Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446874
R. Taylor
The Gravity Recovery And Interior Laboratory (GRAIL) mission was the first Jet Propulsion Laboratory (JPL) project initiated under NASA's revised rules for space flight project management, NPR 7120.5D, “NASA Space Flight Program and Project Management Requirements.” 12 NASA selected GRAIL through a competitive Announcement of Opportunity (AO) process and funded its Phase B Preliminary Design effort. The first major milestone was institutional, the JPL Project Mission System Review (PMSR), which proved an excellent tune-up for the end-of-Phase B NASA life-cycle review, the Preliminary Design Review (PDR). Building on JPL experience with the Prometheus and Juno projects, the team successfully organized for and conducted these reviews on an aggressive schedule. The results were summarized in last year's IEEE paper, “Reducing NPR 7120.5D to Practice: Preparing for a Life-cycle Review.” GRAIL successfully passed its KDP-C Confirmation Review and initiated Phase C in March 2009.
{"title":"Reducing NPR 7120.5D to Practice: Preparing for a remote site Life-cycle Review","authors":"R. Taylor","doi":"10.1109/AERO.2010.5446874","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446874","url":null,"abstract":"The Gravity Recovery And Interior Laboratory (GRAIL) mission was the first Jet Propulsion Laboratory (JPL) project initiated under NASA's revised rules for space flight project management, NPR 7120.5D, “NASA Space Flight Program and Project Management Requirements.” 12 NASA selected GRAIL through a competitive Announcement of Opportunity (AO) process and funded its Phase B Preliminary Design effort. The first major milestone was institutional, the JPL Project Mission System Review (PMSR), which proved an excellent tune-up for the end-of-Phase B NASA life-cycle review, the Preliminary Design Review (PDR). Building on JPL experience with the Prometheus and Juno projects, the team successfully organized for and conducted these reviews on an aggressive schedule. The results were summarized in last year's IEEE paper, “Reducing NPR 7120.5D to Practice: Preparing for a Life-cycle Review.” GRAIL successfully passed its KDP-C Confirmation Review and initiated Phase C in March 2009.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"40 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125036598","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446981
Ying Lin, Fang Zhong, D. Aveline, M. Anderson, Shirley Y. Chung, J. Mennella, W. Schubert
We have designed and built a new Supercritical CO2 Cleaning (SCC) system1,2 to conduct cleaning efficiency studies using Supercritical CO2 and liquid CO2 to remove trace amounts of microbial and organic contaminants from spacecraft material surfaces. The objective of this task is to develop an effective CO2 cleaning method and to demonstrate and validate its ability to achieve ultra-clean surfaces of sample handling devices, sample storage units, and science instruments. This new capability will meet planetary protection and contamination control requirements for future Astrobiology science missions. The initial cleaning test results using this new cleaning device showed that both supercritical CO2 and liquid CO2 could achieve cleanliness levels of 0.01 µg/cm2 or less for hydrophobic contaminants. Experiments under supercritical condition using compressed Martian air mix, which consists of 95% CO2, produced similar cleaning effectiveness on the hydrophobic compounds. This opens up the possibility of further development potential for in situ CO2 cleaning and sterilization using Martian air for future Mars missions. We plan to further investigate the cleaning condition for hydrophilic compounds and bacterial spores, as well as introducing polar co-solvent to the cleaning apparatus.
