Pub Date : 2017-03-04DOI: 10.1109/AERO.2017.7943881
Alexander W. Raymond, B. Drouin, A. Tang, E. Schlecht, Yanghyo Kim, M. Chang
A new instrument for in situ rotational spectroscopy of gases is presented. The design is based on the pulsed Fourier transform method of Balle-Flygare but operates at higher frequency than traditional microwave implementations. A semi-confocal cavity is an essential part of the new technology, which builds field strength for pumping rotational transitions. Details about the cavity quality factor and design are discussed. The cavity is combined with custom CMOS integrated circuits that synthesize, amplify, and mix the transmitter and receiver signals. Proof-of-concept laboratory measurements of molecular gases are presented. Incorporation in a comet surface sample return mission concept is discussed in detail. The sensor could be used in number of different planetary missions.
{"title":"In situ gas sensing with a 100 GHz CMOS spectrometer","authors":"Alexander W. Raymond, B. Drouin, A. Tang, E. Schlecht, Yanghyo Kim, M. Chang","doi":"10.1109/AERO.2017.7943881","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943881","url":null,"abstract":"A new instrument for in situ rotational spectroscopy of gases is presented. The design is based on the pulsed Fourier transform method of Balle-Flygare but operates at higher frequency than traditional microwave implementations. A semi-confocal cavity is an essential part of the new technology, which builds field strength for pumping rotational transitions. Details about the cavity quality factor and design are discussed. The cavity is combined with custom CMOS integrated circuits that synthesize, amplify, and mix the transmitter and receiver signals. Proof-of-concept laboratory measurements of molecular gases are presented. Incorporation in a comet surface sample return mission concept is discussed in detail. The sensor could be used in number of different planetary missions.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132536985","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943571
C. Wargo, B. Capozzi, Michael Graham, Dylan Hasson, J. Glaneuski, Brandon Van Acker
Numerous parties have a desire to operate Unmanned Aircraft Systems (UASs)1 and small UASs (known as “sUAS”) in the complex terminal environment and on the airport surface. New and increasingly available surveillance technologies, data link driven controller instructions such as D-TAXI, and access to NAS system information via SWIM (System Wide Information Management) are potential means to enhance the ability of the UAS Pilot in Command's (PICs) to integrate and operate safely in the terminal environment. Vendors directly connected to SWIM feeds can receive ASDE-X data from equipped airports. Vendors also connect to other NAS data feeds for flight planning, airport status, weather information, and traffic flow management initiatives. These data feeds are transitioning to new formats consistent with international standards. All of these information streams are able to provide the Remote PIC with better Situational Awareness (SA) and the ability to better understand the relationship of their aircraft to other aircraft movements; all of which will assist in maintaining the efficiency of NAS operations as well as the speed and tempo of airports operations. Future airport area surveillance information sources from ADS-B and from Ground Based Sense and Avoid (GBSAA) solutions are also emerging. Enhanced vision technologies for Remotely Piloted Aircraft (RPA) are being deployed to support reduced visibility operations. Additionally, autonomous technologies are being researched to control aircraft movement on the airport surface. Specific pilot alerts are being developed for surface events, such as conformance to taxi path, failure of other aircraft to hold for crossing clearances, or intersection encroachments. This paper provides an integrated view of how these emerging technologies can be leveraged to support the Remote PIC and the UAS operations in congested terminal airspace and on airport surface operations.
