This paper focuses on optimizing the planform and vortex generators (VGs) to improve longitudinal stability of the lambda-wing aircraft by alleviating pitchup. The optimizations are performed in two stages using a Reynolds-averaged Navier–Stokes (RANS) solver that can accurately capture the vortical flow structure, affecting the pitchup. First, the planform configuration is optimized to minimize the rise in the pitching moment while maintaining aerodynamic and stealth performances. The designed planform delays the pitchup by 4 deg and increases the usable lift by 31% due to the leading-edge vortex (LEV) flow over the outboard wing. Second, the VGs are installed and optimized to reduce the sudden increase in the pitching moment at high angles of attack. The designed VGs partially eliminate the separated flow and recover the LEV on the outboard wing, suppressing the radical change in the pitching moment by 75%. Some quantitative difference in aerodynamic coefficients is observed in unsteady RANS computations, but the vortical flow unsteadiness minimally affects the flow structure, and the stability improvement remains over 80%. Overall, the generation and sustainability of the LEV are critical aerodynamic factors to secure longitudinal stability in designing the lambda-wing aircraft.
{"title":"Design Optimization of Lambda-Wing Planform and Vortex Generators for Longitudinal Instability Alleviation","authors":"Seonguk Lee, Chongam Kim","doi":"10.2514/1.c037495","DOIUrl":"https://doi.org/10.2514/1.c037495","url":null,"abstract":"This paper focuses on optimizing the planform and vortex generators (VGs) to improve longitudinal stability of the lambda-wing aircraft by alleviating pitchup. The optimizations are performed in two stages using a Reynolds-averaged Navier–Stokes (RANS) solver that can accurately capture the vortical flow structure, affecting the pitchup. First, the planform configuration is optimized to minimize the rise in the pitching moment while maintaining aerodynamic and stealth performances. The designed planform delays the pitchup by 4 deg and increases the usable lift by 31% due to the leading-edge vortex (LEV) flow over the outboard wing. Second, the VGs are installed and optimized to reduce the sudden increase in the pitching moment at high angles of attack. The designed VGs partially eliminate the separated flow and recover the LEV on the outboard wing, suppressing the radical change in the pitching moment by 75%. Some quantitative difference in aerodynamic coefficients is observed in unsteady RANS computations, but the vortical flow unsteadiness minimally affects the flow structure, and the stability improvement remains over 80%. Overall, the generation and sustainability of the LEV are critical aerodynamic factors to secure longitudinal stability in designing the lambda-wing aircraft.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"13 S3","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-11-02","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135974704","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Aeroelasticity in the transonic regime is challenging because of the strongly nonlinear phenomena involved in the formation of shock waves and flow separation. In this work, we introduce a computationally efficient framework for accurate transonic aeroelastic analysis. We use dynamic mode decomposition with control to extract surrogate models from high-fidelity computational fluid dynamics (CFD) simulations. Instead of identifying models of the full flowfield or focusing on global performance indices, we directly predict the pressure distribution on the body surface. The learned surrogate models provide information about the system’s stability and can be used for control synthesis and response studies. Specific techniques are introduced to avoid spurious instabilities of the aerodynamic model. We use the high-fidelity CFD code SU2 to generate data and test our method on the benchmark supercritical wing. Our Python-based software is fully open source and will be included in the SU2 package to streamline the workflow from defining the high-fidelity aerodynamic model to creating a surrogate model for flutter analysis.
