2005 IEEE Aerospace Conference最新文献

{"title":"Challenges of Remote FPGA Configuration for Space Applications","authors":"M. Surratt, H. Loomis, A. Ross, R. Duren","doi":"10.1109/AERO.2005.1559549","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559549","url":null,"abstract":"There are many unique challenges associated with providing remote access to space experimental payloads. The limited bandwidth to the space craft, the inability to physically monitor and probe the payload, and the management of access time for various researchers working on the project all compound to create a challenging work environment. The configurable fault tolerant processor (CFTP) project aims to alleviate many of the difficulties associated with remote payload operation. We have made use of modular FPGA design, which allows us to transfer only small application modules rather than full configuration files. This dramatically reduces the bandwidth required to upload new applications as we discover new experiments for the CFTP after launch. Another unique aspect of the CFTP project is the collaborative effort in its development. We must manage access time for universities and research institutions across the country for running experiments on the CFTP, downloading CFTP documents, and analyzing telemetry after launch","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"42 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114832666","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":"Simulating elements of the space radiation environment on Earth","authors":"J. Miller, S. Guetersloh, L. Heilbronn, C. Zeitlin","doi":"10.1109/AERO.2005.1559360","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559360","url":null,"abstract":"Space radiation research is laying the groundwork for addressing the problem of radiation exposure to humans on extended space missions. This research relies heavily on investigations at ground-based proton and heavy ion accelerators. The interpretation of the data from these experiments depends sensitively on the details of how these heavily ionizing particles deposit their energy in beamline materials and in the instruments used to measure the radiation. We report on the results of measurements with ion beams at several accelerators, including the Bevalac (Lawrence Berkeley National Laboratory), AGS (Brookhaven National Laboratory), HIMAC (National Institute of Radiological Sciences, Chiba, Japan), and the new NASA Space Radiation Laboratory (NSRL) at Brookhaven. These measurements illustrate some of the critical features of heavy charged particle interactions.","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126306349","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 pragmatic access to space approach for the ST8 mission","authors":"P. R. Turner, L. Herrell","doi":"10.1109/AERO.2005.1559372","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559372","url":null,"abstract":"NASA the new millennium program (NMP) approach to space flight validation of advanced technologies is to alternate between subsystem and system flight validations. Candidates for each NMP project (subsystem or system) are competed through a NASA research announcement process, and proposal selection is determined by NASA headquarters. Space technology 8 (ST8) is the second NMP subsystem project. It includes technology experiments selected from four technology capability areas. The forecast for launch is 2008. The key distinguishing feature between the first subsystem project (ST6) and ST8 is the approach for access to space (ATS). The ST6 Project was initiated in 1999 - a time of great expectations for an expanded launch industry and potential for a great deal of 'ride-sharing' to space. Anticipating an environment rich with partnering possibilities, the ST6 competing teams sought and found a variety of accommodations for ATS (e.g., as payloads on other spacecraft, or as a payload on the shuttle's HitchHiker Program). Lessons learned from ST6 include the loss of partnerships or 'rideshares' in a time of decreasing launch availability, cancellation of a partner's project, and loss of the space shuttle (as of this writing) as a host platform. The ST8 mission was initiated in 2003, after the 'crash' of the launch industry, and the NMP approach for access to space changed. NMP planned to provide a launch vehicle and carrier spacecraft that would accommodate the selection of subsystem technologies. Because of the competitive element of NMP, however, the technologies to be flown would not be known until a year after the start of the competition and that valuable time could be used to prepare for the spacecraft requirements, and align the spacecraft acquisition to coincide with the down-selection of the technology payload. NMP was confronted with a ('chicken-or-the-egg') dilemma: Since the technology payload has not been chosen, how do we scope the NMP carrier requirements? If we wait to begin work on the spacecraft requirements until after NASA selects the technology payloads, we could lose a year or more toward enabling future space science missions. This paper tells the story of the evolution of the access to space approach for the ST8 Project, with some insights and comments on the benefits and risks of this approach.","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128039075","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":"System concepts for