Pub Date : 2009-03-07DOI: 10.1109/AERO.2009.4839331
Erik B. Johnson, E. Chapman, P. Linsay, S. Mukhopadhyay, C. Stapels, J. Christian, E. Benton
A dosimeter-on-a-chip (DoseChip) comprised of a tissue-equivalent scintillator coupled to a solid-state photomultiplier (SSPM) built using CMOS technology represents an ideal technology for a space-worthy, real-time solar-particle monitor for astronauts. It provides a tissue-equivalent response to the relevant energies and types of radiation for low-Earth orbit and interplanetary space flight to the moon or Mars. The DoseChip will complement the existing Crew Passive Dosimeters by providing real-time dosimetry and as an alarming monitor for solar particle events (SPEs). A prototype of the DoseChip was exposed to protons at three incident energies at the NASA space radiation laboratory at Brookhaven National Laboratory. The prototype provides an unambiguous, proportional response for 200, 500, and 1000 MeV protons. The measured response produced a detector response function that was used to model the behavior of an improved instrument. The data presented here indicate that a 3 × 3 × 3 mm3 piece of BC-430 plastic scintillator coupled to a 2000-pixel SSPM can accommodate the needed dynamic range for protons with an incident energy of 20 MeV and greater.
{"title":"Tissue-equivalent solar particle dosimeter using CMOS SSPMs","authors":"Erik B. Johnson, E. Chapman, P. Linsay, S. Mukhopadhyay, C. Stapels, J. Christian, E. Benton","doi":"10.1109/AERO.2009.4839331","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839331","url":null,"abstract":"A dosimeter-on-a-chip (DoseChip) comprised of a tissue-equivalent scintillator coupled to a solid-state photomultiplier (SSPM) built using CMOS technology represents an ideal technology for a space-worthy, real-time solar-particle monitor for astronauts. It provides a tissue-equivalent response to the relevant energies and types of radiation for low-Earth orbit and interplanetary space flight to the moon or Mars. The DoseChip will complement the existing Crew Passive Dosimeters by providing real-time dosimetry and as an alarming monitor for solar particle events (SPEs). A prototype of the DoseChip was exposed to protons at three incident energies at the NASA space radiation laboratory at Brookhaven National Laboratory. The prototype provides an unambiguous, proportional response for 200, 500, and 1000 MeV protons. The measured response produced a detector response function that was used to model the behavior of an improved instrument. The data presented here indicate that a 3 × 3 × 3 mm3 piece of BC-430 plastic scintillator coupled to a 2000-pixel SSPM can accommodate the needed dynamic range for protons with an incident energy of 20 MeV and greater.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"62 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115842063","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839342
M. Calamia, G. Franceschetti, R. Lanari, F. Casu, M. Manzo
We compare the surface deformation measurement capability of the Small BAseline Subset (SBAS) DInSAR technique and of the continuous Global Positioning System (GPS). The analysis is focused on the Los Angeles (California) test area where different deformation phenomena occur and a large amount of SAR data, acquired by the European Remote Sensing Satellite (ERS) sensors, and of continuous GPS measurements is available. Our analysis shows that the SBAS technique allows to achieve an estimate of the single displacement measurements, in the radar line of sight (LOS), with a standard deviation of about 5mm, which is comparable with the LOS-projected GPS data accuracy. A final discussion on the complementariness and integration of SAR and GPS measurements is provided.
{"title":"Comparison and integration of GPS and DInSAR deformation time-series","authors":"M. Calamia, G. Franceschetti, R. Lanari, F. Casu, M. Manzo","doi":"10.1109/AERO.2009.4839342","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839342","url":null,"abstract":"We compare the surface deformation measurement capability of the Small BAseline Subset (SBAS) DInSAR technique and of the continuous Global Positioning System (GPS). The analysis is focused on the Los Angeles (California) test area where different deformation phenomena occur and a large amount of SAR data, acquired by the European Remote Sensing Satellite (ERS) sensors, and of continuous GPS measurements is available. Our analysis shows that the SBAS technique allows to achieve an estimate of the single displacement measurements, in the radar line of sight (LOS), with a standard deviation of about 5mm, which is comparable with the LOS-projected GPS data accuracy. A final discussion on the complementariness and integration of SAR and GPS measurements is provided.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116073662","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839683
Eric Rabeno, Mark S. Bounds
The performance of military ground vehicle systems quickly degrades due to high operation tempo and extreme environments while performing in-theater service. Current maintenance methods associated with this degradation are not sufficiently optimized for cost and performance. To address this issue, the United States Army is implementing a policy of Condition Based Maintenance (CBM) and being supported by the Army Materiel System Analysis Activity (AMSAA). CBM is a plan of maintenance for a system based upon the actual condition of the system as enabled by the application of usage, diagnostic and prognostic processes executed on a Health and Usage Monitoring System (HUMS). AMSAA has developed and is implementing a CBM system for ground vehicles. This development process has included the development of a robust military-grade HUMS in conjunction with the Aberdeen Test Center and the development of data collection, reduction, analysis, and reporting processes. A key requirement underlying these processes is a thorough understanding of both the ways in which system condition is degenerated and the ability of the HUMS to detect, identify, and communicate all conditions that requires maintenance in a timely manner. AMSAA and the US Army Aberdeen Test Center (ATC) have jointly initiated testing and applications as the critical means of filling this requirement.
