Pub Date : 2012-03-03DOI: 10.1109/AERO.2012.6187438
R. Morris, K. Venable, J. Lindsey
NASA and the international community are investing in the development of a commercial transportation infrastructure that includes the increased use of rotorcraft, specifically helicopters and civil tilt rotors. However, there is significant concern over the impact of noise on the communities surrounding the transportation facilities. One way to address the rotorcraft noise problem is by exploiting powerful search techniques coming from artificial intelligence coupled with simulation and field tests to design low-noise flight profiles which can be tested in simulation or through field tests. This paper investigates the use of simulation based on predictive physical models to facilitate the search for low-noise trajectories using a class of automated search algorithms called local search. A novel feature of this approach is the ability to incorporate constraints directly into the problem formulation that addresses passenger safety and comfort.
{"title":"Simulation to support local search in trajectory optimization planning","authors":"R. Morris, K. Venable, J. Lindsey","doi":"10.1109/AERO.2012.6187438","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187438","url":null,"abstract":"NASA and the international community are investing in the development of a commercial transportation infrastructure that includes the increased use of rotorcraft, specifically helicopters and civil tilt rotors. However, there is significant concern over the impact of noise on the communities surrounding the transportation facilities. One way to address the rotorcraft noise problem is by exploiting powerful search techniques coming from artificial intelligence coupled with simulation and field tests to design low-noise flight profiles which can be tested in simulation or through field tests. This paper investigates the use of simulation based on predictive physical models to facilitate the search for low-noise trajectories using a class of automated search algorithms called local search. A novel feature of this approach is the ability to incorporate constraints directly into the problem formulation that addresses passenger safety and comfort.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"4 1","pages":"1-8"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77641381","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 : 2012-03-03DOI: 10.1109/AERO.2012.6187155
David Robinson, T. Okajima, P. Serlemitsos, Y. Soong
The Astro-H is led by the Japanese Space Agency (JAXA) in collaboration with many other institutions including the NASA Goddard Space Flight Center. Goddard's contributions include two soft X-ray telescopes (SXTs). The telescopes have an effective area of 562 cm2 at 1 keV and 425 cm2 at 6 keV with an image quality requirement of 1.7 arc-minutes half power diameter (HPD). The engineering model has demonstrated 1.1 arc-minutes HPD error. The design of the SXT is based on the successful Suzaku mission mirrors with some enhancements to improve the image quality. Two major enhancements are bonding the X-ray mirror foils to alignment bars instead of allowing the mirrors to float, and fabricating alignment bars with grooves within 5 microns of accuracy. An engineering model SXT was recently built and subjected to several tests including vibration, thermal, and X-ray performance in a beamline. Several lessons were learned during this testing that will be incorporated in the flight design. Test results and optical performance are discussed, along with a description of the design of the SXT.
{"title":"The Astro-H soft X-ray mirror","authors":"David Robinson, T. Okajima, P. Serlemitsos, Y. Soong","doi":"10.1109/AERO.2012.6187155","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187155","url":null,"abstract":"The Astro-H is led by the Japanese Space Agency (JAXA) in collaboration with many other institutions including the NASA Goddard Space Flight Center. Goddard's contributions include two soft X-ray telescopes (SXTs). The telescopes have an effective area of 562 cm2 at 1 keV and 425 cm2 at 6 keV with an image quality requirement of 1.7 arc-minutes half power diameter (HPD). The engineering model has demonstrated 1.1 arc-minutes HPD error. The design of the SXT is based on the successful Suzaku mission mirrors with some enhancements to improve the image quality. Two major enhancements are bonding the X-ray mirror foils to alignment bars instead of allowing the mirrors to float, and fabricating alignment bars with grooves within 5 microns of accuracy. An engineering model SXT was recently built and subjected to several tests including vibration, thermal, and X-ray performance in a beamline. Several lessons were learned during this testing that will be incorporated in the flight design. Test results and optical performance are discussed, along with a description of the design of the SXT.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"2 1","pages":"1-9"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91294797","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 : 2012-03-03DOI: 10.1109/AERO.2012.6187225
F. Kraja, G. Acher, A. Bode
Future space application will require High Performance Computing (HPC) capabilities to be available on board of future spacecrafts. To cope with this requirement, multi and many-core processor technologies have to be integrated in the computing platforms of the spacecraft. One of the most important requirements, coming from the nature of space applications, is the efficiency in terms of performance per Watt. In order to improve the efficiency of such systems, algorithms and applications have to be optimized and scaled to the number of cores available in the computing platform. In this paper we describe the parallelization techniques applied to a Synthetic Aperture Radar (SAR) application based on the 2-Dimentional Fourier Matched Filtering and Interpolation (2DFMFI) Algorithm. Other than sequential optimizations, we applied parallelization techniques for shared memory, distributed shared memory and distributed memory environments, using parallel programming models like OpenMP and MPI. It turns out that parallelizing this type of algorithms is not an easy and straightforward task to do, but with a little bit of effort, one can improve performance and scalability, increasing the level of efficiency.
