2022 IEEE Aerospace Conference (AERO)最新文献

{"title":"Applying MBSE to Data Handling System Design of a Small Satellite Platform for Multiple Missions","authors":"T. Firchau, Michael Jetzschmann, F. Nohka","doi":"10.1109/AERO53065.2022.9843471","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843471","url":null,"abstract":"Model-based approaches to system design become more and more established in the space domain, as they promise to increase efficiency and reliability of the design process. This paper presents initial experience in adopting a model-based approach to the systems engineering of the data handling system for a small satellite platform. The goal was to increase engineering efficiency in order to allow the design of two variants of a system to address two different missions in parallel, but with the same team strength. The scope of the paper covers the definition of the MBSE methodology to use and its application to the preliminary design of the data handling system.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"29 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":"126308428","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":"Metrics for Flight Operations: Application to Europa Clipper Tour Selection","authors":"D. Bindschadler, Nari Hwangpo, M. Sarrel","doi":"10.1109/AERO53065.2022.9843410","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843410","url":null,"abstract":"Objective measures are ubiquitous in the formulation, design and implementation of deep space missions. Tour durations, flyby altitudes, propellant budgets, power consumption, and other metrics are essential to developing and managing NASA missions. But beyond the simple metrics of cost and workforce, it has been difficult to identify objective, quantitative measures that assist in evaluating choices made during formulation or implementation phases in terms of their impact on flight operations. As part of the development of the Europa Clipper Mission system, a set of operations metrics have been defined along with the necessary design information and software tooling to calculate them. We have applied these methods and metrics to help assess the impact to the flight team on the six options for the Clipper Tour that are currently being vetted for selection in the fall of 2021. To generate these metrics, the Clipper MOS team first designed the set of essential processes by which flight operations will be conducted, using a standard approach and template to identify (among other aspects) timelines for each process, along with their time constraints (e.g., uplinks for sequence execution). Each of the resulting 50 processes is documented in a common format and concurred by stakeholders. Process timelines were converted into generic schedules and workforce-loaded using COTS scheduling software, based on the inputs of the process authors and domain experts. Custom code was generated to create an operations schedule for a specific portion of Clipper's prime mission, with instances of a given process scheduled based on specific timing rules (e.g., process X starts once per week on Thursdays) or relative to mission events (e.g., sequence generation process begins on a Monday, at least three weeks before each Europa closest approach). Over a 5-month period, and for each of six Clipper candidate tours, the result was a 20,000+ line, workforce-loaded schedule that documents all of the process-driven work effort at the level of individual roles, along with a significant portion of the level-of-effort work. Post-processing code calculated the absolute and relative number of work hours during a nominal 5 day / 40 hour work week, the work effort during 2nd and 3rd shift, as well as 1st shift on weekends. The resultant schedules and shift tables were used to generate objective measures that can be related to both human factors and to operational risk and showed that Clipper tours which utilize 6:1 resonant (21.25 day) orbits instead of 4:1 resonant (14.17 day) orbits during the first dozen or so Europa flybys are advantageous to flight operations. A similar approach can be extended to assist missions in more objective assessments of a number of mission issues and trades, including tour selection and spacecraft design for operability.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"27 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":"128127286","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":"Radar Back End for NASA/ISRO Synthetic Aperture Radar (NISAR) Instrument","authors":"M. Quddus, Brian Custodero, Barry Volain, Brandon Wang, S. Shaffer, Bruce Krohn, Nelson Huang, Ben Tsoi, Steve Tseng","doi":"10.1109/AERO53065.2022.9843519","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843519","url":null,"abstract":"In this paper we present design, manufacture and qualification of a Radar Back End (RBE) for NISAR Mission's Synthetic Aperture Radar (SAR) Instrument. The instrument uses Sweep SAR technique to generate high fidelity radar images while capturing an image over a large swath. It requires highly stable clocks to accomplish that. NISAR RBE is the heart of the L-band Synthetic Aperture Radar (LSAR) instrument. It generates radar's transmit chirp signals, ultra-stable clocks and oscillators signals. In order to generate ultra-stable clocks some novel filtering and frequency multiplication techniques were utilized. These techniques have been presented in this paper. NISAR mission requires over 200 chirps to perform science measurements. Hardware and firmware architecture utilized to generate chirps have been presented in this paper. Unique space qualified techniques for DC to DC conversion has been presented in this paper. In addition, RBE was designed to be block redundant space qualified assembly. Novel cross strapping techniques were implemented to achieve that. Validation and qualification process employed to certify RBE flight hardware for flight has been presented in this paper.