transmit arrays of parabolic antennas for deep space uplinks","authors":"W. Hurd","doi":"10.1109/AERO.2005.1559414","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559414","url":null,"abstract":"Phased arrays of parabolic antennas are a potentially lower-cost way to provide uplink transmission to distant spacecraft, compared to the 34-m and 70-m antennas now used by the NASA Deep Space Network. A large transmit array could provide very high EIRP when needed for spacecraft emergencies, such as the equivalent of 1 MW radiated from a 70-m antenna. Cost-effectiveness is realized by dividing the array into smaller arrays to provide routine support to many spacecraft simultaneously. The antennas might be as small as 12-m in diameter, with as many as 100 antennas covering an area of 0.5 km to 1 km in extent. Such arrays present significant technical challenges in phase alignment, which must be maintained at close to 1 mm. The concept requires a very stable system with accurately known antenna phase center locations. The system is first calibrated by transmitting from all antennas, and observing the signals at a target located in the far fields of the individual antennas. The antennas are then pointed to the operational targets, with the signal phases and time delays set to reinforce in the target directions. This requires accurate knowledge of the target directions and calculation of the required phases. The system must be phase-stable for all directions and over the time between calibrations, which is desired to be at least one day. In this paper, a system concept is presented, the major error sources are identified, a rough error budget is established, and key elements of the system are discussed. A calibration method is recommended which uses satellites as radar targets. The performance goal is to achieve a combining loss of less than 0.2 dB in good weather, and of less than 1 dB in all but extremely bad weather","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"91 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128187797","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":"Using the Hybrid Systems Interchange Format to Input Design Models to Verification & Validation Tools","authors":"J. Sprinkle, R. Miller, O. Shakernia, S. Sastry","doi":"10.1109/AERO.2005.1559595","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559595","url":null,"abstract":"The domain of hybrid systems lacks the set of mature tools which can reliably apply verification and validation (V&V) techniques for all kinds of systems. Currently, no single tool supports analysis, simulation, verification, validation, and code synthesis of controllers for hybrid systems. As such, it becomes necessary to depend on several tools for analysis of different aspects of the system. This paper describes the utilization of the definition of a system in more than one toolsuite, while reducing the required effort for the same engineers that design the controllers to interface to the V&V toolsuites","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121778898","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":"Orthogonal pulsing schemes for improved target detection in space based radar","authors":"S. Unnikrishna Pillai, B. Himed, K. Li","doi":"10.1109/AERO.2005.1559510","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559510","url":null,"abstract":"Two phenomena that degrade the performance of ground moving target detection (GMTI) capabilities of space based radars (SBR) are (i) range foldover effects associated with multiple data points originating from different range bins due to the radar pulse stream and (ii) Earth's rotational effect on clutter Doppler frequency. The degradation in performance due to these phenomena is quantified in this paper and methods to minimize their effect are discussed. In this context, transmit pulsing schemes involving waveform diversity is proposed for improved target detection capabilities","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"12 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121791998","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 Technique for Specifying Dynamically Reconfigurable Embedded Systems","authors":"O. Rawashdeh, J. Lumpp","doi":"10.1109/AERO.2005.1559558","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559558","url":null,"abstract":"This paper describes a framework for developing dynamically reconfiguring distributed embedded systems supporting graceful degradation. Graceful degradation allows embedded systems to reconfigure in response to faults, allowing the systems to reduce their level of service instead of suffering system failures. The approach is based on a graphical software specification technique. Software module dependency graphs are used to specify the interaction and interdependencies between software modules. Individual software modules can be specified with alternate implementations that may require different amounts of system resources. As failures occur, a system manager tracks system status and uses the dependency graphs to choose new system configurations to deploy. The proposed framework also supports traditional fault-tolerance techniques, such as fail-over programming, redundant calculations, and voting, making it an attractive alternative for the design of a wide range of embedded control applications. A high level description of the proposed system architecture as