Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)最新文献
C. Mai, D. Dawson, Rajan Kumar, Simon Kirby, T. Birch
{"title":"Characterization of Independent Aerodynamic Effects of Tail-Fin Deflections on an Axisymmetric Body","authors":"C. Mai, D. Dawson, Rajan Kumar, Simon Kirby, T. Birch","doi":"10.2514/6.2020-1994","DOIUrl":"https://doi.org/10.2514/6.2020-1994","url":null,"abstract":"","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"22 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"82619283","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}
Faith A. Loughnane, Rachael Supina, Michael P. Mongin, Sidaard Gunasekaran
The effect of undulation placement (leading edge, trailing edge, leading and trailing edge) on the wing performance and the wingtip vortex was investigated. Experiments were performed at the University of Dayton Low Speed Wind Tunnel (UD-LSWT) on undulated wings where the NACA 0012 airfoil crosssection is preserved along the wingspan. Sensitivity studies were done on the undulation wavelength along the span (λ/c 0.31, 0.21 and 0.15) and undulation placement (leading edge, trailing edge, and both leading and trailing edge). The leading edge undulations delayed stall until higher angles of attack, however, the maximum aerodynamic efficiency was reduced. The trailing edge undulated wing on the other hand increased the maximum aerodynamic efficiency but was not successful in stall mitigation. Wings with both leading and trailing edge undulations showed improvement in aerodynamic efficiency as well as delayed stall. The effect of the undulations on the wingtip vortex was also investigated through Particle Image Velocimetry (PIV). For the same coefficient of lift, the undulated wing cases reduced the wingtip vortex circulation by 25%. Investigations into the wingtip vortex core RMS and aerodynamic efficiency revealed a direct relationship where a higher vortex core RMS resulted in a higher aerodynamic efficiency and viceversa. Dedication or Acknowledgements The author acknowledges the partial funding from Henry Luce Foundation through the Clare Boothe Luce Scholars Program for the work presented in this thesis. The author would also like to acknowledge the Ohio Space Grant Consortium (OSGC) for partially funding the primary author for performing undergraduate research. The author would also like to thank UD wind tunnel technician, Jielong Cai, and research partner, Michael Mongin, for helping with manufacturing wind tunnel models and performing experiments.
{"title":"Effect of Airfoil-Preserved Undulations on Wing Performance","authors":"Faith A. Loughnane, Rachael Supina, Michael P. Mongin, Sidaard Gunasekaran","doi":"10.2514/6.2020-1784","DOIUrl":"https://doi.org/10.2514/6.2020-1784","url":null,"abstract":"The effect of undulation placement (leading edge, trailing edge, leading and trailing edge) on the wing performance and the wingtip vortex was investigated. Experiments were performed at the University of Dayton Low Speed Wind Tunnel (UD-LSWT) on undulated wings where the NACA 0012 airfoil crosssection is preserved along the wingspan. Sensitivity studies were done on the undulation wavelength along the span (λ/c 0.31, 0.21 and 0.15) and undulation placement (leading edge, trailing edge, and both leading and trailing edge). The leading edge undulations delayed stall until higher angles of attack, however, the maximum aerodynamic efficiency was reduced. The trailing edge undulated wing on the other hand increased the maximum aerodynamic efficiency but was not successful in stall mitigation. Wings with both leading and trailing edge undulations showed improvement in aerodynamic efficiency as well as delayed stall. The effect of the undulations on the wingtip vortex was also investigated through Particle Image Velocimetry (PIV). For the same coefficient of lift, the undulated wing cases reduced the wingtip vortex circulation by 25%. Investigations into the wingtip vortex core RMS and aerodynamic efficiency revealed a direct relationship where a higher vortex core RMS resulted in a higher aerodynamic efficiency and viceversa. Dedication or Acknowledgements The author acknowledges the partial funding from Henry Luce Foundation through the Clare Boothe Luce Scholars Program for the work presented in this thesis. The author would also like to acknowledge the Ohio Space Grant Consortium (OSGC) for partially funding the primary author for performing undergraduate research. The author would also like to thank UD wind tunnel technician, Jielong Cai, and research partner, Michael Mongin, for helping with manufacturing wind tunnel models and performing experiments.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"6 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"90480549","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}
{"title":"Impact-Geometry Maps; Visualization of Kinetic Impact Effectiveness for Asteroid Deflection Missions","authors":"K. Yamaguchi, R. Hayama, Kikuko Miyata, S. Hara","doi":"10.2514/6.2020-0224","DOIUrl":"https://doi.org/10.2514/6.2020-0224","url":null,"abstract":"","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"65 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"89249051","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}
{"title":"Application of Non-Linear Harmonic and Time Marching techniques to analyze aerodynamics of inlet distortion in a Tail-Cone Thruster Fan stage","authors":"Ritangshu Giri, M. Turner, M. Celestina","doi":"10.2514/6.2020-0385","DOIUrl":"https://doi.org/10.2514/6.2020-0385","url":null,"abstract":"","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"67 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85788871","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}
Recent developments in fast additive manufacturing, such as rapid 3D printing of composite materials, present opportunities for the manufacturing of small unmanned aerial vehicles (UAVs) that are tailor-made for the specific mission needs. This paper presents a novel framework for mission-oriented, modular design and construction of mini-UAVs using additive manufacturing. The outcome is a manufacturing method which is suitable for a parametric design that can be tailored for specific mission requirements, and rapidly constructed using additive manufacturing techniques. We show how additive manufacturing enables an agile design methodology by allowing fast and efficient iteration of prototypes during the design process. The proposed framework is demonstrated by the design of a tail-sitter hybrid VTOL vehicle, for which wing-tip geometry and wing dihedral angle were optimized over several iterations of rapid prototyping. Additionally, we present a flight performance validation of the resulting vehicle design through flight tests in a motion capture facility and outdoors. Finally we show several other vehicle configurations, such as quadrotors and a fixed-wing aircraft, that also take advantage of the proposed design and manufacturing methods.
