Journal of Aircraft最新文献_第10页

Stalls and Splines: Current Trends in Flight Testing and Aerodynamic Model Identification 失速和样条:飞行测试和空气动力学模型识别的当前趋势

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-08-25 DOI: 10.2514/1.c037283

C. de Visser, D. Pool

引用次数: 0

Spin Aerodynamic Modeling for a Fixed-Wing Aircraft Using Flight Data 基于飞行数据的固定翼飞机自旋气动建模

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-08-25 DOI: 10.2514/1.c036835

James L. Gresham, Benjamin M. Simmons, Jeremy W. Hopwood, C. Woolsey

引用次数: 0

Stalls and Splines: Current Trends in Flight Testing and Aerodynamic Model Identification 失速和样条:飞行测试和空气动力学模型识别的当前趋势

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-08-25 DOI: 10.2514/1.c037283@ja.2023.virtual_collection.issue-1

Coen C. de Visser, Daan M. Pool

引用次数: 0

Aeroelastic Analysis of Actuated Adaptive Wingtips Based on Pressure Actuation 基于压力驱动的自适应翼尖气动弹性分析

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-08-25 DOI: 10.2514/1.c037390

P. Meyer, C. Hühne, K. Bramsiepe, W. Krüger

{"title":"Aeroelastic Analysis of Actuated Adaptive Wingtips Based on Pressure Actuation","authors":"P. Meyer, C. Hühne, K. Bramsiepe, W. Krüger","doi":"10.2514/1.c037390","DOIUrl":"https://doi.org/10.2514/1.c037390","url":null,"abstract":"Folding wingtips address the challenges posed by high-aspect-ratio wings, such as airport conformity and increased wing root bending moment. Actuated adaptive wingtips extend the functionalities of folding wingtips by using a stiffness-adaptive aeroelastic hinge that is actively adjustable in flight. The objective of this paper is the aeroelastic analysis of a wing equipped with an adaptive-stiffness hinge. While the structural design of the wingtip actuator based on pressure-actuated cellular structures (PACS) was developed in a previous study, in this study the authors verify the concept of actuated adaptive wingtips through aeroelastic analysis. This study shows that the investigated PACS actuator, structurally designed from glass-fiber-reinforced plastic, is capable of bearing the loads acting on the wingtips of a Cessna Citation X. The adaptive-stiffness hinge, positioned between 86.7 and 91.2% of the semispan, reduces the wing root bending moment by up to 7.8% in a 2.5[Formula: see text] maneuver load case, while keeping the wing straight in cruise. A further increase in load alleviation potential can be achieved in the future by extending the actuator’s operating envelope and thus increasing its load-bearing capacity. The functional verification of the actuated adaptive wingtip concept by means of aeroelastic analysis forms the basis for the manufacturing and testing of a functional prototype.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":" ","pages":""},"PeriodicalIF":2.2,"publicationDate":"2023-08-25","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41655171","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}

引用次数: 0

Summary of the 4th High-Lift Prediction Workshop Hybrid RANS/LES Technology Focus Group 第四届高升力预测研讨会RANS/LES混合技术焦点小组总结

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-08-24 DOI: 10.2514/1.c037329

N. Ashton, P. Batten, A. Cary, K. Holst

{"title":"Summary of the 4th High-Lift Prediction Workshop Hybrid RANS/LES Technology Focus Group","authors":"N. Ashton, P. Batten, A. Cary, K. Holst","doi":"10.2514/1.c037329","DOIUrl":"https://doi.org/10.2514/1.c037329","url":null,"abstract":"This paper summarizes the collective efforts of multiple teams that contributed to the hybrid RANS/LES technical focus group for the 4th AIAA CFD High Lift Prediction Workshop (HLPW-4), which took place on January 7, 2022, in San Diego, California. The overall conclusion is that turbulence-resolving methods such as hybrid RANS/LES (HRLES) do offer improved predictions for these high-lift geometries, with respect to the underlying RANS models, but there are nuances, and some unresolved issues remain that should be the focus of future work. In particular, while HRLES methods appear to show clearly improved predictions at higher angles of attack, there is some tendency for HRLES methods to return slightly worse moment predictions at lower angles of attack, suggesting that prediction of the shallow separation from the flaps might need further research. Computing cost also remains a significant issue, with HRLES methods requiring roughly nine times more high-performance computing central processing unit core hours than steady-state RANS methods, indicating that future algorithmic and computational optimization could be beneficial. Finally, there are strong indications that modeling the wind tunnel has a positive impact on correlation with experimental measurements, suggesting that future work might be better focused on in-tunnel simulations.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":" ","pages":""},"PeriodicalIF":2.2,"publicationDate":"2023-08-24","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"41578256","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}

引用次数: 0

Methodology for Preliminary Flight Control Actuator Design 飞行控制执行器初步设计方法

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-08-24 DOI: 10.2514/1.c036717

R. Stephan, E. Stumpf, Henri Schottmüller, T. Röben, N. Dreyer, T. Immler

引用次数: 0

Antidisturbance Slip Ratio Algorithm of Aircraft Braking System Based on On/Off Valves 基于开关阀的飞机制动系统抗扰滑移率算法

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-08-18 DOI: 10.2514/1.c037438