well as its fault detection and handling are presented followed by discussion of the software modeling","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"14 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132311651","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":"Optimal task ordering for troubleshooting systems faults","authors":"Jun Liu","doi":"10.1109/AERO.2005.1559676","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559676","url":null,"abstract":"Automated troubleshooting of system faults is an essential element of modern aerospace equipment. The increased efficiency and accuracy helps in dramatically lowering maintenance costs. The Prognostic Health Management (PHM) group at Pratt & Whitney is responsible for developing automated systems for fault detection, isolation, and accommodation for the Joint Strike Fighter (JSF) propulsion system. A fundamental question that arises in this context is the following: Given a list of suspected components that have been identified a priori as possible causes for failure symptom(s), what is the optimal troubleshooting task assignment strategy? This paper introduces an approach to optimal task ordering. We show that the correct strategy is to order the tasks based on an easily calculated metric - which we call the mean utility function - that takes into consideration the mean troubleshooting time, or cost, or a combination of the two, depending on what is considered to be most critical. A mathematical proof is given for this. The approach shown in the paper can also be applied, as a troubleshooting strategy, for any other machinery health management system","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130479473","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":"System architecture of the vehicular remote tolling (VeRT) project","authors":"D. Teotino, M. Antonini, M. Ruggieri, R. Prasad","doi":"10.1109/AERO.2005.1559477","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559477","url":null,"abstract":"Future Global Navigation Satellite systems (GNSS) have significantly improve the performance of current navigation systems, providing new and enhanced capabilities. This enables the implementation of innovative and advanced services and applications more and more close to the user needs. In this framework, the road sector is one of the major potential market for GNSS applications and therefore it is very promising for future European Geostationary Navigation Overlay Service (EGNOS) and GALILEO related applications. Specifically, a very important commercial opportunity is represented by the tolling-related applications. The paper describes the vehicular remote tolling (VeRT) project sponsored by Galileo Joint Undertaking (GJU) and performed in the frame of the first GJU call under the EC VI Framework Programme, giving attention, in particular, to the communication network issues","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"168 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"134233092","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":"Telemetry, tracking, and commanding (TT&C) link considerations for a LEO Sat","authors":"J. Kreng, M. Ardeshiri, O.C. Barbosa, Y. Krikorian","doi":"10.1109/AERO.2005.1559457","DOIUrl":"https://doi.org/10.1109/AERO.2005.1559457","url":null,"abstract":"Telemetry, tracking, and command are very important functions necessary for the proper operation of a satellite. It becomes a critical issue for the LEO-Sat program, however, when the command and control is provided from a small ground station with limited capabilities (low transmit EIRP and receive G/T), and when the satellite is in a contingency mode of operation, such as tumbling (antennas off pointed). Previous link analyses have shown that the satellite link would be adequate when commanding from large remote tracking stations (RTS) with a larger antenna (45- or 60-foot dish). This paper deals with command and control of this new LEO-Sat in its early orbit, using a small remote tracking station (RTS), with a 33-foot antenna. Our analyses have proven that the uplink and downlink can be closed even with a small RTS station with a 33-ft antenna. The details of these analyses are given in this paper. The communication link performances, both during normal operations as well as in contingency tumbling mode of operations, are presented here. Both the SNR (signal to noise ratio) and the threshold techniques were shown side-by-side, in the link analyses, for normal and anomalous tumbling cases, with similar results. The conclusion in Section 5 summarizes the analyses. Aerospace personnel and the satellite contractor came to a similar conclusion: that the uplink and downlink (to and from the satellite) using small RTS stations with a 33-ft antenna have adequate link margin. In normal mode, worst-case LEO-Sat and nominal small RTS station parameters were used in the analysis. In contingency mode or tumbling mode, the worst worst-case parameters for LEO-Sat and for a small RTS station were used. A summary of the results of the analyses performed for the uplink and downlink communication paths are given in this paper","PeriodicalId":117223,"journal":{"name":"2005 IEEE Aerospace Conference","volume":"209 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2005-03-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"133867322","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}