2017 IEEE Aerospace Conference最新文献

{"title":"3D reconstruction in orbital proximity operations","authors":"Martin Dziura, Tim Wiese, J. Harder","doi":"10.1109/AERO.2017.7943679","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943679","url":null,"abstract":"This paper presents the application of 3D object reconstruction in orbital proximity operations. This promising novel technology is proposed to improve both Human Machine Interfaces (HMI) and autonomous algorithms for Guidance, Navigation and Control (GNC) in terms of situation awareness, docking efficiency and resource consumption. During this study a software framework was developed which implements a flexible real-time-capable toolchain to perform all necessary tasks for 3D object reconstruction. A driver module reads and filters the data stream from a given optical sensor (e.g. stereo camera or combined visual camera and infrared time-of-flight sensor). Image maps and depth information are then provided to computer vision algorithms for Simultaneous Localization and Mapping (SLAM) and algorithms for 3D reconstruction. As an output these algorithms generate a 3D point cloud and a 3D mesh that can be displayed to the human operator, fed into GNC algorithms or further processed to generate adequate surface models for visualization and inspection. This concept was verified in the Robotic Actuation and On-Orbit Navigation Laboratory (RACOON-Lab), a simulation environment for end-to-end technology development and evaluation for close-range proximity operations. A sub-scale hardware mock-up of a geostationary target satellite attached to the RACOON-Lab facility was successfully reconstructed using the described setup. During the simulated maneuver a rotating target satellite was observed by the sensors attached to the simulated chasing satellite. The software was executed on the embedded computer which is part of the facility. The cameras Kinect v2 and ZED produced adequate 3D reconstructions in intervals of less than 10 seconds. The Kinect v2 generates more accurate structures and includes more details, whereas the ZED results in a better color fidelity. Both cameras were sensitive to changes of lighting conditions. For longer acquisition times, drift caused by uncertainties in the pose estimation decreases the quality of the reconstruction significantly.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"48 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124389390","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":"The High Definition Earth Viewing (HDEV) payload","authors":"Paul Muri, S. Runco, Carlos Fontanot, Chris Getteau","doi":"10.1109/AERO.2017.7943749","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943749","url":null,"abstract":"The High Definition Earth Viewing (HDEV) payload enables long-term experimentation of four, commercial-of-the-shelf (COTS) high definition video, cameras mounted on the exterior of the International Space Station. The payload enables testing of cameras in the space environment. The HDEV cameras transmit imagery continuously to an encoder that then sends the video signal via Ethernet through the space station for downlink. The encoder, cameras, and other electronics are enclosed in a box pressurized to approximately one atmosphere, containing dry nitrogen, to provide a level of protection to the electronics from the space environment. The encoded video format supports streaming live video of Earth for viewing online. Camera sensor types include charge-coupled device and complementary metal-oxide semiconductor. Received imagery data is analyzed on the ground to evaluate camera sensor performance. Since payload deployment, minimal degradation to imagery quality has been observed. The HDEV payload continues to operate by live streaming and analyzing imagery. Results from the experiment reduce risk in the selection of cameras that could be considered for future use on the International Space Station and other spacecraft. This paper discusses the payload development, end-to-end architecture, experiment operation, resulting image analysis, and future work.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123490716","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":"Delay/Disruption Tolerant Networking for the International Space Station (ISS)","authors":"Adam M. Schlesinger, Brett M. Willman, L. Pitts, Suzanne R. Davidson, William A. Pohlchuck","doi":"10.1109/AERO.2017.7943857","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943857","url":null,"abstract":"Disruption Tolerant Networking (DTN) is an emerging data networking technology designed to abstract the hardware communication layer from the spacecraft/payload computing resources. DTN is specifically designed to operate in environments where link delays and disruptions are common (e.g., space-based networks). The National Aeronautics and Space Administration (NASA) has demonstrated DTN on several missions, such as the Deep Impact Networking (DINET) experiment, the Earth Observing Mission 1 (EO-1) and the Lunar Laser Communication Demonstration (LLCD). To further the maturation of DTN, NASA is implementing DTN protocols on the International Space Station (ISS). This paper explains the architecture of the ISS DTN network, the operational support for the system, the results from integrated ground testing, and the future work for DTN expansion.