{"title":"Mission-Oriented Additive Manufacturing of Modular Mini-UAVs","authors":"M. Bronz, E. Tal, F. Favalli, S. Karaman","doi":"10.2514/6.2020-0064","DOIUrl":"https://doi.org/10.2514/6.2020-0064","url":null,"abstract":"Recent developments in fast additive manufacturing, such as rapid 3D printing of composite materials, present opportunities for the manufacturing of small unmanned aerial vehicles (UAVs) that are tailor-made for the specific mission needs. This paper presents a novel framework for mission-oriented, modular design and construction of mini-UAVs using additive manufacturing. The outcome is a manufacturing method which is suitable for a parametric design that can be tailored for specific mission requirements, and rapidly constructed using additive manufacturing techniques. We show how additive manufacturing enables an agile design methodology by allowing fast and efficient iteration of prototypes during the design process. The proposed framework is demonstrated by the design of a tail-sitter hybrid VTOL vehicle, for which wing-tip geometry and wing dihedral angle were optimized over several iterations of rapid prototyping. Additionally, we present a flight performance validation of the resulting vehicle design through flight tests in a motion capture facility and outdoors. Finally we show several other vehicle configurations, such as quadrotors and a fixed-wing aircraft, that also take advantage of the proposed design and manufacturing methods.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"2003 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86248733","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}
Recent advances in planetary entry guidance algorithms are motived by precision landing criteria for human-scale Mars missions and improved in-space computing capabilities. An NPC targeting guidance algorithm, originally developed for the Mars Surveyor Program 2001 Missions, has been modified and extended to permit a fully generalized, flexible, and robust approach to spacecraft aerocapture and EDL guidance design. This paper describes this generalized targeting NPC guidance (NPCG) and how its modifications enable its use in precision targeting for human missions. System modeling, trajectory propagation, and guidance segment definition and design are described. Finally, the NPCG capability and performance is demonstrated using a human-scale Mars entry, descent, and landing mission simulation.
{"title":"Overview of a Generalized Numerical Predictor-Corrector Targeting Guidance with Application to Human-Scale Mars Entry, Descent, and Landing","authors":"R. Lugo, R. Powell, A. Dwyer-Cianciolo","doi":"10.2514/6.2020-0846","DOIUrl":"https://doi.org/10.2514/6.2020-0846","url":null,"abstract":"Recent advances in planetary entry guidance algorithms are motived by precision landing criteria for human-scale Mars missions and improved in-space computing capabilities. An NPC targeting guidance algorithm, originally developed for the Mars Surveyor Program 2001 Missions, has been modified and extended to permit a fully generalized, flexible, and robust approach to spacecraft aerocapture and EDL guidance design. This paper describes this generalized targeting NPC guidance (NPCG) and how its modifications enable its use in precision targeting for human missions. System modeling, trajectory propagation, and guidance segment definition and design are described. Finally, the NPCG capability and performance is demonstrated using a human-scale Mars entry, descent, and landing mission simulation.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"27 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"88728340","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}
G. D. Rooij, D. V. Baelen, C. Borst, M. V. Paassen, M. Mulder
This paper describes the design and evaluation of a visual display in supplementing haptic feedback on the side stick as a way to communicate flight envelope boundaries to pilots. The design adds indications for the limits in airspeed, load factor, angle of attack and angle of bank to a standard Airbus primary flight display (PFD). The indications not only show the limits of the flight envelope, but also indicate magnitude and direction of the haptic cues. Fifteen professional Airbus pilots and one Airbus sim instructor participated in an experiment in the SIMONA Research Simulator at Delft University of Technology. Several approaches in three different scenarios were flown in alternate law with the old and new PFD, while haptic feedback was always enabled. Objective results do not show clear improvements with the new display, although the time spent outside the flight envelope is slightly reduced. Subjective results indicate a preference, however, for the new display and an increased understanding of the haptic feedback. Further research is recommended to focus on improving the design by removing unused indications and setting up an experiment with a bank scenario that allows the use of operational bank limits rather than artificially reduced limits.
