Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352641
G. Marcus
Two new low loss radiation hardened technologies for DC power conversion are reported: a pulse width modulator and a digital isolator. Both are shown to be superior to currently available components used in radiation hardened DC/DC converters in terms of both power efficiency and radiation hardness. A method for combining the two technologies to maximize their benefit in DC/DC converter applications is described.
{"title":"New Technologies and Concepts for Low Loss Radiation Hardened DC/DC Converters","authors":"G. Marcus","doi":"10.1109/AERO.2007.352641","DOIUrl":"https://doi.org/10.1109/AERO.2007.352641","url":null,"abstract":"Two new low loss radiation hardened technologies for DC power conversion are reported: a pulse width modulator and a digital isolator. Both are shown to be superior to currently available components used in radiation hardened DC/DC converters in terms of both power efficiency and radiation hardness. A method for combining the two technologies to maximize their benefit in DC/DC converter applications is described.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"41 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81044376","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}
Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352939
D. Taggart, Rajendra Kumar, Y. Krikorian, G. Goo, Joseph Chen, Robert Martinez, Tom Tam, Edward Serhal
In contemporary communication satellite systems, uplink radio frequency (RF) signals are amplified, downconverted to intermediate frequency (IF) and/or baseband, and after appropriate filtering, are input to an analog-to-digital converter (ADC). The ADC digital output is signal processed for a variety of purposes, such as signal channelization and switching. In these systems, a foremost realization problem is the ADC, which must operate to satisfy the sampling theorem, which necessitates a sampling rate at least twice the received signal bandwidth. When the signal consists of numerous multiplexed signals, a critical matter in ADC performance is the degree of signal clipping, which arises when the instantaneous ADC input signal magnitude surpasses the maximum range of the ADC. Since at least some clipping is often present, the total ADC noise output consists of clipping plus quantization noise. A figure of merit for the ADC is the signal-to-noise ratio (SNR) of the ADC, which is defined as the ratio of input signal average power to the ADC output average noise power. The SNR is determined by, among other things, the ADC load factor, which is the ratio of the ADC input signal average power, and the ADC maximum peak power output. This paper describes analysis and simulation results on SNR versus the ADC load factor when the input signal is composed of many digitally modulated carriers. A nine-signal 8-ary phase shift key (8-PSK) modulated carrier case is considered with each signal band limited. It is important to note that for this particular ADC input, it is shown that the probability density function (PDF) is Gaussian-like. This is significant since this means that the SNR versus ADC load factor curve for the nine 8-PSK signal case will have nearly identical characteristics to that when the ADC input is white Gaussian noise. Additionally, this paper discusses what occurs when the ADC is strongly driven into the clipping region. This discussion is enhanced by comparing the ADC to a limiter in this highly distorted region. Analysis and simulation results are provided to describe ADC performance characteristics in this highly distorted region.
