Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10115724
R. Dendy, D. Mortensen, D. Zeleznikar, Stephanie Booth
NASA's Artemis program and other lunar exploration and development programs are planning over 40 lunar missions before 2030. Lunar missions, both crewed and uncrewed, include orbiters, landers, rovers, and surface stations. All these missions require communications with Earth, either via Direct to Earth (DTE) links or through relays in lunar orbit. Multiple DTE options are available among existing and planned ground stations: Deep Space Network (DSN), European Space Agency, and others. Relay options include the planned Lunar Gateway, LunaNet compliant relays, and some lunar landers propose to launch dedicated orbiters. The dilemma for lunar system designers is to identify a communication link which meets mission requirements but does not have issues of limited access (e.g. DSN is in high demand supporting deep space missions with high priority and some with inflexible schedules), system impacts (high power Radio Frequency (RF) for DTE links), cost (dedicated relay), or operational date. To avoid this difficult decision, a Flexible Radio for Lunar Missions is proposed, which will enable system designs to proceed prior to any final decision on the communication network to be used, by enabling compatibility with any of multiple DTE or orbital relay communication systems. The Flexible Radio will support the necessary frequency, bandwidth, modulation, and power requirements to interoperate with the majority of known or planned DTE or relay systems, and can be designed into a lunar mission without prior knowledge of which link will ultimately be used. Furthermore, the link being used can be changed as needed during the mission, in near real time. The Flexible Radio design will leverage work already completed at NASA in the areas of Wideband RF, Software Defined Radio, Adaptive Coding and Modulation, and Phased Array antennas. The Flexible Radio requires sufficient bandwidth to cover the allocated frequencies for both the operation of links in cislunar space and for space-to-Earth links; the flexibility to support multiple modulations, data rates, and coding schemes; the ability to identify available relays, detect and recognize the signals of those relays, and adapt its own frequency, modulation, symbol rate, and code rate to operate with the detected relay (or DTE station); and finally, it requires appropriate software to support network configuration and interoperability with the detected network. The Flexible Radio can be designed in a sufficiently small, lightweight, and low-power package to be used in a wide variety of lunar systems. The initial implementation, as proposed, will focus on the Ka-band, supporting up to 2 GHz bandwidth around the 27 GHz frequency for return links, and 23 GHz for forward links. Other frequency bands are under consideration for future configurations. The software defined modem will support OQPSK, BPSK, and NASA-defined modulations which also support two-way ranging with data. For near-real time adaptation, the Flexible
{"title":"Flexible User Radio for Lunar Missions","authors":"R. Dendy, D. Mortensen, D. Zeleznikar, Stephanie Booth","doi":"10.1109/AERO55745.2023.10115724","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115724","url":null,"abstract":"NASA's Artemis program and other lunar exploration and development programs are planning over 40 lunar missions before 2030. Lunar missions, both crewed and uncrewed, include orbiters, landers, rovers, and surface stations. All these missions require communications with Earth, either via Direct to Earth (DTE) links or through relays in lunar orbit. Multiple DTE options are available among existing and planned ground stations: Deep Space Network (DSN), European Space Agency, and others. Relay options include the planned Lunar Gateway, LunaNet compliant relays, and some lunar landers propose to launch dedicated orbiters. The dilemma for lunar system designers is to identify a communication link which meets mission requirements but does not have issues of limited access (e.g. DSN is in high demand supporting deep space missions with high priority and some with inflexible schedules), system impacts (high power Radio Frequency (RF) for DTE links), cost (dedicated relay), or operational date. To avoid this difficult decision, a Flexible Radio for Lunar Missions is proposed, which will enable system designs to proceed prior to any final decision on the communication network to be used, by enabling compatibility with any of multiple DTE or orbital relay communication systems. The Flexible Radio will support the necessary frequency, bandwidth, modulation, and power requirements to interoperate with the majority of known or planned DTE or relay systems, and can be designed into a lunar mission without prior knowledge of which link will ultimately be used. Furthermore, the link being used can be changed as needed during the mission, in near real time. The Flexible Radio design will leverage work already completed at NASA in the areas of Wideband RF, Software Defined Radio, Adaptive Coding and Modulation, and Phased Array antennas. The Flexible Radio requires sufficient bandwidth to cover the allocated frequencies for both the operation of links in cislunar space and for space-to-Earth links; the flexibility to support multiple