{"title":"Data-Driven Modeling for Transonic Aeroelastic Analysis","authors":"Nicola Fonzi, Steven L. Brunton, Urban Fasel","doi":"10.2514/1.c037409","DOIUrl":"https://doi.org/10.2514/1.c037409","url":null,"abstract":"Aeroelasticity in the transonic regime is challenging because of the strongly nonlinear phenomena involved in the formation of shock waves and flow separation. In this work, we introduce a computationally efficient framework for accurate transonic aeroelastic analysis. We use dynamic mode decomposition with control to extract surrogate models from high-fidelity computational fluid dynamics (CFD) simulations. Instead of identifying models of the full flowfield or focusing on global performance indices, we directly predict the pressure distribution on the body surface. The learned surrogate models provide information about the system’s stability and can be used for control synthesis and response studies. Specific techniques are introduced to avoid spurious instabilities of the aerodynamic model. We use the high-fidelity CFD code SU2 to generate data and test our method on the benchmark supercritical wing. Our Python-based software is fully open source and will be included in the SU2 package to streamline the workflow from defining the high-fidelity aerodynamic model to creating a surrogate model for flutter analysis.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"31 2","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135166878","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
This study presents the development and validation of a computationally efficient prediction framework for the well-known nonlinear F-16 limit cycle oscillation (LCO) phenomenon. The framework relies on a simple physical working model that has been suggested and demonstrated in the past according to which LCO is primarily a flutter instability that is bounded by the existence of nonlinear structural damping (NSD), although potentially affected by nonlinear aerodynamic effects as well. In the framework developed herein, the NSD model is derived and calibrated using a novel method that simplifies the process and allows applicability of the derived NSD models for multiple aircraft download cases. Good LCO prediction capabilities are obtained using the suggested method in terms of LCO levels and trends with flight conditions, as demonstrated using four F-16 test configurations. This framework also allows several practical benefits, which makes it particularly suitable for industrial-level applications.
{"title":"Toward an Efficient Method for F-16 Limit Cycle Oscillation Prediction","authors":"Daniel Kariv, Donald L. Kunz, Michael Iovnovich","doi":"10.2514/1.c037391","DOIUrl":"https://doi.org/10.2514/1.c037391","url":null,"abstract":"This study presents the development and validation of a computationally efficient prediction framework for the well-known nonlinear F-16 limit cycle oscillation (LCO) phenomenon. The framework relies on a simple physical working model that has been suggested and demonstrated in the past according to which LCO is primarily a flutter instability that is bounded by the existence of nonlinear structural damping (NSD), although potentially affected by nonlinear aerodynamic effects as well. In the framework developed herein, the NSD model is derived and calibrated using a novel method that simplifies the process and allows applicability of the derived NSD models for multiple aircraft download cases. Good LCO prediction capabilities are obtained using the suggested method in terms of LCO levels and trends with flight conditions, as demonstrated using four F-16 test configurations. This framework also allows several practical benefits, which makes it particularly suitable for industrial-level applications.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"23 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135168718","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The paper investigates the unpowered descent of a rotor system through the upper atmosphere. Axial and helical trajectories are investigated in the context of fixed points as well as an optimal control problem for maximizing flight time. The mathematical model considered in the paper incorporates the fuselage degrees of freedom, dynamic inflow model, and airfoil characteristics that depend on Mach and Reynolds numbers. Considering a potential application as a descent mechanism, trajectory generation is performed to maximize the flight time. As an example, the performance in the Venusian atmosphere for rotors with different airfoil characteristics is assessed. To delineate the role of constraints, initial conditions, and aerodynamic forces on the optimal descent, the axial trajectory is studied by dividing it into two phases. The first phase corresponds to the trajectory determination through an optimization process wherein control inputs are provided such that states are within bounds. The second phase trajectory (below 70 km), although determined by solving the optimal control problem as in phase-I, is shown to be close to that achieved using control inputs corresponding to fixed points corresponding to each altitude. Apart from the axial flight, helical trajectories and corresponding fixed points are investigated using a rotating constant sideslip frame. Furthermore, optimal helical trajectories are also determined, which could be useful for rotor-based descent mechanisms. A comparison between axial and helical fixed-point solutions is also presented.
