Pub Date : 2023-03-04DOI: 10.1109/AERO55745.2023.10115599
Kyle Logue
A complex-valued autoencoder neural network ca-pable of compressing & denoising radio frequency signals with arbitrary model scaling is proposed. Complex-valued time sam-ples received with various impairments are encoded into an embedding vector, then decoded back into complex-valued time samples. The embedding and the related latent space allow search, comparison, and clustering of signals. Traditional signal processing tasks like specific emitter identification, geolocation, or ambiguity estimation can utilize multiple compressed embed-dings simultaneously. This paper demonstrates an autoencoder implementation capable of compression by a factor of 64 that is still resilient against RF channel impairments. The autoencoder allows individual scaling by network depth, width, and resolution or in a compound sense to target both embedded and data center deployments. The common building block is inspired by the fused inverted residual block (Fused-MBConv), popularized by EfficientNetV2 & MobileNetV3, but with kernel sizes more appropriate for time-series signal processing. A complex-valued PyTorch implementation is available along with a pre-trained model, at https://github.com/the-aerospace-corporation/glaucus.
{"title":"Glaucus: A Complex-Valued Radio Signal Autoencoder","authors":"Kyle Logue","doi":"10.1109/AERO55745.2023.10115599","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115599","url":null,"abstract":"A complex-valued autoencoder neural network ca-pable of compressing & denoising radio frequency signals with arbitrary model scaling is proposed. Complex-valued time sam-ples received with various impairments are encoded into an embedding vector, then decoded back into complex-valued time samples. The embedding and the related latent space allow search, comparison, and clustering of signals. Traditional signal processing tasks like specific emitter identification, geolocation, or ambiguity estimation can utilize multiple compressed embed-dings simultaneously. This paper demonstrates an autoencoder implementation capable of compression by a factor of 64 that is still resilient against RF channel impairments. The autoencoder allows individual scaling by network depth, width, and resolution or in a compound sense to target both embedded and data center deployments. The common building block is inspired by the fused inverted residual block (Fused-MBConv), popularized by EfficientNetV2 & MobileNetV3, but with kernel sizes more appropriate for time-series signal processing. A complex-valued PyTorch implementation is available along with a pre-trained model, at https://github.com/the-aerospace-corporation/glaucus.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"218 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":"134000500","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/AERO55745.2023.10115807
Viktor Langofer, Ralph Bayer, A. Kolb, Kaname Sasaki
The advent of exploring low-gravity environments gives the opportunity to land rovers on celestial bodies without any landing platform and perform manipulative tasks under mostly unknown conditions. In addition to common loads, for example vibration, operation and thermal loads, the rover will face also impact loads during touchdown. This circumstance re-quires additional mechanisms to protect exposed parts, like the legs and wheels of a rover. Previous research attaches the wheels to the rover body or the landing platform through cup-cone interfaces at the wheel hub, which leads to unfavorable force distribution at the wheel rim in certain load cases, especially if the wheel represents the first point of contact during touchdown. This paper gives a detailed description in the mechanical design and testing of the locomotion subsystem (LSS) of the Martian Moons eXploration (MMX) rover. As the rover will fall to the moon Phobos unprotected and without any landing platform, the exposed locomotion subsystem has a high probability of being the initial contact point at touchdown. Besides the driv-etrains and thermal hardware, a novel hold down and release mechanism (HDRM) will be introduced as an integral part of the locomotion subsystem. The HDRM is realized using three support structures at the wheel rim and one fixation in the wheel axis. In this way, the exposed locomotion subsystem will be stabilized in described load cases, since each support structure forms a closed kinematic loop with the wheel and the central fixation in stowed configuration. This approach leads to vibration and impact resistant behavior.