{"title":"Enhancing UAS Pilot safety by terminal and airport shared information situational awareness","authors":"C. Wargo, B. Capozzi, Michael Graham, Dylan Hasson, J. Glaneuski, Brandon Van Acker","doi":"10.1109/AERO.2017.7943571","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943571","url":null,"abstract":"Numerous parties have a desire to operate Unmanned Aircraft Systems (UASs)1 and small UASs (known as “sUAS”) in the complex terminal environment and on the airport surface. New and increasingly available surveillance technologies, data link driven controller instructions such as D-TAXI, and access to NAS system information via SWIM (System Wide Information Management) are potential means to enhance the ability of the UAS Pilot in Command's (PICs) to integrate and operate safely in the terminal environment. Vendors directly connected to SWIM feeds can receive ASDE-X data from equipped airports. Vendors also connect to other NAS data feeds for flight planning, airport status, weather information, and traffic flow management initiatives. These data feeds are transitioning to new formats consistent with international standards. All of these information streams are able to provide the Remote PIC with better Situational Awareness (SA) and the ability to better understand the relationship of their aircraft to other aircraft movements; all of which will assist in maintaining the efficiency of NAS operations as well as the speed and tempo of airports operations. Future airport area surveillance information sources from ADS-B and from Ground Based Sense and Avoid (GBSAA) solutions are also emerging. Enhanced vision technologies for Remotely Piloted Aircraft (RPA) are being deployed to support reduced visibility operations. Additionally, autonomous technologies are being researched to control aircraft movement on the airport surface. Specific pilot alerts are being developed for surface events, such as conformance to taxi path, failure of other aircraft to hold for crossing clearances, or intersection encroachments. This paper provides an integrated view of how these emerging technologies can be leveraged to support the Remote PIC and the UAS operations in congested terminal airspace and on airport surface operations.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130456213","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943684
D. Lorenz, R. Olds, A. May, C. Mario, M. Perry, E. Palmer, M. Daly
The Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer (OSIRIS-REx) spacecraft launched on September 8, 2016 to embark on an asteroid sample return mission. It is expected to rendezvous with the asteroid, Bennu, navigate to the surface, collect a sample (July'20), and return the sample to Earth (September'23). The original mission design called for using one of two Flash Lidar units to provide autonomous navigation to the surface. Following Preliminary design and initial development of the Lidars, reliability issues with the hardware and test program prompted the project to begin development of an alternative navigation technique to be used as a backup to the Lidar. At the critical design review, Natural Feature Tracking (NFT) was added to the mission. NFT is an onboard optical navigation system that compares observed images to a set of asteroid terrain models which are rendered in real-time from a catalog stored in memory on the flight computer. Onboard knowledge of the spacecraft state is then updated by a Kalman filter using the measured residuals between the rendered reference images and the actual observed images. The asteroid terrain models used by NFT are built from a shape model generated from observations collected during earlier phases of the mission and include both terrain shape and albedo information about the asteroid surface. As a result, the success of NFT is dependent on selecting a set of topographic features that can be both identified during descent as well as reliably rendered using the shape model data available. During development, the OSIRIS-REx team faced significant challenges in developing a process conducive to robust operation. This was especially true for terrain models to be used as the spacecraft gets close to the asteroid and higher fidelity models are required for reliable image correlation. This paper will present some of the challenges and lessons learned from the development of the NFT system which includes not just the flight hardware and software but the development of the terrain models used to generate the onboard rendered images.
{"title":"Lessons learned from OSIRIS-REx autonomous navigation using natural feature tracking","authors":"D. Lorenz, R. Olds, A. May, C. Mario, M. Perry, E. Palmer, M. Daly","doi":"10.1109/AERO.2017.7943684","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943684","url":null,"abstract":"The Origins, Spectral Interpretation, Resource Identification, Security-Regolith Explorer (OSIRIS-REx) spacecraft launched on September 8, 2016 to embark on an asteroid sample return mission. It is expected to rendezvous with the asteroid, Bennu, navigate to the surface, collect a sample (July'20), and return the sample to Earth (September'23). The original mission design called for using one of two Flash Lidar units to provide autonomous navigation to the surface. Following Preliminary design and initial development of the Lidars, reliability issues with the hardware and test program prompted the project to begin development of an alternative navigation technique to be used as a backup to the Lidar. At the critical design review, Natural Feature Tracking (NFT) was added to the mission. NFT is an onboard optical navigation system that compares observed images to a set of asteroid terrain models which are rendered in real-time from a catalog stored in memory on the flight computer. Onboard knowledge of the spacecraft state is then updated by a Kalman filter using the measured residuals between the rendered reference images and the actual observed images. The asteroid terrain models used by NFT are built from a shape model generated from observations collected during earlier phases of the mission and include both terrain shape and albedo information about the asteroid surface. As a result, the success of NFT is dependent on selecting a set of topographic features that can be both identified during descent as well as reliably rendered using the shape model data available. During development, the OSIRIS-REx team faced significant challenges in developing a process conducive to robust operation. This was especially true for terrain models to be used as the spacecraft gets close to the asteroid and higher fidelity models are required for reliable image correlation. This paper will present some of the challenges and lessons learned from the development of the NFT system which includes not just the flight hardware and software but the development of the terrain models used to generate the onboard rendered images.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130666588","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943701
Brian J. Barritt, T. Kichkaylo, K. Mandke, Adam Zalcman, Victor Lin
In this paper we describe an application of Tem-porospatial Software Defined Networking (TS-SDN) to UAV networks. Airborne platforms (airplanes, balloons, airships) can be used to carry wireless communication nodes to provide direct-to-user as well as backhaul connections. Such networks also include ground nodes typically equipped with highly directional steerable transceivers. The physics of flight as well as state of the atmosphere lead to time-dynamic link metrics and availability. As nodes move around, the network topology and routing need to adjust to maintain connectivity. Further, mechanical aspects of the system, such as time required to mechanically steer antennas, makes the reactive repair approach more costly than in terrestrial applications. Instead, TS-SDN incorporates reasoning about physical evolution of the system to proactively adjust the network topology in anticipation of future changes. Using airborne networks under development at Google as an example, we discuss the benefits of the TS-SDN approach compared to reactive repair in terms of network availability. We also identify additional constraints one needs to account for when computing the network topology, such as noninterference with other stationary and moving sources. Existing SDN standards do not support scheduled updates necessary in a TS-SDN. We describe our extensions to control messages and software implementation used in field tests.
