2022 IEEE Aerospace Conference (AERO)最新文献

{"title":"Satellite High-Speed On-Board Data Handling: From a Wizardlink Equivalent Transceiver To a Full SpaceFibre Interface","authors":"P. Nannipieri, L. Fanucci, Gainmarco Dinelli, Luca Dello Sterpaio, Antonino Marino","doi":"10.1109/AERO53065.2022.9843395","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843395","url":null,"abstract":"In the last few years, satellite onboard data-handling bandwidth requirements grew significantly. State-of-the-art solutions, like Space Wire, became not always adequate for up-coming missions: this led to the birth of a significant number of communication protocols and standards, with different features, advantages, and disadvantages. The European Space Agency promoted the development of an open protocol solution: Space-Fibre, whose European Cooperation for Space Standardization standard has been published in May 2019, after an extensive review process. It represents a major advancement as a resulting effort to address the requirements for space missions of the present and the next future. The SpaceFibre protocol can sus-tain a line rate of 6.25 Gbps per lane (up to 16 lanes in parallel). It offers advanced and flexible Quality-of-Service features, as well as Fault Detection Isolation and Recovery services. The pro-tocol structure, comprehending physical, lane, multi-lane, data-link and network layers, has been developed so that full hard-ware implementation of its core layers is straightforward, granting high performances at low price in terms of complexity and power consumption. However, all these features, which make SpaceFibre a solid and powerful solution for future missions, are not always required by smaller lower budget satellites. Indeed, some systems may need only streaming-type CoDecs, without the necessity for advanced error recovery or quality of service. In this paper, we introduce three different designs that address the high-speed requirements of future satellites, gradually intro-ducing more features: a Wizardlink equivalent system, which emulates the behaviour of the well-established Texas Instrument TLK2711 transceiver on an FPGA, providing only low-lane layer features (Encoding, symbol synchronization) and leaving the rest of the layer specifications to the user; a reduced features SpaceFibre CoDec, which is fully compatible with standard-compliant SpaceFibre implementation but largely reduces error recovery features, to obtain a much smaller device; a fully standard-compliant SpaceFibre CoDec. These solutions are all implemented on various FPGA technologies and compared in terms of features and performances, to provide satellite system engineers with a valid reference to better understand which solution could better address their high-speed onboard commu-nication requirements.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"38 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130471233","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}

{"title":"MBSE Utilization for Additive Manufactured Rocket Propulsion Components","authors":"Shreyas Lakshmipuram Raghu, Mason Tudor, L. Thomas, Gang Wang","doi":"10.1109/AERO53065.2022.9843586","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843586","url":null,"abstract":"Model Based Systems Engineering (MBSE) has garnered increased utilization among various NASA's spaceflight programs such as the Human-to-Mars In-Situ Resource Utilization (ISRU) and Cis-Lunar Habitat architectures, Commercial Crew Program (CCP), and Space Launch System (SLS). Recently, MBSE has also helped support NASA's Design-for-Reliability (DFR) and Mission Assurance activities. The utilization of MBSE helps visualize the development of the overall system in a digital environment. For the development of rocket propulsion systems, leveraging MBSE helps find ways to achieve reduction in costs, schedule, and risk throughout its life-cycle in a comprehensive and a cohesive manner. In order to deliver affordability in the competitive space race environment, it is important to reap the benefit of newer manufacturing technologies such as Additive Manufacturing (AM). In development of rocket propulsion systems, AM provides new design and performance opportunities for the rocket engine designs that is often complex. The fundamental advantage of an additively manufactured rocket propulsion element is the reduction in lead time and cost against traditional production techniques. AM designs help realize complex shapes and geometries that are often challenging and expensive to be produced using traditional production methodologies. In the context of a development of rocket propulsion system, AM provides the technological opportunity to realize newer engine designs that are technically and economically feasible. Significant efforts such as NASA's Additive Manufacturing Demonstrator Engine (AMDE) employ additive manufacturing in production of rocket propulsion engines. On the other hand, MBSE provides the ability to visualize the impact of a design change in a digital environment. Consequently, the objective of this study is to evaluate the benefits of leveraging MBSE suited to the context of additive manufactured rocket propulsion elements. A literature review is performed for the current state-of-the-art of additive manufactured rocket propulsion elements and potential opportunities to leverage MBSE has been identified. Furthermore, a design example (RS-25 or Space Shuttle Main Engine) has been explored to demonstrate the benefits of the research idea in this study. The choice of the design example is driven by the need to restart production of the engine for NASA's future launch manifests. Finally, the results of this study have been assessed qualitatively within the scope of reducing the time in Test-Fail-Fix (redesign, remanufacturing, retest, and recertification) cycle of the engine.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"45 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134604543","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}

