Hongwei Yang, Limin Qin, Shuang Li, Junpo Niu, Haiyang Li
Periodic orbits are widely used in space missions and are fundamental for us to understand the complex dynamic system of circular restricted three-body problem. However, there are still many potential families of periodic orbits that have not been located and computed. This study aims to generate some new and less-known families of periodic orbits for the Jupiter–Callisto system to obtain an extended database. The numerical methods for the computation and continuation of periodic orbit families are provided. Five bifurcation diagrams are explored in depth, and 108 periodic orbit families are located. Of these, 59 families are continued to the entire families. Twenty asymmetrical families also come into view. New discoveries and the characteristics of several particular families are presented and discussed. Synodic resonant periodic orbits appearing under the perturbation of Ganymede are also identified. The expanded families of periodic orbits are expected to provide a reference for future Callisto exploration mission design.
{"title":"Expanded Families of Periodic Orbits for the Jupiter–Callisto System","authors":"Hongwei Yang, Limin Qin, Shuang Li, Junpo Niu, Haiyang Li","doi":"10.2514/1.a35818","DOIUrl":"https://doi.org/10.2514/1.a35818","url":null,"abstract":"Periodic orbits are widely used in space missions and are fundamental for us to understand the complex dynamic system of circular restricted three-body problem. However, there are still many potential families of periodic orbits that have not been located and computed. This study aims to generate some new and less-known families of periodic orbits for the Jupiter–Callisto system to obtain an extended database. The numerical methods for the computation and continuation of periodic orbit families are provided. Five bifurcation diagrams are explored in depth, and 108 periodic orbit families are located. Of these, 59 families are continued to the entire families. Twenty asymmetrical families also come into view. New discoveries and the characteristics of several particular families are presented and discussed. Synodic resonant periodic orbits appearing under the perturbation of Ganymede are also identified. The expanded families of periodic orbits are expected to provide a reference for future Callisto exploration mission design.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"37 1","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-12-21","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138951057","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
M. Ghoreyshi, Nathan M. Shumway, P. Aref, Adam Jirasek, Jürgen Seidel
This paper summarizes an investigation of the aerodynamic performance of missile configurations with axisymmetric and nonaxisymmetric cross sections. Configurations have either a circular, oval, pentagonal, triangular, or square cross section and were tested at three different flight conditions: [Formula: see text] and Reynolds number per inch of [Formula: see text], [Formula: see text] and Reynolds number per inch of [Formula: see text], and [Formula: see text] and Reynolds number per inch of [Formula: see text]. The influence of Mach number, shape, and fin deflection was investigated. A prescribed body motion was used to expedite the prediction of the missile aerodynamic forces and moments at different angles of attack compared to many static computational fluid dynamics simulations. The results show that the oval missile model is the most aerodynamically efficient body at all the tested speeds. At higher speeds, all nonstandard configurations produce more normal force and better aerodynamic efficiency than the circular body. The triangular configuration is much less stable than the other models.