{"title":"Operating a UAV mesh & internet backhaul network using temporospatial SDN","authors":"Brian J. Barritt, T. Kichkaylo, K. Mandke, Adam Zalcman, Victor Lin","doi":"10.1109/AERO.2017.7943701","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943701","url":null,"abstract":"In this paper we describe an application of Tem-porospatial Software Defined Networking (TS-SDN) to UAV networks. Airborne platforms (airplanes, balloons, airships) can be used to carry wireless communication nodes to provide direct-to-user as well as backhaul connections. Such networks also include ground nodes typically equipped with highly directional steerable transceivers. The physics of flight as well as state of the atmosphere lead to time-dynamic link metrics and availability. As nodes move around, the network topology and routing need to adjust to maintain connectivity. Further, mechanical aspects of the system, such as time required to mechanically steer antennas, makes the reactive repair approach more costly than in terrestrial applications. Instead, TS-SDN incorporates reasoning about physical evolution of the system to proactively adjust the network topology in anticipation of future changes. Using airborne networks under development at Google as an example, we discuss the benefits of the TS-SDN approach compared to reactive repair in terms of network availability. We also identify additional constraints one needs to account for when computing the network topology, such as noninterference with other stationary and moving sources. Existing SDN standards do not support scheduled updates necessary in a TS-SDN. We describe our extensions to control messages and software implementation used in field tests.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"33 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134585289","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943965
M. Lisano, P. Kallemeyn
NASA's InSight Discovery mission to Mars will land its Phoenix-heritage spacecraft to the near-equatorial Elysium Planitia region of Mars in November 2018 — instead of its original planned landing in September 2016 — to collect science measurements over a period longer than one Mars year. Thus, instead of arriving in mid-Mars-global-dust-storm season in 2016 as originally planned, InSight now will arrive in 2018 during the Martian season when dust storms are typically waning. However, it must be able to withstand a global dust storm near the mission's end a Mars year later, by which point dust on the solar arrays is likely to have accumulated significantly more. This paper discusses how the change in launch date has changed the energy management challenges for InSight, and how the energy management approach for surface operations has been adapted to address those challenges. It also describes how energy balance and battery life are protected over the course of the InSight landed mission, in terms of a deliberate balance between autonomous on-board fault protection and ground commanding into reduced-load configurations that still make progress versus specific, prioritized mission success criteria. It describes the project's unique statistical analysis and usage of Mars Exploration Rovers (MER) archived data on solar energy collection to develop and validate an explicit pre-launch margin policy versus energy reductions due to environment variability over multiple-sol sequences. And finally, the paper explains how this archived energy data has influenced the modification of the Phoenix-heritage autonomous fault protection, to guard against quickly-arising inclement power-generation conditions, such as rapid onset of a local dust storm or water ice cloud front.