{"title":"Autorotation-Based Descent with Trajectory Optimization","authors":"Susmitha Patnala, Purnanand Elango, Ranjith Mohan, None Shamrao","doi":"10.2514/1.c036912","DOIUrl":"https://doi.org/10.2514/1.c036912","url":null,"abstract":"The paper investigates the unpowered descent of a rotor system through the upper atmosphere. Axial and helical trajectories are investigated in the context of fixed points as well as an optimal control problem for maximizing flight time. The mathematical model considered in the paper incorporates the fuselage degrees of freedom, dynamic inflow model, and airfoil characteristics that depend on Mach and Reynolds numbers. Considering a potential application as a descent mechanism, trajectory generation is performed to maximize the flight time. As an example, the performance in the Venusian atmosphere for rotors with different airfoil characteristics is assessed. To delineate the role of constraints, initial conditions, and aerodynamic forces on the optimal descent, the axial trajectory is studied by dividing it into two phases. The first phase corresponds to the trajectory determination through an optimization process wherein control inputs are provided such that states are within bounds. The second phase trajectory (below 70 km), although determined by solving the optimal control problem as in phase-I, is shown to be close to that achieved using control inputs corresponding to fixed points corresponding to each altitude. Apart from the axial flight, helical trajectories and corresponding fixed points are investigated using a rotating constant sideslip frame. Furthermore, optimal helical trajectories are also determined, which could be useful for rotor-based descent mechanisms. A comparison between axial and helical fixed-point solutions is also presented.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"69 12","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135266708","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Adarsh Prasannakumar, Anand Sudhi, Arne Seitz, Camli Badrya
Hybrid laminar flow control (HLFC) has shown significant promise in the viscous drag reduction of aircraft. However, the use of HLFC for commercial applications requires further simplification. The current study proposes tools for the conceptual design of transonic HLFC wing and suction system. In the first part of the study, airfoil sections for the wing are optimized for minimum total drag using a multi-objective genetic algorithm approach at six spanwise locations. The induced drag of the wing is estimated using a vortex lattice method solver. In the second part of the study, suction system design is performed using ASPeCT, an in-house solver for HLFC system design. A simplified inner structure for the suction system is proposed, which can be integrated easily within the wing structure. A total drag penalty approach is proposed to establish a tradeoff between matching the target suction distribution and the complexity of the suction system. Finally, the additional weight and off-design performance of the suction system are analyzed for a [Formula: see text] change in the design lift coefficient. A maximum fuel reduction of 7% can be expected with the HLFC system taking into account the additional weight added and power off-take from the engine.
{"title":"Design of Hybrid-Laminar-Flow-Control Wing and Suction System for Transonic Midrange Aircraft","authors":"Adarsh Prasannakumar, Anand Sudhi, Arne Seitz, Camli Badrya","doi":"10.2514/1.c037398","DOIUrl":"https://doi.org/10.2514/1.c037398","url":null,"abstract":"Hybrid laminar flow control (HLFC) has shown significant promise in the viscous drag reduction of aircraft. However, the use of HLFC for commercial applications requires further simplification. The current study proposes tools for the conceptual design of transonic HLFC wing and suction system. In the first part of the study, airfoil sections for the wing are optimized for minimum total drag using a multi-objective genetic algorithm approach at six spanwise locations. The induced drag of the wing is estimated using a vortex lattice method solver. In the second part of the study, suction system design is performed using ASPeCT, an in-house solver for HLFC system design. A simplified inner structure for the suction system is proposed, which can be integrated easily within the wing structure. A total drag penalty approach is proposed to establish a tradeoff between matching the target suction distribution and the complexity of the suction system. Finally, the additional weight and off-design performance of the suction system are analyzed for a [Formula: see text] change in the design lift coefficient. A maximum fuel reduction of 7% can be expected with the HLFC system taking into account the additional weight added and power off-take from the engine.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135883404","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Whirl flutter as an aeroelastic instability can be a limiting factor in the design and certification of turboprop aircraft configurations, especially for the engine suspension. Whirl flutter prediction for these configurations is currently done in the frequency domain using rigid propeller aerodynamic derivatives. Blade flexibility is neglected in this process, although it is known to have an impact on whirl flutter predictions. This paper uses frequency-domain transfer matrices for the propeller hub loads identified from a time-domain multibody simulation model of an isolated turboprop propeller and included into a frequency-domain flutter analysis to study the impact of blade elasticity on propeller whirl flutter. Results demonstrate a significantly stabilizing effect of blade elasticity on propeller whirl flutter due to a reduction of the destabilizing pitch-yaw cross-coupling moment. The method demonstrated in this paper is applicable to arbitrary time-domain propeller models and compatible with standard frequency-domain flutter processes, allowing for increased fidelity in the flutter prediction process.