{"title":"MMX Locomotion Subsystem: mechanics for extraterrestrial low gravity drive","authors":"Viktor Langofer, Ralph Bayer, A. Kolb, Kaname Sasaki","doi":"10.1109/AERO55745.2023.10115807","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115807","url":null,"abstract":"The advent of exploring low-gravity environments gives the opportunity to land rovers on celestial bodies without any landing platform and perform manipulative tasks under mostly unknown conditions. In addition to common loads, for example vibration, operation and thermal loads, the rover will face also impact loads during touchdown. This circumstance re-quires additional mechanisms to protect exposed parts, like the legs and wheels of a rover. Previous research attaches the wheels to the rover body or the landing platform through cup-cone interfaces at the wheel hub, which leads to unfavorable force distribution at the wheel rim in certain load cases, especially if the wheel represents the first point of contact during touchdown. This paper gives a detailed description in the mechanical design and testing of the locomotion subsystem (LSS) of the Martian Moons eXploration (MMX) rover. As the rover will fall to the moon Phobos unprotected and without any landing platform, the exposed locomotion subsystem has a high probability of being the initial contact point at touchdown. Besides the driv-etrains and thermal hardware, a novel hold down and release mechanism (HDRM) will be introduced as an integral part of the locomotion subsystem. The HDRM is realized using three support structures at the wheel rim and one fixation in the wheel axis. In this way, the exposed locomotion subsystem will be stabilized in described load cases, since each support structure forms a closed kinematic loop with the wheel and the central fixation in stowed configuration. This approach leads to vibration and impact resistant behavior.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"130 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":"132210165","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/AERO55745.2023.10115733
Daniel Muradás, F. Nieto, S. Hernández
The last years have witnessed a number of initiatives aimed to generate feasible designs of aircraft able to fly above the speed of sound. Some correspond to projects in the USA, and others are being developed in Europe, with prototypes designed for missions reaching up to Mach 8 speed. Hypersonic Test Bed (HTB) vehicles are an important part in the definition of new supersonic aircraft as they allow to study geometries, propulsion systems and mission performance, among other considerations, that are of utmost importance in aircraft design. This work addresses the research done adopting a HTB prototype of a vehicle aimed to fly up to Mach 5, with a propulsion system consisting of an experimental air-breathing engine situated on the top of the fuselage, and a rear rocket. The main dimensions of the considered aircraft are the following: a total length of 24.53 m, and a wing span of 8.89 m. The work carried out included high-fidelity CFD simulations using RANS techniques, aimed to identify the aerodynamic characteristics and generate a database that contains the relevant properties along a complete mission. The special configuration of the aircraft required previous studies in order to identify the proper boundary conditions at the inlet and outlet of the air-breathing engine. They included pressure value and mass flow conditions. That issue required a campaign of preliminary simulations using 2D and 3D models that helped in identifying the solution to the problems. Afterwards, the computer simulations were worked out using 3D conformal meshes with more than 15 million polyhedral elements. In the numerical models, compressible fluid was considered, as well as the two-equation $k$ - $w$ SST turbulence model. Special care was taken in the definition of the boundary layer mesh in the most sensitive locations of the geometry. The CFD simulations required relevant computing resources, so the calculations were completed in a HPC cluster, using 64 cores and allocating 180 GB of RAM memory for each run. The study provided the aerodynamic properties of the HTB for a range of aircraft speeds from Mach 0.4 to Mach 2.0.