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"42 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123069639","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":"High density packaging technologies for RF electronics in small spacecraft","authors":"Fernando H. Aguirre, D. Schatzel","doi":"10.1109/AERO.2017.7943745","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943745","url":null,"abstract":"This paper will describe a few high density packaging technologies which we are currently exploring for use in current and future small spacecraft applications. The three categories of technologies include organic multichip modules (MCMs), ceramic leadless surface mount technology (SMT) and 3D printed waveguide structures. There are many other packaging technologies that currently exist but these three were selected in part due to their heritage in various commercial, military and space applications along with each having a relatively clear path to flight. For each of these technologies, detailed examples will be included in which hardware has been fabricated and tested for use in RF electronics for spacecraft transponders. The organic MCM example will be described in most detail and it utilizes a packaging technology by the name of CoreEZ which is a trademark of i3 Electronics. This MCM has shrunk a portion of our electronics down to 1/8th of its previous area. The CoreEZ technology has been shown to be rad hard beyond a total ionizing dose (TID) of 300kRad and the MCM which was fabricated has gone through thermal cycling and shown to have no degradation in performance. The ceramic leadless package examples include packages from high reliability manufactures by the name of KCB solutions and Barry Industries. In the case of KCB solutions, we have multiple products that will be described including a hermetic ceramic carrier which houses three microwave monolithic integrated circuits (MMICs) along with small discrete components. Finally, we will discuss the results of our search for a 3D printing process that allows us to reduce the cost and volume of our waveguide filters and diplexers for low cost small satellite applications. We have fabricated a few prototypes using direct metal laser sintering (DMLS) and metal coated plastics. Each of these packaging technology discussions will have a brief overview of its current and future use.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"130 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121538752","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 Mars Ascent Vehicle for potential mars sample return","authors":"R. Shotwell, J. Benito, A. Karp, J. Dankanich","doi":"10.1109/AERO.2017.7943851","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943851","url":null,"abstract":"This paper will cover the conceptual design of a Mars Ascent Vehicle (MAV) and efforts underway to raise the TRL at both the component and system levels. A system down select was executed resulting in a Hybrid Propulsion based Single Stage To Orbit (SSTO) MAV baseline architecture. This paper covers the Point of Departure design, as well as results of hardware developments that will be tested in several upcoming flight opportunities.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"22 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122330288","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":"Machine learning for improved diagnosis and prognosis in healthcare","authors":"Niharika G. Maity, Sreerupa Das","doi":"10.1109/AERO.2017.7943950","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943950","url":null,"abstract":"Machine learning has gained tremendous interest in the last decade fueled by cheaper computing power and inexpensive memory — making it efficient to store, process and analyze growing volumes of data. Enhanced algorithms are being designed and applied on large datasets to help discover hidden insights and correlations amongst data elements not obvious to human. These insights help businesses take better decisions and optimize key indicators of interest. The growing popularity of machine learning also stems from the fact that learning algorithms are agnostic to the domain of application. Classification algorithms, for example, that could be applied to categorize faults in windmill blades can also be used for categorizing TV viewers in a survey. The actual value of machine learning however depends on the ability to adapt and apply these algorithms to solve specific real world problems. In this paper we discuss two such applications for interpreting medical data for automated analysis. Our first case study demonstrates the use of Bayesian Inference, a paradigm of machine learning, for diagnosing Alzheimer's disease based on cognitive test results and demographic data. In the second case study we focus on automated classification of cell images to determine the advancement and severity of breast cancer using artificial neural networks. Although these research are still preliminary, they demonstrate the value of machine learning techniques in providing quick, efficient and automated data analysis. Machine learning offers hope with early diagnosis of diseases, help patients in making informed decisions on treatment options and can help in improving overall quality of their lives.