Journal of Aircraft最新文献

{"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}

{"title":"Multidisciplinary Design Optimization of Transonic Wings with Boundary-Layer Suction","authors":"Valerio Mosca, Anand Sudhi, Camli Badrya, Ali Elham","doi":"10.2514/1.c037362","DOIUrl":"https://doi.org/10.2514/1.c037362","url":null,"abstract":"A quasi-three-dimensional aerodynamic solver is developed for the aerodynamic analysis of wings in a transonic regime that is able to capture the effect of BLS in hybrid laminar flow control (HLFC) application or transition to turbulent flow for natural laminar flow (NLF). The tool provides accurate results, but without the high computational cost of high-fidelity tools. The solver combines the use of an Euler flow solver characterized by an integral boundary-layer method and linear stability analysis using a [Formula: see text] approximation for transition prediction. In particular, a conical transformation is adopted, including the determination of the shock-wave position. The solver is implemented in a multidisciplinary design optimization (MDO) framework, including wing weight estimation and aircraft performance analysis. The framework consists of different modules: aerodynamics, structure, suction system analysis, and performance evaluation. Using a genetic algorithm and considering HLFC technology, wing MDO has been performed to find the optimum wing planform and airfoil shape. A backward-swept wing (BSW) aircraft, developed inside the Cluster of Excellence–Sustainable and Energy Efficient Aviation ([Formula: see text]A) is studied. Novel technologies such as active flow control, limited maximum load factors due to load alleviation, and novel materials allow a fuel weight reduction of 6%.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"24 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":"135590380","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}

{"title":"Off-Design Performance Analysis of a Parallel Hybrid Electric Regional Turboprop Aircraft","authors":"Dominik Quillet, Vincent Boulanger, David Rancourt","doi":"10.2514/1.c036927","DOIUrl":"https://doi.org/10.2514/1.c036927","url":null,"abstract":"Hybrid electric propulsion is one of the alternative solutions for reducing fuel burn and lower [Formula: see text] emissions while keeping a reasonable battery mass for regional turboprop aircraft operating on short routes. Most studies reporting fuel burn reductions evaluate the aircraft on the design mission, although regional transport aircraft rarely operate under these conditions. Therefore, considering its off-design performance is essential for providing a more complete understanding of aircraft capabilities under various operating conditions. Under these flight conditions, the multi-energy management aspect of hybrid propulsion and the fixed size of the batteries could have a significant impact on the system robustness in off-design operation. In this study, the off-design performance of an existing regional turboprop aircraft retrofitted with a parallel hybrid electric powertrain is assessed. Fuel burn benefits are evaluated on the payload–range diagram for an initial hybrid design and compared to the baseline aircraft. Then, using a novel sizing approach, considering a typical mission operation, this study shows an average improvement of [Formula: see text] percentage point on fuel burn benefits relative to the initial hybrid aircraft, creating a more robust design.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"4 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":"135590388","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}

{"title":"Introduction to the Advances in Aircraft System Identification from Flight Test Data Virtual Collection","authors":"Jared A. Grauer, Eugene A. Morelli","doi":"10.2514/1.c037583@ja.2023.virtual_collection.issue-1","DOIUrl":"https://doi.org/10.2514/1.c037583@ja.2023.virtual_collection.issue-1","url":null,"abstract":"Journal of Aircraft, Volume Virtual Collection, Issue 1, Page 1329-1330, September 2023. <br/>","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"1 1","pages":""},"PeriodicalIF":2.2,"publicationDate":"2023-09-28","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"138515517","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}