{"title":"Analog-to-Digital Converter Loading Analysis Considerations for Satellite Communications Systems","authors":"D. Taggart, Rajendra Kumar, Y. Krikorian, G. Goo, Joseph Chen, Robert Martinez, Tom Tam, Edward Serhal","doi":"10.1109/AERO.2007.352939","DOIUrl":"https://doi.org/10.1109/AERO.2007.352939","url":null,"abstract":"In contemporary communication satellite systems, uplink radio frequency (RF) signals are amplified, downconverted to intermediate frequency (IF) and/or baseband, and after appropriate filtering, are input to an analog-to-digital converter (ADC). The ADC digital output is signal processed for a variety of purposes, such as signal channelization and switching. In these systems, a foremost realization problem is the ADC, which must operate to satisfy the sampling theorem, which necessitates a sampling rate at least twice the received signal bandwidth. When the signal consists of numerous multiplexed signals, a critical matter in ADC performance is the degree of signal clipping, which arises when the instantaneous ADC input signal magnitude surpasses the maximum range of the ADC. Since at least some clipping is often present, the total ADC noise output consists of clipping plus quantization noise. A figure of merit for the ADC is the signal-to-noise ratio (SNR) of the ADC, which is defined as the ratio of input signal average power to the ADC output average noise power. The SNR is determined by, among other things, the ADC load factor, which is the ratio of the ADC input signal average power, and the ADC maximum peak power output. This paper describes analysis and simulation results on SNR versus the ADC load factor when the input signal is composed of many digitally modulated carriers. A nine-signal 8-ary phase shift key (8-PSK) modulated carrier case is considered with each signal band limited. It is important to note that for this particular ADC input, it is shown that the probability density function (PDF) is Gaussian-like. This is significant since this means that the SNR versus ADC load factor curve for the nine 8-PSK signal case will have nearly identical characteristics to that when the ADC input is white Gaussian noise. Additionally, this paper discusses what occurs when the ADC is strongly driven into the clipping region. This discussion is enhanced by comparing the ADC to a limiter in this highly distorted region. Analysis and simulation results are provided to describe ADC performance characteristics in this highly distorted region.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"5 1","pages":"1-16"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88733235","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}
Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352855
J. Booth
This paper will be a continuation of the work presented last year at the 2006 IEEE Aerospace Conference in a paper titled," Electromagnetic Study of Multilayer Media", Joel P. Booth. This paper will discuss the process of a basic electromagnetic analysis for a multilayer material. This discussion will include computer simulations, real world situations and graduate studies. The relationships between different materials and their effects on electromagnetic energy will be explored. This effort is being conducted in the RF Technology Division of the Applied Sensors, Guidance, and Electronics Directorate of the Aviation and Missile Research, Development, and Engineering Center (AMRDEC) on the Redstone Arsenal in Huntsville, Alabama. This paper will explore using material properties and geometric configurations to redirect electromagnetic energy as a means create a low-cost, low-loss radome material (or radome design) to extend the current range of both gimbaled and electronically-steered phased arrays. At the present time, most missile seekers are restricted to 60deg in azimuth and elevation due to (1) mechanical limitations of the gimbal and also to (2) limitations of electronically steerable systems due to the phase shifter elements of the system creating large sidelobes at large angles. The concept is to extend steering range without the addition of mechanical means or more intensive processing while not impeding the function of multimode configurations. The data obtained from this effort will be used in the selection of new missile seeker system parameters. The effects of the research could drive cost, manufacturing, and new design concepts. The results could also effect the combination of modes in radar design to achieve the mission. The goal of this research is to develop and investigate a concept that is low-cost, low-loss, easy to manufacture, and novel in design.
这篇论文将是去年在2006年IEEE航空航天会议上发表的一篇题为“多层介质的电磁研究”的论文的延续，作者是Joel P. Booth。本文将讨论多层材料的基本电磁分析过程。这个讨论将包括计算机模拟，现实世界的情况和研究生研究。将探讨不同材料之间的关系及其对电磁能的影响。这项工作是在位于阿拉巴马州亨茨维尔红石兵工厂的航空和导弹研究、开发和工程中心(AMRDEC)应用传感器、制导和电子理事会的射频技术部进行的。本文将探索利用材料特性和几何结构来重定向电磁能，作为一种创造低成本、低损耗的天线罩材料(或天线罩设计)的手段，以扩大平衡和电子控制相控阵的电流范围。目前，由于(1)万向节的机械限制和(2)由于系统的移相器元件在大角度产生大副瓣的限制，大多数导弹导引头在方位角和仰角上被限制为60度。其概念是在不增加机械手段或更密集的加工的情况下扩大转向范围，同时不妨碍多模式配置的功能。从这项工作中获得的数据将用于选择新的导弹导引头系统参数。这项研究的影响可能会推动成本、制造和新的设计概念。结果也可能影响雷达设计模式的组合以实现任务。本研究的目标是开发和研究一种低成本、低损耗、易于制造和设计新颖的概念。