{"title":"CFD Simulations of an Experimental Hypersonic Test Bed Aircraft in Subsonic and Supersonic Regime","authors":"Daniel Muradás, F. Nieto, S. Hernández","doi":"10.1109/AERO55745.2023.10115733","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115733","url":null,"abstract":"The last years have witnessed a number of initiatives aimed to generate feasible designs of aircraft able to fly above the speed of sound. Some correspond to projects in the USA, and others are being developed in Europe, with prototypes designed for missions reaching up to Mach 8 speed. Hypersonic Test Bed (HTB) vehicles are an important part in the definition of new supersonic aircraft as they allow to study geometries, propulsion systems and mission performance, among other considerations, that are of utmost importance in aircraft design. This work addresses the research done adopting a HTB prototype of a vehicle aimed to fly up to Mach 5, with a propulsion system consisting of an experimental air-breathing engine situated on the top of the fuselage, and a rear rocket. The main dimensions of the considered aircraft are the following: a total length of 24.53 m, and a wing span of 8.89 m. The work carried out included high-fidelity CFD simulations using RANS techniques, aimed to identify the aerodynamic characteristics and generate a database that contains the relevant properties along a complete mission. The special configuration of the aircraft required previous studies in order to identify the proper boundary conditions at the inlet and outlet of the air-breathing engine. They included pressure value and mass flow conditions. That issue required a campaign of preliminary simulations using 2D and 3D models that helped in identifying the solution to the problems. Afterwards, the computer simulations were worked out using 3D conformal meshes with more than 15 million polyhedral elements. In the numerical models, compressible fluid was considered, as well as the two-equation $k$ - $w$ SST turbulence model. Special care was taken in the definition of the boundary layer mesh in the most sensitive locations of the geometry. The CFD simulations required relevant computing resources, so the calculations were completed in a HPC cluster, using 64 cores and allocating 180 GB of RAM memory for each run. The study provided the aerodynamic properties of the HTB for a range of aircraft speeds from Mach 0.4 to Mach 2.0.","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":"134201183","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/AERO55745.2023.10115694
Patrick D. Maley, Alan M. Hubbard, Jude M. Urban, L. Hook
General aviation, the mode of air travel typified by small personal aircraft, accounts for roughly 19 of every 20 fatalities every year in the US. However, recent technological solutions are becoming available which may bring the total number of fatalities in general aviation down considerably. Potentially the most effective of these solutions is the Ground Collision Avoidance System or GCAS. GCAS avoids ground collision in a large number of cases: pilot error, disorientation, and temporary incapacitation. However, GCAS does not yet exist for general aviation, despite it being a field that would widely benefit from it's implementation. In response to this reality, GCAS development for general aviation has begun. This paper describes the design and verification of a GCAS controller on a simulated Cessna 172 aircraft. The GCAS controller provides the ability for the aircraft to automatically avoid ter-rain and is an important step in the initial phases of GCAS design. Considerations for the design of the controller's lateral and longitudinal axes are provided along with discussions on the overall controller structure. Controller modes and limiters have been designed and described to ensure safe operation of the controller, along with considerations for transient switching effects. Analysis of controller response along with verification of mode and limiter operation are provided. Finally, a comparison between the trajectory generated by the GCAS controller and one predicted by the GCAS system are included. With these sections, this paper provides important considerations on the initial stages of GCAS design for general aviation, and the beginning of safety assurance for GA.
{"title":"Recovery Autopilot Analysis for a General Aviation Ground Collision Avoidance System","authors":"Patrick D. Maley, Alan M. Hubbard, Jude M. Urban, L. Hook","doi":"10.1109/AERO55745.2023.10115694","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115694","url":null,"abstract":"General aviation, the mode of air travel typified by small personal aircraft, accounts for roughly 19 of every 20 fatalities every year in the US. However, recent technological solutions are becoming available which may bring the total number of fatalities in general aviation down considerably. Potentially the most effective of these solutions is the Ground Collision Avoidance System or GCAS. GCAS avoids ground collision in a large number of cases: pilot error, disorientation, and temporary incapacitation. However, GCAS does not yet exist for general aviation, despite it being a field that would widely benefit from it's implementation. In response to this reality, GCAS development for general aviation has begun. This paper describes the design and verification of a GCAS controller on a simulated Cessna 172 aircraft. The GCAS controller provides the ability for the aircraft to automatically avoid ter-rain and is an important step in the initial phases of GCAS design. Considerations for the design of the controller's lateral and longitudinal axes are provided along with discussions on the overall controller structure. Controller modes and limiters have been designed and described to ensure safe operation of the controller, along with considerations for transient switching effects. Analysis of controller response along with verification of mode and limiter operation are provided. Finally, a comparison between the trajectory generated by the GCAS controller and one predicted by the GCAS system are included. With these sections, this paper provides important considerations on the initial stages of GCAS design for general aviation, and the beginning of safety assurance for GA.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"195 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":"134312088","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/AERO55745.2023.10115660
J. Velazco
This paper discusses the development of an omnidirectional optical terminal (OOT) that will provide fast connectivity and navigation information to small spacecraft forming a swarm or a constellation in cislunar space. The cislunar OOT operates at 1550nm, employs a dodecahedron body holding 6 optical telescopes and 20 external arrays of detectors for angle-of-arrival determination. The cislunar OOT will provide full sky (4π steradian) coverage and gigabit connectivity among smallsats forming a swarm or constellation (e.g., LunaNet). The OOT will also provide continuous positional information among these spacecraft including bearing, elevation, and range. We also envision the OOT to provide fast low-latency connectivity to assets on the surface of the moon such as landers, rovers, instruments, and astronauts. In this paper we will present results of a thorough study of the cislunar OOT architecture including key factors that affect angular accuracy and available ranging techniques suitable for accurate range calculation. We also present design details that will lead to successful OOT prototype construction and testing. We believe that, once fully developed, the OOT will provide commercial, high data rate connectivity and navigation to future scientific, military, and commercial missions around cislunar space and beyond.