{"title":"Wind Tunnel and Grid Resolution Effects in Large-Eddy Simulation of the High-Lift Common Research Model","authors":"Konrad A. Goc, Parviz Moin, Sanjeeb T. Bose, Adam M. Clark","doi":"10.2514/1.c037238","DOIUrl":"https://doi.org/10.2514/1.c037238","url":null,"abstract":"This paper describes the application of a compressible large-eddy simulation (LES) solver to the flow over the High-Lift Common Research Model (CRM-HL) in landing configuration, a complex external aerodynamic flow configuration with deployed slats, flaps, a flow-through nacelle, and the associated brackets/fairings on the high-lift devices. The bulk Mach number is (0.2) and the mean-aerodynamic-chord-based Reynolds number is typical of a wind tunnel experiment ([Formula: see text]). A key development in these simulations relative to previous work is that this work serves to establish robustness of LES methods to Reynolds number and aircraft configuration. Previous studies focused on the Japan Aerospace Exploration Agency Standard Model, which featured a nearly [Formula: see text] lower Reynolds number than the present CRM-HL investigation and less aggressive wing/slat leading-edge curvature than the CRM-HL geometry, which led to lower leading-edge pressure suction peak magnitudes, both of which led to less stringent grid resolution requirements. In these LES simulations, an algebraic equilibrium wall modeling approach is employed along with a dynamic implementation of the Smagorinsky subgrid-scale model. The calculations are carried out in both a free air setting and one that includes the wind tunnel facility at seven angles of attack at five grid resolution levels, ranging from [Formula: see text] million control volumes. In free air, the solutions show decreasing sensitivity to the grid with each successive refinement level and systematically approach the experimental lift coefficient data as the grid is refined, with the 1.5 billion control volume case showing excellent agreement with the corrected experimental data. The simulations in both free air and in the wind tunnel predict a stall mechanism featuring a large inboard juncture stall and a nose-down break in the pitching moment curve, both of which agree with the experimental observations. The accuracy of the simulations is assessed via comparisons of integrated forces/moments, surface pressures, and surface skin friction visualizations. Graphics processing unit (GPU) acceleration of the charLES solver results in tractable turnaround times that make LES a useful tool in the aerospace industry design cycle. Recent GPU acceleration of the flow solver has made LES solutions that are highly accurate in lift/drag/moment for relevant high-lift aircraft flows achievable within about 5 h of wall time on 600 GPU cores.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135815695","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}

{"title":"Aeroelastic Analysis of Highly Flexible Wings with Linearized Frequency-Domain Aerodynamics","authors":"Bret K. Stanford, Kevin E. Jacobson, Pawel Chwalowski","doi":"10.2514/1.c037432","DOIUrl":"https://doi.org/10.2514/1.c037432","url":null,"abstract":"Aeroelastic flutter analysis of configurations with geometric structural nonlinearities typically is done with time-domain analysis. The results from this process are computationally expensive and can yield cumbersome results that may be difficult to manage and interpret. Compared to time-domain methods, frequency-domain flutter analysis can provide additional insight into the characteristics of a flutter instability. By linearizing the aeroelastic problem about the nonlinear equilibrium state, this work applies frequency-domain aeroelastic analysis to the Pazy wing, the subject of the Large Deformation Working Group in the Aeroelastic Prediction Workshop. Generalized aerodynamic forces (GAFs) are computed with both a doublet-lattice method and a computational fluid dynamics solver at a range of reduced frequencies as well as a range of dynamic pressures to account for the dependence of the mode shapes on the nonlinear equilibrium state. These GAFs are used in a [Formula: see text] flutter solver, which is modified to handle the nonlinear dependence of the stiffness matrix and GAFs on the dynamic pressure. The hump mode flutter mechanism predicted by the linear doublet-lattice method is found to underpredict the severity of the instability, relative to the computational fluid dynamics-based tool, though the overall static and dynamic aeroelastic mechanisms predicted by the two fidelities are similar.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"20 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135815832","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}

{"title":"Prediction of the Oswald Efficiency Factor for Cambered and Swept Wings","authors":"Lance W. Traub","doi":"10.2514/1.c037444","DOIUrl":"https://doi.org/10.2514/1.c037444","url":null,"abstract":"","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"66 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135816959","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}

