, Florian Steidle, W. Stürzl
In recent years, Micro Aerial Vehicles (MAVs) have drawn attention to the aerospace community. With such autonomous flying platforms, it is possible to explore foreign extraterrestrial bodies in an efficient and faster manner than other robotic platforms, like rovers. In addition, they can be equipped with a variety of different sensors. Cameras are especially well suited, since they are light, energy-efficient and deliver a broad spectrum of information. Following the underlying terrain in a defined height is a fundamental task for any exploring MAV. To accomplish this, many systems possess a designated height sensor, which in most cases only delivers a single height estimation taken from nadir. In such a setup, the MAV is just adjusting its height based on the current height estimation and does not take any terrain lying ahead into account, which results in delayed height adjustments. In this paper, we propose a novel method based on a wide-angle stereo camera setup, which is attached to the MAV, to overcome such problems. Due to the wide vertical field of view, the vehicle is able to not only measure its current height, but also the terrain lying ahead. Therefore, the MAV is able to perform a better terrain following compared to other methods, which use just a single nadir height sample. Our algorithm only needs to take the depth image, calculated by the stereo cameras, and the estimated gravity vector into account. Therefore, our method is very fast and computationally efficient, compared to other methods, which build up an entire map beforehand. As a result, the procedure presented here is also suitable for tiny flying systems with low computational capabilities and memory resources. The terrain following algorithm runs in real-time and on board the system, and is therefore also suitable for confined environments, like caves, and where communication delays are present. We evaluate our method with simulated data and real tests on an MAV. To demonstrate that our method works in a variety of different terrains, we show experiments with different slopes and obstacles in the flight path. We also compare our method to a basic terrain following by using just a single height measurement in a more classical approach.
{"title":"Efficient Terrain Following for a Micro Aerial Vehicle with Ultra-Wide Stereo Cameras","authors":"M. Müller, S. Stoneman, Ingo von Bargen, Florian Steidle, W. Stürzl","doi":"10.1109/AERO47225.2020.9172781","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172781","url":null,"abstract":"In recent years, Micro Aerial Vehicles (MAVs) have drawn attention to the aerospace community. With such autonomous flying platforms, it is possible to explore foreign extraterrestrial bodies in an efficient and faster manner than other robotic platforms, like rovers. In addition, they can be equipped with a variety of different sensors. Cameras are especially well suited, since they are light, energy-efficient and deliver a broad spectrum of information. Following the underlying terrain in a defined height is a fundamental task for any exploring MAV. To accomplish this, many systems possess a designated height sensor, which in most cases only delivers a single height estimation taken from nadir. In such a setup, the MAV is just adjusting its height based on the current height estimation and does not take any terrain lying ahead into account, which results in delayed height adjustments. In this paper, we propose a novel method based on a wide-angle stereo camera setup, which is attached to the MAV, to overcome such problems. Due to the wide vertical field of view, the vehicle is able to not only measure its current height, but also the terrain lying ahead. Therefore, the MAV is able to perform a better terrain following compared to other methods, which use just a single nadir height sample. Our algorithm only needs to take the depth image, calculated by the stereo cameras, and the estimated gravity vector into account. Therefore, our method is very fast and computationally efficient, compared to other methods, which build up an entire map beforehand. As a result, the procedure presented here is also suitable for tiny flying systems with low computational capabilities and memory resources. The terrain following algorithm runs in real-time and on board the system, and is therefore also suitable for confined environments, like caves, and where communication delays are present. We evaluate our method with simulated data and real tests on an MAV. To demonstrate that our method works in a variety of different terrains, we show experiments with different slopes and obstacles in the flight path. We also compare our method to a basic terrain following by using just a single height measurement in a more classical approach.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"81 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":"126909647","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/AERO47225.2020.9172440
E. Kopp, Sascha Mueller, F. Greif, A. Boerner
In the development of space instruments it is common practice to analyze the software, developed in the course of the project, for errors by extensive tests as well as to simulate the different application scenarios to determine the behavior of the software. The hardware is often only modeled as a black box to the software and is usually not an active part of the simulation. In general, the interface between hardware and software is described and analyzed by a Hardware/Software Interaction Analysis (HSIA) at a late stage of the project, when the development of the hardware has generally been completed. In order to be able to integrate the hardware into a representative simulation of the system, especially with regard to Fault Detection Isolation and Recovery (FDIR), it is necessary to develop an interface that contains all important information about the structure of the hardware and its behavior. Thus the current state of the hardware can be described at any stage of the project and can be taken into account for software development. This paper describes a hardware/software-interface description using HSIA and Fault Tree Analysis (FTA) as a baseline. The overall goal is to model the interaction of hardware and software as accurately as possible in order to identify errors both in the software and in the hardware design. The description can also be used at a later stage to implement it into the Model-Based Systems Engineering framework Virtual Satellite (VirSat), developed by the German Aerospace Center (DLR). Concept and implementation of the hardware/software-interface with special focus on fault cases, detectability and fault mitigation will be described. The benefits of an interface description in an early stage of the hardware design are discussed. On the basis of an actual project, a hardware analysis is performed and the interface is described with the developed approach in order to evaluate its suitability. Finally, the feasibility and limits of this approach are assessed.