modulations, data rates, and coding schemes; the ability to identify available relays, detect and recognize the signals of those relays, and adapt its own frequency, modulation, symbol rate, and code rate to operate with the detected relay (or DTE station); and finally, it requires appropriate software to support network configuration and interoperability with the detected network. The Flexible Radio can be designed in a sufficiently small, lightweight, and low-power package to be used in a wide variety of lunar systems. The initial implementation, as proposed, will focus on the Ka-band, supporting up to 2 GHz bandwidth around the 27 GHz frequency for return links, and 23 GHz for forward links. Other frequency bands are under consideration for future configurations. The software defined modem will support OQPSK, BPSK, and NASA-defined modulations which also support two-way ranging with data. For near-real time adaptation, the Flexible","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"4 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":"129507554","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/AERO55745.2023.10115568
Angela Alves dos Santos, J. L. Emeri, E. G. Carvalho, W. B. Moraes, L. Seixas, A. Telles, S. Finco
This paper presents the Total Ionizing Dose radi-ation results for a radiation tolerant Sigma-Delta Analogto-Digital Converters for aerospace applications, in 0.6 $boldsymbol{mu} mathbf{m}$ Silicon-On-Insulator Technology. The ADC topology circuit was de-signed from continuous-time sigma-delta modulator (CT-SDM) for High-Speed A/D Conversion. The digital filter is based on the Cascaded Integrator Comb what is a lowpass linear phase-line finite impulse response filters, well suited for anti-aliasing filtering. In order to mitigate the effects of ionizing radiation some features are approached, such as the adoption of the Radiation hardened by design Enclosed-LayoutTransistor-Based technique that increases radiation tolerance. Another technique used was SOl, which enables transistor isolation, thereby reducing parasitic capacitance. These two techniques are alternatives for Low-Power Low-Voltage circuits. During X-ray ionizing radiation testing, it was found that from a TID dose of order above 50 krad (Si) and 10KeV effective energy. The results obtained from the tests showed that the Integrated Circuit (IC) of the sigma delta ADC behaved as expected and can be used in environments for space applications.
{"title":"TID Radiation Effects on a 0.6 μm Sigma Delta ADC Radiation-Hardened-by-Design using ELTs","authors":"Angela Alves dos Santos, J. L. Emeri, E. G. Carvalho, W. B. Moraes, L. Seixas, A. Telles, S. Finco","doi":"10.1109/AERO55745.2023.10115568","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115568","url":null,"abstract":"This paper presents the Total Ionizing Dose radi-ation results for a radiation tolerant Sigma-Delta Analogto-Digital Converters for aerospace applications, in 0.6 $boldsymbol{mu} mathbf{m}$ Silicon-On-Insulator Technology. The ADC topology circuit was de-signed from continuous-time sigma-delta modulator (CT-SDM) for High-Speed A/D Conversion. The digital filter is based on the Cascaded Integrator Comb what is a lowpass linear phase-line finite impulse response filters, well suited for anti-aliasing filtering. In order to mitigate the effects of ionizing radiation some features are approached, such as the adoption of the Radiation hardened by design Enclosed-LayoutTransistor-Based technique that increases radiation tolerance. Another technique used was SOl, which enables transistor isolation, thereby reducing parasitic capacitance. These two techniques are alternatives for Low-Power Low-Voltage circuits. During X-ray ionizing radiation testing, it was found that from a TID dose of order above 50 krad (Si) and 10KeV effective energy. The results obtained from the tests showed that the Integrated Circuit (IC) of the sigma delta ADC behaved as expected and can be used in environments for space applications.","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":"129529429","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/AERO55745.2023.10115559
I. Standley, W. Pike, S. Calcutt, J. P. Hoffman
As part of the Payloads and Research Investigations on the Surface of the Moon (PRISM), the Farside Seismic Suite (FSS), will carry a pair of seismometers to the Schrödinger crater. One of these, the three-component Short-Period seismometer, is based on the MEMS seismometer successfully deployed by the InSight mission to Mars. This paper will describe the adaption of the Martian design to operate on the moon and potential future performance improvements made possible by operating in the low lunar gravity and vacuum conditions. Future possible developments of penetrator instruments and measurements in low gravity conditions leading to different deployment techniques will be briefly discussed along with the parallel development with JPL of a high dynamic range low frequency digitizer (DC-100 Hz) suitable for recording this sensor and other geophysical instrumentation in the space environment