{"title":"Electromagnetic Redirection thru Material Manipulation","authors":"J. Booth","doi":"10.1109/AERO.2007.352855","DOIUrl":"https://doi.org/10.1109/AERO.2007.352855","url":null,"abstract":"This paper will be a continuation of the work presented last year at the 2006 IEEE Aerospace Conference in a paper titled,\" Electromagnetic Study of Multilayer Media\", Joel P. Booth. This paper will discuss the process of a basic electromagnetic analysis for a multilayer material. This discussion will include computer simulations, real world situations and graduate studies. The relationships between different materials and their effects on electromagnetic energy will be explored. This effort is being conducted in the RF Technology Division of the Applied Sensors, Guidance, and Electronics Directorate of the Aviation and Missile Research, Development, and Engineering Center (AMRDEC) on the Redstone Arsenal in Huntsville, Alabama. This paper will explore using material properties and geometric configurations to redirect electromagnetic energy as a means create a low-cost, low-loss radome material (or radome design) to extend the current range of both gimbaled and electronically-steered phased arrays. At the present time, most missile seekers are restricted to 60deg in azimuth and elevation due to (1) mechanical limitations of the gimbal and also to (2) limitations of electronically steerable systems due to the phase shifter elements of the system creating large sidelobes at large angles. The concept is to extend steering range without the addition of mechanical means or more intensive processing while not impeding the function of multimode configurations. The data obtained from this effort will be used in the selection of new missile seeker system parameters. The effects of the research could drive cost, manufacturing, and new design concepts. The results could also effect the combination of modes in radar design to achieve the mission. The goal of this research is to develop and investigate a concept that is low-cost, low-loss, easy to manufacture, and novel in design.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"11 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89338565","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}
Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352922
M. Sudolsky
Commercial-off-the-shelf (COTS) aircraft condition monitoring system (ACMS) hardware supports critical health management functionality; real-time event forwarding or recording of any parametric/discrete data can be performed using the digital flight data acquisition unit (DFDAU). The ubiquitous DFDAU is the predominant fielded hardware supporting this important functionality -every 737, 757 and 767 airplane must have the unit installed and the same DFDAU can be used on any of the three aircraft (derivative implementations are on other airplane models). A predominant application of integrated vehicle health management (IVHM) is DFDAU-based flight operation quality assurance (FOQA) and/or engine condition monitoring (ECM) programs, and leveraging this on-going maintenance frame recording and/or Data Link type reporting can lead to dramatically improved IVHM operations. Critical functionality supports ACMS updates or continual maturation prior to a following vehicle mission, and associated Boeing On-Line Diagnostic Reporting (BOLDRtrade) IVHM data bus optimization methods are discussed. All of the aforementioned DFDAU features and future enhancements such as the import of code for sophisticated reasoning are planned for Boeing IVHM Lab prototyping.
{"title":"IVHM Solutions Using Commercially-available Aircraft Condition Monitoring Systems","authors":"M. Sudolsky","doi":"10.1109/AERO.2007.352922","DOIUrl":"https://doi.org/10.1109/AERO.2007.352922","url":null,"abstract":"Commercial-off-the-shelf (COTS) aircraft condition monitoring system (ACMS) hardware supports critical health management functionality; real-time event forwarding or recording of any parametric/discrete data can be performed using the digital flight data acquisition unit (DFDAU). The ubiquitous DFDAU is the predominant fielded hardware supporting this important functionality -every 737, 757 and 767 airplane must have the unit installed and the same DFDAU can be used on any of the three aircraft (derivative implementations are on other airplane models). A predominant application of integrated vehicle health management (IVHM) is DFDAU-based flight operation quality assurance (FOQA) and/or engine condition monitoring (ECM) programs, and leveraging this on-going maintenance frame recording and/or Data Link type reporting can lead to dramatically improved IVHM operations. Critical functionality supports ACMS updates or continual maturation prior to a following vehicle mission, and associated Boeing On-Line Diagnostic Reporting (BOLDRtrade) IVHM data bus optimization methods are discussed. All of the aforementioned DFDAU features and future enhancements such as the import of code for sophisticated reasoning are planned for Boeing IVHM Lab prototyping.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"20 1","pages":"1-8"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87380178","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}
Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352699
David R. Thompson, Rebecca Castano
Detecting rocks in images is a valuable capability for autonomous planetary science. Rock detection facilitates selective data collection and return. It also assists with image analysis on Earth. This work reviews seven rock detection algorithms from the autonomous science literature. We evaluate each algorithm with respect to several autonomous geology applications. Tests show the algorithms' performance on Mars Exploration Rover imagery, terrestrial images from analog environments, and synthetic images from a Mars terrain simulator. This provides insight into the detectors' performance under different imaging conditions.
