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.2012.6187202
T. Castaings, B. Pannetier, F. Muller, M. Rombaut
This paper deals with the association problem of sparse data provided by a ground-based radar system for space surveillance. The method we propose and investigate aims at correlating sets of short arcs originating from successive orbits. When orbital states are unavailable due to limited information contained in each report, metric distances are introduced and used jointly with a time window for the gating, which contributes significantly to reducing the number of association possibilities. Resulting tracks should contain enough information for obtaining adequate initial estimates for the initial orbit determination step.
{"title":"Sparse data association for Low Earth Orbit tracking","authors":"T. Castaings, B. Pannetier, F. Muller, M. Rombaut","doi":"10.1109/AERO.2012.6187202","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187202","url":null,"abstract":"This paper deals with the association problem of sparse data provided by a ground-based radar system for space surveillance. The method we propose and investigate aims at correlating sets of short arcs originating from successive orbits. When orbital states are unavailable due to limited information contained in each report, metric distances are introduced and used jointly with a time window for the gating, which contributes significantly to reducing the number of association possibilities. Resulting tracks should contain enough information for obtaining adequate initial estimates for the initial orbit determination step.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"27 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":"85925162","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.2012.6187031
J. Brophy, L. Friedman, F. Culick
This paper describes the interim results of a study sponsored by the Keck Institute for Space Studies to investigate the feasibility of identifying, robotically capturing, and returning an entire Near-Earth Asteroid (NEA) to the vicinity of the Earth by the middle of the next decade. The feasibility hinges on finding an overlap between the smallest NEAs that can be reasonably discovered and characterized and the largest NEAs that can be captured and transported in a reasonable flight time. This overlap appears to be centered on NEAs with a nominal diameter of roughly 7 m corresponding to masses in the range of 250,000 kg to 1,000,000 kg. Trajectory analysis based on asteroid 2008HU4 suggests that such an asteroid could be returned to a high-Earth orbit using a single Atlas V-class launch vehicle and a 40-kW solar electric propulsion system by 2026. The return of such an object could serve as a testbed for human operations in the vicinity of an asteroid. It would provide a wealth of scientific and engineering information and would enable detailed evaluation of its resource potential, determination of its internal structure and other aspects important for planetary defense activities.
{"title":"Asteroid retrieval feasibility","authors":"J. Brophy, L. Friedman, F. Culick","doi":"10.1109/AERO.2012.6187031","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187031","url":null,"abstract":"This paper describes the interim results of a study sponsored by the Keck Institute for Space Studies to investigate the feasibility of identifying, robotically capturing, and returning an entire Near-Earth Asteroid (NEA) to the vicinity of the Earth by the middle of the next decade. The feasibility hinges on finding an overlap between the smallest NEAs that can be reasonably discovered and characterized and the largest NEAs that can be captured and transported in a reasonable flight time. This overlap appears to be centered on NEAs with a nominal diameter of roughly 7 m corresponding to masses in the range of 250,000 kg to 1,000,000 kg. Trajectory analysis based on asteroid 2008HU4 suggests that such an asteroid could be returned to a high-Earth orbit using a single Atlas V-class launch vehicle and a 40-kW solar electric propulsion system by 2026. The return of such an object could serve as a testbed for human operations in the vicinity of an asteroid. It would provide a wealth of scientific and engineering information and would enable detailed evaluation of its resource potential, determination of its internal structure and other aspects important for planetary defense activities.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"20 1","pages":"1-16"},"PeriodicalIF":0.0,"publicationDate":"2012-03-03","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"81330158","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.2012.6187000
E. Stern, M. Barnhardt, E. Venkatapathy, G. Candler, D. Prabhu
A numerical investigation of transonic flow around a mechanically deployable entry system being considered for a robotic mission to Venus has been performed, and preliminary results are reported. The flow around a conceptual representation of the vehicle geometry was simulated at discrete points along a ballistic trajectory using Detached Eddy Simulation (DES). The trajectory points selected span the low supersonic to transonic regimes with freestream Mach numbers from 1.5 to 0.8, and freestream Reynolds numbers (based on diameter) between 2.09 × 106 and 2.93 × 106. Additionally, the Mach 0.8 case was simulated at angles of attack between 0° and 5°. Static aerodynamic coefficients obtained from the data show qualitative agreement with data from 70° sphere-cone wind tunnel tests performed for the Viking program. Finally, the effect of choices of models and numerical algorithms is addressed by comparing the DES results to those using a Reynolds Averaged Navier-Stokes (RANS) model, as well as to results using a more dissipative numerical scheme.