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"93 3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132443856","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 trilateration scheme for relative positioning","authors":"K. Cheung, Charles Lee","doi":"10.1109/AERO.2017.7943800","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943800","url":null,"abstract":"We introduce a trilateration scheme that evaluates the 3-dimensional (3-D) relative position between a reference spacecraft and a target spacecraft using raw-range measurements from a distance baseline of known locations, which we call “anchors”. The anchors can be antennas of a ground-based network (e.g., Deep Space Network (DSN) or Near Earth Network (NEN) stations), or satellites of a space-based network (e.g., global positioning system (GPS) or tracking and data relay satellite (TDRS)). We define raw-range as the range that includes all the systematic errors that occur during range measurements. A unique feature of this approach is that accurate relative position is derived from a “differencing function” of raw-range measurements of the reference spacecraft and target spacecraft, thereby eliminating most of the systematic errors, such as media effects, ephemeris errors, instrument delays, clock bias, etc. There can be an arbitrary number of target spacecraft, and relative positioning of target spacecraft with respect to the reference spacecraft can be done simultaneously. In this paper, we first assume an idealized system in which clocks on the reference and target spacecraft are synchronized, with clocks of the anchors synchronized as well.2 We develop a novel iterative algorithm that computes the relative position of the target spacecraft with respect to the reference spacecraft. We illustrate the relative positioning method using the scenario of a network of three ground stations (i.e., the anchors) at Goldstone, California, USA, Madrid, Spain, and Marlargue, Argentina tracking two spacecraft at geosynchronous orbit distance. We demonstrate that the algorithm converges to sub-meter accuracy in estimating the relative position, in the presence of random errors and systematic errors in raw-range measurements, and in the presence of angular errors in estimating the pointing vectors between the anchors and the reference spacecraft. Next, we relax the requirement of perfect time synchronization between spacecraft, and show that by using an additional anchor, one can estimate and remove the clock biases between the reference and target spacecraft. We add a ground station at Kourou to the above example of three ground stations of Goldstone, Madrid, and Marlargue, and demonstrate that the updated algorithm also converges to meter-level accuracy (sub-meter in some cases) in the presence of clock biases in addition to the random errors, systematic errors, and angular errors as shown in the above case. We compare this scheme with a similar trilateration scheme for relative positioning scheme first proposed by Montenbruck in 2002.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"62 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130899924","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":"Trajectory design of formation flying constellation for space-based solar power","authors":"A. Goel, Nicolas Lee, S. Pellegrino","doi":"10.1109/AERO.2017.7943711","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943711","url":null,"abstract":"The concept of collecting solar power in space and transmitting it to the Earth using a microwave beam has appealed to the imagination of numerous researchers in the past. The Space Solar Power Initiative at Caltech is working towards turning this idea into reality, by developing the critical technologies necessary to make this an economically feasible solution. The proposed system comprises an array of ultralight, membrane-like deployable modules with high efficiency photovoltaics and microwave transmission antennas embedded in the structure. Each module is 60 m χ 60 m in size and in the final configuration, ∼2500 of these modules form a 3 km χ 3 km array in a geosynchronous orbit. As the constellation orbits the Earth, the orientation and position of each module has to be changed so as to optimize the angle made by the photovoltaic surface with respect to the sun and by the antenna surface with respect to the receiving station on Earth. We derive the optimum orientation profile for the modules and find that modules with dual-sided RF transmission can provide 1.5 times more orbit-averaged power than modules with single-sided RF transmission. To carry out the corresponding orbital maneuvers, an optimization framework using the Hill-Clohessy-Wiltshire (HCW) equations is developed to achieve the dual goal of maximizing the power delivered, while minimizing the propellant required to carry out the desired orbital maneuvers. Results are presented for a constellation with modules in fixed relative positions and also for a constellation where the modules execute circularized periodic relative motion in the HCW frame. We show that the use of these periodic relative orbits reduces the propellant consumption from ∼150 kg to ∼50 kg. This drastic reduction makes the propellant mass a significantly smaller fraction of the module's dry mass (370 kg), thereby solving a major technical hurdle in the realization of space-based solar power.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"65 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133965748","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":"NASA's deep space habitation strategy","authors":"Jason Crusan, D. Craig, Nicole B. Herrmann","doi":"10.1109/AERO.2017.7943624","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943624","url":null,"abstract":"NASA is seeking to expand human presence into the solar system in a sustainable way. NASA's goal is not just a destination to reach, but rather it is to develop the capacity for people to work, learn, operate, and live safely beyond the Earth for extended periods of time, ultimately in ways that are more sustainable and even indefinite. The deep space habitation capability is one of the key foundations of this strategy and for human space missions beyond low-Earth orbit (LEO), habitation capabilities