{"title":"Cislunar Omnidirectional Optical Terminal for Fast Connectivity and Accurate Navigation","authors":"J. Velazco","doi":"10.1109/AERO55745.2023.10115660","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115660","url":null,"abstract":"This paper discusses the development of an omnidirectional optical terminal (OOT) that will provide fast connectivity and navigation information to small spacecraft forming a swarm or a constellation in cislunar space. The cislunar OOT operates at 1550nm, employs a dodecahedron body holding 6 optical telescopes and 20 external arrays of detectors for angle-of-arrival determination. The cislunar OOT will provide full sky (4π steradian) coverage and gigabit connectivity among smallsats forming a swarm or constellation (e.g., LunaNet). The OOT will also provide continuous positional information among these spacecraft including bearing, elevation, and range. We also envision the OOT to provide fast low-latency connectivity to assets on the surface of the moon such as landers, rovers, instruments, and astronauts. In this paper we will present results of a thorough study of the cislunar OOT architecture including key factors that affect angular accuracy and available ranging techniques suitable for accurate range calculation. We also present design details that will lead to successful OOT prototype construction and testing. We believe that, once fully developed, the OOT will provide commercial, high data rate connectivity and navigation to future scientific, military, and commercial missions around cislunar space and beyond.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"584 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":"134189913","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/AERO55745.2023.10115586
Hrudayavani S Vellore, R. Galvan-Garza, A. Diaz-Artiles
Future human aerospace systems will consist of a complex integration of multiple technologies, including Artificial Intelligence (AI) driven autonomy. We expect autonomous systems to support and augment human performance, especially when humans are experiencing physiological or cognitive decrements in operational scenarios. To accomplish this, we need the ability to identify these human performance decrements in different individuals and in different mission contexts (e.g., varying g-levels, acceleration profiles). Factors such as sex, weight, and height can alter physiological response to various stressors. Therefore, accounting for these differences is essential to build effective autonomous systems in these operational contexts. Computational models and algorithms that drive our human assessment systems are rooted in theory but also need realistic data for testing and evaluation. While there is a basic understanding of expected changes in physiology under varying stressors, available data are largely lab-based and sparse. However, experimentally determining the response of each individual in a large variety of mission contexts is prohibitively expensive and time-consuming. Thus, future human assessment algorithm development efforts would substantially benefit from simulated, representative datasets created through configurable human models. We will build on prior cardiovascular, metabolic, and other modeling work to create a physiological model tailorable to specific operational mission contexts and personalized input parameters. In particular, we have implemented a 21-compartment lumped-parameter model to simulate physiological responses of a 50th percentile female and a 50th percentile male during a parabolic flight maneuver. The modeled individuals were differentiated by anthropometric and total blood volume data based on U.S. Army personnel. Results of the simulations highlight and quantify the differences in physiological responses between the two individuals when exposed to the same parabolic fight maneuver. Differences between the male and female models were greatest during hypergravity for almost all parameters except for Stroke Volume (SV), which presented the greatest differences between the two individuals during the transition between hypergravity and 1g. Our preliminary modeling effort demonstrates that differences exist in the cardiovascular response between two simulated, anthropometrically different individuals during a parabolic flight maneuver. In addition, those physiological differences are dependent on the magnitude of the gravity level. These results support and further justify the need for individualized modeling.