{"title":"Parallelization techniques for the 2D Fourier Matched Filtering and Interpolation SAR algorithm","authors":"F. Kraja, G. Acher, A. Bode","doi":"10.1109/AERO.2012.6187225","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187225","url":null,"abstract":"Future space application will require High Performance Computing (HPC) capabilities to be available on board of future spacecrafts. To cope with this requirement, multi and many-core processor technologies have to be integrated in the computing platforms of the spacecraft. One of the most important requirements, coming from the nature of space applications, is the efficiency in terms of performance per Watt. In order to improve the efficiency of such systems, algorithms and applications have to be optimized and scaled to the number of cores available in the computing platform. In this paper we describe the parallelization techniques applied to a Synthetic Aperture Radar (SAR) application based on the 2-Dimentional Fourier Matched Filtering and Interpolation (2DFMFI) Algorithm. Other than sequential optimizations, we applied parallelization techniques for shared memory, distributed shared memory and distributed memory environments, using parallel programming models like OpenMP and MPI. It turns out that parallelizing this type of algorithms is not an easy and straightforward task to do, but with a little bit of effort, one can improve performance and scalability, increasing the level of efficiency.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"85 1","pages":"1-10"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91363899","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 : 2012-03-03DOI: 10.1109/AERO.2012.6187367
A. Fijany, A. Barrett, F. Vatan
In this paper we present a novel fast model-based diagnosis engine. Our novel engine is based on a two-step approach to diagnosis, i.e., off-line system analysis and on-line diagnosis. The efficiency of our novel method results from the fact that, by performing a detailed analysis of the target system, it drastically reduces the amount of computation needed for diagnosis. In particular, our new algorithm relies on the concept and use of minimal set of ARRs to achieve a much better efficiency in the diagnosis process. Our novel diagnosis engine is based on our two recent results. First, it uses our recently developed method for generation of the complete set of ARRs. Second, it uses the minimal set of ARRs; as we have recently shown that for any given number of faults, i.e., single, double, triple, etc., there is a corresponding minimal set of ARRs which is usually significantly smaller than the complete set of ARRs. We present and discuss the performance of our diagnosis engine by its application to several examples. We show that, even by using a non-exoneration assumption, we achieve a much better efficiency over the GDE as well as full ARR-based approaches for model-based diagnosis.