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"26 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":"125659731","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":"First Results of Differential Doppler Positioning with Unknown Starlink Satellite Signals","authors":"M. Neinavaie, Z. Shadram, Sharbel E. Kozhaya, Zaher M. Kassas","doi":"10.1109/AERO53065.2022.9843493","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843493","url":null,"abstract":"This paper shows the first results of differential Doppler positioning with unknown low Earth orbit (LEO) Star-link satellite signals. To this end, a receiver capable of acquiring and tracking the Doppler frequency of Starlink satellites is developed. A sequential method is proposed to estimate the number of active Starlink satellites and their corresponding reference signals (RSs). The proposed method is based on the classic linear model, where it is shown that the classic linear model results in the so-called matched subspace detector. A closed form of the probability of false alarm in the presence of Doppler estimation error is derived. Next, a Doppler tracking algorithm is designed, which is based on the generalized likelihood ratio (GLR) detector. In order to compensate for the high dynamics of Starlink LEO satellites, a linear chirp model is employed in the Doppler tracking algorithm, and a Kalman filter (KF)-based tracking algorithm is designed to track the chirp parameters. To validate the proposed framework, experimental results are presented in which a base with a known position and a rover with an unknown position were equipped with the proposed receiver. Despite the unknown nature of Starlink satellite signals, it is shown that the proposed receiver is capable of acquiring three Starlink satellites and tracking their Doppler frequencies. Next, two baselines between the base and rover receivers were considered: 1 km and 9 m. Despite the fact that the satellites' ephemerides are poorly known (with errors on the order of several kilometersm since they are predicted from two-line element (TLE) files and an SGP4 propagator), the proposed differential framework was able to estimate the rover's two-dimensional position with an error of 5.6 m and 2.6 m, respectively.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"474 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":"126005788","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":"Improving Computational Efficiency of Prognostics Algorithms in Resource-Constrained Settings","authors":"K. Jarvis, C. Teubert, Wendy A. Okolo, Chetan S. Kulkarni","doi":"10.1109/AERO53065.2022.9843250","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843250","url":null,"abstract":"The field of prognostics and health management provides quantitative methods for monitoring and predicting the health of physical systems. Prognostic algorithms are useful in that they can be employed to assess the current state of a system, propagate the system state throughout time, and pre-dict potential anomalies or failures that may occur. However, effective prognosis can be challenging to achieve in resource-constrained settings due to computational limitations and high computational latency, leading to obsolete predictions. Thus, computationally efficient and accurate algorithms are necessary for some prognostics applications. In this work, we implement three new algorithmic approaches to prediction (sampling meth-ods, variable prediction time step, variable prediction sample size) with the goal of improving computational efficiency while minimizing decrease in model accuracy. To quantitatively an-alyze our results, we examine a use-case of degradation of a Lithium-ion battery. Notably, through this work it was found that none of the sampling approaches had a significant impact on computational efficiency or model accuracy in predicting EOD of the battery. However, our results show that prediction accuracy is highly dependent on the time step used, and that an appropriate time step can optimize both model accuracy and simulation efficiency. Finally, implementing a variable sample size also affected prediction, and our results show that tuning both the magnitude and timing of the sample size adjustment in an application-specific manner may prove useful in some Applications. Taken together, our findings highlight the challenge of performing prognostics in resource-constrained settings, and illustrate the potential of developing new prediction algorithms to improve computational efficiency of prognosis.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"29 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":"127984561","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":"Relative Flash LiDAR Aided-Inertial Navigation using Surfel Grid Maps","authors":"Bangshang Liu, Vasko Sazdovski, K. Janschek","doi":"10.1109/AERO53065.2022.9843616","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843616","url":null,"abstract":"This paper proposes a relative navigation framework using flash LiDAR aided-inertial navigation and surfel grid maps for in-situ autonomous exploration of small solar system bodies' (SSSB) surfaces. The key idea of the relative navigation is division of an entire flight area into several sub-areas, in each of which local navigation estimates and a local map are created in a node frame representing local frame in that sub-area. By changing the node frame in different sub-areas, estimation error and mapping error are bounded and do not accumulate. Varying local gravity vector on the SSSB surface is taken into account when a new node frame is defined. Our flash LiDAR pre-processing applies a scan-to-map matching algorithm and provides direct observation of spacecraft's position and attitude in the node frame to an error state Kalman filter. The surfel grid map representing local terrestrial environment around the spacecraft permits efficient scan-to-map matching and straightforward analysis on the SSSB surface. Simulation tests in a specialized high fidelity simulated SSSB environment present results of validation and performance evaluation of our relative navigation solution and show the viability of this novel navigation solution.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"97 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"113963805","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":"Signature-Aware RF Exploitation (SNARE) Fingerprinting using Deep Learning to identify UAVs","authors":"Hossein Jafari, Erik Blasch, K. Pham, Genshe Chen","doi":"10.1109/AERO53065.2022.9843479","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843479","url":null,"abstract":"Currently, there are emerging challenges with non-cooperative unmanned aerial vehicle (UAV) operating in urban airspaces. Likewise, law-enforcement groups need UAV detection capabilities to respond for safety and security (e.g., as defined for situation awareness at airports and forest fires where protocols restrict UAVs from operating within a few nautical miles from the event). This paper presents a novel physical layer authentication solution to identify UAVs that have identical visual signatures such as the same drone type and manufacturer. Within each UAV, the radio frequency (RF) signals transmitted from UAVs have a unique signature, called RF fingerprint, that can be used to distinguish among UAVs. The proposed Signal-to-Noise Ratio (SNR) of the transmitted signal in the wireless domain knowledge signifies the equipment onboard the UAV. The SNR-Aware RF Exploitation (SNARE) method solution improves the overall performance of conventional machine learning neural network models applied to imagery. This paper compares the performance metrics of different deep learning techniques including convolutional neural network (CNN), deep neural network (DNN), recurrent neural network (RNN), and the effect of related hyper parameters such as size of sliding window, learning rate, and SNR range. Experimental RF data collected from multiple identical UAVs hovering in different ranges from the receiver node are employed in this study. Compared to the traditional models that do not consider the received RF signal related SNR information, our proposed SNARE improves UAV classification of the CNN, DNN, and RNN models from 84% to 96%, 91% to 96%, and 80% to 86%, respectively.