{"title":"Computational Modeling of Individual Differences in Cardiovascular Response during Parabolic Flight","authors":"Hrudayavani S Vellore, R. Galvan-Garza, A. Diaz-Artiles","doi":"10.1109/AERO55745.2023.10115586","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115586","url":null,"abstract":"Future human aerospace systems will consist of a complex integration of multiple technologies, including Artificial Intelligence (AI) driven autonomy. We expect autonomous systems to support and augment human performance, especially when humans are experiencing physiological or cognitive decrements in operational scenarios. To accomplish this, we need the ability to identify these human performance decrements in different individuals and in different mission contexts (e.g., varying g-levels, acceleration profiles). Factors such as sex, weight, and height can alter physiological response to various stressors. Therefore, accounting for these differences is essential to build effective autonomous systems in these operational contexts. Computational models and algorithms that drive our human assessment systems are rooted in theory but also need realistic data for testing and evaluation. While there is a basic understanding of expected changes in physiology under varying stressors, available data are largely lab-based and sparse. However, experimentally determining the response of each individual in a large variety of mission contexts is prohibitively expensive and time-consuming. Thus, future human assessment algorithm development efforts would substantially benefit from simulated, representative datasets created through configurable human models. We will build on prior cardiovascular, metabolic, and other modeling work to create a physiological model tailorable to specific operational mission contexts and personalized input parameters. In particular, we have implemented a 21-compartment lumped-parameter model to simulate physiological responses of a 50th percentile female and a 50th percentile male during a parabolic flight maneuver. The modeled individuals were differentiated by anthropometric and total blood volume data based on U.S. Army personnel. Results of the simulations highlight and quantify the differences in physiological responses between the two individuals when exposed to the same parabolic fight maneuver. Differences between the male and female models were greatest during hypergravity for almost all parameters except for Stroke Volume (SV), which presented the greatest differences between the two individuals during the transition between hypergravity and 1g. Our preliminary modeling effort demonstrates that differences exist in the cardiovascular response between two simulated, anthropometrically different individuals during a parabolic flight maneuver. In addition, those physiological differences are dependent on the magnitude of the gravity level. These results support and further justify the need for individualized modeling.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"35 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":"133104191","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/AERO55745.2023.10115561
A. Aziz, Shawki A. Saad, M. Mostafa, Ahmed S. Shalaby
In multitarget tracking, measurement correlation uncertainty occurs when remote sensors, such as radars, yield measurements whose origin is uncertain. Using incorrect measurements in multitarget tracking systems leads to tracks loss. In such cases, efficient measurement correlation methods are needed to select measurements from many to be used to update the target tracks of interest in the tracking systems. This paper proposes a measurement correlation approach for multitarget tracking in a noisy environment. In this approach, measurements-to-targets correlation is computed across all targets and measurements based on minimization of weighted total squared errors. For a given track, the measurement that has the maximum correlation is used for updating the target track. The proposed correlation approach is applied to a scenario of multitarget tracking system and performance comparison with other correlation approaches is also presented. The results showed that performance improvement in terms of correct measurements correlation is achieved.