{"title":"A fast model-based diagnosis engine","authors":"A. Fijany, A. Barrett, F. Vatan","doi":"10.1109/AERO.2012.6187367","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187367","url":null,"abstract":"In this paper we present a novel fast model-based diagnosis engine. Our novel engine is based on a two-step approach to diagnosis, i.e., off-line system analysis and on-line diagnosis. The efficiency of our novel method results from the fact that, by performing a detailed analysis of the target system, it drastically reduces the amount of computation needed for diagnosis. In particular, our new algorithm relies on the concept and use of minimal set of ARRs to achieve a much better efficiency in the diagnosis process. Our novel diagnosis engine is based on our two recent results. First, it uses our recently developed method for generation of the complete set of ARRs. Second, it uses the minimal set of ARRs; as we have recently shown that for any given number of faults, i.e., single, double, triple, etc., there is a corresponding minimal set of ARRs which is usually significantly smaller than the complete set of ARRs. We present and discuss the performance of our diagnosis engine by its application to several examples. We show that, even by using a non-exoneration assumption, we achieve a much better efficiency over the GDE as well as full ARR-based approaches for model-based diagnosis.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"6 1","pages":"1-11"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"87273336","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 : 2012-03-03DOI: 10.1109/AERO.2012.6187303
K. Miller, J. Masciarelli, R. Rohrschneider
Relative Navigation (RelNav) applications, have been identified as an enabling function of many of NASA's future mission architectures, including Rendezvous, Proximity Operations and Docking (RPOD), as well as planetary surface rendezvous and landing, surface mobility and in space servicing. Functional capabilities have been maintained and exercised for decades, but recent design and test efforts have validated revolutionary improvements in functionality and performance levels of active and passive relative navigation sensors and processing, providing a pathway for advanced autonomous operations The advances are multidisciplinary and include compact, multimission algorithm design, high performance camera technology, flash LIDAR advances, spatial light modulation and systems engineering. Many of the key technologies have been demonstrated in airborne test programs, and some of the key flash LIDAR advances were flight qualified on the Sensor Test for Orion RelNav Risk Mitigation (STORRM) relative navigation sensor suite, flown in 2011 on STS-134. The STORRM sensor suite has been developed to provide a highly reliable, compact, lightweight solution for human and robotic missions. This paper provides progress and performance results associated with relative navigation via STORRM, as well as other RelNav technology advancement and relevance to future mission applications. Cooperative and noncooperative mission application environments with natural and manmade targets and feature sets and varying degrees of autonomy are addressed.
{"title":"Advances in multi-mission autonomous rendezvous and docking and relative navigation capabilities","authors":"K. Miller, J. Masciarelli, R. Rohrschneider","doi":"10.1109/AERO.2012.6187303","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187303","url":null,"abstract":"Relative Navigation (RelNav) applications, have been identified as an enabling function of many of NASA's future mission architectures, including Rendezvous, Proximity Operations and Docking (RPOD), as well as planetary surface rendezvous and landing, surface mobility and in space servicing. Functional capabilities have been maintained and exercised for decades, but recent design and test efforts have validated revolutionary improvements in functionality and performance levels of active and passive relative navigation sensors and processing, providing a pathway for advanced autonomous operations The advances are multidisciplinary and include compact, multimission algorithm design, high performance camera technology, flash LIDAR advances, spatial light modulation and systems engineering. Many of the key technologies have been demonstrated in airborne test programs, and some of the key flash LIDAR advances were flight qualified on the Sensor Test for Orion RelNav Risk Mitigation (STORRM) relative navigation sensor suite, flown in 2011 on STS-134. The STORRM sensor suite has been developed to provide a highly reliable, compact, lightweight solution for human and robotic missions. This paper provides progress and performance results associated with relative navigation via STORRM, as well as other RelNav technology advancement and relevance to future mission applications. Cooperative and noncooperative mission application environments with natural and manmade targets and feature sets and varying degrees of autonomy are addressed.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"77 1","pages":"1-9"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90628580","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 : 2012-03-03DOI: 10.1109/AERO.2012.6187123
G. Bussey, W. Horne
The National Aeronautics and Space Administration's (NASA) Goddard Space Flight Center (GSFC) has developed a tool for generating representative schedules of satellite communication sessions to aid in architecture assessments and data throughput analyses. Essentially, the tool provides an efficient method to address the Multi-Satellite Scheduling Problem (MSSP), an example competitive resource allocation problem. The tool interacts with a commercially available simulation environment, Satellite Tool Kit (STK), using a custom developed MATLAB interface. This paper details the reasoning behind the development of the tool, provides a description of the genetic algorithms used in the tool, and discusses example applications of the tool in supporting the future development of space missions and NASA's space communications infrastructure.