{"title":"Short Period Seismometer for the Lunar Farside Seismic Suite Mission","authors":"I. Standley, W. Pike, S. Calcutt, J. P. Hoffman","doi":"10.1109/AERO55745.2023.10115559","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115559","url":null,"abstract":"As part of the Payloads and Research Investigations on the Surface of the Moon (PRISM), the Farside Seismic Suite (FSS), will carry a pair of seismometers to the Schrödinger crater. One of these, the three-component Short-Period seismometer, is based on the MEMS seismometer successfully deployed by the InSight mission to Mars. This paper will describe the adaption of the Martian design to operate on the moon and potential future performance improvements made possible by operating in the low lunar gravity and vacuum conditions. Future possible developments of penetrator instruments and measurements in low gravity conditions leading to different deployment techniques will be briefly discussed along with the parallel development with JPL of a high dynamic range low frequency digitizer (DC-100 Hz) suitable for recording this sensor and other geophysical instrumentation in the space environment","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"199 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":"129550387","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/AERO55745.2023.10115844
J. Velazco
One of Chascii's specific goals is to provide ubiquitous superfast, low-latency connectivity along the solar system through the deployment of its INterplanetary SPace InteRnEt (INSPIRE) network. INSPIRE seeks to deploy a large number of small spacecraft (smallsats), arranged as autonomous swarms, to create optically interconnected network nodes around planetary bodies and their Lagrange points. It is envisioned that future scientific and commercial space missions along the solar system can use INSPIRE as their low-latency fast-data-rate connectivity provider. Each INSPIRE spacecraft is furnished with a set of fast communications systems. High-speed intra-swarm communications is achieved via omnidirectional optical links. The swarms act as autonomous network nodes that can form large synthetic optical apertures that enable high data rate communications among INSPIRE nodes. We see INSPIRE as the basis for the space internet and we plan to systematically implement this network to provide commercial and reliable connectivity to space users. In this paper we will present the architecture under development for implementing the cislunar INSPIRE. Chascii plans to deploy INSPIRE nodes along low-Earth-orbit and GEO as well as along Earth-Moon Lagrange points 1 and 2 to provide gigabit connectivity to future scientific, military, and commercial missions around the moon.
{"title":"INSPIRE - A Connectivity Network for the Solar System","authors":"J. Velazco","doi":"10.1109/AERO55745.2023.10115844","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115844","url":null,"abstract":"One of Chascii's specific goals is to provide ubiquitous superfast, low-latency connectivity along the solar system through the deployment of its INterplanetary SPace InteRnEt (INSPIRE) network. INSPIRE seeks to deploy a large number of small spacecraft (smallsats), arranged as autonomous swarms, to create optically interconnected network nodes around planetary bodies and their Lagrange points. It is envisioned that future scientific and commercial space missions along the solar system can use INSPIRE as their low-latency fast-data-rate connectivity provider. Each INSPIRE spacecraft is furnished with a set of fast communications systems. High-speed intra-swarm communications is achieved via omnidirectional optical links. The swarms act as autonomous network nodes that can form large synthetic optical apertures that enable high data rate communications among INSPIRE nodes. We see INSPIRE as the basis for the space internet and we plan to systematically implement this network to provide commercial and reliable connectivity to space users. In this paper we will present the architecture under development for implementing the cislunar INSPIRE. Chascii plans to deploy INSPIRE nodes along low-Earth-orbit and GEO as well as along Earth-Moon Lagrange points 1 and 2 to provide gigabit connectivity to future scientific, military, and commercial missions around the moon.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"7 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":"130362176","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/AERO55745.2023.10115608
R. Nallapu, Bhavi Jagatia, P. Linden, Lisa McGill Donahue, A. Ayasse
The phenomenon of glint occurs when an observer catches specular reflections of sunlight from the surface of open water. An imaging spectrometer can measure crucial information about local atmospheric composition by observing absorption spectra from glint between 0.3 and 2.4 microns. The genesis of the Carbon Mapper mission came from a need to use high-quality hyperspectral data to locate methane point source emitters at the facility scale to support mitigation action. As part of its overall strategy for global greenhouse gas monitoring, the Carbon Mapper mission is designed to utilize glint imagery to study offshore emissions of CH4 and CO2. The partnership includes the non-profit Carbon Mapper, Planet, and JPL. The Carbon Mapper mission is designed to utilize glint imagery to study off-shore emissions of greenhouse gasses. In most satellite sensing applications, glint is often a serendipitous event. It is usually captured by coincidence when the satellites are in the right configuration at the right time, or even skipped to avoid