{"title":"How to Build a Rover: An Overview of the Mars 2020 Mission's Vehicle System Testbed","authors":"Christopher S. R. Matthes, Matthew Stumbo, J. Foley, Terence Dang, Jose Trujillo Rojas","doi":"10.1109/AERO53065.2022.9843658","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843658","url":null,"abstract":"While NASA's Mars rover Perseverance continues to make groundbreaking achievements on the Red Planet, its twin is hard at work here on Earth. The Operational Perseverance Twin for the Integration of Mechanisms and Instruments Sent to Mars, or OPTIMISM, is the Mars 2020 Vehicle System Testbed (VSTB) rover operated by NASA Jet Propulsion Laboratory (JPL) in Pasadena, California. OPTIMISM's home is the JPL Mars Yard; an outdoor field with red soil that simulates the terrain encountered by Perseverance. The VSTB is a full-scale engineering model of the flight rover, serving a number of functions to ensure mission operations can continue smoothly and on schedule. The VSTB possesses instrumentation, computers, mechanisms, cameras, and a Mobility subsystem that are nearly identical to its extraterrestrial twin. Its high fidelity allows the rover to be a highly effective tool to fully test system functionality and performance prior to commanding the flight rover. The early stages of building OPTIMISM began a few months prior to Perseverance departing JPL for Cape Canaveral, FL in early 2020. Electrical integration of the flight system avionics, and compatibility checkouts of the electrical ground support equipment ensured that the foundation of the electrical system was operational and in place. Next, the internal harnessing was installed and compatibility checks of the rover instrumentation and mechanisms were performed to confirm the system was prepared for full buildup. Finally, mechanical assembly of the rover chassis with its external components completed the integration of the system before it was moved to the Mars Yard for its initial phase of testing to perform verification & validation (V&V) of the Mobility subsystem requirements. By the time Perseverance landed at Jezero Crater in February 2021, the first phase of VSTB operations was underway. Surface guidance, navigation, and control (SGNC) testing for the Mobility subsystem ensured functionality and performance requirements were met for various capabilities such as visual odometry (VO), mapping, and automatic navigation (AutoNav). Subsequent integration of the robotic arm (RA) onto the VSTB enabled the V&V campaign for surface sampling operations (SSO) to commence. As the mission's engineering operations (EO) have gotten underway, the VSTB has been utilized for an array of purposes including troubleshooting software anomalies, and performing dry-runs for first time activities (FTAs) prior to sending the commands to Perseverance. OPTIMISM will continue to serve mission critical functions as long as Perseverance is roving the Red Planet.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131528195","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}