{"title":"Solid-State Electroaerodynamic Aircraft Design Using Signomial Programming","authors":"Arthur Brown, Haofeng Xu, Christopher K. Gilmore, Steven R. H. Barrett","doi":"10.2514/1.c037374","DOIUrl":"https://doi.org/10.2514/1.c037374","url":null,"abstract":"Electroaerodynamics (EAD) is a form of airbreathing electric propulsion that uses high voltages to produce and accelerate ions, generating thrust without any moving parts. This method of solid-state propulsion is nearly silent and produces no direct combustion emissions. This paper describes a program for designing and optimizing fixed-wing solid-state aircraft propelled solely using EAD. Signomial programming (SP), an emerging method of efficient multidisciplinary design optimization, is employed. The program incorporates performance models for state-of-the-art EAD thrusters, and for custom high-voltage power electronics. It can be used to generate vehicle specifications, or to assess the effect of technological improvements on vehicle performance. The program was used to design and build a flight demonstrator aircraft, based on a goal of achieving steady level flight. In 2017–2018, the demonstrator successfully achieved steady level flight, a first for a fixed-wing electric aircraft with solid-state propulsion. The unproven nature of the EAD propulsion system necessitated a design philosophy centered around minimal technical risk, affecting configuration selection and choice of objective function. A similar design philosophy may prove useful for other design projects with unproven propulsion systems. Finally, endurance values greater than 30 min are achievable with recent improvements in EAD thruster and battery technology.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135149735","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}

{"title":"Exploration of the Effects of Rotor Blade Twist on Whirl-Flutter Stability Boundaries","authors":"Vincenzo Muscarello, Giuseppe Quaranta","doi":"10.2514/1.c037479","DOIUrl":"https://doi.org/10.2514/1.c037479","url":null,"abstract":"This paper investigates the influence of tiltrotor blade twist on whirl-flutter stability boundaries. Preliminary evaluations indicate that the whirl-flutter speed can be increased if the blade twist slope is reduced. This positive effect results from the shift in the overall thrust toward the blade tip, increasing the flapwise bending moment at the blade root and the trim coning angle. This, in turn, generates a positive pitch-lag coupling, increasing the whirl-flutter speed. However, the shift of high sectional thrust forces toward the blade tip sections returns a higher induced drag, showing the tendency to increase the power required. The paper shows that, by using blade twist laws based on piecewise linear functions and adding the wing airfoil thickness as a second design parameter, it is possible to identify aircraft configurations that improve the whirl-flutter stability boundaries without penalizing the power required in airplane and helicopter mode flight. This is possible because the blade twist and the wing airfoil thickness have an impact on both power required and whirl-flutter speed, so a simple optimization algorithm can identify good tradeoffs. A detailed tiltrotor model representative of the Bell XV-15 is used to display the effectiveness of the proposed approach. The examples show that increases up to 21% on the whirl-flutter speed are achievable without penalties in the aircraft power required and with the additional benefit of a benign impact on rotor pitch link loads.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135149598","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}

{"title":"Fretting Fatigue of Riveted Lap Joints in Aircraft Fuselage","authors":"Huayang Zhang, Jinxiang Liu, Xin Liu","doi":"10.2514/1.c037475","DOIUrl":"https://doi.org/10.2514/1.c037475","url":null,"abstract":"Failure of riveted lap joints originating from fretting fatigue has been responsible for a number of structural failures of aircraft in midflight. Using a combination of extended finite element method analysis and experimental data, this paper investigates the formation and propagation of cracks initiated by fretting, and how it is influenced by rivet squeeze force and by the applied fatigue stresses. It is found that fretting and plain fatigue crack growth life increase with the increase of rivet squeeze force. However, the rise of applied fatigue stress reduces fretting and plain fatigue crack growth life. Moreover, enhancing rivet squeeze force or applied fatigue stress decreases the ratio of fretting to total fatigue crack growth life.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":"219 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2023-09-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"135149713","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}