{"title":"Including Blade Elasticity into Frequency-Domain Propeller Whirl Flutter Analysis","authors":"Christopher Koch, Benedikt Koert","doi":"10.2514/1.c037501","DOIUrl":"https://doi.org/10.2514/1.c037501","url":null,"abstract":"Whirl flutter as an aeroelastic instability can be a limiting factor in the design and certification of turboprop aircraft configurations, especially for the engine suspension. Whirl flutter prediction for these configurations is currently done in the frequency domain using rigid propeller aerodynamic derivatives. Blade flexibility is neglected in this process, although it is known to have an impact on whirl flutter predictions. This paper uses frequency-domain transfer matrices for the propeller hub loads identified from a time-domain multibody simulation model of an isolated turboprop propeller and included into a frequency-domain flutter analysis to study the impact of blade elasticity on propeller whirl flutter. Results demonstrate a significantly stabilizing effect of blade elasticity on propeller whirl flutter due to a reduction of the destabilizing pitch-yaw cross-coupling moment. The method demonstrated in this paper is applicable to arbitrary time-domain propeller models and compatible with standard frequency-domain flutter processes, allowing for increased fidelity in the flutter prediction process.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"24 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135883088","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Mikhail Shur, Mikhail Strelets, Andrey Travin, Philippe Spalart
{"title":"Reynolds-Averaged Studies of the Sandia Transonic Bump Validation Challenge, with Loss of Symmetry","authors":"Mikhail Shur, Mikhail Strelets, Andrey Travin, Philippe Spalart","doi":"10.2514/1.c037473","DOIUrl":"https://doi.org/10.2514/1.c037473","url":null,"abstract":"","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"6 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-11","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"136097977","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Stephen A. Rizzi, Stefan J. Letica, D. Douglas Boyd, Leonard V. Lopes
In contrast to most commercial air traffic today, vehicles serving the urban air mobility (UAM) market are anticipated to operate within communities and be close to the public at large. The approved model for assessing environmental impact of air traffic actions in the United States, the Federal Aviation Administration Aviation Environmental Design Tool (AEDT), does not directly support analysis of such operations due to a combined lack of UAM aircraft flight performance model data and aircraft noise data. This paper addresses the latter by offering two prediction-based approaches for generation of noise–power–distance data for use within AEDT. One utilizes the AEDT fixed-wing aircraft modeling approach, and the other utilizes the AEDT rotary-wing aircraft modeling approach.
{"title":"Prediction of Noise-Power-Distance Data for Urban Air Mobility Vehicles","authors":"Stephen A. Rizzi, Stefan J. Letica, D. Douglas Boyd, Leonard V. Lopes","doi":"10.2514/1.c037435","DOIUrl":"https://doi.org/10.2514/1.c037435","url":null,"abstract":"In contrast to most commercial air traffic today, vehicles serving the urban air mobility (UAM) market are anticipated to operate within communities and be close to the public at large. The approved model for assessing environmental impact of air traffic actions in the United States, the Federal Aviation Administration Aviation Environmental Design Tool (AEDT), does not directly support analysis of such operations due to a combined lack of UAM aircraft flight performance model data and aircraft noise data. This paper addresses the latter by offering two prediction-based approaches for generation of noise–power–distance data for use within AEDT. One utilizes the AEDT fixed-wing aircraft modeling approach, and the other utilizes the AEDT rotary-wing aircraft modeling approach.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135350263","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
The Fire Dynamics Simulator (FDS) model was utilized in this study to replicate a full-scale aircraft postcrash experiment conducted within the C-133 test facility by the Federal Aviation Administration. FDS is a computational fire field model that incorporates submodels for soot formation, pyrolysis, and thermal radiation transport. It solves three-dimensional time-dependent Navier–Stokes equations and is grounded in the large-eddy simulation approach and the eddy dissipation concept, serving as turbulence and combustion models. The obtained results, including the heat release rate and temperature, were validated against experimental data and compared with earlier prediction studies employing different turbulence and combustion models. The results from this simulation closely align with the experiment’s findings. The impact of fire-blocking layers and carry-on baggage on interior material was examined. Moreover, two boundary conditions were imposed on the fuselage structure: 1) the adiabatic wall, and 2) heat loss within the wall. Both the fire-blocking layers and the adiabatic boundary condition played a significant role in the flashover occurrence. The large-eddy simulation and eddy dissipation concept approaches have demonstrated a reliable ability to predict flashover and general fire properties to a considerable extent.