sensor saturation. Having a dedicated glint imagery product requires a reliable methodology of tasking a satellite to autonomously capture glint images. This paper presents novel approaches taken to address the above-mentioned problem, which were then validated by tasking Planet's existing fleet of satellites and are planned for the upcoming Tanager satellites which are fulfilling the Carbon Mapper mission. Specifically, we present a formalized methodology to predict future glint windows over a specific region. We then study various tasking approaches that describe the satellite's actions during these windows to autonomously acquire glint captures. These actions are then demonstrated by orbiting satellites, and their captures are then analyzed. Tasking an imaging satellite requires precise window prediction models of imaging opportunities. Collecting a glint image, however, also requires the target on the ground to act as a perfect mirror during the imaging event. This is modeled as additional constraints on the opportunity generation model: (1) the Sun-satellite relative azimuth is required to be 180 degrees, and (2) the satellite elevation must equal the Sun elevation. This model is used to find opportunities to capture glint over desired targets. Satellites from Planet's two operational constellations, SkySats, and Doves, are tasked for validation. SkySats and Doves operate on different tasking philosophies, so we test two different tasking philosophies on these constellations. SkySats employ a “Target Track” approach wherein the satellite camera is pointed at the desired target as the satellite orbits over the target. The Doves, on the other hand, employ a “Pushbroom” approach wherein the satellite maintains a fixed, off-axis attitude as it passes over the target region. The two strategies were deployed on these constellations and were able to demonstrate successful glint captures. While both strategies can validat
{"title":"On-Orbit Demonstrations of Proactive Tasking of Glint Imagery","authors":"R. Nallapu, Bhavi Jagatia, P. Linden, Lisa McGill Donahue, A. Ayasse","doi":"10.1109/AERO55745.2023.10115608","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115608","url":null,"abstract":"The phenomenon of glint occurs when an observer catches specular reflections of sunlight from the surface of open water. An imaging spectrometer can measure crucial information about local atmospheric composition by observing absorption spectra from glint between 0.3 and 2.4 microns. The genesis of the Carbon Mapper mission came from a need to use high-quality hyperspectral data to locate methane point source emitters at the facility scale to support mitigation action. As part of its overall strategy for global greenhouse gas monitoring, the Carbon Mapper mission is designed to utilize glint imagery to study offshore emissions of CH4 and CO2. The partnership includes the non-profit Carbon Mapper, Planet, and JPL. The Carbon Mapper mission is designed to utilize glint imagery to study off-shore emissions of greenhouse gasses. In most satellite sensing applications, glint is often a serendipitous event. It is usually captured by coincidence when the satellites are in the right configuration at the right time, or even skipped to avoid sensor saturation. Having a dedicated glint imagery product requires a reliable methodology of tasking a satellite to autonomously capture glint images. This paper presents novel approaches taken to address the above-mentioned problem, which were then validated by tasking Planet's existing fleet of satellites and are planned for the upcoming Tanager satellites which are fulfilling the Carbon Mapper mission. Specifically, we present a formalized methodology to predict future glint windows over a specific region. We then study various tasking approaches that describe the satellite's actions during these windows to autonomously acquire glint captures. These actions are then demonstrated by orbiting satellites, and their captures are then analyzed. Tasking an imaging satellite requires precise window prediction models of imaging opportunities. Collecting a glint image, however, also requires the target on the ground to act as a perfect mirror during the imaging event. This is modeled as additional constraints on the opportunity generation model: (1) the Sun-satellite relative azimuth is required to be 180 degrees, and (2) the satellite elevation must equal the Sun elevation. This model is used to find opportunities to capture glint over desired targets. Satellites from Planet's two operational constellations, SkySats, and Doves, are tasked for validation. SkySats and Doves operate on different tasking philosophies, so we test two different tasking philosophies on these constellations. SkySats employ a “Target Track” approach wherein the satellite camera is pointed at the desired target as the satellite orbits over the target. The Doves, on the other hand, employ a “Pushbroom” approach wherein the satellite maintains a fixed, off-axis attitude as it passes over the target region. The two strategies were deployed on these constellations and were able to demonstrate successful glint captures. While both strategies can validat","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"142 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":"123456917","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/AERO55745.2023.10115697