{"title":"Dependency of Surface Temperature on Coolant Mass Flow and Heat Flux in Rocket Combustion Chambers","authors":"P. H. Kringe, Chris Bürger, J. Riccius, Evgeny B. Zametaev, M. Oschwald, Andreas Gernoth, S. Soller, Marcus Lehmann, S. Reese","doi":"10.1109/AERO53065.2022.9843694","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843694","url":null,"abstract":"This paper presents the simulation and experimental results of the dependency of the surface temperature of a heat transfer test (HTT) panel representing liquid rocket engine combustion chamber geometry on the coolant mass flow rate and heat flow rate. The HTT panel is made of a high-conductivity copper material. This material is appropriate for the inner liner of lowly loaded regeneratively cooled combustion chambers like upper stages. In the experimental setup the HTT panel uses only a small section of the actual combustion chamber geometry, typically five cooling channels. The panel is heated by a high power diode laser providing realistic amounts of heat flux. For safety and cost reasons supercritical nitrogen is used as coolant instead of hydrogen or methane. Within the experiment different combinations of surface temperature, heat flux and mass flow rate were examined, in total 24 different test conditions. Subsequently a coupled steady state thermal fluid-structure-interaction analysis was conducted in ANSYS and validated with the experimental data. ANSYS CFX was used to analyze the nitrogen coolant fluid flow with a Shear Stress Turbulence (SST) model. ANSYS Mechanical was used for the thermal finite element analysis. The relevant thermophysical parameters like heat conductivity, diffusivity and heat capacity were measured for temperatures above 273 K. For lower temperatures these parameters were determined theoretically. The results gained in this study will be used for the accurate modeling of the heat transfer in a thermomechanical fatigue life analysis by adding a dedicated structural Finite Element (FE) Analysis in ANSYS Mechanical. The accurate modeling of thermomechanical fatigue is particularly important for reusability of rocket engines. Furthermore the results of the validated numerical simulation are useful for the estimation of heat transfer in new developments of liquid rocket engines, particularly upper stages.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"10 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131580508","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}

{"title":"Feedback-Directed Random Sequence Generation for Verifying Spacecraft Flight Rule Violations","authors":"Shubhodeep Mukherji, Shaheer A. Khan, Vicken Voskanian, Laura Su","doi":"10.1109/AERO53065.2022.9843780","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843780","url":null,"abstract":"The Psyche: Journey to a Metal World mission will be launched in 2022 to study the largest metal asteroid in the main asteroid belt, (16) Psyche. The spacecraft will perform a Mars Flyby in 2023 and enter (16) Psyche's orbit in 2026. Throughout the mission, safely operating the spacecraft will require abiding by a set of flight rules that can be defined at any point in the mission lifecycle. These flight rules ensure that the spacecraft is operating within allowed regimes and a discrete event simulation tool, SEQGEN, will be used to model all command sequences prior to uplink. One of SEQGEN's responsibilities is to determine if a command sequence violates any flight rules. For each flight rule, the necessary logic to determine if a violation has occurred is implemented in the SEQGEN adaptation, which is maintained by the mission. This adaptation must be tested thoroughly to ensure that the flight rule logic was interpreted and implemented correctly. This work describes a tool, RandSEQ, that autogenerates a suite of flight rule violating test sequences for each flight rule implemented in SEQGEN, and can be used by any mission using SEQGEN. The Psyche SEQGEN adaptation is still being developed, but so far, RandSEQ has been used to generate 532 test cases, that can be reviewed by various stakeholders, for 40 flight rules. The ability to autogenerate these test cases has significantly reduced the amount of time required to implement and test each flight rule.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"4 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132635602","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}

