2022 IEEE Aerospace Conference (AERO)最新文献

{"title":"Autonomous Balloon Technology: Automated Methods for Rapid Balloon Inflation and Launching","authors":"Arun Bishop, Nicholas Hennigan","doi":"10.1109/AERO53065.2022.9843206","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843206","url":null,"abstract":"Traditional High-Altitude Balloon (HAB) platforms provide a realistic and cost-effective strategy for a range of applications. However, manual launches often take hours and require many people. The National Aeronautics and Space Administration Jet Propulsion Laboratory's Innovation To Flight program has begun work on a completely autonomous multi-balloon launching system called the autolauncher. The aim of the autolauncher is to expedite the launching process while allowing HABs to be launched in challenging or remote terrain. The new design would fully automate the set up and successive launch of multiple balloons with at most 30 minutes between each flight. The autolauncher manipulates a novel balloon packing and transport container called a Balloon Capsule and operates as follows: capsules are autonomously loaded into an inflation/launch staging area, where the Helium Engagement and Locking (HEL) system connects the balloon to helium and restrains it while it is inflated, releasing the balloon when ready for launch. The balloon inflation occurs within a Balloon Inflation Barrier (BiB) that protects the balloon during inflation. The proposed design is quasi-modular and incorporates discrete subsystems for controlling payload and balloon storage, balloon setup and loading, and balloon inflation and launch. This paper focuses on development of the Balloon Capsule, BiB, and the HEL system, primary components necessary for the inflation and launch subsystem. Results from two investigative studies used to determine new balloon packing and balloon inflation protection methods are presented. The first study examined the deployment characteristics of compressed, thin-walled balloons and tested a new cascading-folding method to tightly pack balloons. The BiB design was validated experimentally in the second study by measuring balloon deflection under wind speeds up to 42 km/h. A prototype of the HEL system was built and successfully tested under 1.5x the expected lift forces and incorporated into a structural prototype of the autolauncher. The prototype weighs less than 9.0 kg and is 88.4 cm long, 56.4 cm wide, and 37.2 cm tall. This design will significantly reduce the time and labor necessary for HAB launches. Remaining work includes: implementing the helium control; design of balloon payload storage systems; and testing the prototype during a full launch.","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":"126446703","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":"In-Flight Demonstration of Enhanced-Low-Dose-Rate-Sensitivity (ELDRS) in Bipolar Junction Transistors","authors":"A. Benedetto, H. Barnaby, Cheyenne Cook, M. Campola, Anna Tender","doi":"10.1109/AERO53065.2022.9843335","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843335","url":null,"abstract":"Data on bipolar junction transistors (BJTs) acquired from an in-flight mission experiment are recorded and downloaded for analysis. These data are analyzed for the purpose of characterizing the effects of low dose rate space irradiation on BJTs using a simulated PNP model that has been shown to accurately represent real-life effects of temperature on base current degradation. Results are compared to ground-based tests and show similar trends to LDR ground-based tests. These results will be used for validating recommended hardness assurance test methods for Enhanced-Low-Dose-Rate-Sensitivity (ELDRS) in the space environments and to gain insight into ELDRS mechanisms and the effects of the complex real space environment on BJTs.","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":"126692433","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":"Regenerative ECLSS and Logistics Analysis for Sustained Lunar Surface Missions","authors":"C. Stromgren, C. Burke, Jason Cho, W. Cirillo, Andrew C. Owens, D. Howard","doi":"10.1109/AERO53065.2022.9843674","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843674","url":null,"abstract":"As NASA develops concepts for sustained crew missions to the lunar surface, a crucial component of mission planning will be evaluating the required amount of logistics to support the crew, surface systems, and science operations. This amount could be substantial. Because NASA plans to conduct these missions on an annual basis, the complexity and cost of logistics delivery will likely drive campaign sustainability. Logistics quantity is partially a function of the regenerative Environmental Control and Life Support System (ECLSS) capability in habitable elements on the surface. The regenerative ECLSS recycles human waste to produce water and oxygen, reducing the consumables needed for a mission. Thus, an ECLSS with increased regenerative capability will require less logistics. However, an ECLSS with enhanced regenerative abilities will also increase the initial delivery mass of elements and require extra maintenance items and spares. This paper analyzes the tradeoff between initial delivery masses of different regenerative ECLSS options and the amount of logistics resupply required for each option. Sustained lunar surface missions will involve crews of two to four astronauts living on the surface for periods of 30 days or longer. Astronauts will live in some combination of a surface habitat and/or a pressurized rover. To conduct the study, the authors created the Lunar Surface Integrated ECLSS Analysis Tool to model different configurations of rover and habitat with different ECLSS options. The tool can simulate ECLSS operations in the integrated architecture, including potential commodity transfers between the habitat and the rover. In this paper, the authors describe the use of the tool to evaluate different possible ECLSS configurations and their corresponding logistics requirements. The authors then complete a sensitivity analysis that compares logistics requirements for annual resupply and the initial delivery mass over increasing regenerative ECLSS capabilities. Finally, the authors recommend ECLSS architecture options that potentially improve the balance between logistics requirements and ECLSS system mass.