{"title":"Aerodynamic Characteristics of Circular and Noncircular Cross-Sectional Missile Configurations","authors":"M. Ghoreyshi, Nathan M. Shumway, P. Aref, Adam Jirasek, Jürgen Seidel","doi":"10.2514/1.a35745","DOIUrl":"https://doi.org/10.2514/1.a35745","url":null,"abstract":"This paper summarizes an investigation of the aerodynamic performance of missile configurations with axisymmetric and nonaxisymmetric cross sections. Configurations have either a circular, oval, pentagonal, triangular, or square cross section and were tested at three different flight conditions: [Formula: see text] and Reynolds number per inch of [Formula: see text], [Formula: see text] and Reynolds number per inch of [Formula: see text], and [Formula: see text] and Reynolds number per inch of [Formula: see text]. The influence of Mach number, shape, and fin deflection was investigated. A prescribed body motion was used to expedite the prediction of the missile aerodynamic forces and moments at different angles of attack compared to many static computational fluid dynamics simulations. The results show that the oval missile model is the most aerodynamically efficient body at all the tested speeds. At higher speeds, all nonstandard configurations produce more normal force and better aerodynamic efficiency than the circular body. The triangular configuration is much less stable than the other models.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"105 3","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-12-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139010680","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
In this paper, a mesh-adaptive Hermite–Simpson sequential convex programming (SCP) method is proposed for solving low-thrust orbit transfer problems efficiently and accurately. First, we develop a Hermite–Simpson convex programming method that utilizes quadratic polynomial control interpolation to improve discretization accuracy. Then, a mesh-adaptive Hermite–Simpson SCP method is proposed by incorporating an improved adaptive mesh refinement method into the Hermite–Simpson SCP method for solving optimal control accurately and efficiently. The proposed method is applied to two-dimensional time-optimal and three-dimensional fuel-optimal low-thrust orbit transfer problems to show its features, and its performance is compared against several existing methods. Numerical simulations show that the proposed method achieves more accurate solutions while being computationally more efficient compared to the trapezoidal SCP method. In comparison to the GPOPS-II software, the proposed method produces solutions of comparable accuracy but is more computationally efficient.
{"title":"Low-Thrust Transfer Orbit Optimization Using Sequential Convex Programming and Adaptive Mesh Refinement","authors":"Jisong Zhao, Jia Li, Shuanglin Li","doi":"10.2514/1.a35817","DOIUrl":"https://doi.org/10.2514/1.a35817","url":null,"abstract":"In this paper, a mesh-adaptive Hermite–Simpson sequential convex programming (SCP) method is proposed for solving low-thrust orbit transfer problems efficiently and accurately. First, we develop a Hermite–Simpson convex programming method that utilizes quadratic polynomial control interpolation to improve discretization accuracy. Then, a mesh-adaptive Hermite–Simpson SCP method is proposed by incorporating an improved adaptive mesh refinement method into the Hermite–Simpson SCP method for solving optimal control accurately and efficiently. The proposed method is applied to two-dimensional time-optimal and three-dimensional fuel-optimal low-thrust orbit transfer problems to show its features, and its performance is compared against several existing methods. Numerical simulations show that the proposed method achieves more accurate solutions while being computationally more efficient compared to the trapezoidal SCP method. In comparison to the GPOPS-II software, the proposed method produces solutions of comparable accuracy but is more computationally efficient.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"6 11","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-12-09","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138585544","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The stable extended and coiled states of thin-shelled composite booms with parabolic cross sections are investigated in this paper. These conic shapes potentially offer greater stiffness properties when compared to circular cross sections, which is critical for improving the load-bearing performance of deployed booms. Inducing bistability through composite layups in parabolic booms would allow for controllable self-deployment due to a less energetic coiled state when compared to monostable booms. An inextensional analytical model is used to predict the stable coiled diameters of tape spring and collapsible tubular mast (CTM) booms with parabolic cross sections. The parabolic section is discretized into circular segments using biarc spline interpolation, which allows them to be integrated into the strain energy minimization procedure used to obtain the equilibrium states. When the parabolic booms are parametrically compared against circular booms with identical layups, flattened height, and mass, the former are found to generally have better stiffness performance while being less efficient in stowed volume, as evidenced by larger coiled diameters. Analytical coiled diameters and their strain energy are verified with finite element simulations for an optimal parabolic tape spring and CTM booms. Additional validation of the parabolic tape spring’s coiled diameter is provided by experimental measurements of boom specimens.