{"title":"Energy management operations for the Insight solar-powered mission at Mars","authors":"M. Lisano, P. Kallemeyn","doi":"10.1109/AERO.2017.7943965","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943965","url":null,"abstract":"NASA's InSight Discovery mission to Mars will land its Phoenix-heritage spacecraft to the near-equatorial Elysium Planitia region of Mars in November 2018 — instead of its original planned landing in September 2016 — to collect science measurements over a period longer than one Mars year. Thus, instead of arriving in mid-Mars-global-dust-storm season in 2016 as originally planned, InSight now will arrive in 2018 during the Martian season when dust storms are typically waning. However, it must be able to withstand a global dust storm near the mission's end a Mars year later, by which point dust on the solar arrays is likely to have accumulated significantly more. This paper discusses how the change in launch date has changed the energy management challenges for InSight, and how the energy management approach for surface operations has been adapted to address those challenges. It also describes how energy balance and battery life are protected over the course of the InSight landed mission, in terms of a deliberate balance between autonomous on-board fault protection and ground commanding into reduced-load configurations that still make progress versus specific, prioritized mission success criteria. It describes the project's unique statistical analysis and usage of Mars Exploration Rovers (MER) archived data on solar energy collection to develop and validate an explicit pre-launch margin policy versus energy reductions due to environment variability over multiple-sol sequences. And finally, the paper explains how this archived energy data has influenced the modification of the Phoenix-heritage autonomous fault protection, to guard against quickly-arising inclement power-generation conditions, such as rapid onset of a local dust storm or water ice cloud front.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128712834","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943648
Brett J. Streetman, J. Shoer, L. Singh
As a spacecraft becomes smaller, a number of physical effects scale both favorably and unfavorably for passive stabilization of the craft. Unfortunately, two separate quantities both scale unfavorably for the use of traditional spinning rotor actuators (e.g. reaction wheels, momentum wheels, control moment gyros) for momentum and attitude control. First, the dominant disturbance torques on small spacecraft in low earth orbit, aerodynamic drag and solar radiation pressure, both become relatively larger as spacecraft size decreases. Second, the effectiveness of spinning rotors reduces as the rotor inertia decreases with the square or the wheel radius. These two factors conspire to greatly reduce the effectiveness of rotor-based momentum control systems at small scales. This reduction requires small spacecraft designers to either devote a significantly larger mass fraction to momentum control or adopt alternative momentum control systems. In this study we examine this problem from two viewpoints. First, empirical data is used to find a relationship between spacecraft size and mass fraction devoted to attitude control. While the International Space Station can devote less than 1% of its mass fraction to momentum control effectors, GEO telecom spacecraft tend to need around 1–2% of available mass, and some CubeSats must devote greater than 50% of their mass fraction. Second, we derive an expression for the smallest spacecraft that can use a reaction wheel for effective momentum management. For reasonable assumptions, this lower limit is on the order of 1 cm length scale, which is in good agreement with the empirical trend. Finally, we list some alternative momentum management strategies and discuss how they apply to spacecraft at the smallest size: the centimeter scale ChipSat.
{"title":"Limitations of scaling momentum control strategies to small spacecraft","authors":"Brett J. Streetman, J. Shoer, L. Singh","doi":"10.1109/AERO.2017.7943648","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943648","url":null,"abstract":"As a spacecraft becomes smaller, a number of physical effects scale both favorably and unfavorably for passive stabilization of the craft. Unfortunately, two separate quantities both scale unfavorably for the use of traditional spinning rotor actuators (e.g. reaction wheels, momentum wheels, control moment gyros) for momentum and attitude control. First, the dominant disturbance torques on small spacecraft in low earth orbit, aerodynamic drag and solar radiation pressure, both become relatively larger as spacecraft size decreases. Second, the effectiveness of spinning rotors reduces as the rotor inertia decreases with the square or the wheel radius. These two factors conspire to greatly reduce the effectiveness of rotor-based momentum control systems at small scales. This reduction requires small spacecraft designers to either devote a significantly larger mass fraction to momentum control or adopt alternative momentum control systems. In this study we examine this problem from two viewpoints. First, empirical data is used to find a relationship between spacecraft size and mass fraction devoted to attitude control. While the International Space Station can devote less than 1% of its mass fraction to momentum control effectors, GEO telecom spacecraft tend to need around 1–2% of available mass, and some CubeSats must devote greater than 50% of their mass fraction. Second, we derive an expression for the smallest spacecraft that can use a reaction wheel for effective momentum management. For reasonable assumptions, this lower limit is on the order of 1 cm length scale, which is in good agreement with the empirical trend. Finally, we list some alternative momentum management strategies and discuss how they apply to spacecraft at the smallest size: the centimeter scale ChipSat.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"81 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133505429","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943565
A. Mahran
When selecting an error correcting code, it is desired to fulfill a data error rate criterion, but also the code that is selected does this without being excessively complicated. For specific channel conditions it is quite difficult to optimize the error correcting code parameters' analytically. This work proposes multi-objective optimization by applying the Genetic Algorithm (GA) in the selection of Turbo Product Codes (TPC) parameters' that are used for transmission of data over an AWGN channel. The results show that the GA is capable of converging to a set of sensible solutions and giving the pareto-optimum set for error performance against code complexity.