Renjie Li, Yaoxing Shang, Xiaochao Liu, Shuai Wu, P. Qi

{"title":"Antidisturbance Slip Ratio Algorithm of Aircraft Braking System Based on On/Off Valves","authors":"Renjie Li, Yaoxing Shang, Xiaochao Liu, Shuai Wu, P. Qi","doi":"10.2514/1.c037438","DOIUrl":"https://doi.org/10.2514/1.c037438","url":null,"abstract":"A safe and high-efficiency braking process is the primary consideration for the aircraft braking system. The traditional servo valve is prone to blockage, which can cause serious safety accidents. Based on the analysis of the operation principle of the braking system, a safer aircraft braking system based on an on/off valve is proposed, which uses a normally open valve as the downstream valve. The braking system based on on/off valves has problems such as fluctuating pressure, harsh working conditions, and strong nonlinearity of the system. An algorithm with a strong antidisturbance ability and high braking efficiency is proposed to solve the above three problems. The algorithm typically consists of two main components: outer and inner loops. The outer loop uses the active disturbance rejection control, and the inner loop adopts the segmented nonlinear predictive pressure regulation algorithm with compensation. The outer loop can compensate for the internal uncertainty and external disturbance of the system. The inner loop can compensate for the flow rate during the closing process of the on/off valve to ensure the pressure regulation effect and the life of the on/off valve. The experimental results show that the proposed algorithm has a strong antidisturbance ability and high regulation precision. The braking distance of the algorithm can be reduced by 5.48–15.15% under three different working conditions, which significantly improves the braking efficiency of the aircraft.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":" ","pages":""},"PeriodicalIF":2.2,"publicationDate":"2023-08-18","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"45825115","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}

引用次数: 0

Experimental Study of an Asymmetric Tandem Wing Configuration for Drone Application 无人机非对称串联机翼结构的实验研究

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-08-02 DOI: 10.2514/1.c037377

L. Traub

引用次数: 0

DPW-7: Steady and Unsteady Computations of the Common Research Model at Different Reynolds Numbers DPW-7：不同雷诺数下常用研究模型的稳态和非稳态计算

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-07-30 DOI: 10.2514/1.c037231

D. Hue, F. Sartor, I. Petropoulos, Camille Fournis

{"title":"DPW-7: Steady and Unsteady Computations of the Common Research Model at Different Reynolds Numbers","authors":"D. Hue, F. Sartor, I. Petropoulos, Camille Fournis","doi":"10.2514/1.c037231","DOIUrl":"https://doi.org/10.2514/1.c037231","url":null,"abstract":"This article presents the numerical computations performed at ONERA for the Seventh AIAA Drag Prediction Workshop. By introducing Reynolds numbers up to 30 million closer to the flight conditions, greater lift levels beyond the design point, and time-accurate simulations, this new session has allowed the previous studies to be extended. The Common Research Model aircraft configuration has been considered in its academic wing-body version and calculated in this work with point-matched structured grids. The ONERA Cassiopee software as well as the elsA solver and the FFDπ far-field drag code have been used. The grid convergence study has shown larger pressure drag variations than what was obtained at the cruise lift coefficient, but increasing the Reynolds number seems to reduce this trend. Then, the angle-of-attack sweep study with the lift, drag, and moment polars has given the opportunity to assess different numerical settings such as the Spalart–Allmaras and [Formula: see text] shear stress transport turbulence models with the quadratic constitutive relation approach (QCR-2000) and to discuss the comparison between computational fluid dynamics results and wind-tunnel data. Concerning the Reynolds number increase, it has appeared that the main part of drag reduction comes from the friction ([Formula: see text]) and viscous pressure drag ([Formula: see text]) components. The prediction of pitching moment increments due to Reynolds number variations still needs to be significantly improved. Finally, for an angle of attack above 4.00 deg, by the use of unsteady Reynolds-averaged Navier–Stokes computations, an unsteady buffet phenomenon has been observed and analyzed.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":" ","pages":""},"PeriodicalIF":2.2,"publicationDate":"2023-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"47049382","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}

引用次数: 0

Estimation of the Fan Rotational Speed Using Flyover Audio Recordings 利用飞越音频记录估算风扇转速

IF 2.2 3区工程技术

Journal of Aircraft Pub Date : 2023-07-30 DOI: 10.2514/1.c037371

Thomas Ramseier, R. Pieren

{"title":"Estimation of the Fan Rotational Speed Using Flyover Audio Recordings","authors":"Thomas Ramseier, R. Pieren","doi":"10.2514/1.c037371","DOIUrl":"https://doi.org/10.2514/1.c037371","url":null,"abstract":"Aircraft noise emissions affect societies around the world by impacting the population’s health and land use planning. This calls for simulation tools able to predict these types of noise emissions with high accuracy. A crucial aircraft parameter to achieve satisfying precision is the rotating frequency of the low-pressure shaft of the turbofan engine, called [Formula: see text]. [Formula: see text] determines the engine’s power use and is here estimated acoustically from ground-based microphones. A new method for dynamic [Formula: see text] estimation is presented, which is more robust as compared to earlier approaches. It makes use of different aircraft sound characteristics and combines two methods. The first method tracks multiple fan tone harmonics over time within a de-Dopplerized sound pressure spectrogram. This frequency-tracking task is solved by dynamic programming to find the global optimum. The second method relates to buzz-saw noise, and is thus applied to departures only. The buzz-saw fundamental frequency is estimated in the cepstral domain. Both submethods are separately validated and assessed with concurrent sound pressure measurements and flight deck recording data of [Formula: see text]. The new robust [Formula: see text] estimation method will be applied in noise measurement campaigns with the goal of improving current aircraft noise emission models.","PeriodicalId":14927,"journal":{"name":"Journal of Aircraft","volume":" ","pages":""},"PeriodicalIF":2.2,"publicationDate":"2023-07-30","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"46213337","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}

引用次数: 0