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"76 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":"121108284","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":"Viability of Small Dimension Crew Quarters for Surface Habitation","authors":"H. Litaker, R. Howard","doi":"10.1109/AERO53065.2022.9843291","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843291","url":null,"abstract":"It is possible that in the next twenty years NASA may fly crew sleep quarters (CQ) on twice as many spacecraft as it has in the past fifty years. In short, US experience with spacecraft crew sleep quarters is limited. With few available standards to guide their design, there is significant uncertainty facing spacecraft currently in development, several of which face substantial mass and volume challenges. Those spacecraft developments will face considerable pressure to minimize crew quarters size, including those intended for use on the lunar surface. Given that a crew quarters is the only space a crew member can call his or her own during missions that can last weeks to years in duration, providing an appropriate volume is especially important and the reality is that all crew quarters flown to date have been smaller than minimum standards for US jail cells. This research will categorize functional capabilities of crew quarters and explore physical and virtual prototypes of small crew quarters that have attempted to include these capabilities. The Exploration Atmospheres Test at NASA Johnson Space Center represents the first opportunity to collect multi-day test data on crew quarters of this size in a gravitational environment. Intended to validate exploration prebreathe protocols, this test will house eight people inside a vacuum chamber that has been outfitted as a habitat prototype for twelve days. In addition to their other test activity, the crew will evaluate the acceptability of their crew quarters. This data will aid in establishing design guidelines and requirements for crew quarters in both short and long duration missions beyond low Earth orbit.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"116 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":"121396276","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":"Next Generation Phased Arrays for Deep Space Communications","authors":"Aaron Pereira, E. Kruzins, Said Al Sarawi, Derek Abbott, F. Menk, Okan Yuversedyan, B. Schwitter, T. Fattorini","doi":"10.1109/AERO53065.2022.9843226","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843226","url":null,"abstract":"In the coming decades there is going to be a significant increase in the number of spacecrafts, orbiters, landers and rovers that will be launched into deep space on various exploration missions. The ground segment supporting such missions primarily consists of a high gain parabolic reflector antenna, which are legacy systems and represents a single point of failure. Moreover, with the return of humans to moon and the establishment of the lunar gateway, there will be significant increase in data and command traffic between ground control and space segment. Additionally with the entry of commercial parties, there will be a large number of constellations of satellites launched into low earth orbit (LEO), geostationary earth orbit (GEO) and Low lunar orbit (LLO). All of these will place significant stress on existing communications architecture. This paper examines the use of new and emerging technologies to develop innovative planar array tiles for active electronically scanned array (AESA) based deep space communications architecture that is highly modular, scalable and enabling multibeam operations across multiple spacecrafts in space.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"8 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":"125194286","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":"Radiation Test and in Orbit Performance of MpSoC AI Accelerator","authors":"Leénie Buckley, A. Dunne, G. Furano, M. Tali","doi":"10.1109/AERO53065.2022.9843440","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843440","url":null,"abstract":"Φ-Sat-1 is part of the European Space Agency initiative to promote the development of disruptive innovative technology and capabilities on-board EO missions. The Φ-Sat-l satellite represents the first-ever on-board Artificial Intelligence (AI) deep Convolutional Neural Network (CNN) inference on a dedicated chip attempting to exploit artificial Deep Neural Network (DNN) capability for Earth Observation. It utilises the Myriad Vision Processing Unit (VPU), a System On Chip (SOC) that has been designed ex novo for high-performance edge compute for vision applications. In order to support Myriad's deployment on Φ-Sat-l, the first mission using AI processing for operational purposes, and future applications in general, the SOC has undergone radiation characterisation via several test campaigns in European test facilities. The first AI application developed for in-flight inference was CloudScout, a segmentation neural network that was designed specifically for Φ-Sat-l in order to achieve high detail and good granularity in the classification result, and eventually discard on-board the cloudy images acquired by the hyperspectral sensor, thus greatly enhancing the data throughput capability of the mission. In addition to the CloudScout cloud detection AI SW results acquired during Φ-Sat-l's mission, in-flight performance data was also acquired for the hardware inference engine. Four separate VPU-based inference engine test phases were executed over 70 days during the mission. The in-flight diagnostics tests for the VPU inference engine indicate that the device performed as expected on-board Φ-Sat-l without experiencing any functional upsets, or any functional degradation effects due to radiation. All future installations of the Myriad VPU in space will be equipped with this Built-In Self Test (BIST) that will allow monitoring the performance of the inference engine hardware.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"13 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":"114295807","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":"Space Launch System (SLS): Artemis I, Evolution, and Capability","authors":"Terry D. Haws, Jacob P. Bartkiewicz, Michael E. Fuller","doi":"10.1109/AERO53065.2022.9843675","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843675","url":null,"abstract":"A human mission to the moon and Mars is the stated space exploration goal of the United States and the international community. To achieve these goals, NASA is developing the Space Launch System (SLS) and the Orion crew capsule as key elements in the architecture for missions to the moon and Mars. The capability of SLS makes it a key piece of the campaign, important for lifting large components necessary for the lunar surface and the Martian surface, as well as science missions to the outer planets.