Pub Date : 2010-03-06DOI: 10.1109/AERO.2010.5446725
E. Oland, R. Kristiansen, P. J. Nicklasson
In this paper we present a method for performing plume avoidance in a leader-follower spacecraft formation. By using the null-space-based behavioral method we show that the follower is able to avoid entering the plume of the leader while performing a reconfiguration maneuver.
{"title":"Spacecraft formation reconfiguration with plume avoidance","authors":"E. Oland, R. Kristiansen, P. J. Nicklasson","doi":"10.1109/AERO.2010.5446725","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446725","url":null,"abstract":"In this paper we present a method for performing plume avoidance in a leader-follower spacecraft formation. By using the null-space-based behavioral method we show that the follower is able to avoid entering the plume of the leader while performing a reconfiguration maneuver.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"21 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":"133867223","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.2010.5446717
L. Del Castillo, A. Moussessian, R. McPherson, Tan Zhang, Z. Hou, R. Dean, R. Johnson
This work describes the development and evaluation of advanced technologies for the integration of electronic devices within membrane polymers.123 Specifically, investigators thinned silicon die, electrically connecting them with circuits on flexible (liquid crystal polymer (LCP) and polyimide (PI)) circuits, using gold thermo-compression flip chip bonding, and embedding them within the material. The influence of temperature and flexure on the electrical behavior of active embedded assemblies was evaluated. In addition, the long term thermal cycle resistance of the passive daisy chain assemblies was determined within the Mil Std (−55 to +125°C), extreme low #1 (−125 to +85°C), and extreme low #2 (−125 to +125°C) temperature ranges. The results of these evaluations will be discussed, along with the application of this technology for future NASA missions.
{"title":"Flexible electronic assemblies for space applications","authors":"L. Del Castillo, A. Moussessian, R. McPherson, Tan Zhang, Z. Hou, R. Dean, R. Johnson","doi":"10.1109/AERO.2010.5446717","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446717","url":null,"abstract":"This work describes the development and evaluation of advanced technologies for the integration of electronic devices within membrane polymers.123 Specifically, investigators thinned silicon die, electrically connecting them with circuits on flexible (liquid crystal polymer (LCP) and polyimide (PI)) circuits, using gold thermo-compression flip chip bonding, and embedding them within the material. The influence of temperature and flexure on the electrical behavior of active embedded assemblies was evaluated. In addition, the long term thermal cycle resistance of the passive daisy chain assemblies was determined within the Mil Std (−55 to +125°C), extreme low #1 (−125 to +85°C), and extreme low #2 (−125 to +125°C) temperature ranges. The results of these evaluations will be discussed, along with the application of this technology for future NASA missions.","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":"131784897","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.2010.5446823
A. Fijany, F. Vatan
We present a novel concept of Minimal Set of Analytical Redundancy Relation (ARRs) and an efficient method for its calculation for application to system diagnosis. ARRs are one of the crucial tools for model-based diagnosis as well as for optimizing, analyzing, and validating the system of sensors. However, despite the importance of the ARRs for system diagnosis, it seems that less attention has been paid to their efficient application. In this paper, we first discuss the complexity of model-based diagnosis by using ARRs. We then present the concept of Minimal Set of ARRs which enables a faster system diagnosis by significantly reducing the number of ARRs to be evaluated for diagnosis purpose. We then show that the derivation of minimal set of ARRs can be mapped as a 0–1 Integer Programming problem and present an efficient branch-and-bound algorithm for this derivation. We also present the results of application of our method for generating the minimal set of ARRs, to both synthetic and industrial examples, to show the significant reduction in the computational cost that can be achieved for system diagnosis.1 2
{"title":"A novel method for derivation of Minimal Set of Analytical Redundancy Relations for system diagnosis","authors":"A. Fijany, F. Vatan","doi":"10.1109/AERO.2010.5446823","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446823","url":null,"abstract":"We present a novel concept of Minimal Set of Analytical Redundancy Relation (ARRs) and an efficient method for its calculation for application to system diagnosis. ARRs are one of the crucial tools for model-based diagnosis as well as for optimizing, analyzing, and validating the system of sensors. However, despite the importance of the ARRs for system diagnosis, it seems that less attention has been paid to their efficient application. In this paper, we first discuss the complexity of model-based diagnosis by using ARRs. We then present the concept of Minimal Set of ARRs which enables a faster system diagnosis by significantly reducing the number of ARRs to be evaluated for diagnosis purpose. We then show that the derivation of minimal set of ARRs can be mapped as a 0–1 Integer Programming problem and present an efficient branch-and-bound algorithm for this derivation. We also present the results of application of our method for generating the minimal set of ARRs, to both synthetic and industrial examples, to show the significant reduction in the computational cost that can be achieved for system diagnosis.1 2","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":"131786171","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.2010.5446702