{"title":"Towards an H/W-S/W Interface description for a comprehensive space systems simulation environment","authors":"E. Kopp, Sascha Mueller, F. Greif, A. Boerner","doi":"10.1109/AERO47225.2020.9172440","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172440","url":null,"abstract":"In the development of space instruments it is common practice to analyze the software, developed in the course of the project, for errors by extensive tests as well as to simulate the different application scenarios to determine the behavior of the software. The hardware is often only modeled as a black box to the software and is usually not an active part of the simulation. In general, the interface between hardware and software is described and analyzed by a Hardware/Software Interaction Analysis (HSIA) at a late stage of the project, when the development of the hardware has generally been completed. In order to be able to integrate the hardware into a representative simulation of the system, especially with regard to Fault Detection Isolation and Recovery (FDIR), it is necessary to develop an interface that contains all important information about the structure of the hardware and its behavior. Thus the current state of the hardware can be described at any stage of the project and can be taken into account for software development. This paper describes a hardware/software-interface description using HSIA and Fault Tree Analysis (FTA) as a baseline. The overall goal is to model the interaction of hardware and software as accurately as possible in order to identify errors both in the software and in the hardware design. The description can also be used at a later stage to implement it into the Model-Based Systems Engineering framework Virtual Satellite (VirSat), developed by the German Aerospace Center (DLR). Concept and implementation of the hardware/software-interface with special focus on fault cases, detectability and fault mitigation will be described. The benefits of an interface description in an early stage of the hardware design are discussed. On the basis of an actual project, a hardware analysis is performed and the interface is described with the developed approach in order to evaluate its suitability. Finally, the feasibility and limits of this approach are assessed.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"29 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124114645","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/AERO47225.2020.9172722
L. Pratt, Alvin L. Smith
During the current phase of robotic exploration, Mars missions plan to search for evidence of extinct or extant biological activity. The conceptual mission architecture for Mars Sample Return (MSR) must demonstrate robust containment and rigorous control of all unsterilized materials as assurance of no inadvertent harm to Earth's biosphere. Launch of NASA's drilling and caching Mars rover in summer 2020 could potentially be the first step in an extraordinary campaign to bring carefully collected and sealed samples of sedimentary and igneous rocks from Mars to Earth for scientific study. As part of this notional architecture, NASA would launch a sample return platform early as 2026 to land near the area explored by the Mars 2020 rover and ESA would launch separately an Earth Return Orbiter (ERO). A small ESA fetch rover would depart from the platform and drive rapidly to locations where samples tubes have been placed on the ground for retrieval. The fetch rover and/or the Mars 2020 rover could return to the platform, allowing a robotic arm to transfer samples tubes into a sample container on a Mars Ascent Vehicle (MAV). The sample container would be launched and then released by the MAV in Mars orbit where the waiting ERO would capture the container and seal it in a doubled-walled containment canister. Various combinations of sterilization and dust mitigation are under consideration for breaking the chain of contact with putative contaminants. Minimizing the area of surfaces exposed to Martian dust and performing one or more sterilization procedures are key options for compliance with backward planetary protection prior to departure from Mars orbit. Once landed on Earth, entry vehicle inspection followed by additional cleaning and biobarrier deployment would ensure safe handling during transport to a state-of-the-art receiving facility. Herein, we describe NASA and ESAs joint coordination efforts with COSPAR to engage disciplinary experts across academic, regulatory, and industrial organizations to discuss current technology for life detection and sample safety protocols for handling and studying Mars materials on Earth.