Kullen W. Waggoner, D. Curtis, Bryan D. Little
This paper demonstrates an innovative approach for cislunar Space Situational Awareness (SSA) by demonstrating state estimation using time difference of arrival (TDOA)/frequency difference of arrival (FDOA) from radio frequency (RF) signals transmitted by a cislunar traversing satellite. Traditional SSA methods such as electro-optical (EO) and radar have challenges that include illumination, light saturation, and signal power loss over long distances. These can be avoided with an architecture that relies on passive RF TDOA and FDOA. For this paper, RF signals are modeled as having been collected at two or more receivers and stochastic estimation techniques are applied to determine the transmitter's state estimate and covariance. To simulate the performance of the TDOA/FDOA system, this paper uses additive Gaussian white noise on the RF TDOA/FDOA measurements. The circularly restricted three body problem dynamics (CR3BP) are utilized to model the movement of the space object as it traverses cislunar space. To assess performance of this method, this paper models three two-node space-based receiver architectures and three three-node architectures and compares them to show potential advantages and disadvantages of each. All modeled receivers are in earth centered Keplerian orbits. Each receiver has knowledge of all receivers' locations and compares its collected signals with the other receivers to create the TDOA/FDOA measurements. Iterative batch least-squares estimation techniques were used for each scenario to estimate the transmitter's position and velocity as it moves in a periodic CR3BP orbit about one of the earth-moon Lagrange points. Finally, this paper analyzes how the stability of the transmitter's orbit impacts the accuracy of TDOA/FDOA state estimation.
{"title":"Analysis of TDOA/FDOA State Estimation Accuracy of Cislunar Objects for Space Situational Awareness","authors":"Kullen W. Waggoner, D. Curtis, Bryan D. Little","doi":"10.1109/AERO55745.2023.10115697","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115697","url":null,"abstract":"This paper demonstrates an innovative approach for cislunar Space Situational Awareness (SSA) by demonstrating state estimation using time difference of arrival (TDOA)/frequency difference of arrival (FDOA) from radio frequency (RF) signals transmitted by a cislunar traversing satellite. Traditional SSA methods such as electro-optical (EO) and radar have challenges that include illumination, light saturation, and signal power loss over long distances. These can be avoided with an architecture that relies on passive RF TDOA and FDOA. For this paper, RF signals are modeled as having been collected at two or more receivers and stochastic estimation techniques are applied to determine the transmitter's state estimate and covariance. To simulate the performance of the TDOA/FDOA system, this paper uses additive Gaussian white noise on the RF TDOA/FDOA measurements. The circularly restricted three body problem dynamics (CR3BP) are utilized to model the movement of the space object as it traverses cislunar space. To assess performance of this method, this paper models three two-node space-based receiver architectures and three three-node architectures and compares them to show potential advantages and disadvantages of each. All modeled receivers are in earth centered Keplerian orbits. Each receiver has knowledge of all receivers' locations and compares its collected signals with the other receivers to create the TDOA/FDOA measurements. Iterative batch least-squares estimation techniques were used for each scenario to estimate the transmitter's position and velocity as it moves in a periodic CR3BP orbit about one of the earth-moon Lagrange points. Finally, this paper analyzes how the stability of the transmitter's orbit impacts the accuracy of TDOA/FDOA state estimation.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116329984","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/AERO55745.2023.10115553
E. Staudinger, R. Pöhlmann, Siwei Zhang, A. Dammann, Riccardo Giubilato, Ryo Sakagami, Peter Lehner, M. J. Schuster, Andreas Dömel, B. Vodermayer, A. Prince, A. Wedler
Measurement of the red-shifted 21-cm signal of neu-tral hydrogen, and thus observing The Dark Ages is expected to be the holy grail of 21-cm Cosmology. A Radio-telescope to observe low radio frequency signals is needed, but radio interfer-ence on Earth and Earth's ionosphere blocking these signals are limiting science investigations in this field. Hence, such a radio-telescope composed of dozens to hundreds of antennas shall be deployed on the lunar far side. Such arrays are shielded from interference from Earth and Earth's ionosphere blocking very low radio frequencies is not present. Within the Helmholtz Future Topic Project Autonomous Robotic Networks to Help Modern Societies (ARCHES) we developed necessary technologies for autonomous robotic de-ployment of antenna elements, modular payload box design, and robust radio-localization to enable such distributed low-frequency arrays. In particular the antennas' positions must be determined accurately, such that the array can be operated as phased array. Our developments lead to the execution of an analog-demonstration on the volcano Mt. Etna, Sicily, Italy, in June and July 2022 over the course of four weeks. We successfully demonstrated the autonomous robotic deployment of antenna elements and our decentralized real-time radio-localization system to obtain the antenna element positions. Ad-ditionally, we showed a proof-of-concept operation of the phased array comprising four antenna elements: estimating the signal direction of arrival of a radio-beacon with unknown position, and the beamforming capabilities itself, for a carrier frequency of 20 MHz. In this paper, we give insights into our developed technologies and the analog-demonstration on the volcano Mt. Etna, Sicily, Italy. We show results of the successfully executed mission and give an outlook how our developed technologies can be further used for lunar exploration.