{"title":"A Measurement Correlation Approach for Multitarget Tracking in a Noisy Environment","authors":"A. Aziz, Shawki A. Saad, M. Mostafa, Ahmed S. Shalaby","doi":"10.1109/AERO55745.2023.10115561","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115561","url":null,"abstract":"In multitarget tracking, measurement correlation uncertainty occurs when remote sensors, such as radars, yield measurements whose origin is uncertain. Using incorrect measurements in multitarget tracking systems leads to tracks loss. In such cases, efficient measurement correlation methods are needed to select measurements from many to be used to update the target tracks of interest in the tracking systems. This paper proposes a measurement correlation approach for multitarget tracking in a noisy environment. In this approach, measurements-to-targets correlation is computed across all targets and measurements based on minimization of weighted total squared errors. For a given track, the measurement that has the maximum correlation is used for updating the target track. The proposed correlation approach is applied to a scenario of multitarget tracking system and performance comparison with other correlation approaches is also presented. The results showed that performance improvement in terms of correct measurements correlation is achieved.","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":"134096370","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/AERO55745.2023.10115940
C. Whiting
The Next Generation Radioisotope Thermoelectric Generator (Next Gen RTG) is a project aimed at restarting production of the high performing General Purpose Heat Source (GPHS) RTG. Unfortunately, the performance of most GPHS-RTG missions is not expected to be representative of the Next Gen RTG. Heat sources used by the U.S. today are the slightly larger Step-2 GPHS module. This will reduce the amount of $^{238}mathbf{PuO_{2}}$ fuel that can fit within the RTG down to $boldsymbol{sim 3900mathrm{W}_{text{th}} (text{from}sim 4400 mathrm{W}_{text{th}})}$. This reduced thermal inventory will lower RTG temperatures, which will reduce performance. New Horizons is a current GPHS-RTG mission that was loaded with 3948 $mathbf{W}_{mathbf{th}}$ of $^{238}mathbf{PuO_{2}}$, suggesting that New Horizons performance may be similar to the future Next Gen RTG. The rate law analysis method has been successfully used to convert RTG telemetry into equations that describe behavior. A rate law analysis of New Horizons was used to determine the degree of thermoelectric degradation and thermal inventory losses. This analysis showed that the thermoelectric degradation mechanism on New Horizons changed after 8.0 years, and that this change in mechanism is likely tied to the thermal inventory of the fuel at that time. These equations were then used to produce a preliminary estimate the performance of the Next Gen RTG. Based on this estimate, Next Gen RTG will produce $boldsymbol{184 mathrm{W}_{e}}$ at the end-of-design-life (EODL) if the unit is not stored before launch, and $boldsymbol{177 mathrm{W}_{mathrm{e}}}$ if the unit is stored for 3 years before launch. Performance curves were also produced. It is important to realize that this preliminary estimate is based on a lot of assumptions, including: how the Step-2 module will affect performance, mission specific parameters, and potential changes to the Next Gen RTG as the design evolves. A discussion of these assumptions is provided. It may be necessary to update this estimate as additional Next Gen RTG design information becomes public.
{"title":"Estimating the Next Gen RTG Mod 1 Performance Based on Analysis of the New Horizons Mission","authors":"C. Whiting","doi":"10.1109/AERO55745.2023.10115940","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115940","url":null,"abstract":"The Next Generation Radioisotope Thermoelectric Generator (Next Gen RTG) is a project aimed at restarting production of the high performing General Purpose Heat Source (GPHS) RTG. Unfortunately, the performance of most GPHS-RTG missions is not expected to be representative of the Next Gen RTG. Heat sources used by the U.S. today are the slightly larger Step-2 GPHS module. This will reduce the amount of $^{238}mathbf{PuO_{2}}$ fuel that can fit within the RTG down to $boldsymbol{sim 3900mathrm{W}_{text{th}} (text{from}sim 4400 mathrm{W}_{text{th}})}$. This reduced thermal inventory will lower RTG temperatures, which will reduce performance. New Horizons is a current GPHS-RTG mission that was loaded with 3948 $mathbf{W}_{mathbf{th}}$ of $^{238}mathbf{PuO_{2}}$, suggesting that New Horizons performance may be similar to the future Next Gen RTG. The rate law analysis method has been successfully used to convert RTG telemetry into equations that describe behavior. A rate law analysis of New Horizons was used to determine the degree of thermoelectric degradation and thermal inventory losses. This analysis showed that the thermoelectric degradation mechanism on New Horizons changed after 8.0 years, and that this change in mechanism is likely tied to the thermal inventory of the fuel at that time. These equations were then used to produce a preliminary estimate the performance of the Next Gen RTG. Based on this estimate, Next Gen RTG will produce $boldsymbol{184 mathrm{W}_{e}}$ at the end-of-design-life (EODL) if the unit is not stored before launch, and $boldsymbol{177 mathrm{W}_{mathrm{e}}}$ if the unit is stored for 3 years before launch. Performance curves were also produced. It is important to realize that this preliminary estimate is based on a lot of assumptions, including: how the Step-2 module will affect performance, mission specific parameters, and potential changes to the Next Gen RTG as the design evolves. A discussion of these assumptions is provided. It may be necessary to update this estimate as additional Next Gen RTG design information becomes public.