Proceedings of the Vertical Flight Society 77th Annual Forum最新文献_第7页

A New Approach to Comprehensive Rotorcraft Aeromechanics Simulation 旋翼机综合气动力学仿真新方法

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16838

Johannes Hofmann, M. Mindt, Felix Weiss

引用次数: 0

The Design of Pilot Cueing for the Degraded Visual Environment Mitigation (DVE-M) System for Rotorcraft 旋翼机视觉环境退化缓解(ve - m)系统飞行员提示设计

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16746

Z. Szoboszlay, Martine Godfroy-Cooper, J. Miller

引用次数: 2

Comprehensive Simulation Based Rotorcraft Loads/Fatigue Analysis and Alleviation Method 基于综合仿真的旋翼机载荷/疲劳分析与缓解方法

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16903

Chen He, E. Bae, Tzikang Chen, Dooyong Lee, M. Haile

引用次数: 0

CFD Turbulence Transition Models Validation for Rotors in Unsteady Axial and Forward-flight Conditions using CREATETM-AV Helios 基于CREATETM-AV Helios的非定常轴向和前飞条件下旋翼的CFD湍流过渡模型验证

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16722

R. Jain

{"title":"CFD Turbulence Transition Models Validation for Rotors in Unsteady Axial and Forward-flight Conditions using CREATETM-AV Helios","authors":"R. Jain","doi":"10.4050/f-0077-2021-16722","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16722","url":null,"abstract":"\u0000 Computational Fluid Dynamics (CFD) turbulence transition models are evaluated for rotors in unsteady axial and in forward flight conditions. The study is carried out using CREATETM -AV Helios with NASA codes, Overflow and FUN3D, as the near-body solvers. Three transition models are considered, Amplification Factor Transport (AFT), Langtry-Menter γ-Reθt (LM), and the LM with a crossflow transition model. The LM model is modified to allow for Galilean invariance. The validation study utilizes the data from two recent rotor tests where unsteady transition measurements were obtained on the upper (suction) surface of rotor blades using a novel application of the Differential Infrared Thermography (DIT) technique. The first configuration, the DLR RTG rotor, is a four-blade, 2.13-foot radius rotor in axial flow with pitching blades, operating at Reynolds numbers of 3.2 x 10-5 and 1.7 x 10-5> at three quarter radius, for the two test cases studied. The second configuration, the PSP rotor, is a model-scale, 5.58-foot radius, three-blade rotor in a high-advance-ratio, high-thrust forward flight condition, mounted on a ROBIN-Mod7 fuselage, and operating at a hover Reynolds number of 1.25 x 10-6 at three quarter radius. For this rotor, the validation study also included the DIT measurements on the lower (pressure) surface. Both configurations exhibit large unsteadiness in transition locations. CFD predictions are obtained using consistent grid resolution and numerical settings across the three models and the two rotor configurations. The computed results are analyzed in terms of the rotor transition maps, separation maps, and surface streamlines on the blade upper and lower surfaces. The agreement with the test data is good, in general, including the rapid, unsteady movement of the transition locations.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"132674329","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Wind Tunnel Test of Optimal Rotor Blade Tip for a Winged Compound Helicopter at High Advance Ratio 大推进比复合翼直升机最佳旋翼叶尖风洞试验

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16870

M. Sugiura, Akira Yoshida, Takuya Furumoto, Kuniyuki Takekawa, K. Kimura, N. Kobiki, H. Sugawara, Y. Tanabe, Yoshiki Iwasaki, Takahiro Noda, Y. Shibata, Tomoka Tsujiuchi, Kentaro Ueda, Hidemasa Yasuda

{"title":"Wind Tunnel Test of Optimal Rotor Blade Tip for a Winged Compound Helicopter at High Advance Ratio","authors":"M. Sugiura, Akira Yoshida, Takuya Furumoto, Kuniyuki Takekawa, K. Kimura, N. Kobiki, H. Sugawara, Y. Tanabe, Yoshiki Iwasaki, Takahiro Noda, Y. Shibata, Tomoka Tsujiuchi, Kentaro Ueda, Hidemasa Yasuda","doi":"10.4050/f-0077-2021-16870","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16870","url":null,"abstract":"\u0000 Aerodynamic characteristics of optimized blade tip geometries for flight at high advance ratio are identified by wind tunnel tests conducted in October 2020. Several types of high-speed compound helicopters are in the development process today after the successful technology demonstrations. JAXA has been studying a high-speed compound helicopter for emergency medical service since it is expected to help save lives significantly in Japan. In this study, optimized blade shapes are invented, whose high-speed performance is twice as high as a conventional blade shape while maintaining hovering performance. In this paper, an optimized rotor blade with a swept-back angle is evaluated highest among optimized rotors and UH-60A rotor in the items of hover performance, high-speed performance, reduction effect of rotor drive power, control hydraulic system output reduction effect, and static aerodynamic stability. Thus, it is concluded that an optimized rotor blade with a swept-back angle is the most practical from the viewpoint of the aerodynamic characteristics of the rotor blade tips.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"52 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130411275","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Intelligent Helipad Detection from Satellite Imagery 基于卫星图像的智能直升机停机坪探测