{"title":"Supercritical CO2 Cleaning for planetary protection and contamination control","authors":"Ying Lin, Fang Zhong, D. Aveline, M. Anderson, Shirley Y. Chung, J. Mennella, W. Schubert","doi":"10.1109/AERO.2010.5446981","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446981","url":null,"abstract":"We have designed and built a new Supercritical CO2 Cleaning (SCC) system1,2 to conduct cleaning efficiency studies using Supercritical CO2 and liquid CO2 to remove trace amounts of microbial and organic contaminants from spacecraft material surfaces. The objective of this task is to develop an effective CO2 cleaning method and to demonstrate and validate its ability to achieve ultra-clean surfaces of sample handling devices, sample storage units, and science instruments. This new capability will meet planetary protection and contamination control requirements for future Astrobiology science missions. The initial cleaning test results using this new cleaning device showed that both supercritical CO2 and liquid CO2 could achieve cleanliness levels of 0.01 µg/cm2 or less for hydrophobic contaminants. Experiments under supercritical condition using compressed Martian air mix, which consists of 95% CO2, produced similar cleaning effectiveness on the hydrophobic compounds. This opens up the possibility of further development potential for in situ CO2 cleaning and sterilization using Martian air for future Mars missions. We plan to further investigate the cleaning condition for hydrophilic compounds and bacterial spores, as well as introducing polar co-solvent to the cleaning apparatus.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125351024","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}
Successful launch and imagery from the Herschel Space Telescope has demonstrated a nominally in focus telescope. There still remains a discrepancy between the prediction and measurement of the telescope back focal length prior to launch. New material strain data has been applied to the structural/optical model of the telescope. The new data significantly closed the gap between the previous optical test measurement and prediction. However, a discrepancy still exists. Model results and techniques will be presented and discussed. 1 2
{"title":"Herschel Space Telescope: Impact of new material strain data on optical test and model correlation","authors":"B. Catanzaro, D. Doyle, E. Cohen","doi":"10.1117/12.857732","DOIUrl":"https://doi.org/10.1117/12.857732","url":null,"abstract":"Successful launch and imagery from the Herschel Space Telescope has demonstrated a nominally in focus telescope. There still remains a discrepancy between the prediction and measurement of the telescope back focal length prior to launch. New material strain data has been applied to the structural/optical model of the telescope. The new data significantly closed the gap between the previous optical test measurement and prediction. However, a discrepancy still exists. Model results and techniques will be presented and discussed. 1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"384 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126730177","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446690
V. Baraniello, M. Cicala, F. Corraro
This paper presents an algorithm for estimating the rigid and elastic motions of aircrafts showing significant elastic displacements, based on an EKF (Extended Kalman Filter) technique. The proposed algorithm can be applied to HALE (High Attitude Long Endurance Vehicle) unmanned vehicles, which typically show a configuration with high aspect ratios wings, fuselages with high length to diameter ratios and, above all, lightweight structures. 1 2 The knowledge of their actual structure shape is fundamental essentially for three reasons: health monitoring of the structure, control purposes (Active Control Technologies) and finally for the determination of onboard sensors exact position and attitude, relative to a specified reference frame, to improve the accuracy of their measurements. Filter equations have been developed considering the coupling between rigid and elastic motions. The elastic motions are modeled in the assumptions of modal decomposition. Sensors budget of the presented algorithm, consists in two GPS Antennas/Receivers for speed/position measurements, an Inertial Measurement Unit with tri-axial accelerometers, gyros and magnetometers, and at least one auxiliary tri-axial accelerometer. The matrix formulation of the algorithm allows using the desired number of auxiliary accelerometers without changes to its implementation or its mathematical structure. Filter implementation also allows defining a numerical criterion to determine the better allocation of auxiliary accelerometers. The observability of the filter error state vector is also exhaustively analyzed, considering different scenarios concerning the elastic features of the structure. Finally simulation test results are reported, which demonstrate effectiveness of the proposed algorithm.
{"title":"An extension of integrated navigation algorithms to estimate elastic motions of very flexible aircrafts","authors":"V. Baraniello, M. Cicala, F. Corraro","doi":"10.1109/AERO.2010.5446690","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446690","url":null,"abstract":"This paper presents an algorithm for estimating the rigid and elastic motions of aircrafts showing significant elastic displacements, based on an EKF (Extended Kalman Filter) technique. The proposed algorithm can be applied to HALE (High Attitude Long Endurance Vehicle) unmanned vehicles, which typically show a configuration with high aspect ratios wings, fuselages with high length to diameter ratios and, above all, lightweight structures. 1 2 The knowledge of their actual structure shape is fundamental essentially for three reasons: health monitoring of the structure, control purposes (Active Control Technologies) and finally for the determination of onboard sensors exact position and attitude, relative to a specified reference frame, to improve the accuracy of their measurements. Filter equations have been developed considering the coupling between rigid and elastic motions. The elastic motions are modeled in the assumptions of modal decomposition. Sensors budget of the presented algorithm, consists in two GPS Antennas/Receivers for speed/position measurements, an Inertial Measurement Unit with tri-axial accelerometers, gyros and magnetometers, and at least one auxiliary tri-axial accelerometer. The matrix formulation of the algorithm allows using the desired number of auxiliary accelerometers without changes to its implementation or its mathematical structure. Filter implementation also allows defining a numerical criterion to determine the better allocation of auxiliary accelerometers. The observability of the filter error state vector is also exhaustively analyzed, considering different scenarios concerning the elastic features of the structure. Finally simulation test results are reported, which demonstrate effectiveness of the proposed algorithm.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"59 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115085479","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446815
J. Lacaille
Snecma builds CFM engines with GE for commercial aircrafts and now faces with the challenge of providing assistance to the maintenance operations of its wide fleet. Some years ago, Snecma engaged in the development of a set of algorithmic applications to monitor engine subsystems. Some health-monitoring (HM) application examples developed for Snecma's engines are presented below. An architecture proposition for HM applications is given with a list of quality indicators used in validation process. Finally, the problem of how to reach the drastic requirements in use for civil aircrafts is addressed. The conclusion sketches the methodology and software solution tested by Snecma's HM team to manage the algorithms.