{"title":"Expectations for Backward Planetary Protection Planning During Mars Sample Return Planning","authors":"L. Pratt, Alvin L. Smith","doi":"10.1109/AERO47225.2020.9172722","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172722","url":null,"abstract":"During the current phase of robotic exploration, Mars missions plan to search for evidence of extinct or extant biological activity. The conceptual mission architecture for Mars Sample Return (MSR) must demonstrate robust containment and rigorous control of all unsterilized materials as assurance of no inadvertent harm to Earth's biosphere. Launch of NASA's drilling and caching Mars rover in summer 2020 could potentially be the first step in an extraordinary campaign to bring carefully collected and sealed samples of sedimentary and igneous rocks from Mars to Earth for scientific study. As part of this notional architecture, NASA would launch a sample return platform early as 2026 to land near the area explored by the Mars 2020 rover and ESA would launch separately an Earth Return Orbiter (ERO). A small ESA fetch rover would depart from the platform and drive rapidly to locations where samples tubes have been placed on the ground for retrieval. The fetch rover and/or the Mars 2020 rover could return to the platform, allowing a robotic arm to transfer samples tubes into a sample container on a Mars Ascent Vehicle (MAV). The sample container would be launched and then released by the MAV in Mars orbit where the waiting ERO would capture the container and seal it in a doubled-walled containment canister. Various combinations of sterilization and dust mitigation are under consideration for breaking the chain of contact with putative contaminants. Minimizing the area of surfaces exposed to Martian dust and performing one or more sterilization procedures are key options for compliance with backward planetary protection prior to departure from Mars orbit. Once landed on Earth, entry vehicle inspection followed by additional cleaning and biobarrier deployment would ensure safe handling during transport to a state-of-the-art receiving facility. Herein, we describe NASA and ESAs joint coordination efforts with COSPAR to engage disciplinary experts across academic, regulatory, and industrial organizations to discuss current technology for life detection and sample safety protocols for handling and studying Mars materials on Earth.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"35 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":"123514827","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/AERO47225.2020.9172483
Jackson L. Shannon, M. Ozimek, J. Atchison, C. Hartzell
Spiral trajectories to the Moon present a difficult trajectory design problem. In this paper we show that the well-known Q-Law guidance algorithm can be leveraged to rapidly produce near optimal, high fidelity trajectories. By combining forward and backward propagated Q-Law, continuous trajectories are generated from an Earth parking orbit to a target Lunar orbit. The Q-Law result can then be refined using direct collocation. To demonstrate this process, we solve a problem inspired by the SMART-1 mission and compare to literature results. Then, an ESPA-class mission scenario is analyzed. We demonstrate that this technique can be used to efficiently explore the trajectory trade space and provide suitable initial guesses for direct optimization.
{"title":"Rapid Design and Exploration of High-Fidelity Low-Thrust Transfers to the Moon","authors":"Jackson L. Shannon, M. Ozimek, J. Atchison, C. Hartzell","doi":"10.1109/AERO47225.2020.9172483","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172483","url":null,"abstract":"Spiral trajectories to the Moon present a difficult trajectory design problem. In this paper we show that the well-known Q-Law guidance algorithm can be leveraged to rapidly produce near optimal, high fidelity trajectories. By combining forward and backward propagated Q-Law, continuous trajectories are generated from an Earth parking orbit to a target Lunar orbit. The Q-Law result can then be refined using direct collocation. To demonstrate this process, we solve a problem inspired by the SMART-1 mission and compare to literature results. Then, an ESPA-class mission scenario is analyzed. We demonstrate that this technique can be used to efficiently explore the trajectory trade space and provide suitable initial guesses for direct optimization.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"7 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":"121289283","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/AERO47225.2020.9172491
A. Schutte, J. Delaune, Evgeniy Skylanskiy, Robert A. Hewitt, S. Daftry, M. Quadrelli, L. Matthies
This paper reports on a study of the application of a ram-air parafoil to Entry, Descent, and Landing (EDL) on Titan. A comprehensive simulation was constructed to enable simulation of EDL state estimation performance from 10 minutes before entry (E-10 min) to touchdown on the surface of Titan. EDL performance is characterized assuming an entry phase starting at E-10 min followed by a parafoil guided phase for descent and landing to enable precise landing on a predetermined target. Guided descent during the parafoil phase is achieved using the parafoil steering capability while state estimation is accomplished using vision-based Terrain Relative Navigation (TRN). The simulation is used in this study to conduct Monte Carlo analysis of TRN state estimation for a full entry phase sequence followed by a straight line flight path descent and landing.