{"title":"A multiple asset scheduler for satellite data throughput and variable rate analysis","authors":"G. Bussey, W. Horne","doi":"10.1109/AERO.2012.6187123","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187123","url":null,"abstract":"The National Aeronautics and Space Administration's (NASA) Goddard Space Flight Center (GSFC) has developed a tool for generating representative schedules of satellite communication sessions to aid in architecture assessments and data throughput analyses. Essentially, the tool provides an efficient method to address the Multi-Satellite Scheduling Problem (MSSP), an example competitive resource allocation problem. The tool interacts with a commercially available simulation environment, Satellite Tool Kit (STK), using a custom developed MATLAB interface. This paper details the reasoning behind the development of the tool, provides a description of the genetic algorithms used in the tool, and discusses example applications of the tool in supporting the future development of space missions and NASA's space communications infrastructure.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"95 12 1","pages":"1-8"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91153230","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 : 2012-03-03DOI: 10.1109/AERO.2012.6187361
A. Hassan, I. Manarvi
As aero-engines operate, metal and other material particles are removed from the contact surfaces and are carried away in the flow of lubricating oil. Spectrometric Oil Analysis Program (SOAP) is a powerful tool for elemental analysis of structural metals in the lubricating oils circulating inside the machine, and is suitable for determining wear metal quantity, elemental composition, rate of wear and its source. The oil samples from the aero-engines are analyzed through spectrometry and the readings are assessed against pre-defined values to ascertain the physical health of the engines. This method is employed to continuously monitor the condition of the engine internal parts without any stripping, thus reducing maintenance time and costs. The predefined values or limits for SOAP are defined by the Original Equipment Manufacturer and are normally formalized during design process of the equipment. For the Chinese range engines powering the fighter jet aircraft, the limits for SOAP are not defined and thus this valuable technique cannot be fully applied to these engines. As a consequence the benefits of continuous condition monitoring together with reduced maintenance cost and time are not fully accrued. Iron (Fe) is the major element of the engine internal parts and its inclusion in oil sample gives a clear picture of the wear and tear of the engine internal parts. In order to accrue benefits of SOAP on Chinese range aero-engines there is a need to define the alert and hazard thresholds limits for SOAP on these engines. Once defined, the SOAP data can be used to decide about the continued operation of the engine or its induction for maintenance. In this paper the SOAP data for Chinese range engines operating in the fighter aircraft is collected and then it is statistically analysed to establish the limits for alerts and hazard for Iron (Fe).