{"title":"Bistable Deployable Composite Booms with Parabolic Cross Sections","authors":"Andrew J. Lee, Juan M. Fernandez, Jacob G. Daye","doi":"10.2514/1.a35840","DOIUrl":"https://doi.org/10.2514/1.a35840","url":null,"abstract":"The stable extended and coiled states of thin-shelled composite booms with parabolic cross sections are investigated in this paper. These conic shapes potentially offer greater stiffness properties when compared to circular cross sections, which is critical for improving the load-bearing performance of deployed booms. Inducing bistability through composite layups in parabolic booms would allow for controllable self-deployment due to a less energetic coiled state when compared to monostable booms. An inextensional analytical model is used to predict the stable coiled diameters of tape spring and collapsible tubular mast (CTM) booms with parabolic cross sections. The parabolic section is discretized into circular segments using biarc spline interpolation, which allows them to be integrated into the strain energy minimization procedure used to obtain the equilibrium states. When the parabolic booms are parametrically compared against circular booms with identical layups, flattened height, and mass, the former are found to generally have better stiffness performance while being less efficient in stowed volume, as evidenced by larger coiled diameters. Analytical coiled diameters and their strain energy are verified with finite element simulations for an optimal parabolic tape spring and CTM booms. Additional validation of the parabolic tape spring’s coiled diameter is provided by experimental measurements of boom specimens.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"23 3","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-11-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139197011","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Experiments and computations were performed at Mach number 2.0 for various nose cone fairing bodies with a sharp spike and conical spike of [Formula: see text] and with a sharp spike having a fixed tip location of different [Formula: see text] ratios. Attempts were made to alter the flowfield of various nose cone fairing bodies with the adoption of the spike. Qualitative and quantitative measurement studies indicate the changes that support the reduction of drag forces, not only on hemispherical blunt bodies but also on various nose cone fairings. This drag reduction with the configurations tested in this study indicates the importance of the region between the spike and the blunt-body face. The results presented here justify the quality and quantity of recirculating flow and its implication for drag reduction.
{"title":"Influence of Nose Cone Fairing and Spike on Supersonic Blunt Body Flows","authors":"MD. G. Sarwar, Priyank Kumar, S. Das","doi":"10.2514/1.a35757","DOIUrl":"https://doi.org/10.2514/1.a35757","url":null,"abstract":"Experiments and computations were performed at Mach number 2.0 for various nose cone fairing bodies with a sharp spike and conical spike of [Formula: see text] and with a sharp spike having a fixed tip location of different [Formula: see text] ratios. Attempts were made to alter the flowfield of various nose cone fairing bodies with the adoption of the spike. Qualitative and quantitative measurement studies indicate the changes that support the reduction of drag forces, not only on hemispherical blunt bodies but also on various nose cone fairings. This drag reduction with the configurations tested in this study indicates the importance of the region between the spike and the blunt-body face. The results presented here justify the quality and quantity of recirculating flow and its implication for drag reduction.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"94 1","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-11-20","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139259217","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
This paper presents a theoretical examination of the potential debris conjunction dangers faced by mega-constellations in both low Earth orbit (LEO) and medium Earth orbit (MEO). The analysis focuses on the risks posed by debris fields created by breakups occurring during an orbit-raising maneuver for vehicle replacement and/or capability reconstitution, using current telecommunications mega-constellations, such as Starlink and OneWeb, as examples. The mega-constellation designs consist of 750 and 150 satellites arranged using the Walker-Delta design for the LEO and MEO cases, respectively. The research employs physics-based orbital propagation and Monte Carlo simulations to evaluate the potential consequences of a single satellite breakup during orbit raising. The results of the simulations are used to calculate the probability of catastrophic collision and compare the debris risk between the LEO and MEO mega-constellations, with a bimodality analysis conducted for the MEO constellation. Monte Carlo analysis indicates that the LEO mega-constellation features the highest percentage of potential catastrophic collisions between debris fragments and the mega-constellation. Specifically, satellite breakup events starting within an altitude range of 100–199 km below the LEO mega-constellation, or approximately at the midpoint of a Hohmann transfer from a 300-km parking orbit, pose the greatest risk to the constellation.