{"title":"Performance Comparison of Rock Detection Algorithms for Autonomous Planetary Geology","authors":"David R. Thompson, Rebecca Castano","doi":"10.1109/AERO.2007.352699","DOIUrl":"https://doi.org/10.1109/AERO.2007.352699","url":null,"abstract":"Detecting rocks in images is a valuable capability for autonomous planetary science. Rock detection facilitates selective data collection and return. It also assists with image analysis on Earth. This work reviews seven rock detection algorithms from the autonomous science literature. We evaluate each algorithm with respect to several autonomous geology applications. Tests show the algorithms' performance on Mars Exploration Rover imagery, terrestrial images from analog environments, and synthetic images from a Mars terrain simulator. This provides insight into the detectors' performance under different imaging conditions.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"90 1","pages":"1-9"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90589273","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}
Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352767
L. Markosian, M. Mansouri-Samani, P. Mehlitz, T. Pressburger
Model checking is a verification technique developed in the 1980s that has a history of industrial application in hardware verification and verification of communications protocol specifications. Program model checking is a technique for model checking software in which the program itself is the model to be checked. Program model checking has shown potential for detecting software defects that are extremely difficult to detect through traditional testing. The technique has been the subject of research and relatively small-scale applications but faces several barriers to wider deployment. This paper is a report on continuing work applying Java PathFinder (JPF), a program model checker developed at NASA Ames Research Center, to the shuttle abort flight management system, a situational awareness application originally developed for the space shuttle. The paper provides background on the model checking tools that were used and the target application, and then focuses on the application of a "design for verification" (D4V) principle and its effect on model checking. The case study helps validate the applicability of program model checking technology to real NASA flight software. A related conclusion is that application of D4V principles can increase the efficiency of model checking in detecting subtle software defects. The paper is oriented toward software engineering technology transfer personnel and software practitioners considering introducing program model checking technology into their organizations.
{"title":"Program Model Checking Using Design-for-Verification: NASA Flight Software Case Study","authors":"L. Markosian, M. Mansouri-Samani, P. Mehlitz, T. Pressburger","doi":"10.1109/AERO.2007.352767","DOIUrl":"https://doi.org/10.1109/AERO.2007.352767","url":null,"abstract":"Model checking is a verification technique developed in the 1980s that has a history of industrial application in hardware verification and verification of communications protocol specifications. Program model checking is a technique for model checking software in which the program itself is the model to be checked. Program model checking has shown potential for detecting software defects that are extremely difficult to detect through traditional testing. The technique has been the subject of research and relatively small-scale applications but faces several barriers to wider deployment. This paper is a report on continuing work applying Java PathFinder (JPF), a program model checker developed at NASA Ames Research Center, to the shuttle abort flight management system, a situational awareness application originally developed for the space shuttle. The paper provides background on the model checking tools that were used and the target application, and then focuses on the application of a \"design for verification\" (D4V) principle and its effect on model checking. The case study helps validate the applicability of program model checking technology to real NASA flight software. A related conclusion is that application of D4V principles can increase the efficiency of model checking in detecting subtle software defects. The paper is oriented toward software engineering technology transfer personnel and software practitioners considering introducing program model checking technology into their organizations.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"151 1","pages":"1-9"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86644882","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}
Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352705
K. Nickels, Eric Huber, M. DiCicco
The project described in this paper designed and implemented a hand-eye calibration method for manipulators under observation by stereo cameras. This method has been utilized on Johnson Space Center's Robonaut, and on a planetary manipulator mock-up at the Jet Propulsion Laboratory. The intent of this calibration is to improve the manipulator's hand-eye coordination. The approach uses kinematic and stereo vision measurements, namely the joint angles self-reported by the arm and 3-D positions of a calibration fixture as measured by vision, to estimate the transformation from the arm's base coordinate system to its hand coordinate system and to its vision coordinate system. In this formulation, the stereo measurements are assumed to be accurate, and any mismatches are absorbed in a modified model of the arm. These methods have shown to reduce mismatch between kinematically derived positions and visually derived positions on Robonaut Unit A from a mean of 13.75 cm to a mean of 1.85 cm. Improved performance in semi-autonomous tasks is also described. On JPL's manipulator, with kinematics similar to that of the Mars Exploration Rover, the calibration reduced the mismatch from 15.26 mm to between 3 mm and 5.5 mm.