{"title":"Supplementing Haptic Feedback Through the Visual Display of Flight Envelope Boundaries","authors":"G. D. Rooij, D. V. Baelen, C. Borst, M. V. Paassen, M. Mulder","doi":"10.2514/6.2020-0373","DOIUrl":"https://doi.org/10.2514/6.2020-0373","url":null,"abstract":"This paper describes the design and evaluation of a visual display in supplementing haptic feedback on the side stick as a way to communicate flight envelope boundaries to pilots. The design adds indications for the limits in airspeed, load factor, angle of attack and angle of bank to a standard Airbus primary flight display (PFD). The indications not only show the limits of the flight envelope, but also indicate magnitude and direction of the haptic cues. Fifteen professional Airbus pilots and one Airbus sim instructor participated in an experiment in the SIMONA Research Simulator at Delft University of Technology. Several approaches in three different scenarios were flown in alternate law with the old and new PFD, while haptic feedback was always enabled. Objective results do not show clear improvements with the new display, although the time spent outside the flight envelope is slightly reduced. Subjective results indicate a preference, however, for the new display and an increased understanding of the haptic feedback. Further research is recommended to focus on improving the design by removing unused indications and setting up an experiment with a bank scenario that allows the use of operational bank limits rather than artificially reduced limits.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"75 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"86176959","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}
HAL is a multi-disciplinary open access archive for the deposit and dissemination of scientific research documents, whether they are published or not. The documents may come from teaching and research institutions in France or abroad, or from public or private research centers. L’archive ouverte pluridisciplinaire HAL, est destinée au dépôt et à la diffusion de documents scientifiques de niveau recherche, publiés ou non, émanant des établissements d’enseignement et de recherche français ou étrangers, des laboratoires publics ou privés. Receptivity to synthetic jet actuation in boundary layer flows Andrea Palumbo, Onofrio Semeraro, Jean-Christophe Robinet, Luigi de Luca
它是一个多学科的开放获取档案，用于科学研究文件的存储和传播，无论它们是否出版。这些文件可能来自法国或国外的教学和研究机构，也可能来自公共或私人研究中心。HAL开放多学科档案旨在存放和传播来自法国或外国教育和研究机构、公共或私人实验室的已发表或未发表的研究级科学文件。Andrea Palumbo, Onofrio Semeraro, Jean-Christophe Robinet, Luigi de Luca
{"title":"Receptivity to synthetic jet actuation in boundary layer flows","authors":"A. Palumbo, Onofrio Semeraro, J. Robinet, L. Luca","doi":"10.2514/6.2020-0099","DOIUrl":"https://doi.org/10.2514/6.2020-0099","url":null,"abstract":"HAL is a multi-disciplinary open access archive for the deposit and dissemination of scientific research documents, whether they are published or not. The documents may come from teaching and research institutions in France or abroad, or from public or private research centers. L’archive ouverte pluridisciplinaire HAL, est destinée au dépôt et à la diffusion de documents scientifiques de niveau recherche, publiés ou non, émanant des établissements d’enseignement et de recherche français ou étrangers, des laboratoires publics ou privés. Receptivity to synthetic jet actuation in boundary layer flows Andrea Palumbo, Onofrio Semeraro, Jean-Christophe Robinet, Luigi de Luca","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"74 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"85715994","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}
In this paper, an online flight envelope protection system is developed and implemented on impaired aircraft with structural damage. The whole protection system is designed to be a closed-loop of several sub-systems, including system identification, damage classification, flight-envelope prediction and fault-tolerant control. Based on the information given by damage classification, the flight envelopes are explicitly retrieved and processed online from the database and fed into the fault-tolerant controller, which makes the protection system adaptive to a wide range of abnormal conditions. Simulation results show that with envelope protection, loss-of-control accidents are more likely to be prevented, since both the controller and pilots are aware of the shrunken flight envelopes after damage and excessive commands are restricted. In this way, the fault-tolerance of the impaired aircraft can be effectively enhanced.