{"title":"Analysis of spectrometric data of aeroengines to establish hazard threshold limits for Iron content","authors":"A. Hassan, I. Manarvi","doi":"10.1109/AERO.2012.6187361","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187361","url":null,"abstract":"As aero-engines operate, metal and other material particles are removed from the contact surfaces and are carried away in the flow of lubricating oil. Spectrometric Oil Analysis Program (SOAP) is a powerful tool for elemental analysis of structural metals in the lubricating oils circulating inside the machine, and is suitable for determining wear metal quantity, elemental composition, rate of wear and its source. The oil samples from the aero-engines are analyzed through spectrometry and the readings are assessed against pre-defined values to ascertain the physical health of the engines. This method is employed to continuously monitor the condition of the engine internal parts without any stripping, thus reducing maintenance time and costs. The predefined values or limits for SOAP are defined by the Original Equipment Manufacturer and are normally formalized during design process of the equipment. For the Chinese range engines powering the fighter jet aircraft, the limits for SOAP are not defined and thus this valuable technique cannot be fully applied to these engines. As a consequence the benefits of continuous condition monitoring together with reduced maintenance cost and time are not fully accrued. Iron (Fe) is the major element of the engine internal parts and its inclusion in oil sample gives a clear picture of the wear and tear of the engine internal parts. In order to accrue benefits of SOAP on Chinese range aero-engines there is a need to define the alert and hazard thresholds limits for SOAP on these engines. Once defined, the SOAP data can be used to decide about the continued operation of the engine or its induction for maintenance. In this paper the SOAP data for Chinese range engines operating in the fighter aircraft is collected and then it is statistically analysed to establish the limits for alerts and hazard for Iron (Fe).","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"28 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"72736387","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 : 2012-03-03DOI: 10.1109/AERO.2012.6187052
A. Parness, M. Frost
The Microspine Drill, a self-contained anchor and rotary percussive drill, is presented. The Microspine Drill can core in an inverted orientation into consolidated rock, a harder-than-zero-g proof of concept. The anchor extends the use of mi-crospines to microgravity environments. Microspines, originally developed for climbing robots, use arrays of hooks with passive suspension structures to opportunistically grasp rough surfaces and share loads across many contacts. Utilizing radial arrays and hierarchical compliance, this new system creates omnidirectional anchors. Prototypes have demonstrated anchoring strengths of >;155 N tangent to, >;150 N at 45° to, and >;180 N normal to the rock surface. Using a weight-on-bit of ~60N, 20 mm diameter boreholes were drilled 83 mm deep into vesicular basalt and a'a samples while retaining 12 mm diameter cores. The anchor-drill combination can be used to acquire samples and set up rope networks during future manned missions to near earth objects. The instrument also enables gravity independent sample acquisition from rock surfaces for science missions to asteroids, comets, or the walls and ceilings of lava tubes, craters, caves, and other extreme planetary terrains.
{"title":"Microgravity coring: A self-contained anchor and drill for consolidated rock","authors":"A. Parness, M. Frost","doi":"10.1109/AERO.2012.6187052","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187052","url":null,"abstract":"The Microspine Drill, a self-contained anchor and rotary percussive drill, is presented. The Microspine Drill can core in an inverted orientation into consolidated rock, a harder-than-zero-g proof of concept. The anchor extends the use of mi-crospines to microgravity environments. Microspines, originally developed for climbing robots, use arrays of hooks with passive suspension structures to opportunistically grasp rough surfaces and share loads across many contacts. Utilizing radial arrays and hierarchical compliance, this new system creates omnidirectional anchors. Prototypes have demonstrated anchoring strengths of >;155 N tangent to, >;150 N at 45° to, and >;180 N normal to the rock surface. Using a weight-on-bit of ~60N, 20 mm diameter boreholes were drilled 83 mm deep into vesicular basalt and a'a samples while retaining 12 mm diameter cores. The anchor-drill combination can be used to acquire samples and set up rope networks during future manned missions to near earth objects. The instrument also enables gravity independent sample acquisition from rock surfaces for science missions to asteroids, comets, or the walls and ceilings of lava tubes, craters, caves, and other extreme planetary terrains.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"41 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77331766","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 : 2012-03-03DOI: 10.1109/AERO.2012.6187112
H. Benzerrouk, A. Nebylov, G. Yatsevitch
Original algorithms for navigation on the surface of Mars planet, especially applied to astronauts, are proposed in this paper. The autonomous navigation system for astronaut is based on inertial measurement unit (redundant) and Laser (redundant), which permits to localize and navigate in known environment and unknown environment constructing its map in real time, using adaptive algorithms and physical and natural constraints of astronaut's body. The estimation of the position of astronauts is done using non linear adaptive filters such as the Extended Kalman Filter (EKF) and other non linear variant filters. Finally, additional smart idea is to use Phobos and Deimos as navigation constellation in addition to one more satellite.