{"title":"Integrated Simulation and State Estimation for Precision Landing on Titan","authors":"A. Schutte, J. Delaune, Evgeniy Skylanskiy, Robert A. Hewitt, S. Daftry, M. Quadrelli, L. Matthies","doi":"10.1109/AERO47225.2020.9172491","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172491","url":null,"abstract":"This paper reports on a study of the application of a ram-air parafoil to Entry, Descent, and Landing (EDL) on Titan. A comprehensive simulation was constructed to enable simulation of EDL state estimation performance from 10 minutes before entry (E-10 min) to touchdown on the surface of Titan. EDL performance is characterized assuming an entry phase starting at E-10 min followed by a parafoil guided phase for descent and landing to enable precise landing on a predetermined target. Guided descent during the parafoil phase is achieved using the parafoil steering capability while state estimation is accomplished using vision-based Terrain Relative Navigation (TRN). The simulation is used in this study to conduct Monte Carlo analysis of TRN state estimation for a full entry phase sequence followed by a straight line flight path descent and landing.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-03-01","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114082973","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/AERO47225.2020.9172337
G. Doran, S. Lu, M. Liukis, L. Mandrake, U. Rebbapragada, K. Wagstaff, Jimmie Young, Erik Langert, A. Braunegg, P. Horton, Daniel Jeong, Asher Trockman
Interplanetary exploration occurs at vast distances that severely limit communication bandwidth to spacecraft exploring other planets. It is possible to collect much more scientific data than can ever be downlinked given current communication capabilities. Therefore, we are developing a system called COSMIC (Content-based Onboard Summarization to Monitor Infrequent Change) that will opportunistically analyze data onboard a Mars orbiter to alert scientists when meaningful changes have occurred. COSMIC will allow future spacecraft to continuously collect data to search for rare, transient phenomena such as fresh impacts or seasonally changing polar landforms under a constrained downlink budget. In this paper, we describe the overall goals and architecture of COSMIC, plans to enable specific scientific studies, label acquisition to enable supervised approaches to surface landform classification, a new machine learning evaluation framework for analyzing the trade-offs between classifier accuracy and computational requirements, and lessons learned about constraints that COSMIC will face operating onboard a spacecraft. In particular, we discuss design considerations surrounding computational and storage constraints, change detection strategies, and localizing detected landforms of interest within a global coordinate frame. Finally, we describe challenges and open research questions that must be addressed prior to deploying COSMIC.
{"title":"COSMIC: Content-based Onboard Summarization to Monitor Infrequent Change","authors":"G. Doran, S. Lu, M. Liukis, L. Mandrake, U. Rebbapragada, K. Wagstaff, Jimmie Young, Erik Langert, A. Braunegg, P. Horton, Daniel Jeong, Asher Trockman","doi":"10.1109/AERO47225.2020.9172337","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172337","url":null,"abstract":"Interplanetary exploration occurs at vast distances that severely limit communication bandwidth to spacecraft exploring other planets. It is possible to collect much more scientific data than can ever be downlinked given current communication capabilities. Therefore, we are developing a system called COSMIC (Content-based Onboard Summarization to Monitor Infrequent Change) that will opportunistically analyze data onboard a Mars orbiter to alert scientists when meaningful changes have occurred. COSMIC will allow future spacecraft to continuously collect data to search for rare, transient phenomena such as fresh impacts or seasonally changing polar landforms under a constrained downlink budget. In this paper, we describe the overall goals and architecture of COSMIC, plans to enable specific scientific studies, label acquisition to enable supervised approaches to surface landform classification, a new machine learning evaluation framework for analyzing the trade-offs between classifier accuracy and computational requirements, and lessons learned about constraints that COSMIC will face operating onboard a spacecraft. In particular, we discuss design considerations surrounding computational and storage constraints, change detection strategies, and localizing detected landforms of interest within a global coordinate frame. Finally, we describe challenges and open research questions that must be addressed prior to deploying COSMIC.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"97 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":"114726323","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/AERO47225.2020.9172675
C. Okino, D. Abraham, J. Baker, S. Finley, Jay L. Gao, D. Kahan, A. Klesh, J. Krajewski, N. Lay, Shanu Malhotra, Andrew O'Dea, K. Oudrhiri, A. Tkacenko, Zaid J. Towfic, Andrew Johnstone
This paper discusses recent activities at JPL that are focused on extending the Opportunistic Multiple Spacecraft Per Antenna (OMSPA) concept to include arraying multiple antennas. Specifically, we explore the ability to process multiple open loop recordings associated with multiple antennas and perform the appropriate alignment and combining. We focus on using the symbol stream combining technique and provide examples of performance measurements on actual spacecraft signals for MarCO A and B as well as the Mars Express.