D. Lemaster
Microgrid polarization imaging systems inherently suffer from spatial aliasing in addition to the image degrading effects of camera blur and noise. In this paper, microgrid aliasing is reduced by a factor of two and noise is suppressed via a fast image fusion technique borrowed from the study of super resolution. Additionally, a new regularization cost function for microgrid super resolution estimators is proposed. Polarimetric image fusion results are demonstrated with laboratory data.1 2
{"title":"Resolution enhancement by image fusion for microgrid polarization imagers","authors":"D. Lemaster","doi":"10.1109/AERO.2010.5446702","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446702","url":null,"abstract":"Microgrid polarization imaging systems inherently suffer from spatial aliasing in addition to the image degrading effects of camera blur and noise. In this paper, microgrid aliasing is reduced by a factor of two and noise is suppressed via a fast image fusion technique borrowed from the study of super resolution. Additionally, a new regularization cost function for microgrid super resolution estimators is proposed. Polarimetric image fusion results are demonstrated with laboratory data.1 2","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":"130815595","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.2010.5446736
B. Drake, S. Hoffman, D. Beaty
This paper provides a summary of the 2007 Mars Design Reference Architecture 5.0 (DRA 5.0) [1], which is the latest in a series of NASA Mars reference missions. It provides a vision of one potential approach to human Mars exploration, including how Constellation systems could be used. The strategy and example implementation concepts that are described here should not be viewed as constituting a formal plan for the human exploration of Mars, but rather provide a common framework for future planning of systems concepts, technology development, and operational testing as well as potential Mars robotic missions, research that is conducted on the International Space Station, and future potential lunar exploration missions. This summary of the Mars DRA 5.0 provides an overview of the overall mission approach, surface strategy and exploration goals, as well as the key systems and challenges for the first three concepts for human missions to Mars.1,2
{"title":"Human exploration of Mars, Design Reference Architecture 5.0","authors":"B. Drake, S. Hoffman, D. Beaty","doi":"10.1109/AERO.2010.5446736","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446736","url":null,"abstract":"This paper provides a summary of the 2007 Mars Design Reference Architecture 5.0 (DRA 5.0) [1], which is the latest in a series of NASA Mars reference missions. It provides a vision of one potential approach to human Mars exploration, including how Constellation systems could be used. The strategy and example implementation concepts that are described here should not be viewed as constituting a formal plan for the human exploration of Mars, but rather provide a common framework for future planning of systems concepts, technology development, and operational testing as well as potential Mars robotic missions, research that is conducted on the International Space Station, and future potential lunar exploration missions. This summary of the Mars DRA 5.0 provides an overview of the overall mission approach, surface strategy and exploration goals, as well as the key systems and challenges for the first three concepts for human missions to Mars.1,2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"42 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":"131227200","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.2010.5446934
A. A. Emadzadeh, J. Speyer
The relative position estimation problem between two spacecraft, based on utilizing signals emitted from X-ray pulsars, is introduced. The pulse delay estimation problem is formulated, and the Cramér-Rao Lower Bound (CRLB) for any unbiased estimator of the pulse delay is presented as well. Two different estimation strategies are proposed, and an asymptotically efficient estimator is chosen, which is based on the maximum-likelihood criterion. The navigation system is equipped with inertial measurement units (IMUs). The time delay estimates are used as measurements, and based on the models of spacecraft and IMU dynamics, a Kalman filter is employed to obtain the three-dimensional relative position estimate. Numerical simulations are performed to verify the theoretical results.