{"title":"Validation of health-monitoring algorithms for civil aircraft engines","authors":"J. Lacaille","doi":"10.1109/AERO.2010.5446815","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446815","url":null,"abstract":"Snecma builds CFM engines with GE for commercial aircrafts and now faces with the challenge of providing assistance to the maintenance operations of its wide fleet. Some years ago, Snecma engaged in the development of a set of algorithmic applications to monitor engine subsystems. Some health-monitoring (HM) application examples developed for Snecma's engines are presented below. An architecture proposition for HM applications is given with a list of quality indicators used in validation process. Finally, the problem of how to reach the drastic requirements in use for civil aircrafts is addressed. The conclusion sketches the methodology and software solution tested by Snecma's HM team to manage the algorithms.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"100 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116009197","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446932
P. Stadter, B. Kantsiper, D. Jablonski, A. Golshan, James Costrell
The Deep Space Network provides the National Aeronautics and Space Administration (NASA) and partner organizations essential communication links to interplanetary and deep space robotic missions. Managed by NASA's Space Operations Mission Directorate (SOMD), the challenge of maintaining this asset has led to several efforts to explore concepts of a distributed array of ground antennas to augment or replace current DSN antennas. This paper describes independent analysis by The Johns Hopkins University Applied Physics Laboratory to evaluate several uplink array concepts under consideration by NASA/SOMD, including efforts by the Jet Propulsion Laboratory and industry offerings for experimental approaches. The work details the analysis to validate the ability to form beams, achieve target gain patterns, and the sensitivities to array geometries and error sources. Also included are risk areas and potential techniques to address implementation and performance challenges.
{"title":"Uplink arraying analysis for NASA's Deep Space Network","authors":"P. Stadter, B. Kantsiper, D. Jablonski, A. Golshan, James Costrell","doi":"10.1109/AERO.2010.5446932","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446932","url":null,"abstract":"The Deep Space Network provides the National Aeronautics and Space Administration (NASA) and partner organizations essential communication links to interplanetary and deep space robotic missions. Managed by NASA's Space Operations Mission Directorate (SOMD), the challenge of maintaining this asset has led to several efforts to explore concepts of a distributed array of ground antennas to augment or replace current DSN antennas. This paper describes independent analysis by The Johns Hopkins University Applied Physics Laboratory to evaluate several uplink array concepts under consideration by NASA/SOMD, including efforts by the Jet Propulsion Laboratory and industry offerings for experimental approaches. The work details the analysis to validate the ability to form beams, achieve target gain patterns, and the sensitivities to array geometries and error sources. Also included are risk areas and potential techniques to address implementation and performance challenges.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"38 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122424399","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446733
Fenghua He, Yu Yao
In this paper, a maneuver decision-making strategy in air combat is investigated via a hybrid control theory. A Hybrid Input/Output Automaton (HIOA) model is established to describe a maneuver decision-making system for a flight vehicle in air combat.An evaluation index function is proposed considering angle, space range and acceleration of two aircraft. The two-point boundary value problem is converted into two single optimization ones, and a saddle point solution is obtained for an optimal problem. A hybrid decision-making algorithm is formulated. Simulation results show the effectiveness of the proposed method.