{"title":"Condition based maintenance of military ground vehicles","authors":"Eric Rabeno, Mark S. Bounds","doi":"10.1109/AERO.2009.4839683","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839683","url":null,"abstract":"The performance of military ground vehicle systems quickly degrades due to high operation tempo and extreme environments while performing in-theater service. Current maintenance methods associated with this degradation are not sufficiently optimized for cost and performance. To address this issue, the United States Army is implementing a policy of Condition Based Maintenance (CBM) and being supported by the Army Materiel System Analysis Activity (AMSAA). CBM is a plan of maintenance for a system based upon the actual condition of the system as enabled by the application of usage, diagnostic and prognostic processes executed on a Health and Usage Monitoring System (HUMS). AMSAA has developed and is implementing a CBM system for ground vehicles. This development process has included the development of a robust military-grade HUMS in conjunction with the Aberdeen Test Center and the development of data collection, reduction, analysis, and reporting processes. A key requirement underlying these processes is a thorough understanding of both the ways in which system condition is degenerated and the ability of the HUMS to detect, identify, and communicate all conditions that requires maintenance in a timely manner. AMSAA and the US Army Aberdeen Test Center (ATC) have jointly initiated testing and applications as the critical means of filling this requirement.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"8 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115317754","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839548
B. Muirhead
This paper describes and discusses the Constellation point of departure lunar capability architecture. Constellation is NASA's program to implement the human exploration of the moon and Mars. This paper focuses on the overall design and operational strategy for the Constellation lunar transportation system architecture including the Ares V heavy lift launch vehicle, Altair lunar lander and early concepts for lunar surface systems including habitats and mobile vehicles. The architecture builds on the initial capability vehicles of Ares I and Orion as they will initially fly to the international space station. The architecture is based on extensive trade studies of surface system objectives, lunar lander design options and Ares V design options. In addition to the description of the architecture this paper will briefly provide status of the initial capability building blocks of Ares I and Orion.
{"title":"Constellation lunar capability point of departure architecture","authors":"B. Muirhead","doi":"10.1109/AERO.2009.4839548","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839548","url":null,"abstract":"This paper describes and discusses the Constellation point of departure lunar capability architecture. Constellation is NASA's program to implement the human exploration of the moon and Mars. This paper focuses on the overall design and operational strategy for the Constellation lunar transportation system architecture including the Ares V heavy lift launch vehicle, Altair lunar lander and early concepts for lunar surface systems including habitats and mobile vehicles. The architecture builds on the initial capability vehicles of Ares I and Orion as they will initially fly to the international space station. The architecture is based on extensive trade studies of surface system objectives, lunar lander design options and Ares V design options. In addition to the description of the architecture this paper will briefly provide status of the initial capability building blocks of Ares I and Orion.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"17 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123450572","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839583
Henric Boiardt, C. Rodriguez
Nanosatellite communication in Low Earth Orbit (LEO) is limited by line of sight twice a day transmissions that last a total average of 15 minutes. Using Iridium's satellite network as a gateway, satellites in LEO may achieve near continuous communications with earth. This paper discusses the use of the Iridium network for nanosatellite satellite communications by NASA's Florida Space Grant Consortium funded researchers at Florida International University (FIU). Specifically, the paper focuses on FIU's Florida University SATellite (FUNSAT) IV competition award winning payload submission, named PicoPanther, orbiting in a sun synchronous polar orbit. An introduction to the network and hardware is presented as well as simulation results. An analysis of cost, Doppler Effect shifts and possible uses are also performed.