{"title":"Practical Interstellar Probe Concepts: Mission Study Results","authors":"J. Kinnison, Alice Corcoros, D. Napolillo, D. Mehoke, G. Rogers, F. Siddique, A. Haapala-Chalk, W. Schlei, D. Copeland, R. Ashtari","doi":"10.1109/AERO53065.2022.9843339","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843339","url":null,"abstract":"From the beginning of space exploration, humans have looked forward to escaping the solar system into interstellar space. As early as 1958, before NASA was established, mission concepts for an Interstellar Probe have been proposed. None have been attempted, mainly because the technologies required to do this mission have not been developed. However, with the development of the Space Launch System (SLS), the main difficulty - how to launch a system with the necessary speed to reach interstellar space in a reasonable time - has been addressed. In 2018, NASA asked The Johns Hopkins University Applied Physics Laboratory to develop a practical near-term mission concept that could finally achieve the goal of exploring interstellar space. In this study, we have identified three classes of trajectories that could achieve an escape speed of greater than 7 Astronomical Units (AU)/year, about twice the speed of the Voyager spacecraft which allows for transit into interstellar space well within a 50-year mission lifetime. These trajectory classes are: (i) launch on SLS with solid rocket motor upper stage followed by a ballistic Jupiter gravity assist, (ii) SLS launch followed by a powered Jupiter gravity assist (JGA) using a solid-rocket motor fired at Jupiter, and (iii) SLS launch followed by a JGA to target a deep dive into the Sun's gravity well for a Solar Oberth Maneuver (SOM) to achieve escape velocity. Each of these trajectory classes imposes significant requirements on the launch vehicle and spacecraft, and represents increasing levels of risk and difficulty. The powered JGA trajectory class would require carrying a large solid rocket motor to Jupiter such that it can successfully fire during the Jupiter flyby, which imposes requirements on thermal control of the system, as well as the ability to target the flyby accurately with a significantly larger flight system than for the unpowered JGA option. The SOM trajectory option imposes even more difficult requirements on the flight system, given that the maneuver requires a closest approach of 3–4 solar radii (Rs) to achieve a significant escape speed. This perihelion is well beyond that planned for Parker Solar Probe, and will require a heat shield capable of withstanding even higher temperatures than existing heat shields. Preliminary development work in this area has provided a potential path forward, which we have used to develop a heat shield design that can be employed to study whether such a mission is possible, the constraints and requirements on the flight system, and risks associated with an SOM mission concept. In this work, we present the three trajectory classes and associated example flight system configurations. We compare two example mission concepts along with science goals for each one, discussing the advantages and risks of both. We conclude by identifying the mission concept that represents the best option for a practical Interstellar Probe.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131099290","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}

{"title":"Sheaf Theoretic Models for Routing in Delay Tolerant Networks","authors":"Robert Short, Alan Hylton, Jacob Cleveland, Michael Moy, R. Cardona, Robert Green, Justin Curry, B. Mallery, Gabriel Bainbridge, Zander Memon","doi":"10.1109/AERO53065.2022.9843504","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843504","url":null,"abstract":"One key to communications scalability is routing; as such the goal of this paper is to build upon successful efforts towards general routing for space-based networks. With the ever-increasing accessibility of space, the number of assets is increasing, which becomes a critical communications burden in terms of scheduling, spectrum allocation, and resource allocation. In order to mitigate these concerns, a true networking approach is necessary; a standard approach for space systems is Delay Tolerant Networking (DTN). For DTN to be a meaningful answer to the Solar System Internet (SSI) question, DTN must offer meaningful routing solutions that span the heterogeneous collection of links and nodes. This, in turn, depends on the general structure of these disconnected networks - a structure that remains largely unknown. In ground communications networks, routing decisions are made based on several pathfinding algorithms working in tandem. In previous work, we modeled Dijkstra's pathfinding algorithm using sheaves and provided a more general framework for determining paths using sheaves over graphs. Continuing our sheaf-theoretic approach, we introduce here an expansion of our pathfinding sheaf to handle more general information, and we expand on additional pathfinding algorithms that can be represented using sheaves. Moreover, we demonstrate means of combining multiple algorithms into a single sheaf structure so that changes of scale can be presented in the language of sheaves. In addition, space communications networks rely upon radio transmitter antennas which can establish broadcast and multicast communications options, rather than the primarily uni-cast options available to wired networks. Last year, we also introduced a multicast routing sheaf for presenting broadcast, unicast, and multicast communications over a graph. Extending that work, we also introduce queuing sheaves so that we can blend these communications options together to simulate a variety of routing options across space networks. In addition, we include examples to illustrate the applicability of this abstract theory to routing in disconnected networks.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"151 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132143283","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}