{"title":"Numerical Modeling of Aircraft Fire: Postcrash Fire","authors":"Houssam Eddine Nadir Hiber, Hadj Miloua","doi":"10.2514/1.c037397","DOIUrl":"https://doi.org/10.2514/1.c037397","url":null,"abstract":"The Fire Dynamics Simulator (FDS) model was utilized in this study to replicate a full-scale aircraft postcrash experiment conducted within the C-133 test facility by the Federal Aviation Administration. FDS is a computational fire field model that incorporates submodels for soot formation, pyrolysis, and thermal radiation transport. It solves three-dimensional time-dependent Navier–Stokes equations and is grounded in the large-eddy simulation approach and the eddy dissipation concept, serving as turbulence and combustion models. The obtained results, including the heat release rate and temperature, were validated against experimental data and compared with earlier prediction studies employing different turbulence and combustion models. The results from this simulation closely align with the experiment’s findings. The impact of fire-blocking layers and carry-on baggage on interior material was examined. Moreover, two boundary conditions were imposed on the fuselage structure: 1) the adiabatic wall, and 2) heat loss within the wall. Both the fire-blocking layers and the adiabatic boundary condition played a significant role in the flashover occurrence. The large-eddy simulation and eddy dissipation concept approaches have demonstrated a reliable ability to predict flashover and general fire properties to a considerable extent.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"94 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-06","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135350320","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"RegionCategory":"工程技术","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}
Civilian aviation continues to contribute significantly to the total economic and environmental impact of aeronautics. Reduction of the fuel burn and environmental impact of civilian aviation is critical to the overall sustainability of the industry, and it can be accomplished, in part, through the optimization of arrival and approach procedures. This paper proposes the development of a method for measuring the degree of compliance of optimized approach trajectories with air traffic management (ATM) intentions, using an intention compliance level (ICL) indicator. Based on fuzzy logic, this measure reflects the extent to which approach trajectories satisfy the required time-of-arrival constraints. This research demonstrates an approach trajectory strategy that maximizes the ICL, maintains compliance with ATM intent, and achieves efficiency goals inclusive of reduced fuel consumption through selective airspeed changes. Simulations on the Airbus A320 indicate that achieving the optimal trajectory and flight parameters can significantly guide trajectory-based operations to minimize airline economic costs and reduce environmental impact while complying with ATM commands. In this paper we will organize the data as follows. The Introduction will summarize past research as a means of identifying the gaps that this research seeks to bridge and introduce the premise of our findings. Section II proposes the concept of ICL to evaluate the relationship between flight time and the required time of arrival and establishes an en-route descent trajectory model. Section III constructs the optimization strategy based on simulated annealing genetic algorithm (SAGA), evaluates the effectiveness of the algorithm, and verifies the contributions of the ICL in a basic scenario. Section IV analyzes the impacts of various factors on the optimization results in a complex scenario.
{"title":"Research on Fuel-Saving and Environmentally Friendly Approach Trajectory Considering Air Traffic Management Intention","authors":"Yuan Jie, Pei Yang, Ge Yuxue","doi":"10.2514/1.c036593","DOIUrl":"https://doi.org/10.2514/1.c036593","url":null,"abstract":"Civilian aviation continues to contribute significantly to the total economic and environmental impact of aeronautics. Reduction of the fuel burn and environmental impact of civilian aviation is critical to the overall sustainability of the industry, and it can be accomplished, in part, through the optimization of arrival and approach procedures. This paper proposes the development of a method for measuring the degree of compliance of optimized approach trajectories with air traffic management (ATM) intentions, using an intention compliance level (ICL) indicator. Based on fuzzy logic, this measure reflects the extent to which approach trajectories satisfy the required time-of-arrival constraints. This research demonstrates an approach trajectory strategy that maximizes the ICL, maintains compliance with ATM intent, and achieves efficiency goals inclusive of reduced fuel consumption through selective airspeed changes. Simulations on the Airbus A320 indicate that achieving the optimal trajectory and flight parameters can significantly guide trajectory-based operations to minimize airline economic costs and reduce environmental impact while complying with ATM commands. In this paper we will organize the data as follows. The Introduction will summarize past research as a means of identifying the gaps that this research seeks to bridge and introduce the premise of our findings. Section II proposes the concept of ICL to evaluate the relationship between flight time and the required time of arrival and establishes an en-route descent trajectory model. Section III constructs the optimization strategy based on simulated annealing genetic algorithm (SAGA), evaluates the effectiveness of the algorithm, and verifies the contributions of the ICL in a basic scenario. Section IV analyzes the impacts of various factors on the optimization results in a complex scenario.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"50 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-10-04","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135596323","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":3,"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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