{"title":"Innovative astronaut navigation system based on smart integrated sensors","authors":"H. Benzerrouk, A. Nebylov, G. Yatsevitch","doi":"10.1109/AERO.2012.6187112","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187112","url":null,"abstract":"Original algorithms for navigation on the surface of Mars planet, especially applied to astronauts, are proposed in this paper. The autonomous navigation system for astronaut is based on inertial measurement unit (redundant) and Laser (redundant), which permits to localize and navigate in known environment and unknown environment constructing its map in real time, using adaptive algorithms and physical and natural constraints of astronaut's body. The estimation of the position of astronauts is done using non linear adaptive filters such as the Extended Kalman Filter (EKF) and other non linear variant filters. Finally, additional smart idea is to use Phobos and Deimos as navigation constellation in addition to one more satellite.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"72 1","pages":"1-9"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"77024802","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 : 2012-03-03DOI: 10.1109/AERO.2012.6187197
H. Gholizadeh, M. J. V. Zoej, B. Mojaradi
This paper aims at a decision fusion approach for combining three spectral unmixing methods to cluster hyperspectral data. Unlike standard image clustering techniques, analyzing hyperspectral data on a pure pixel basis may not be a true assumption. Meanwhile, multiple classifier systems often show better performance than each of the constituent classifiers. This is due to the fact that each classifier makes errors on different regions of the input space. With these facts in mind, this paper distills these two approaches into a single approach and exploits the advantages of both spectral unmixing algorithms and decision fusion methods. In this paper, three unmixing methods namely, Fully Constrained Least Squares (FCLS), Nonnegatively Constrained Least Squares (NCLS) and Sum-to-one Constrained Least Squares (SCLS) are employed as the ensemble classifiers and their results are combined at two different fusion levels: the abstract level and the measurement level. Experimental results on a real-world hyperspectral data proved that the proposed approach shows better clustering results compared to those of K-Means and Fuzzy c-Means in terms of the Adjusted Random Index (ARI) measure.
本文研究了一种结合三种光谱分解方法对高光谱数据进行聚类的决策融合方法。与标准的图像聚类技术不同，在纯像素的基础上分析高光谱数据可能不是一个真正的假设。同时，多个分类器系统通常比单个分类器表现出更好的性能。这是因为每个分类器在输入空间的不同区域会产生错误。考虑到这些事实，本文将这两种方法提炼成一种方法，并利用光谱分解算法和决策融合方法的优点。本文采用全约束最小二乘(FCLS)、非负约束最小二乘(NCLS)和和一约束最小二乘(SCLS)三种解混方法作为集成分类器，并将其结果在抽象级和测量级两个不同的融合层次上进行组合。在实际高光谱数据上的实验结果表明，该方法在调整随机指数(Adjusted Random Index, ARI)度量方面比K-Means和模糊c-Means具有更好的聚类效果。
{"title":"A decision fusion approach for clustering of hyperspectral data using spectral unmixing methods","authors":"H. Gholizadeh, M. J. V. Zoej, B. Mojaradi","doi":"10.1109/AERO.2012.6187197","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187197","url":null,"abstract":"This paper aims at a decision fusion approach for combining three spectral unmixing methods to cluster hyperspectral data. Unlike standard image clustering techniques, analyzing hyperspectral data on a pure pixel basis may not be a true assumption. Meanwhile, multiple classifier systems often show better performance than each of the constituent classifiers. This is due to the fact that each classifier makes errors on different regions of the input space. With these facts in mind, this paper distills these two approaches into a single approach and exploits the advantages of both spectral unmixing algorithms and decision fusion methods. In this paper, three unmixing methods namely, Fully Constrained Least Squares (FCLS), Nonnegatively Constrained Least Squares (NCLS) and Sum-to-one Constrained Least Squares (SCLS) are employed as the ensemble classifiers and their results are combined at two different fusion levels: the abstract level and the measurement level. Experimental results on a real-world hyperspectral data proved that the proposed approach shows better clustering results compared to those of K-Means and Fuzzy c-Means in terms of the Adjusted Random Index (ARI) measure.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"11 1","pages":"1-7"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"76420082","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}
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