{"title":"Investigation of transonic wake dynamics for mechanically deployable entry systems","authors":"E. Stern, M. Barnhardt, E. Venkatapathy, G. Candler, D. Prabhu","doi":"10.1109/AERO.2012.6187000","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187000","url":null,"abstract":"A numerical investigation of transonic flow around a mechanically deployable entry system being considered for a robotic mission to Venus has been performed, and preliminary results are reported. The flow around a conceptual representation of the vehicle geometry was simulated at discrete points along a ballistic trajectory using Detached Eddy Simulation (DES). The trajectory points selected span the low supersonic to transonic regimes with freestream Mach numbers from 1.5 to 0.8, and freestream Reynolds numbers (based on diameter) between 2.09 × 106 and 2.93 × 106. Additionally, the Mach 0.8 case was simulated at angles of attack between 0° and 5°. Static aerodynamic coefficients obtained from the data show qualitative agreement with data from 70° sphere-cone wind tunnel tests performed for the Viking program. Finally, the effect of choices of models and numerical algorithms is addressed by comparing the DES results to those using a Reynolds Averaged Navier-Stokes (RANS) model, as well as to results using a more dissipative numerical scheme.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"46 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":"81631957","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.2012.6187214
C. Xianxiang, S. Jianmei, C. Gaohua
Robust gain-scheduled acceleration autopilot design using Linear Parameter Varying(LPV) reference model is presented for portable missile with large-scale parameter variation and unmodelled dynamics. Damping loop is designed firstly with a varying feedback gain to improve the dynamics characteristics of the portable missile. The LPV reference model and the damped missile dynamics are integrated together as the generalized controlled plant. Then the robust gain-scheduled control technique, i.e. LPV/μ mixed control, is applied to design the acceleration tracking autopilot for the portable missile. The D-K-D iteration with GEVP is utilized to optimize the performance index and obtain the control structure. Simulation results show that with the LPV/μ mixed control and LPV reference model being applied in the portable missile, deflection angle and deflection angular rate can be constrained to the reasonable limit at slow speed, and desired autopilot performance can be achieved in the full flight envelope and with some unmodelled dynamics. The design method is suitable and effective for the portable missile.
{"title":"Robust gain-scheduled autopilot design with LPV reference model for portable missile","authors":"C. Xianxiang, S. Jianmei, C. Gaohua","doi":"10.1109/AERO.2012.6187214","DOIUrl":"https://doi.org/10.1109/AERO.2012.6187214","url":null,"abstract":"Robust gain-scheduled acceleration autopilot design using Linear Parameter Varying(LPV) reference model is presented for portable missile with large-scale parameter variation and unmodelled dynamics. Damping loop is designed firstly with a varying feedback gain to improve the dynamics characteristics of the portable missile. The LPV reference model and the damped missile dynamics are integrated together as the generalized controlled plant. Then the robust gain-scheduled control technique, i.e. LPV/μ mixed control, is applied to design the acceleration tracking autopilot for the portable missile. The D-K-D iteration with GEVP is utilized to optimize the performance index and obtain the control structure. Simulation results show that with the LPV/μ mixed control and LPV reference model being applied in the portable missile, deflection angle and deflection angular rate can be constrained to the reasonable limit at slow speed, and desired autopilot performance can be achieved in the full flight envelope and with some unmodelled dynamics. The design method is suitable and effective for the portable missile.","PeriodicalId":6421,"journal":{"name":"2012 IEEE Aerospace Conference","volume":"78 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":"84056977","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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