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"52 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":"122471657","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":"Automated Onboard Mission Planning for Robust and Flexible Rover Operations","authors":"T. Cunningham, D. Spencer","doi":"10.1109/AERO53065.2022.9843729","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843729","url":null,"abstract":"Activity planning for space mission operations has traditionally been a human-in-the-loop effort, conducted by ground operators. The outputs of the mission planning process are scripted sequences of activities that are uplinked to the space vehicle for execution. Over the past two decades, advances have been made toward automating the mission planning process, in an effort to improve the efficiency of the mission operations system, while increasing the mission return. Some aspects of onboard mission planning are increasingly used for complex missions, particularly for planetary surface missions that are subject to long communication delays. This paper applies an automated mission planning framework to a resource-constrained science rover mission case study. The plans are optimized on the basis of science return, accommodating traverse to sites of scientific interest according to ground-team preferences, while staying within rover engineering and traverse-related constraints. Automated mission planners offer the capability to schedule engineering and science activities onboard, without ground-in-the-loop interaction. Resource modeling and path planning can be done onboard, reducing the need for modeling and validation by ground operators. Further, automated mission planners may incorporate an optimization executive that maximizes the mission return within the available resource constraints. The proposed planners may be utilized on the ground by mission planning teams to provide additional insight during the planning process, or onboard autonomous rovers with limited human support. Using optimization methods, the developed automated mission planner establishes the planned sequence of routes to be followed to sites of high scientific value while adhering to constraints imposed by pathing requirements and resource availability. The activity plans coordinate the traverse planning and science data acquisition within the context of the evolving knowledge of the scientific value of the nearby terrain. The automated mission planning framework is designed to be adapted based upon the application. Optimization methods suitable for different mission planning problems are presented, comparing methods on the basis of computation speed, resources required and solution optimality. Measures of “robustness” and “flexibility” are incorporated into the framework to enable the system to adapt to changing conditions without violating constraints, and to provide additional criteria with which to evaluate and compare the produced activity plans.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"132 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":"122755660","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":"Implementing Low-Density Parity-Check Codes in the Mars Relay Network","authors":"N. Chamberlain, S. Allen, K. Andrews, Harvey Elliott, R. Gladden, J. Hamkins, I. Kuperman, R. Mendoza","doi":"10.1109/AERO53065.2022.9843399","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843399","url":null,"abstract":"This paper describes the implementation of Low-Density Parity-Check (LDPC) channel codes in the Mars Relay Network; specifically in the NASA MAVEN orbiter and the ESA ExoMars Trace Gas Orbiter. LDPC codes, also known as Gallager codes, were invented in the early 1960s. At the time, available computational hardware was not powerful enough to implement these codes, so they became “forgotten.” They were later “rediscovered” in the 1990s, whereupon it was demonstrated that practical LDPC decoders performed substantially better than standard convolutional codes. This spurred research and development of LDPC codes at JPL, which culminated in the implementation of a rate 1/2 LDPC decoder and encoder in the Electra proximity radio delivered to MAVEN in 2012 and subsequently to other Mars spacecraft. The paper starts with a brief history of LDPC code development and then goes on to describe the development and validation of recent firmware and software updates to facilitate LDPC code operation with adaptive data rate control. The LDPC codes developed for Electra were verified to produce approximately 3 dB coding gain relative to NASA's standard convolutional code, increasing data return by up to a factor of two. The paper concludes with an assessment of in-flight performance of LDPC-enabled relay passes between MAVEN and the Mars 2020 rover.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"24 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":"127796643","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":"Multi-Robot Assembly Scheduling for the Lunar Crater Radio Telescope on the Far-Side of the Moon","authors":"Preston Culbertson, Saptarshi Bandyopadhyay, A. Goel, P. McGarey, M. Schwager","doi":"10.1109/AERO53065.2022.9843304","DOIUrl":"https://doi.org/10.1109/AERO53065.2022.9843304","url":null,"abstract":"The Lunar Crater Radio Telescope (LCRT) is a proposed ultra-long-wavelength radio telescope to be constructed on the far side of the moon. The proposed telescope will be constructed by deploying a 1km wire mesh in a 3-5km crater using a team of wall-climbing DuAxel robots. In this work, we consider the problem of generating minimum-time assembly sequences for LCRT, using realistic models of travel speed and lighting. We pose the assembly sequencing problem as a mixed-integer linear program (MILP), which we solve to global optimality using commercial solvers. We present methods for modeling time-varying travel and assembly times, based on variable lighting conditions (including crater shadowing), and show how such time-varying parameters can be incorporated into the MILP. Finally, we present numerical studies of our method, showing how makespan varies with the number of assembly robots.","PeriodicalId":219988,"journal":{"name":"2022 IEEE Aerospace Conference (AERO)","volume":"31 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":"132732234","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}