{"title":"Enabling Distributed Low Radio Frequency Arrays - Results of an Analog Campaign on Mt. Etna","authors":"E. Staudinger, R. Pöhlmann, Siwei Zhang, A. Dammann, Riccardo Giubilato, Ryo Sakagami, Peter Lehner, M. J. Schuster, Andreas Dömel, B. Vodermayer, A. Prince, A. Wedler","doi":"10.1109/AERO55745.2023.10115553","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115553","url":null,"abstract":"Measurement of the red-shifted 21-cm signal of neu-tral hydrogen, and thus observing The Dark Ages is expected to be the holy grail of 21-cm Cosmology. A Radio-telescope to observe low radio frequency signals is needed, but radio interfer-ence on Earth and Earth's ionosphere blocking these signals are limiting science investigations in this field. Hence, such a radio-telescope composed of dozens to hundreds of antennas shall be deployed on the lunar far side. Such arrays are shielded from interference from Earth and Earth's ionosphere blocking very low radio frequencies is not present. Within the Helmholtz Future Topic Project Autonomous Robotic Networks to Help Modern Societies (ARCHES) we developed necessary technologies for autonomous robotic de-ployment of antenna elements, modular payload box design, and robust radio-localization to enable such distributed low-frequency arrays. In particular the antennas' positions must be determined accurately, such that the array can be operated as phased array. Our developments lead to the execution of an analog-demonstration on the volcano Mt. Etna, Sicily, Italy, in June and July 2022 over the course of four weeks. We successfully demonstrated the autonomous robotic deployment of antenna elements and our decentralized real-time radio-localization system to obtain the antenna element positions. Ad-ditionally, we showed a proof-of-concept operation of the phased array comprising four antenna elements: estimating the signal direction of arrival of a radio-beacon with unknown position, and the beamforming capabilities itself, for a carrier frequency of 20 MHz. In this paper, we give insights into our developed technologies and the analog-demonstration on the volcano Mt. Etna, Sicily, Italy. We show results of the successfully executed mission and give an outlook how our developed technologies can be further used for lunar exploration.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"19 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":"121505474","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/AERO55745.2023.10115894
D. Messmann, W. Jordaan
Small bodies such as asteroids and comets are becoming more and more exciting destinations. Traditional deep-space missions such as NEAR-Shoemaker or Rosetta require interaction with the ground segment on Earth for successful mission operation. Despite some a-priori information on these objects, little is known about their environment. Autonomous navigation in the vicinity of these bodies can be very challenging. Therefore, increasing the autonomy level is required to enable future deep-space missions. Several previous studies have investigated the problem of autonomous navigation for deep-space missions to small bodies. For instance, a number of simultaneous localization and mapping approaches with various sensors have been discussed and proposed. However, existing works have several assumptions or limitations. Some studies consider missions only to a particular small body or implicitly assume accurate model information. Other concepts suffer from high computational complexity, whose robust performance is not analyzed in detail. Unlike existing approaches, we investigate the feasibility of utilizing the spacecraft's attitude determination and control system (ADCS) to recover its orbital behavior. This idea has the benefit of reusing the existing equipment and algorithms. Using star trackers and gyroscope measurements, we can constrain the attitude and the angular velocity of the spacecraft relative to the celestial reference frame. Euler's equation, describing the rotational dynamics of a spacecraft, also encodes the orbital information. We measure the change in its angular momentum vector relative to the reference to infer the orbital information. While orbiting the small body, the spacecraft may conduct attitude maneuvers to leverage the determination process. The extracted orbital information can aid autonomous navigation. This paper presents the mathematical foundations of the concept and analyzes its feasibility. A number of numerical simulations are conducted in different scenarios. Finally, the robustness is assessed against disturbances and sensor noise.