{"title":"Hand-Eye Calibratilon Using Active Vision","authors":"K. Nickels, Eric Huber, M. DiCicco","doi":"10.1109/AERO.2007.352705","DOIUrl":"https://doi.org/10.1109/AERO.2007.352705","url":null,"abstract":"The project described in this paper designed and implemented a hand-eye calibration method for manipulators under observation by stereo cameras. This method has been utilized on Johnson Space Center's Robonaut, and on a planetary manipulator mock-up at the Jet Propulsion Laboratory. The intent of this calibration is to improve the manipulator's hand-eye coordination. The approach uses kinematic and stereo vision measurements, namely the joint angles self-reported by the arm and 3-D positions of a calibration fixture as measured by vision, to estimate the transformation from the arm's base coordinate system to its hand coordinate system and to its vision coordinate system. In this formulation, the stereo measurements are assumed to be accurate, and any mismatches are absorbed in a modified model of the arm. These methods have shown to reduce mismatch between kinematically derived positions and visually derived positions on Robonaut Unit A from a mean of 13.75 cm to a mean of 1.85 cm. Improved performance in semi-autonomous tasks is also described. On JPL's manipulator, with kinematics similar to that of the Mars Exploration Rover, the calibration reduced the mismatch from 15.26 mm to between 3 mm and 5.5 mm.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"98 1","pages":"1-9"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85329093","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}
Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.352788
S. Serva, F. Colone, P. Lombardo
This paper deals with the potentialities obtained by splitting the passive antenna of a space-based bistatic SAR into multiple sub-apertures. A preliminary analysis is performed in order to identify the main orbital and system design parameters for a satellite equipped with a multichannel passive radar sensor. The effectiveness of the resulting bistatic system is investigated paying particular attention to the assessment of the achievable MTI capabilities. In particular the conceived system is shown to allow: (i) clutter cancellation and detection of slowly moving ground targets for surveillance purpose, and (ii) relocation of moving targets in high resolution SAR images.
{"title":"A Study for a Space-Based Passive Multi-Channel SAR","authors":"S. Serva, F. Colone, P. Lombardo","doi":"10.1109/AERO.2007.352788","DOIUrl":"https://doi.org/10.1109/AERO.2007.352788","url":null,"abstract":"This paper deals with the potentialities obtained by splitting the passive antenna of a space-based bistatic SAR into multiple sub-apertures. A preliminary analysis is performed in order to identify the main orbital and system design parameters for a satellite equipped with a multichannel passive radar sensor. The effectiveness of the resulting bistatic system is investigated paying particular attention to the assessment of the achievable MTI capabilities. In particular the conceived system is shown to allow: (i) clutter cancellation and detection of slowly moving ground targets for surveillance purpose, and (ii) relocation of moving targets in high resolution SAR images.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"37 1","pages":"1-11"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85341726","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}
Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.353091
P. Pingree, J. Blavier, G. Toon, D. Bekker
A proposed Mars Scout Mission known as MARVEL is vying for the 2011 launch opportunity. One of its primary instruments, MATMOS, will produce large volumes of data in short, 3-minute bursts during its on-orbit observation of sunrise and sunset. The remaining orbit time of 112 minutes is available for on-board data processing to reduce data volume prior to downlink. This data processing relies heavily on floating-point FFTs. The Xilinx Virtex-II Pro FPGA was evaluated in a previous research task, but could not meet the performance requirements, even with an integrated soft-core floating-point unit (FPU). The next-generation Virtex-4 FPGA contains an auxiliary processor unit (APU) that provides a flexible high bandwidth interface for fabric co-processor modules (FCM) to the PowerPC405 core. In this paper we show that coupling the FPU FCM with the APU provides sufficient computation power to meet MATMOS's data processing requirements when implemented in a multi-processor, dual-FPGA system.