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"23 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":"125709887","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/AERO55745.2023.10115847
P. Banerjee, Evelyn Muschter, Harsimran Singh, Bernhard M. Weber, T. Hulin
Research and development of telerobotic systems supplemented by haptic feedback for future planetary exploration missions has gained significant importance in the past decade. Major space agencies endeavor to deploy such systems before sending humans to the surface of unknown or unexplored celestial bodies. Astronauts control these telerobotic systems from remote locations, such as an orbital space station. Haptic feedback for teleoperating the robots in outer space is extremely important, not only to improve user immersion and task performance, but also to improve our understanding of surface properties. At the same time, for spaceflight, making use of compact, light-weight and robust devices are preferred for precise tactile feedback from telemanipulation tasks. In this paper, we introduce “ViESTac”, a first attempt to develop a generic VR suite to be able to evaluate and compare fingertip-wearable tactile devices. Applications of such a suite include, but are not limited to allowing teleoperators to judiciously choose suitable tactile devices for a particular task. To account for the wide variety of existing fingertip-wearable tactile devices and their display capabilities, the suite contains a set of virtual scenarios to investigate different tactile properties of virtual objects. It also dedicates a virtual scenario to evaluate how tactile feedback may govern the accuracy of human positioning in standard tasks. This proposed suite is advocated by a pilot study with 13 participants and two distinct state-of-the-art tactile devices. Results of the study clearly indicate that the virtual suite can successfully cater to the need of evaluating and comparing fingertip-wearable tactile devices.
{"title":"Towards a VR Evaluation Suite for Tactile Displays in Telerobotic Space Missions","authors":"P. Banerjee, Evelyn Muschter, Harsimran Singh, Bernhard M. Weber, T. Hulin","doi":"10.1109/AERO55745.2023.10115847","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115847","url":null,"abstract":"Research and development of telerobotic systems supplemented by haptic feedback for future planetary exploration missions has gained significant importance in the past decade. Major space agencies endeavor to deploy such systems before sending humans to the surface of unknown or unexplored celestial bodies. Astronauts control these telerobotic systems from remote locations, such as an orbital space station. Haptic feedback for teleoperating the robots in outer space is extremely important, not only to improve user immersion and task performance, but also to improve our understanding of surface properties. At the same time, for spaceflight, making use of compact, light-weight and robust devices are preferred for precise tactile feedback from telemanipulation tasks. In this paper, we introduce “ViESTac”, a first attempt to develop a generic VR suite to be able to evaluate and compare fingertip-wearable tactile devices. Applications of such a suite include, but are not limited to allowing teleoperators to judiciously choose suitable tactile devices for a particular task. To account for the wide variety of existing fingertip-wearable tactile devices and their display capabilities, the suite contains a set of virtual scenarios to investigate different tactile properties of virtual objects. It also dedicates a virtual scenario to evaluate how tactile feedback may govern the accuracy of human positioning in standard tasks. This proposed suite is advocated by a pilot study with 13 participants and two distinct state-of-the-art tactile devices. Results of the study clearly indicate that the virtual suite can successfully cater to the need of evaluating and comparing fingertip-wearable tactile devices.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"54 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":"134155460","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/AERO55745.2023.10115650
R. K. Rangel, A. Maitelli, Joacy L. Freitas, Rhaclley F. de Araújo