{"title":"Optimizing the parameters of turbo product codes using genetic algorithms","authors":"A. Mahran","doi":"10.1109/AERO.2017.7943565","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943565","url":null,"abstract":"When selecting an error correcting code, it is desired to fulfill a data error rate criterion, but also the code that is selected does this without being excessively complicated. For specific channel conditions it is quite difficult to optimize the error correcting code parameters' analytically. This work proposes multi-objective optimization by applying the Genetic Algorithm (GA) in the selection of Turbo Product Codes (TPC) parameters' that are used for transmission of data over an AWGN channel. The results show that the GA is capable of converging to a set of sensible solutions and giving the pareto-optimum set for error performance against code complexity.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"45 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130149973","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943789
F. Alibay, J. Kasper, T. Lazio, T. Neilsen
The authors present a space-based array designed to localize and track the radio emission associated with coronal mass ejections (CMEs) from the Sun. Radio emission from CMEs is a direct tracer of the particle acceleration in the inner heliosphere and potential magnetic connections from the lower solar corona to the larger heliosphere. These questions are among those highlighted in the current Solar Decadal Servey, e.g., “Discover and characterize fundamental processes that occur both within the heliosphere and throughout the Universe.” Furthermore, CME radio emission is quite strong, such that only a relatively small number of antennas is required, and a small mission would make a fundamental advancement in our scientific understanding. Indeed, the current state-of-the-art for tracking CME radio emission is defined by single antennas (Wind/WAVES, Stereo/SWAVES) in which the tracking is accomplished by assuming a frequency-to-density mapping. This type of heliophysics mission has been studied several times in the past, but had so far been found to be cost prohibitive, due to the inherent complexity of building multiple spacecraft and flying them in constellation. However, with the increased popularity and success of CubeSat concepts, accompanied by the miniaturization of subsystem components, a range of missions are now being enabled at lower cost than ever before. The paper presents the science requirements for a Small Explorer (SMEX)-class (typically < ∼$100M, including all lifecycle costs) mission concept, and walks through the major features of the SunRISE mission study. SunRISE is composed of six 6U (where 1U is defined as a 10 by 10 by 10cm form-factor) CubeSats placed in an orbit slightly above the Geostationary Equatorial Orbit (GEO) to achieve the aforementioned science goals. The spacecraft fly in a passive formation, which allows them to form an interferometer while minimizing the impact on operations complexity. The paper provides an overview of the mission and spacecraft design, as well as the concept of operations for the mission. Finally, it discusses how the SunRISE mission concept could serve as a stepping stone in demonstrating space-based interferometry and enable more complex mission concepts in the future.
{"title":"Sun radio interferometer space experiment (SunRISE): Tracking particle acceleration and transport in the inner heliosphere","authors":"F. Alibay, J. Kasper, T. Lazio, T. Neilsen","doi":"10.1109/AERO.2017.7943789","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943789","url":null,"abstract":"The authors present a space-based array designed to localize and track the radio emission associated with coronal mass ejections (CMEs) from the Sun. Radio emission from CMEs is a direct tracer of the particle acceleration in the inner heliosphere and potential magnetic connections from the lower solar corona to the larger heliosphere. These questions are among those highlighted in the current Solar Decadal Servey, e.g., “Discover and characterize fundamental processes that occur both within the heliosphere and throughout the Universe.” Furthermore, CME radio emission is quite strong, such that only a relatively small number of antennas is required, and a small mission would make a fundamental advancement in our scientific understanding. Indeed, the current state-of-the-art for tracking CME radio emission is defined by single antennas (Wind/WAVES, Stereo/SWAVES) in which the tracking is accomplished by assuming a frequency-to-density mapping. This type of heliophysics mission has been studied several times in the past, but had so far been found to be cost prohibitive, due to the inherent complexity of building multiple spacecraft and flying them in constellation. However, with the increased popularity and success of CubeSat concepts, accompanied by the miniaturization of subsystem components, a range of missions are now being enabled at lower cost than ever before. The paper presents the science requirements for a Small Explorer (SMEX)-class (typically < ∼$100M, including all lifecycle costs) mission concept, and walks through the major features of the SunRISE mission study. SunRISE is composed of six 6U (where 1U is defined as a 10 by 10 by 10cm form-factor) CubeSats placed in an orbit slightly above the Geostationary Equatorial Orbit (GEO) to achieve the aforementioned science goals. The spacecraft fly in a passive formation, which allows them to form an interferometer while minimizing the impact on operations complexity. The paper provides an overview of the mission and spacecraft design, as well as the concept of operations for the mission. Finally, it discusses how the SunRISE mission concept could serve as a stepping stone in demonstrating space-based interferometry and enable more complex mission concepts in the future.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123762947","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943765