{"title":"A new relative navigation system based on X-ray pulsar measurements","authors":"A. A. Emadzadeh, J. Speyer","doi":"10.1109/AERO.2010.5446934","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446934","url":null,"abstract":"The relative position estimation problem between two spacecraft, based on utilizing signals emitted from X-ray pulsars, is introduced. The pulse delay estimation problem is formulated, and the Cramér-Rao Lower Bound (CRLB) for any unbiased estimator of the pulse delay is presented as well. Two different estimation strategies are proposed, and an asymptotically efficient estimator is chosen, which is based on the maximum-likelihood criterion. The navigation system is equipped with inertial measurement units (IMUs). The time delay estimates are used as measurements, and based on the models of spacecraft and IMU dynamics, a Kalman filter is employed to obtain the three-dimensional relative position estimate. Numerical simulations are performed to verify the theoretical results.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"31 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":"133597371","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.2010.5446799
T. Bayer, L. Cooney, C. Delp, C. Dutenhoffer, R. Gostelow, M. Ingham, J. S. Jenkins, B. Smith
As JPL's missions grow more complex, the need for improved systems engineering processes is becoming clear. Of significant promise in this regard is the move toward a more integrated and model-centric approach to mission conception, design, implementation and operations. The Integrated Model-Centric Engineering (IMCE) Initiative, now underway at JPL, seeks to lay the groundwork for these improvements. This paper will report progress on three fronts: articulating JPL's need for IMCE; characterizing the enterprise into which IMCE capabilities will be deployed; and constructing an operations concept for a flight project development in an integrated model-centric environment.1 2
{"title":"An operations concept for Integrated Model-Centric Engineering at JPL","authors":"T. Bayer, L. Cooney, C. Delp, C. Dutenhoffer, R. Gostelow, M. Ingham, J. S. Jenkins, B. Smith","doi":"10.1109/AERO.2010.5446799","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446799","url":null,"abstract":"As JPL's missions grow more complex, the need for improved systems engineering processes is becoming clear. Of significant promise in this regard is the move toward a more integrated and model-centric approach to mission conception, design, implementation and operations. The Integrated Model-Centric Engineering (IMCE) Initiative, now underway at JPL, seeks to lay the groundwork for these improvements. This paper will report progress on three fronts: articulating JPL's need for IMCE; characterizing the enterprise into which IMCE capabilities will be deployed; and constructing an operations concept for a flight project development in an integrated model-centric environment.1 2","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"22 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":"132728803","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.2010.5446900
T. Evans, Kai-wing Chan, T. Saha
The optics for the International X-Ray Observatory (IXO) require alignment and integration of about fourteen thousand thin mirror segments to achieve the mission goal of 3.0 square meters of effective area at 1.25 keV with an angular resolution of five arc-seconds. These mirror segments are 0.4 mm thick, and 200 to 400 mm in size, which makes it hard to meet the strict angular resolution requirement of 5 arc-seconds for the telescope. This paper outlines the precise alignment, verification testing, and permanent bonding techniques developed at NASA's Goddard Space Flight Center (GSFC). These techniques are used to overcome the challenge of transferring thin mirror segments from a temporary mount to a fixed structure with arc-second alignment and minimal figure distortion. Recent advances in technology development in addition to the automation of several processes have produced significant results. Recent advances in the mirror fixture process known as the suspension mount has allowed for a mirror to be mounted to a fixture with minimal distortion. Once on the fixture, mirror segments have been aligned to around 5 arc-seconds which is halfway to the goal of 2.5 arc-seconds per mirror segment. This paper will highlight the recent advances in alignment, testing, and permanent bonding techniques as well as the results they have produced. 12
{"title":"Arc-second alignment of International X-Ray Observatory mirror segments in a fixed structure","authors":"T. Evans, Kai-wing Chan, T. Saha","doi":"10.1109/AERO.2010.5446900","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446900","url":null,"abstract":"The optics for the International X-Ray Observatory (IXO) require alignment and integration of about fourteen thousand thin mirror segments to achieve the mission goal of 3.0 square meters of effective area at 1.25 keV with an angular resolution of five arc-seconds. These mirror segments are 0.4 mm thick, and 200 to 400 mm in size, which makes it hard to meet the strict angular resolution requirement of 5 arc-seconds for the telescope. This paper outlines the precise alignment, verification testing, and permanent bonding techniques developed at NASA's Goddard Space Flight Center (GSFC). These techniques are used to overcome the challenge of transferring thin mirror segments from a temporary mount to a fixed structure with arc-second alignment and minimal figure distortion. Recent advances in technology development in addition to the automation of several processes have produced significant results. Recent advances in the mirror fixture process known as the suspension mount has allowed for a mirror to be mounted to a fixture with minimal distortion. Once on the fixture, mirror segments have been aligned to around 5 arc-seconds which is halfway to the goal of 2.5 arc-seconds per mirror segment. This paper will highlight the recent advances in alignment, testing, and permanent bonding techniques as well as the results they have produced. 12","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":"128810916","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.2010.5446666
S. Askari, B. Dwivedi, A. Saeed, M. Nourani
Redundancy techniques, such as N-tuple modular redundancy has been widely used to improve the reliability of digital circuits. Unfortunately nothing substantial has been done for the analog and mixed signal systems. In this paper, we propose a redundancy based fault-tolerant methodology to design a highly reliable analog and digital circuits and systems. The key contribution of our work is an innovative mean voter. This mean voter is a low power, small area, very high bandwidth and linearly scalable voting circuit. Unlike other conventional voters which works with odd N in an NMR, the mean voter works for both odd and even N for analog units and hence reduces the area and power further. For the proof of concept, we designed two fault tolerant analog circuits i.e. a low pass anti-aliasing analog filter and a 4-bit flash ADC. We also presented fault-tolerance mechanism in 4-bit binary adder and an FPGA cell for demonstrating its advantage in digital applications. Experimental results are reported to verify the concepts and measure the system's reliability when single upset transient may occur.