{"title":"Preliminary Debris Risk Analysis for Mega-Constellation Architectures After Orbit-Raising Fragmentation Event","authors":"Joseph C. Canoy, Robert A. Bettinger","doi":"10.2514/1.a35723","DOIUrl":"https://doi.org/10.2514/1.a35723","url":null,"abstract":"This paper presents a theoretical examination of the potential debris conjunction dangers faced by mega-constellations in both low Earth orbit (LEO) and medium Earth orbit (MEO). The analysis focuses on the risks posed by debris fields created by breakups occurring during an orbit-raising maneuver for vehicle replacement and/or capability reconstitution, using current telecommunications mega-constellations, such as Starlink and OneWeb, as examples. The mega-constellation designs consist of 750 and 150 satellites arranged using the Walker-Delta design for the LEO and MEO cases, respectively. The research employs physics-based orbital propagation and Monte Carlo simulations to evaluate the potential consequences of a single satellite breakup during orbit raising. The results of the simulations are used to calculate the probability of catastrophic collision and compare the debris risk between the LEO and MEO mega-constellations, with a bimodality analysis conducted for the MEO constellation. Monte Carlo analysis indicates that the LEO mega-constellation features the highest percentage of potential catastrophic collisions between debris fragments and the mega-constellation. Specifically, satellite breakup events starting within an altitude range of 100–199 km below the LEO mega-constellation, or approximately at the midpoint of a Hohmann transfer from a 300-km parking orbit, pose the greatest risk to the constellation.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"15 4","pages":""},"PeriodicalIF":1.6,"publicationDate":"2023-11-14","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"139277615","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
A semi-empirical physics-based ablation and thermal response model was developed for the 3-Dimensional Multifunctional Ablative Thermal Protection System (3D-MAT) material. Model validation was achieved through comparison between computation and available data obtained in the arc-jet test series, which were conducted at NASA Ames Research Center from 2014 to 2020. The charring ablator simulations for arc-jet test models presented in this work were computed by the Two-Dimensional Implicit Thermal Response and Ablation (TITAN) code, and the Data-Parallel Line Relaxation Method (DPLR) code was used for arc-jet flow simulations to estimate the arc-jet stream total enthalpy and define the aerothermal boundary conditions over the test model surface for TITAN simulations. Because of low surface catalytic efficiency of 3D-MAT char, the exact surface heating could not be determined. Thus, three different types of boundary conditions, including 1) fully catalytic surface heating, 2) noncatalytic surface heating, and 3) surface temperature and recession, were used in the TITAN simulation for model validation. The predicted surface and in-depth temperature history for arc-jet test models were compared with pyrometer and thermocouple data, and the predicted test model surface recession and char depth were compared against the posttest measurements.
{"title":"Validation of Ablation and Thermal Response Model for Three-Dimensional Multifunctional Ablator","authors":"Yih-Kanq Chen, Tahir Gökçen","doi":"10.2514/1.a35761","DOIUrl":"https://doi.org/10.2514/1.a35761","url":null,"abstract":"A semi-empirical physics-based ablation and thermal response model was developed for the 3-Dimensional Multifunctional Ablative Thermal Protection System (3D-MAT) material. Model validation was achieved through comparison between computation and available data obtained in the arc-jet test series, which were conducted at NASA Ames Research Center from 2014 to 2020. The charring ablator simulations for arc-jet test models presented in this work were computed by the Two-Dimensional Implicit Thermal Response and Ablation (TITAN) code, and the Data-Parallel Line Relaxation Method (DPLR) code was used for arc-jet flow simulations to estimate the arc-jet stream total enthalpy and define the aerothermal boundary conditions over the test model surface for TITAN simulations. Because of low surface catalytic efficiency of 3D-MAT char, the exact surface heating could not be determined. Thus, three different types of boundary conditions, including 1) fully catalytic surface heating, 2) noncatalytic surface heating, and 3) surface temperature and recession, were used in the TITAN simulation for model validation. The predicted surface and in-depth temperature history for arc-jet test models were compared with pyrometer and thermocouple data, and the predicted test model surface recession and char depth were compared against the posttest measurements.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"104 51","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-11-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135137129","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Randy Spicer, Fatima Miranda, Tom Cote, Thomas Itchkawich, Jonathan Black
The ability to additively manufacture structures on-orbit has the potential to fundamentally alter the traditional paradigm for how large spacecraft are constructed and launched into space. The space environment presents several unique challenges for additive manufacturing, including the need to operate in a vacuum. This paper presents the design, analysis, and test results for a passively cooled fused filament fabrication (FFF) 3D printer capable of manufacturing parts out of engineering-grade thermoplastics in the vacuum of space. Four high-temperature materials were successfully printed in high vacuum, including polyetherketoneketone, carbon-nanotube–polyetherketoneketone, polyetherimide, and carbon-nanotube–polyetherimide. Over 100 test coupons were printed in a vacuum and tested to confirm the feasibility of applying the FFF process in this environment. Lessons learned were documented throughout the vacuum printing test campaigns and are discussed here. This paper is part of a two-part series. Part I presented results for using a low-temperature hotend capable of printing hobby-grade materials in high vacuum and documented initial findings and lessons learned. Part II presents the results for a high-temperature hotend capable of printing engineering-grade plastics that are suitable for on-orbit manufacturing. The combined results of the two papers in this series can be used to inform future on-orbit additive manufacturing.