一个被称为MARVEL的火星侦察任务正在争夺2011年的发射机会。它的主要仪器之一MATMOS将在对日出和日落的在轨观测期间，以3分钟的短时间爆发产生大量数据。剩余的轨道时间为112分钟，可用于星上数据处理，以便在下行之前减少数据量。这种数据处理严重依赖于浮点fft。Xilinx Virtex-II Pro FPGA在之前的研究任务中进行了评估，但即使具有集成的软核浮点单元(FPU)，也无法满足性能要求。下一代Virtex-4 FPGA包含一个辅助处理器单元(APU)，为fabric协处理器模块(FCM)与PowerPC405核心提供灵活的高带宽接口。在本文中，我们展示了当在多处理器，双fpga系统中实现时，FPU FCM与APU的耦合提供了足够的计算能力来满足MATMOS的数据处理要求。
{"title":"An FPGA/SoC Approach to On-Board Data Processing Enabling New Mars Science with Smart Payloads","authors":"P. Pingree, J. Blavier, G. Toon, D. Bekker","doi":"10.1109/AERO.2007.353091","DOIUrl":"https://doi.org/10.1109/AERO.2007.353091","url":null,"abstract":"A proposed Mars Scout Mission known as MARVEL is vying for the 2011 launch opportunity. One of its primary instruments, MATMOS, will produce large volumes of data in short, 3-minute bursts during its on-orbit observation of sunrise and sunset. The remaining orbit time of 112 minutes is available for on-board data processing to reduce data volume prior to downlink. This data processing relies heavily on floating-point FFTs. The Xilinx Virtex-II Pro FPGA was evaluated in a previous research task, but could not meet the performance requirements, even with an integrated soft-core floating-point unit (FPU). The next-generation Virtex-4 FPGA contains an auxiliary processor unit (APU) that provides a flexible high bandwidth interface for fabric co-processor modules (FCM) to the PowerPC405 core. In this paper we show that coupling the FPU FCM with the APU provides sufficient computation power to meet MATMOS's data processing requirements when implemented in a multi-processor, dual-FPGA system.","PeriodicalId":6295,"journal":{"name":"2007 IEEE Aerospace Conference","volume":"280 5 1","pages":"1-12"},"PeriodicalIF":0.0,"publicationDate":"2007-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86574256","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}
Pub Date : 2007-03-03DOI: 10.1109/AERO.2007.353007
B. Saif, Marcel Bluth, B. Eegholm, Barbara Zukowski, R. Keski-kuha, Peter Blake
Development of many new technologies is required to successfully produce the large, lightweight, deployable, cryogenic telescope with segmented primary mirror for the James Webb Space Telescope (JWST) mission. One of the technologies is interferometry to verify structural deformations in large, deployable, lightweight, cryogenic, precision structures to nanometer level accuracy. An instantaneous acquisition phase shifting speckle interferometer was designed and built to support the development of JWST optical telescope element (OTE) primary mirror backplane. This paper discusses characterization of the electronic speckle pattern interferometer (SPS-DSPI) developed for JWST to verify its capability to measure structural deformations in large composite structures at cryogenic temperature.
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