{"title":"Scalable mean voter for fault-tolerant mixed-signal circuits","authors":"S. Askari, B. Dwivedi, A. Saeed, M. Nourani","doi":"10.1109/AERO.2010.5446666","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446666","url":null,"abstract":"Redundancy techniques, such as N-tuple modular redundancy has been widely used to improve the reliability of digital circuits. Unfortunately nothing substantial has been done for the analog and mixed signal systems. In this paper, we propose a redundancy based fault-tolerant methodology to design a highly reliable analog and digital circuits and systems. The key contribution of our work is an innovative mean voter. This mean voter is a low power, small area, very high bandwidth and linearly scalable voting circuit. Unlike other conventional voters which works with odd N in an NMR, the mean voter works for both odd and even N for analog units and hence reduces the area and power further. For the proof of concept, we designed two fault tolerant analog circuits i.e. a low pass anti-aliasing analog filter and a 4-bit flash ADC. We also presented fault-tolerance mechanism in 4-bit binary adder and an FPGA cell for demonstrating its advantage in digital applications. Experimental results are reported to verify the concepts and measure the system's reliability when single upset transient may occur.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"25 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":"134484325","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.2010.5446793
Dioselin Courter, J. P. Springer, Carsten Neumann, C. Cruz-Neira, D. Reiners
There are a number of 3D applications that have shown the benefits of using visualization techniques for virtual prototyping and education in aerospace engineering. However, these applications typically run only on desktop computers and user interaction is limited to mouse and keyboard. Virtual reality technologies provide a richer set of user experience by combining stereoscopic images with interactive, multi-sensory, and viewer-centered environments. We present an interactive and immersive walk-through application of a space station that can be configured and executed on multiple operating systems and platforms. The hardware setup may vary for each platform. Some may be fully immersive environments with multiple projection screens that surround the user and provide spatial tracking, while others may only provide a single PC equipped with active stereo graphics output. Even a laptop using only monoscopic images is supported. The application has been tested in our omni-directional treadmill system, which includes spatial tracking of the user's head and is run on a graphics cluster which drives three projection screens around the treadmill. This kind of immersion using stereo projection and correctly scaled structures allows for a better sense of spatial relationships, because users receive bio-mechanical feedback during navigation by walking. For computer desktop setups, the software can be configured to run on a single screen and with a game controller for navigation.
{"title":"Beyond desktop point and click: Immersive walkthrough of aerospace structures","authors":"Dioselin Courter, J. P. Springer, Carsten Neumann, C. Cruz-Neira, D. Reiners","doi":"10.1109/AERO.2010.5446793","DOIUrl":"https://doi.org/10.1109/AERO.2010.5446793","url":null,"abstract":"There are a number of 3D applications that have shown the benefits of using visualization techniques for virtual prototyping and education in aerospace engineering. However, these applications typically run only on desktop computers and user interaction is limited to mouse and keyboard. Virtual reality technologies provide a richer set of user experience by combining stereoscopic images with interactive, multi-sensory, and viewer-centered environments. We present an interactive and immersive walk-through application of a space station that can be configured and executed on multiple operating systems and platforms. The hardware setup may vary for each platform. Some may be fully immersive environments with multiple projection screens that surround the user and provide spatial tracking, while others may only provide a single PC equipped with active stereo graphics output. Even a laptop using only monoscopic images is supported. The application has been tested in our omni-directional treadmill system, which includes spatial tracking of the user's head and is run on a graphics cluster which drives three projection screens around the treadmill. This kind of immersion using stereo projection and correctly scaled structures allows for a better sense of spatial relationships, because users receive bio-mechanical feedback during navigation by walking. For computer desktop setups, the software can be configured to run on a single screen and with a game controller for navigation.","PeriodicalId":378029,"journal":{"name":"2010 IEEE Aerospace Conference","volume":"480 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":"133771666","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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