{"title":"High Vacuum Capable Fused Filament Fabrication 3D Printer, Part II: High-Temperature Polymers Suitable for In-Space Manufacturing","authors":"Randy Spicer, Fatima Miranda, Tom Cote, Thomas Itchkawich, Jonathan Black","doi":"10.2514/1.a35709","DOIUrl":"https://doi.org/10.2514/1.a35709","url":null,"abstract":"The ability to additively manufacture structures on-orbit has the potential to fundamentally alter the traditional paradigm for how large spacecraft are constructed and launched into space. The space environment presents several unique challenges for additive manufacturing, including the need to operate in a vacuum. This paper presents the design, analysis, and test results for a passively cooled fused filament fabrication (FFF) 3D printer capable of manufacturing parts out of engineering-grade thermoplastics in the vacuum of space. Four high-temperature materials were successfully printed in high vacuum, including polyetherketoneketone, carbon-nanotube–polyetherketoneketone, polyetherimide, and carbon-nanotube–polyetherimide. Over 100 test coupons were printed in a vacuum and tested to confirm the feasibility of applying the FFF process in this environment. Lessons learned were documented throughout the vacuum printing test campaigns and are discussed here. This paper is part of a two-part series. Part I presented results for using a low-temperature hotend capable of printing hobby-grade materials in high vacuum and documented initial findings and lessons learned. Part II presents the results for a high-temperature hotend capable of printing engineering-grade plastics that are suitable for on-orbit manufacturing. The combined results of the two papers in this series can be used to inform future on-orbit additive manufacturing.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"120 48","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-11-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135137880","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Bruno Tacchi, Tyler D. Stoffel, Alexandre Martin, Savio J. Poovathingal
The Kentucky Re-entry Universal Payload System (KRUPS) is a small spacecraft developed to provide flight data during atmospheric reentry. The KRUPS capsules made a historic reentry into the Earth’s atmosphere in 2021, and this work details the reconstruction of the flight trajectories by inverse estimation based on the flight data. A trajectory modeling program is used with a one-dimensional material response solver to generate a prediction of the stagnation wall temperature of the KRUPS capsule during of the KRUPS capsule during reentry. These temperature results are compared to the temperature data obtained during the mission, and the initial parameters of the trajectory simulation are optimized to find the best estimated trajectories. The inverse estimation is performed in three ways: by assuming radiative equilibrium at the wall, by estimating the wall temperature after the trajectory simulations are first performed, and by coupling the trajectory and one-dimensional material response solver. Finally, the best estimated trajectories are compared against simulations performed using a three-dimensional material response solver, the Kentucky Aerodynamics and Thermal-response System Fluid Material Response module. It is observed that all approaches converge to a possible ejection of the KRUPS capsule into the Earth’s atmosphere at 35 km.