{"title":"The use of Iridium's satellite network for nanosatellite communications in Low Earth Orbit","authors":"Henric Boiardt, C. Rodriguez","doi":"10.1109/AERO.2009.4839583","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839583","url":null,"abstract":"Nanosatellite communication in Low Earth Orbit (LEO) is limited by line of sight twice a day transmissions that last a total average of 15 minutes. Using Iridium's satellite network as a gateway, satellites in LEO may achieve near continuous communications with earth. This paper discusses the use of the Iridium network for nanosatellite satellite communications by NASA's Florida Space Grant Consortium funded researchers at Florida International University (FIU). Specifically, the paper focuses on FIU's Florida University SATellite (FUNSAT) IV competition award winning payload submission, named PicoPanther, orbiting in a sun synchronous polar orbit. An introduction to the network and hardware is presented as well as simulation results. An analysis of cost, Doppler Effect shifts and possible uses are also performed.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"16 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124486479","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839626
G. Abdelal, A. Elhady, A. Gad
Mounting accuracy of satellite payload and ADCS (attitude determination and control subsystem) seats is one of the requirements to achieve the satellite mission with satisfactory performance. Deviation of the position of the mounting seat for Multi-Band-Earth-Imager (MBEI) is caused by cracks in the plate of the basis unit and bracket for attachment of MBEI. These cracks were detected during inspection of the satellite strength mock-up after vibration testing for air transportation phase. Most probable reason of the cracking is fatigue damage as strength mock-up structure was subjected to prolonged vibration loading during various loading cases. Total vibration duration during testing is about 56 hours. In order to study the cracking reasons, finite element modeling of the structural parts of the basis unit including MBEI bracket and instrument MBEI is subjected to harmonic response to simulate vibration loading for the case of air transportation. Numerical results are compared with the experimental ones, and mechanical design of the basis-plate unit is modified.
{"title":"Micro-satellite structure fracture investigation techniques","authors":"G. Abdelal, A. Elhady, A. Gad","doi":"10.1109/AERO.2009.4839626","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839626","url":null,"abstract":"Mounting accuracy of satellite payload and ADCS (attitude determination and control subsystem) seats is one of the requirements to achieve the satellite mission with satisfactory performance. Deviation of the position of the mounting seat for Multi-Band-Earth-Imager (MBEI) is caused by cracks in the plate of the basis unit and bracket for attachment of MBEI. These cracks were detected during inspection of the satellite strength mock-up after vibration testing for air transportation phase. Most probable reason of the cracking is fatigue damage as strength mock-up structure was subjected to prolonged vibration loading during various loading cases. Total vibration duration during testing is about 56 hours. In order to study the cracking reasons, finite element modeling of the structural parts of the basis unit including MBEI bracket and instrument MBEI is subjected to harmonic response to simulate vibration loading for the case of air transportation. Numerical results are compared with the experimental ones, and mechanical design of the basis-plate unit is modified.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"102 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124728694","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839298
L. Randall
We investigate the possibility that there can be more dimensions of space and my work investigating what their effect might be on the observable universe. I will explain how this proposal will be tested at the Large Hadron Collider (LHC) and speak more broadly about the questions the LHC will address.
{"title":"Warped passages: The universe's extra dimensions","authors":"L. Randall","doi":"10.1109/AERO.2009.4839298","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839298","url":null,"abstract":"We investigate the possibility that there can be more dimensions of space and my work investigating what their effect might be on the observable universe. I will explain how this proposal will be tested at the Large Hadron Collider (LHC) and speak more broadly about the questions the LHC will address.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"15 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"122941122","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839437
M. Thelen, D. Moore
The detector assembly for the Mid Infrared Instrument (MIRI) of the James Webb Space Telescope (JWST) is mechanically supported in the Focal Plane Module (FPM) Assembly with an efficient hexapod design. The kinematic mount design allows for precision adjustment of the detector boresight to assembly alignment fiducials and maintains optical alignment requirements during flight conditions of launch and cryogenic operations below 7 Kelvin. This kinematic mounting technique is able to be implemented in a variety of optical-mechanical designs and is capable of micron level adjustment control and stability over wide dynamic and temperature ranges.