{"title":"Database-driven Safe Flight Envelope Protection for Impaired Aircraft","authors":"Yong Zhang, Yamin Huang, Q. Chu, C. C. Visser","doi":"10.2514/6.2020-1374","DOIUrl":"https://doi.org/10.2514/6.2020-1374","url":null,"abstract":"In this paper, an online flight envelope protection system is developed and implemented on impaired aircraft with structural damage. The whole protection system is designed to be a closed-loop of several sub-systems, including system identification, damage classification, flight-envelope prediction and fault-tolerant control. Based on the information given by damage classification, the flight envelopes are explicitly retrieved and processed online from the database and fed into the fault-tolerant controller, which makes the protection system adaptive to a wide range of abnormal conditions. Simulation results show that with envelope protection, loss-of-control accidents are more likely to be prevented, since both the controller and pilots are aware of the shrunken flight envelopes after damage and excessive commands are restricted. In this way, the fault-tolerance of the impaired aircraft can be effectively enhanced.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"16 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"91088475","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}
Previous studies have shown that implementing trajectory optimization can reduce state estimations errors. These navigation based path planning problems are often diffcult to solve being computationally burdensome and exhibiting other numerical issues, so former studies have often used lower-?delity methods or lacked explanatory power.This work utilizes indirect optimization methods, particularly optimal control theory, to obtain high-quality solutions minimizing state estimation errors approximated by a continuous-time extended Kalman ?lter. Indirect methods are well-suited to this because necessary conditions of optimality are found prior to discretization and numerical computation. They are also highly parallelizable enabling application to increasingly larger problems.A simple one dimensional problem shows some potential obstacles to solving problems of this type including regions of the trajectory where the control is unimportant. Indirect trajectory optimization is applied to a more complex scenario to minimize location estimation errors of a single cart traveling in a 2-D plane to a goal location and measuring range from a ?xed beacon. This resulted in a 96% reduction of the location error variance when compared to the minimum time solution. The single cart problem also highlights the importance of the matrix that encodes the linearization of the vehicle's measurement with respect to state. It is shown in this case that the vehicle roughly attempts to maximize the magnitude of its elements. Additionally, the cart problem further illustrates problematic regions of a design space where the objective is not signi?cantly affected by the trajectory.An aircraft descent problem demonstrates the applicability of these methods to aerospace problems. In this case, estimation error variance is reduced 28.6% relative to the maximum terminal energy trajectory. Results are shown from two formulations of this problem, one with control constraints and one with control energy cost, to show the bene?ts and disadvantages of the two methods. Furthermore, the ability to perform trade studies on vehicle and trajectory parameters is shown with this problem by solving for di?erent terminal velocities and different initial locations.
{"title":"Navigation Based Path Planning by Optimal Control Theory","authors":"Sean M. Nolan, M. J. Grant, Adam J. Rutkowski","doi":"10.25394/PGS.7501865.V1","DOIUrl":"https://doi.org/10.25394/PGS.7501865.V1","url":null,"abstract":"Previous studies have shown that implementing trajectory optimization can reduce state estimations errors. These navigation based path planning problems are often diffcult to solve being computationally burdensome and exhibiting other numerical issues, so former studies have often used lower-?delity methods or lacked explanatory power.This work utilizes indirect optimization methods, particularly optimal control theory, to obtain high-quality solutions minimizing state estimation errors approximated by a continuous-time extended Kalman ?lter. Indirect methods are well-suited to this because necessary conditions of optimality are found prior to discretization and numerical computation. They are also highly parallelizable enabling application to increasingly larger problems.A simple one dimensional problem shows some potential obstacles to solving problems of this type including regions of the trajectory where the control is unimportant. Indirect trajectory optimization is applied to a more complex scenario to minimize location estimation errors of a single cart traveling in a 2-D plane to a goal location and measuring range from a ?xed beacon. This resulted in a 96% reduction of the location error variance when compared to the minimum time solution. The single cart problem also highlights the importance of the matrix that encodes the linearization of the vehicle's measurement with respect to state. It is shown in this case that the vehicle roughly attempts to maximize the magnitude of its elements. Additionally, the cart problem further illustrates problematic regions of a design space where the objective is not signi?cantly affected by the trajectory.An aircraft descent problem demonstrates the applicability of these methods to aerospace problems. In this case, estimation error variance is reduced 28.6% relative to the maximum terminal energy trajectory. Results are shown from two formulations of this problem, one with control constraints and one with control energy cost, to show the bene?ts and disadvantages of the two methods. Furthermore, the ability to perform trade studies on vehicle and trajectory parameters is shown with this problem by solving for di?erent terminal velocities and different initial locations.","PeriodicalId":93413,"journal":{"name":"Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)","volume":"361 1","pages":""},"PeriodicalIF":0.0,"publicationDate":"2020-01-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"80249635","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}
Applied aerodynamics : papers presented at the AIAA SciTech Forum and Exposition 2020 : Orlando, Florida, USA, 6-10 January 2020. AIAA SciTech Forum and Exposition (2020 : Orlando, Fla.)
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