{"title":"Reconstruction of the Kentucky Re-Entry Universal Payload System Hypersonic Flight Trajectory","authors":"Bruno Tacchi, Tyler D. Stoffel, Alexandre Martin, Savio J. Poovathingal","doi":"10.2514/1.a35826","DOIUrl":"https://doi.org/10.2514/1.a35826","url":null,"abstract":"The Kentucky Re-entry Universal Payload System (KRUPS) is a small spacecraft developed to provide flight data during atmospheric reentry. The KRUPS capsules made a historic reentry into the Earth’s atmosphere in 2021, and this work details the reconstruction of the flight trajectories by inverse estimation based on the flight data. A trajectory modeling program is used with a one-dimensional material response solver to generate a prediction of the stagnation wall temperature of the KRUPS capsule during of the KRUPS capsule during reentry. These temperature results are compared to the temperature data obtained during the mission, and the initial parameters of the trajectory simulation are optimized to find the best estimated trajectories. The inverse estimation is performed in three ways: by assuming radiative equilibrium at the wall, by estimating the wall temperature after the trajectory simulations are first performed, and by coupling the trajectory and one-dimensional material response solver. Finally, the best estimated trajectories are compared against simulations performed using a three-dimensional material response solver, the Kentucky Aerodynamics and Thermal-response System Fluid Material Response module. It is observed that all approaches converge to a possible ejection of the KRUPS capsule into the Earth’s atmosphere at 35 km.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"112 7","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-11-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135138517","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
This paper studies an orbital inspection game, which involves two spacecraft competing for imaging conditions in an on-orbit inspection mission. First, the main factors affecting the imaging conditions, including the sun angle, sun-angle changing rate, relative distance, and distance changing rate, are analyzed to formulate a realistic multiple-factor inspection game. An approximate switching-type payoff function is specially designed to incorporate all the boundary constraints of those factors into the game model. Then, the analytical necessary conditions for the Nash equilibrium are derived and converted as a two-point boundary value problem (TPBVP). But different from conventional routes to solve the challenging TPBVP, a lighter costate optimization method is proposed, which transforms the TPBVP to a direct optimization problem by employing the conclusion that the optimal thrust directions of both sides are the same and utilizing the theory of the epsilon-Nash equilibrium. The existence of the epsilon-Nash equilibrium is proven, and the necessary conditions for a small epsilon are derived to support the method. Finally, simulations of the GEO inspection missions demonstrated the superiority of the proposed game formulation and the high efficiency and accuracy of the proposed method.
{"title":"Orbital Inspection Game Formulation and Epsilon-Nash Equilibrium Solution","authors":"Zhen-Yu Li, Hai Zhu, Ya-Zhong Luo","doi":"10.2514/1.a35800","DOIUrl":"https://doi.org/10.2514/1.a35800","url":null,"abstract":"This paper studies an orbital inspection game, which involves two spacecraft competing for imaging conditions in an on-orbit inspection mission. First, the main factors affecting the imaging conditions, including the sun angle, sun-angle changing rate, relative distance, and distance changing rate, are analyzed to formulate a realistic multiple-factor inspection game. An approximate switching-type payoff function is specially designed to incorporate all the boundary constraints of those factors into the game model. Then, the analytical necessary conditions for the Nash equilibrium are derived and converted as a two-point boundary value problem (TPBVP). But different from conventional routes to solve the challenging TPBVP, a lighter costate optimization method is proposed, which transforms the TPBVP to a direct optimization problem by employing the conclusion that the optimal thrust directions of both sides are the same and utilizing the theory of the epsilon-Nash equilibrium. The existence of the epsilon-Nash equilibrium is proven, and the necessary conditions for a small epsilon are derived to support the method. Finally, simulations of the GEO inspection missions demonstrated the superiority of the proposed game formulation and the high efficiency and accuracy of the proposed method.","PeriodicalId":50048,"journal":{"name":"Journal of Spacecraft and Rockets","volume":"33 S124","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-11-08","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135343360","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":4,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
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