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"22 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":"131969410","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":"Attitude Control of Hansa-3 Aircraft with Perturbation Using Sliding-Mode Controller","authors":"Prabhjeet Singh, Salahudden, D. Giri, A. Ghosh","doi":"10.1109/AERO53065.2022.9843547","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843547","url":null,"abstract":"This paper presents a robust control design law for stabilizing the fixed-wing aircraft attitude. For stable flying within the flight envelope, attitude control is the crux for conventional aviation flight control systems. For practical implications, control laws are designed in such a way to reject disturbances and uncertainties. One of the robust control methods is sliding mode control (SMC) which has established itself over the last few decades due to its simplicity and wide applicability in numerous engineering systems. SMC with the first-order error dynamics has been exploited in this paper to track the reference signal for Hansa-3 research aircraft. Power rate reaching law (PRRL) has been used in combination with SMC to rapidly drive the aircraft states from the reaching phase to the sliding phase. The manifold sliding surfaces of pitch, roll and yaw attitudes are designed systematically in combination with the PRRL. Five attitude profiles including the perturbation in aircraft's inertial properties were considered to substantiate the working of the proposed control law. These profiles test the robustness of the control law and are pertinent to the real-world scenarios. In this paper, it is demonstrated through exhaustive simulations of the considered profiles that SMC design explicitly follows the desired input signals with asymptotic stability without the well-known problem of chattering. Simulations show that there is finite-time convergence of the desired aircraft states achieved within the constrained design limits of respective control surfaces. These simulation results exemplify the efficacy of the proposed control law.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"98 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":"131973230","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":"Evaluation of a Distributed Kalman Filter for Autonomous Satellite Navigation Using DASEE","authors":"Eric D. Yuan, J. Neff, Jeffrey Won","doi":"10.1109/AERO53065.2022.9843329","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843329","url":null,"abstract":"Distributed Application Simulation and Evaluation Environment (DASEE) is an edge computing testbed built on a cloud-native software platform. Distributed applications at the edge are resource constrained and failure-prone, have disadvantaged communications, often require local autonomy, and exhibit non-deterministic global behavior. DASEE was created to support mission concept of operations (CONOPS) development, architecture trades, and demonstration of distributed compute algorithms in a realistic test environment. DASEE was recently used to simulate the performance of a distributed Kalman filter (DKF) for autonomous satellite navigation in a 112-node Low Earth Orbit (LEO) spacecraft constellation. Preliminary results show that the DKF algorithm converges in a centralized simulation but clearly diverges when executed in a decentralized simulation. Divergence is caused by the covariance matrix some-times losing positive-definiteness. Root cause of the divergence is traced back to asymmetric partner updates between nodes, in which one node successfully completes the update while its partner fails. This result demonstrates the need for an edge computing simulation environment for distributed computing applications.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"19 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":"130212819","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":"Differential Ranging Experiments with NASA's High-Gain Deep Space Network Antennas","authors":"V. Vilnrotter, K. Cheung","doi":"10.1109/AERO53065.2022.9843654","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843654","url":null,"abstract":"Radar experiments are currently under way at the Goldstone Deep Space Communications Complex (GDSCC) to determine the range of cis-lunar objects using a single high-gain 34m antenna transmitting 20 kW at X-band wavelengths, and two 34m receivers located at the GDSCC. The 34m antennas of the Deep Space Network (DSN) have effective fields-of-view of approximately 1 milli-radians, hence predetermined pointing predicts with accuracies on the order of 1 milli-degree are required. The extremely accurate 1 nano-second timing distribution of the DSN network enables sub-meter level ranging in the radial direction, by measuring delays in phase-modulated pseudonoise (PN) echoes reflected from the target. In this paper we demonstrate initial experimental verification of the proposed techniques by post-processing radar reflections obtained from a decommissioned geo-synchronous satellite, GOES-8. The characteristics of correlation-based delay measurements obtained simultaneously with two different receiving antennas are described and analyzed for a single spacecraft and two co-located spacecrafts. These are the fundamental quantities used to form the “time difference of arrival” (TDOA) observables commonly used in GPS positioning algorithms, enabling hyperbolic position location as well as determining the differential range between co-located spacecraft, that could be utilized in the future to monitor spacecraft in cis-lunar space.","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":"130264496","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}