This paper describes the development of a wireless Drone charge station, navigation and control methodology using Artificial Intelligence and Computer Vision, based on Commercial-Of-The-Shelf (COTS) equipment and a dedicated management software to “help” a single Drone or a swarm squadron operation in VLOS and BVLOS, over urban regions. The Concept of Smart Cities consider the Drone use for power line asset monitoring, homeland security, delivery of medicine and logistics, epidemiological control and environmental monitoring. Due the modular design of the aerial platform and the wireless charge station, the use of COTS equipment allows more flexibility in all processes and result in cost reduction as well as development process optimization, where the focus is on the system intearation. The wireless Drone charge station is a dedicated structure located at a strategic position within city limits, which is able to be used as communication relay, and to charge the Drones automatically via wireless, according the mission scope, increasing the Drone operation range over urban region. The sensors inside the wireless Drone charge station are loT devices for the collection of meteorological data, images, command / control Drones and data from the other Stations, through a dedicated Command and Control Situation Room. By utilizing a dedicated management software at the Situation room - called by SIGI software - the system can control the drone and the airspace, collect field data from sensors and process them in real time. The situational analysis makes it possible to the administrator to optimize resources (material and human) by improving the efficiency of resource allocation in these areas while providing the real time situational awareness. The Drone design is a quadcopter with Embedded Artificial Intelligence and Computer Vision, defined as mission board, totally integrated with autopilot board and navigation sensors. A.I. and Computer vision are used to increase the Drone navigation precision, without a GPS-RTK/PPK device. In terms of mission requirements or customization, the Drone recognizes patterns and makes decisions according to each operational scope, e.g., visual identification of wireless charge stations, mosquito outbreaks, power lines assets in need of maintenance, swarm control for area saturation mapping and others. As described, this system focuses on a new concept of Smart Cities, the Drones as a Service Tool, to be employed in urban regions, helping the population in air mobility.
{"title":"Smart Drone, Wireless Charge Station and Management System applied to air mobility","authors":"R. K. Rangel, A. Maitelli, Joacy L. Freitas, Rhaclley F. de Araújo","doi":"10.1109/AERO55745.2023.10115650","DOIUrl":"https://doi.org/10.1109/AERO55745.2023.10115650","url":null,"abstract":"This paper describes the development of a wireless Drone charge station, navigation and control methodology using Artificial Intelligence and Computer Vision, based on Commercial-Of-The-Shelf (COTS) equipment and a dedicated management software to “help” a single Drone or a swarm squadron operation in VLOS and BVLOS, over urban regions. The Concept of Smart Cities consider the Drone use for power line asset monitoring, homeland security, delivery of medicine and logistics, epidemiological control and environmental monitoring. Due the modular design of the aerial platform and the wireless charge station, the use of COTS equipment allows more flexibility in all processes and result in cost reduction as well as development process optimization, where the focus is on the system intearation. The wireless Drone charge station is a dedicated structure located at a strategic position within city limits, which is able to be used as communication relay, and to charge the Drones automatically via wireless, according the mission scope, increasing the Drone operation range over urban region. The sensors inside the wireless Drone charge station are loT devices for the collection of meteorological data, images, command / control Drones and data from the other Stations, through a dedicated Command and Control Situation Room. By utilizing a dedicated management software at the Situation room - called by SIGI software - the system can control the drone and the airspace, collect field data from sensors and process them in real time. The situational analysis makes it possible to the administrator to optimize resources (material and human) by improving the efficiency of resource allocation in these areas while providing the real time situational awareness. The Drone design is a quadcopter with Embedded Artificial Intelligence and Computer Vision, defined as mission board, totally integrated with autopilot board and navigation sensors. A.I. and Computer vision are used to increase the Drone navigation precision, without a GPS-RTK/PPK device. In terms of mission requirements or customization, the Drone recognizes patterns and makes decisions according to each operational scope, e.g., visual identification of wireless charge stations, mosquito outbreaks, power lines assets in need of maintenance, swarm control for area saturation mapping and others. As described, this system focuses on a new concept of Smart Cities, the Drones as a Service Tool, to be employed in urban regions, helping the population in air mobility.","PeriodicalId":344285,"journal":{"name":"2023 IEEE Aerospace Conference","volume":"12 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":"134072868","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}
京公网安备 11010802042870号
京ICP备2023020795号-1
扫码关注我们
求助内容：
应助结果提醒方式：