{"title":"Optimization of Conceptual Design of Air Breathing Hypersonic Vehicle","authors":"Kanishka Deepak, Aaditya U Wangikar, Chathura G R, Sanmukh Sharad Khadtare, Anagha G. Rao, Yatin Yogesh, M. M., Srisha Rao M V","doi":"10.1109/AERO53065.2022.9843693","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843693","url":null,"abstract":"In the past few years, many countries have invested their time and efforts in research of hypersonic flight to realize commercial and research benefits. This has led to a rocketing development in the domain of Hypersonic flow. More research is being done on the complexities present exclusively in hypersonic flow. These flow complexities when faced by hypersonic vehicles makes it very important to have increased performance for ensuring sustained and economic flight. Based on this, the paper focuses on obtaining optimized models of forebody waverider integrated Hypersonic vehicles for Mach number 6 and Dynamic pressure of 47.8 kPa at an altitude of 27 km using conventional hypersonic theories. The models are parameterized with respect to inlet height, inlet width and equivalence ratio and are further evaluated to obtain Specific impulse (Isp) and Lift to Drag ratio (L/D) as objective parameters. To account for tradeoffs and computational cost, the multi-objective optimization process is performed using Non-dominated Sorting Genetic Algorithm (NSGA) with Artificial Neural Network (ANN) as a surrogate model. Subsequently, the optimized solutions are obtained in the form of pareto front and were later evaluated for stability and steady state conditions. The results obtained give optimized stabilized vehicles and the methodology followed can be used to design hypersonic vehicles for commercial or research purposes based on desired mission requirements.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"35 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128896551","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}

{"title":"A Survey of Near-Earth Asteroids for Low-Thrust Round-Trip Missions","authors":"Ruida Xie, A. Dempster","doi":"10.1109/AERO53065.2022.9843463","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843463","url":null,"abstract":"The objective of this study is to perform a broad low thrust (LT) round-trip accessibility analysis for near-Earth asteroids (NEAs). The impulsive missions to NEAs have been investigated in several studies from various perspectives, while NEAs' low-thrust missions have not been properly investigated due to the complexity of LT trajectory design. A Deep Neural Network (DNN) classifier is constructed and trained to predict the feasibility of low thrust transfers between Earth and NEAs. This model has a prediction accuracy of 98%, and it is used for filtering out infeasible transfers and enhance the search efficiency. A Deep Neural Network (DNN) regressor is constructed and trained as the surrogate of the LT optimization process. The DNN-regressor outputs the spacecraft final mass with a prediction mean-relative error (MRE) of less than 1%. These two models are integrated into a grid search framework and enable efficient searches for LT journeys. For the given spacecraft configurations, 7% (1,684) of the 24,149 studied NEAs are LT round-trip accessible, and 95.4% of the LT accessible ones have minimum propellant mass fractions between 0.08 and 0.29. The identified LT accessible NEAs have inclinations less than 9 deg and eccentricities less than 0.4. Some asteroids, such as 2017 CF32, are found to be more accessible by the low-thrust propulsion option than the impulsive propulsion. The results of this study can be used as a reference for future low-thrust NEA mission target selection.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"137 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134463882","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}

{"title":"Reliable GNSS Joint Position and Attitude Estimation in Harsh Environments through Robust Statistics","authors":"Andrea Bellés, D. Medina, P. Chauchat, J. Vilà‐Valls","doi":"10.1109/AERO53065.2022.9843300","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843300","url":null,"abstract":"Next-generation navigation systems require precise and robust solutions, providing information about both the system position and its attitude, of particular interest in intelligent transportation systems and robotics applications. Within this context, Global Navigation Satellite Systems (GNSS) are the main source of positioning data and, in multiple antenna setups, can also provide attitude information. Notice that the use of phase observables is mandatory to obtain a precise solution. In this contribution, we leverage the recently introduced recursive GNSS joint position and attitude (JPA) estimation framework, which has been shown to provide good performance under nominal conditions. The main goal is to further elaborate the JPA problem and to propose a new robust filtering solution able to mitigate the impact of possible outliers, which may otherwise cause a performance breakdown of standard JPA, because of the sensitivity of carrier phase measurements. Illustrative results are provided to support the discussion and show the performance improvement of the proposed approach.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"30 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131400000","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}