{"title":"The mechanical design of a kinematic mount for the Mid Infrared Instrument Focal Plane Module on the James Webb Space Telescope","authors":"M. Thelen, D. Moore","doi":"10.1109/AERO.2009.4839437","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839437","url":null,"abstract":"The detector assembly for the Mid Infrared Instrument (MIRI) of the James Webb Space Telescope (JWST) is mechanically supported in the Focal Plane Module (FPM) Assembly with an efficient hexapod design. The kinematic mount design allows for precision adjustment of the detector boresight to assembly alignment fiducials and maintains optical alignment requirements during flight conditions of launch and cryogenic operations below 7 Kelvin. This kinematic mounting technique is able to be implemented in a variety of optical-mechanical designs and is capable of micron level adjustment control and stability over wide dynamic and temperature ranges.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"67 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123475315","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839474
H. Ghaemi, M. Galletti, T. Boerner, F. Gekat, M. Viberg
The maximum obtainable resolution of a strip-map synthetic aperture radar (SAR) system can be retained by simply avoiding weighting, or tapering, data samples in the along-track compression process. However, this will lead to hazardous artifacts caused by strong sidelobes of the corresponding adjacent scatterers whose interference might severely weaken the desired targets or even introduce false targets. On the other hand, some residual artifacts, even after tapering process, may still deteriorate the quality (contrast) of the SAR image. These issues can be remedied by applying the so-called CLEAN technique, which can mitigate these ill-effects in strip-map SAR imagery while maintaining the maximum resolution. This, indeed, is carried out as a post processing step, i.e., after the azimuth compression is accomplished, in the SAR system. The objective of this paper is to extend the CLEAN technique to strip-map SAR system to produce high-quality images with a very good along-track resolution. The algorithm is then applied to data from a ground-based circular SAR (CSAR) system to verify its implementation as well as this new application of the CLEAN technique.
{"title":"CLEAN technique in strip-map SAR for high-quality imaging","authors":"H. Ghaemi, M. Galletti, T. Boerner, F. Gekat, M. Viberg","doi":"10.1109/AERO.2009.4839474","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839474","url":null,"abstract":"The maximum obtainable resolution of a strip-map synthetic aperture radar (SAR) system can be retained by simply avoiding weighting, or tapering, data samples in the along-track compression process. However, this will lead to hazardous artifacts caused by strong sidelobes of the corresponding adjacent scatterers whose interference might severely weaken the desired targets or even introduce false targets. On the other hand, some residual artifacts, even after tapering process, may still deteriorate the quality (contrast) of the SAR image. These issues can be remedied by applying the so-called CLEAN technique, which can mitigate these ill-effects in strip-map SAR imagery while maintaining the maximum resolution. This, indeed, is carried out as a post processing step, i.e., after the azimuth compression is accomplished, in the SAR system. The objective of this paper is to extend the CLEAN technique to strip-map SAR system to produce high-quality images with a very good along-track resolution. The algorithm is then applied to data from a ground-based circular SAR (CSAR) system to verify its implementation as well as this new application of the CLEAN technique.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"45 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123514424","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 : 2009-03-07DOI: 10.1109/AERO.2009.4839319
P. Tsou
STARDUST, the 4th NASA Discovery Mission, returned the world's first coma sample from a comet with known history. The returned samples gave the world the first opportunity to perform detailed laboratory studies of comet Wild 2 and a time capsule of the formational times of our Solar System. The completion of a comet coma flyby sample return mission required heroic endeavors from many participants, extensive advocacy by officials and reviewers, considerable doses of serendipitous miracles and, invariably, disappointments. This chronicle recounts some of the technology breakthroughs and significant engineering and strategic innovations that made STARDUST possible. For those who dream of future space exploration, this account may provide inspiration for even more incredible discoveries to come. A flight project distinguished by the excellence of its technical concept is only a necessary condition; completing such a mission successfully depends on sufficiency factors that are often slighted-programmatic, interpersonal and cosmic happenstances.
{"title":"STARDUST: A comet coma flyby sample return","authors":"P. Tsou","doi":"10.1109/AERO.2009.4839319","DOIUrl":"https://doi.org/10.1109/AERO.2009.4839319","url":null,"abstract":"STARDUST, the 4th NASA Discovery Mission, returned the world's first coma sample from a comet with known history. The returned samples gave the world the first opportunity to perform detailed laboratory studies of comet Wild 2 and a time capsule of the formational times of our Solar System. The completion of a comet coma flyby sample return mission required heroic endeavors from many participants, extensive advocacy by officials and reviewers, considerable doses of serendipitous miracles and, invariably, disappointments. This chronicle recounts some of the technology breakthroughs and significant engineering and strategic innovations that made STARDUST possible. For those who dream of future space exploration, this account may provide inspiration for even more incredible discoveries to come. A flight project distinguished by the excellence of its technical concept is only a necessary condition; completing such a mission successfully depends on sufficiency factors that are often slighted-programmatic, interpersonal and cosmic happenstances.","PeriodicalId":117250,"journal":{"name":"2009 IEEE Aerospace conference","volume":"31 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2009-03-07","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121604921","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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