{"title":"Extracting Orbital Information from the Attitude Control System of a Spacecraft near Small Bodies","authors":"D. Messmann, W. Jordaan","doi":"10.1109/AERO55745.2023.10115894","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115894","url":null,"abstract":"Small bodies such as asteroids and comets are becoming more and more exciting destinations. Traditional deep-space missions such as NEAR-Shoemaker or Rosetta require interaction with the ground segment on Earth for successful mission operation. Despite some a-priori information on these objects, little is known about their environment. Autonomous navigation in the vicinity of these bodies can be very challenging. Therefore, increasing the autonomy level is required to enable future deep-space missions. Several previous studies have investigated the problem of autonomous navigation for deep-space missions to small bodies. For instance, a number of simultaneous localization and mapping approaches with various sensors have been discussed and proposed. However, existing works have several assumptions or limitations. Some studies consider missions only to a particular small body or implicitly assume accurate model information. Other concepts suffer from high computational complexity, whose robust performance is not analyzed in detail. Unlike existing approaches, we investigate the feasibility of utilizing the spacecraft's attitude determination and control system (ADCS) to recover its orbital behavior. This idea has the benefit of reusing the existing equipment and algorithms. Using star trackers and gyroscope measurements, we can constrain the attitude and the angular velocity of the spacecraft relative to the celestial reference frame. Euler's equation, describing the rotational dynamics of a spacecraft, also encodes the orbital information. We measure the change in its angular momentum vector relative to the reference to infer the orbital information. While orbiting the small body, the spacecraft may conduct attitude maneuvers to leverage the determination process. The extracted orbital information can aid autonomous navigation. This paper presents the mathematical foundations of the concept and analyzes its feasibility. A number of numerical simulations are conducted in different scenarios. Finally, the robustness is assessed against disturbances and sensor noise.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"87 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":"126315843","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/AERO55745.2023.10115538
Osama H. Zekry, Tamer Attia, A. T. Hafez, M. Ashry
This paper presents a Proportional-Integration-Derivative (PID) trajectory tracking control of a Crazyflie nanoquadcopter dependent upon the Genetic Algorithm (GA) technique to improve the dynamic performance of the Crazyflie. The comparison between the original PID and the proposed PID-based GA controllers is demonstrated using experimental data from the Crazyflie (CF) as the desired trajectory feeding both controllers. These data are the outcome of laboratory experiments. Experiments are carried out using simulation to compare as well as evaluate how the Crazyflie performs at different speeds for real-time desired trajectories in terms of dynamic performance and stability.
{"title":"PID Trajectory Tracking Control of Crazyflie Nanoquadcopter Based on Genetic Algorithm","authors":"Osama H. Zekry, Tamer Attia, A. T. Hafez, M. Ashry","doi":"10.1109/AERO55745.2023.10115538","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115538","url":null,"abstract":"This paper presents a Proportional-Integration-Derivative (PID) trajectory tracking control of a Crazyflie nanoquadcopter dependent upon the Genetic Algorithm (GA) technique to improve the dynamic performance of the Crazyflie. The comparison between the original PID and the proposed PID-based GA controllers is demonstrated using experimental data from the Crazyflie (CF) as the desired trajectory feeding both controllers. These data are the outcome of laboratory experiments. Experiments are carried out using simulation to compare as well as evaluate how the Crazyflie performs at different speeds for real-time desired trajectories in terms of dynamic performance and stability.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"20 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":"132388298","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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