represent a critical component of NASA's plans for Mars-class distances and duration missions. An effective habitation capability is comprised of a pressurized volume, and an integrated array of complex habitation systems and components that include a docking capability, environmental control and life support systems, logistics management, radiation mitigation and monitoring, fire safety technologies, autonomy, and crew health capabilities. NASA's habitation development strategy is to test these systems and components on the ground and in LEO on ISS, then with the potential of incremental deployment as an integrated habitation capability for long-duration missions in cislunar space for validation before Mars-class mission transits. This paper will address this incremental and phased approach of NASA's deep-space habitat development strategy including the progression from Earth Reliant activities in LEO to advancing systems and operational capabilities in the Proving Ground of cislunar space and gradually transitioning toward Earth Independent missions. The near-term need for initial short-duration habitation beyond LEO will be explored including how this capability fulfills NASA's Human Exploration Objectives while leading to a validated system to conduct missions beyond the Earth-Moon system. Various implementation approaches will be discussed including potential commercial design concepts that are currently being investigated under the NextSTEP Broad Agency Announcement (BAA) including a summary of Phase 1 activities, a status on the progress of Phase 2 and forward work plans leading to the planned Phase 3. This paper will also address similar approaches and additions that are provided via international contributions as an integrated portion of the strategy for deep space habitation and the final acquisition approaches under consideration for Phase 3. The paper will conclude with a discussion of how each of the potential options and their element and program dependencies feed into decisions on implementation of habitation in deep space and commercial investment in LEO.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"46 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133192659","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":"NASA's Kilopower reactor development and the path to higher power missions","authors":"M. Gibson, S. Oleson, D. Poston, P. McClure","doi":"10.1109/AERO.2017.7943946","DOIUrl":"https://doi.org/10.1109/AERO.2017.7943946","url":null,"abstract":"The development of NASA's Kilopower fission reactor is taking large strides toward flight development with several successful tests completed during its technology demonstration trials. The Kilopower reactors are designed to provide 1–10 kW of electrical power to a spacecraft or lander, which could be used for additional science instruments, the ability to power electric propulsion systems, or support human exploration on another planet. Power rich nuclear missions have been excluded from NASA mission proposals because of the lack of radioisotope fuel and the absence of a flight qualified fission system. NASA has partnered with the Department of Energy's National Nuclear Security Administration to develop the Kilopower reactor using existing facilities and infrastructure and determine if the reactor design is suitable for flight development. The three-year Kilopower project started in 2015 with a challenging goal of building and testing a full-scale flight-prototypic nuclear reactor by the end of 2017. Initially, the power system will undergo several non-nuclear tests using an electrical heat source and a depleted uranium core to verify the complete non-nuclear system design prior to any nuclear testing. After successful completion of the depleted uranium test, the system will be shipped to the Nevada National Security Site where it will be fueled with the highly enriched uranium core and re-tested using the nuclear heat source. At completion of the project, NASA will have a significant sum of experimental data with a flight-prototypic fission power system, greatly reducing the technical and programmatic risks associated with further flight development. To compliment the hardware rich development progress, a review of several higher power mission studies are included to emphasize the impact of having a flight qualified fission reactor. The studies cover several science missions that offer nuclear electric propulsion with the reactor supplying power to the spacecraft's propulsion system and the science instruments, enabling a new class of outer planet missions. A solar versus nuclear trade for Mars surface power is also reviewed to compare the advantages of each system in support of ascent vehicle propellant production and human expeditions. These mission studies offer insight into some of the benefits that fission power has to offer but still lacks a wider audience of influence. For example, mission directorates won't include a fission power system in their solicitations until it's flight qualified, and scientists won't propose new missions that require more power than what's currently proven and available. An attempt to break this chicken and egg effect has been ongoing with the Kilopower project with the goal of advancing the technology to a level that encourages a flight development program and allows scientists to propose new ideas for higher power missions.","PeriodicalId":224475,"journal":{"name":"2017 IEEE Aerospace Conference","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2017-03-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130279350","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}