A. Ho, Eric Shea, Alan D. George, A. Gordon-Ross
Requirements for higher video quality in space applications continuously calls for increased resolution in imaging sensors, higher bit-depth codecs, more creative solutions for preprocessing and compression techniques, and faster, yet resilient, space-grade platforms. Understanding how these variables interact and affect each other on different platforms is crucial in system development when trying to meet requirements and constraints, such as compression speed, compression ratio (CR), image quality, bandwidth, etc. To analyze this interaction, we present a comparative analysis between compression speed and compression ratio using serial and parallel compression codes on different platforms and architectures, focusing upon video data from overhead-persistent infrared (OPIR) sensors on spacecraft. Previous research allowed us to compare CR and image quality with new preprocessing techniques, but it did not evaluate and address the challenges of compression speed on space-grade processors. Performance is critical, since of course the preprocessing and compression codes plus downlink of compressed data must require less total time than downlink of the raw data, in order for compression to be fully effective.
{"title":"Comparative analysis of parallel OPIR compression on space processors","authors":"A. Ho, Eric Shea, Alan D. George, A. Gordon-Ross","doi":"10.1109/AERO.2017.7943765","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943765","url":null,"abstract":"Requirements for higher video quality in space applications continuously calls for increased resolution in imaging sensors, higher bit-depth codecs, more creative solutions for preprocessing and compression techniques, and faster, yet resilient, space-grade platforms. Understanding how these variables interact and affect each other on different platforms is crucial in system development when trying to meet requirements and constraints, such as compression speed, compression ratio (CR), image quality, bandwidth, etc. To analyze this interaction, we present a comparative analysis between compression speed and compression ratio using serial and parallel compression codes on different platforms and architectures, focusing upon video data from overhead-persistent infrared (OPIR) sensors on spacecraft. Previous research allowed us to compare CR and image quality with new preprocessing techniques, but it did not evaluate and address the challenges of compression speed on space-grade processors. Performance is critical, since of course the preprocessing and compression codes plus downlink of compressed data must require less total time than downlink of the raw data, in order for compression to be fully effective.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123189589","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 : 2017-03-04DOI: 10.1109/AERO.2017.7943953
S. Herzig, S. Mandutianu, Hongman Kim, S. Hernandez, T. Imken
In this paper, a model-based approach to exploring the trade space of multi-spacecraft mission architectures is introduced. Missions involving multiple spacecraft are inherently more complex to design than traditional single spacecraft missions. This is particularly true for fractionated mission concepts, where spacecraft have diverse roles and distributed responsibilities, and fulfilling mission goals requires communication and collaboration. In practice, this complexity and the lack of computational models and tools limit design teams to consider small design spaces and force them to quickly fixate on a single mission design. However, design fixation at such early stages often leads to sub-optimal designs. Towards overcoming this limitation, we propose an automated approach to exploring and visualizing the trade space of multi-spacecraft mission architectures that aids users in decision making, and provides a basis for identifying solutions that are Pareto-optimal with respect to user-defined science requirements, technical and resource constraints, and mission objectives. Central to our approach is the automated synthesis and analysis of mission architecture alternatives from a set of user-provided functional requirements and mission goals, as well as a library of spacecraft components and analysis models. Design rules (synthesis knowledge) are provided in the form of model-transformation rules. Sequences of endogenous model transformations are applied in-place to produce sets of candidate solutions, thereby effectively searching the design space. The search process is guided by the specified objectives, and is implemented using evolutionary algorithms. We demonstrate our approach to architectural optimization using a simplified radio interferometry mission design as a case study. We conclude that using the proposed approach, the number and diversity of candidate mission architectures available for consideration can be significantly increased. Furthermore, the automated synthesis and evaluation of mission architectures can lead to emergent and non-intuitive solutions to be discovered.
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