{"title":"Maneuver decision-making on air-to-air combat via hybrid control","authors":"Fenghua He, Yu Yao","doi":"10.1109/AERO.2010.5446733","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446733","url":null,"abstract":"In this paper, a maneuver decision-making strategy in air combat is investigated via a hybrid control theory. A Hybrid Input/Output Automaton (HIOA) model is established to describe a maneuver decision-making system for a flight vehicle in air combat.An evaluation index function is proposed considering angle, space range and acceleration of two aircraft. The two-point boundary value problem is converted into two single optimization ones, and a saddle point solution is obtained for an optimal problem. A hybrid decision-making algorithm is formulated. Simulation results show the effectiveness of the proposed method.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"35 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122681438","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446909
E. Grayver
Software-defined radios (SDRs) allow the user or operator to switch between multiple waveforms without any changes to the underlying radio hardware. Minimally configurable radios that support only a few waveforms are easily managed using proprietary interfaces. However, true software radios allow thousands of different waveforms, making their configuration a nontrivial task. The level of complexity introduced by SDR has been recognized for over a decade. This paper provides an overview of different efforts to standardize the configuration and operation of SDRs. I discuss the Joint Tactical Radio Systems (JTRS) standard developed by the U.S. Army, based on the Software Communications Architecture (SCA) framework. JTRS is compared to the NASA proposal known as STRS. Both of these standards deal with higher network layers and treat the physical layer as a ‘black box.’ A new standard to describe the physical layer, SDRPHY, is discussed in detail. Finally, a few hardware-specific standardization efforts are discussed. 1 2
{"title":"Standardization efforts for software-defined radio","authors":"E. Grayver","doi":"10.1109/AERO.2010.5446909","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446909","url":null,"abstract":"Software-defined radios (SDRs) allow the user or operator to switch between multiple waveforms without any changes to the underlying radio hardware. Minimally configurable radios that support only a few waveforms are easily managed using proprietary interfaces. However, true software radios allow thousands of different waveforms, making their configuration a nontrivial task. The level of complexity introduced by SDR has been recognized for over a decade. This paper provides an overview of different efforts to standardize the configuration and operation of SDRs. I discuss the Joint Tactical Radio Systems (JTRS) standard developed by the U.S. Army, based on the Software Communications Architecture (SCA) framework. JTRS is compared to the NASA proposal known as STRS. Both of these standards deal with higher network layers and treat the physical layer as a ‘black box.’ A new standard to describe the physical layer, SDRPHY, is discussed in detail. Finally, a few hardware-specific standardization efforts are discussed. 1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"79 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122878218","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 : 2010-03-06DOI: 10.1109/AERO.2010.5447034
Christopher Jones, D. Masse, C. Glass, A. Wilhite, M. Walker
Collection and storage of propellant on-orbit has the potential to dramatically reduce launch mass for future exploration missions.12 A proposed method for this collection utilizes an orbiting vehicle that collects ambient air at a high altitude and uses a fraction of the air for orbital maintenance while storing the remainder for exploration propellant. The derivation of the relations governing propulsion requirements of thrust and specific impulse is presented. Initial requirements for the collector are defined through design maps based on a notional Mars mission.
{"title":"PHARO—Propellant harvesting of atmospheric resources in orbit","authors":"Christopher Jones, D. Masse, C. Glass, A. Wilhite, M. Walker","doi":"10.1109/AERO.2010.5447034","DOIUrl":"https://doi.org/10.1109/AERO.2010.5447034","url":null,"abstract":"Collection and storage of propellant on-orbit has the potential to dramatically reduce launch mass for future exploration missions.12 A proposed method for this collection utilizes an orbiting vehicle that collects ambient air at a high altitude and uses a fraction of the air for orbital maintenance while storing the remainder for exploration propellant. The derivation of the relations governing propulsion requirements of thrust and specific impulse is presented. Initial requirements for the collector are defined through design maps based on a notional Mars mission.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"129502799","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 : 2010-03-06DOI: 10.1109/AERO.2010.5446917
R. Kumar, Swapnaja Ranade, Balaram Gowda
Efficient tracking schemes are becoming very important due to the increasing availability of wireless networks and the importance of location information for applications such as vehicle and object tracking, surveillance, military uses etc. This paper12 presents a simple approach based on the measurements of the received signal strength to determine the position of wireless nodes. An estimation algorithm, using range measurements from multiple, scattered, beacon transmitter stations with known locations, is presented that lowers position location inaccuracies, has relatively low complexity and uses only the local information. Various simulation results are presented that demonstrate the performance of the algorithm.
{"title":"An effective localization algorithm based on received signal strength","authors":"R. Kumar, Swapnaja Ranade, Balaram Gowda","doi":"10.1109/AERO.2010.5446917","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446917","url":null,"abstract":"Efficient tracking schemes are becoming very important due to the increasing availability of wireless networks and the importance of location information for applications such as vehicle and object tracking, surveillance, military uses etc. This paper12 presents a simple approach based on the measurements of the received signal strength to determine the position of wireless nodes. An estimation algorithm, using range measurements from multiple, scattered, beacon transmitter stations with known locations, is presented that lowers position location inaccuracies, has relatively low complexity and uses only the local information. Various simulation results are presented that demonstrate the performance of the algorithm.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"58 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2010-03-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128692907","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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