{"title":"Opportunistic Arraying","authors":"C. Okino, D. Abraham, J. Baker, S. Finley, Jay L. Gao, D. Kahan, A. Klesh, J. Krajewski, N. Lay, Shanu Malhotra, Andrew O'Dea, K. Oudrhiri, A. Tkacenko, Zaid J. Towfic, Andrew Johnstone","doi":"10.1109/AERO47225.2020.9172675","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172675","url":null,"abstract":"This paper discusses recent activities at JPL that are focused on extending the Opportunistic Multiple Spacecraft Per Antenna (OMSPA) concept to include arraying multiple antennas. Specifically, we explore the ability to process multiple open loop recordings associated with multiple antennas and perform the appropriate alignment and combining. We focus on using the symbol stream combining technique and provide examples of performance measurements on actual spacecraft signals for MarCO A and B as well as the Mars Express.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"23 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":"124445117","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/AERO47225.2020.9172708
J. Jordan, G. Ponchak, P. Neudeck, D. Spry
The first iteration communication system circuitry for the Venus Long-Lived In-situ Solar System Explorer (LLISSE) lander was developed using NASA Glenn Research Center SiC JFET technology. The atmosphere of Venus is a harsh environment that experiences temperatures upward of 460 °C, pressures of 1344 psi, and a dense, corrosive atmosphere composed of CO2, N2, SO2, HF, HCl, CO, OCS, H2S, and H2O making Venus a challenging environment for electronics. Previous missions to Venus have lasted for less than two hours, but LLISSE is being planned and developed to survive 60 Earth days. The communications circuit was designed in Keysight Advance Design Systems (ADS), using three stages of differential amplifiers with the bias circuit designed to be turned on and off for On-Off Keying (OOK) modulation. Buffer amplifiers are integrated into the circuit to facilitate testing. Based on JFET SiC technology developed at NASA Glenn Research Center, it's designed to operate at 5 MHz at room temperature, and 2 MHz at 460 °C. OOK gives the advantage of low power consumption and is ideal for the low frequency transmission. The SiC JFET has been shown to survive 60 days in a simulated Venusian environment. The circuits are tested in the laboratory on a high temperature probe station. The die is mounted and wirebonded on an alumina carrier for probing. Two output ports provide positive and negatively swinging signals to supply a balanced signal to the antenna; the input ports are for bias and a control signal that will come from a digital output of the sensors. The oscillation frequency, output power, phase noise, and data rate are measured as a function of temperature. The output power and phase noise are shown as a function of frequency. The output voltage is measured as a function of time at room temperature and Venus temperature for different bit rates. As a result, this paper demonstrates the first SiC-based communication circuit designed to operate on a long-lived Venus lander.
{"title":"First Iteration Communications Circuit for a Long-Lived In-situ Solar System Explorer (LLISSE)","authors":"J. Jordan, G. Ponchak, P. Neudeck, D. Spry","doi":"10.1109/AERO47225.2020.9172708","DOIUrl":"https://doi.org/10.1109/AERO47225.2020.9172708","url":null,"abstract":"The first iteration communication system circuitry for the Venus Long-Lived In-situ Solar System Explorer (LLISSE) lander was developed using NASA Glenn Research Center SiC JFET technology. The atmosphere of Venus is a harsh environment that experiences temperatures upward of 460 °C, pressures of 1344 psi, and a dense, corrosive atmosphere composed of CO2, N2, SO2, HF, HCl, CO, OCS, H2S, and H2O making Venus a challenging environment for electronics. Previous missions to Venus have lasted for less than two hours, but LLISSE is being planned and developed to survive 60 Earth days. The communications circuit was designed in Keysight Advance Design Systems (ADS), using three stages of differential amplifiers with the bias circuit designed to be turned on and off for On-Off Keying (OOK) modulation. Buffer amplifiers are integrated into the circuit to facilitate testing. Based on JFET SiC technology developed at NASA Glenn Research Center, it's designed to operate at 5 MHz at room temperature, and 2 MHz at 460 °C. OOK gives the advantage of low power consumption and is ideal for the low frequency transmission. The SiC JFET has been shown to survive 60 days in a simulated Venusian environment. The circuits are tested in the laboratory on a high temperature probe station. The die is mounted and wirebonded on an alumina carrier for probing. Two output ports provide positive and negatively swinging signals to supply a balanced signal to the antenna; the input ports are for bias and a control signal that will come from a digital output of the sensors. The oscillation frequency, output power, phase noise, and data rate are measured as a function of temperature. The output power and phase noise are shown as a function of frequency. The output voltage is measured as a function of time at room temperature and Venus temperature for different bit rates. As a result, this paper demonstrates the first SiC-based communication circuit designed to operate on a long-lived Venus lander.","PeriodicalId":114560,"journal":{"name":"2020 IEEE Aerospace Conference","volume":"113 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":"124120127","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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