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16856

D. Specht, C. Johnson, N. Bouaynaya, G. Rasool

{"title":"Intelligent Helipad Detection from Satellite Imagery","authors":"D. Specht, C. Johnson, N. Bouaynaya, G. Rasool","doi":"10.4050/f-0077-2021-16856","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16856","url":null,"abstract":"\u0000 Location data about U.S. heliports is often inaccurate or nonexistent in the FAA's databases, which leaves pilots and air ambulance operators with inaccurate information about where to find safe landing zones. In the 2018 FAA Reauthorization Act, Congress required the FAA to collect better information from the helicopter industry under part 157, which covers the construction, alteration, activation and deactivation of airports and heliports. At the same time, there is no requirement to report private helipads to the FAA when constructed or removed, and some public heliports do not have up to date records. This paper proposes an autonomous system that can authenticate the coordinates in the FAA master database, as well as search for helipads in a designated large area. The proposed system is based on a convolutional neural network model that learns optimal helipad features from the data. We used the FAA's 5010 database and others to construct a benchmark database of rotocraft landing sites. The database consists of 9,324 aerial images, containing helipads, helistops, helidecks, and helicopter runways in rural and urban areas, as well as negative examples, such as rooftop buildings and fields. The dataset was then used to train various state-of-the-art convolutional neural network models. The outperforming model, EfficientNet-bθ, achieved nearly 95% accuracy on the validation set.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"16 7 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128190341","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

Dragonfly - Aerodynamics during Transition to Powered Flight 蜻蜓——向动力飞行过渡期间的空气动力学

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16698

Jason K. Cornelius, D. Adams, L. Young, J. Langelaan, T. Opazo, S. Schmitz, Lev Rodovskiy, B. Villac

{"title":"Dragonfly - Aerodynamics during Transition to Powered Flight","authors":"Jason K. Cornelius, D. Adams, L. Young, J. Langelaan, T. Opazo, S. Schmitz, Lev Rodovskiy, B. Villac","doi":"10.4050/f-0077-2021-16698","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16698","url":null,"abstract":"\u0000 The Dragonfly lander will enter the Titan atmosphere following an approximate 7–10-year journey through space inside its aeroshell. After atmospheric entry, deployment of the main parachute, and heatshield release, the lander will begin its transition to powered flight (TPF). TPF is a maneuver sequence used for mid-air deployment of the Dragonfly rotorcraft lander. The sequence starts just after lander release with the rotors lightly loaded and finishes when a steadystate descent condition has been attained. Mid-air deployment of a multicopter unmanned aerial system is a multidisciplinary problem involving controller choice and tuning, trajectory planning and optimization, and computational fluid dynamics analyses. This paper is an introduction to the transition of rotor flow states in TPF from the windmill brake state, through the turbulent wake state and vortex ring state, and the successful emergence into a normal operating state. A particle swarm optimized controller’s nominal trajectory is plotted on a rotor aerodynamics state chart to show the trajectory’s path through the flow states along the TPF maneuver. Results of preliminary CFD simulations show the variance of individual rotor thrust and power in the early stages of TPF followed by a successful stabilization of rotor performance. Interactional aerodynamic studies also characterize the pre-release flowfield around the lander to be benign at the start of the maneuver. Additionally, results for the lander in steady axial descent show a previously observed coaxial rotor shielding phenomenon of the upper rotor from the effects of vortex ring state.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"1 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131919928","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 3

Anthropometric Accommodation and Ergonomics in the MH-60S NextGen Gunners Seat MH-60S下一代炮手座椅的人体测量调节和人体工程学

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16749

Lori Basham, Justin C. Blankenship, Andrew Koch

引用次数: 0

Parameter Sensitivity studies for the Performance of an Electric BiCP-VTOL UAV 电动BiCP-VTOL无人机性能参数灵敏度研究

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16822

S. Esteban, Álvaro Blanco

{"title":"Parameter Sensitivity studies for the Performance of an Electric BiCP-VTOL UAV","authors":"S. Esteban, Álvaro Blanco","doi":"10.4050/f-0077-2021-16822","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16822","url":null,"abstract":"\u0000 The objective of the presented study is to provide tools for the power plant selection that meet the performance requirements of a VTOL prototype. The tool is integrated in a Mission-Oriented Design Calculator MODC that receives information of the VTOL prototype through a General Block Data (GBD), and then process the information using two algorithms that work together to obtain sub-optimal power plant selections. The data fed to the MODC receives the information of the candidate prototype via four smaller structures that provide geometric, weights, aerodynamic, and propulsive properties that are updated during the iteration process using a series of update rules. This information is then fed to two algorithms: Sensitivity Analysis Algorithm (SAA) and the Fixed-MTOW Analysis Algorithm (FMAA) for the selection of sub-optimal configurations. The SAA generates desired target performance levels for varying aircraft speed (V), propellers' diameter (D), number of engines, and scaling factor SF. The sensitivity analysis provides families of plausible solutions of power plant selections (engine, propeller and batteries) that satisfy the performance target requirements for both axial and longitudinal flight, which are denoted Convergence Zones. The FMAA finds the sub-optimal configuration within the Convergence Zones in order to maximize the Range/Endurance of the UAV for all flight regimes, and extends the study for different combinations for payload and battery mass. After each cycle of iteration the MODC updates the VTOL prototype characteristics in the GBD, hence serving as new data to conduct new sensitivity analysis using the SAA and fine tuning of the FMAA. Results are presented for both algorithms, and conclusions are presented indicating interesting trends towards defining sub-optimal power plant combinations.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"101 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124552577","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0

On Leveraging Network-wide Information from Hotspot Sensor Networks using Multi-output Gaussian Process Regression Model 利用多输出高斯过程回归模型从热点传感器网络中获取全网信息

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16807

Ahmad Amer, F. Kopsaftopoulos

{"title":"On Leveraging Network-wide Information from Hotspot Sensor Networks using Multi-output Gaussian Process Regression Model","authors":"Ahmad Amer, F. Kopsaftopoulos","doi":"10.4050/f-0077-2021-16807","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16807","url":null,"abstract":"\u0000 With the needs for full structural state awareness and health monitoring as well as emerging challenges of Urban Air Mobility (UAV) and Future Vertical Lift (FVL), Health and Usage Monitoring systems (HUMS) need to be more accurate, robust and reliable than ever before. In active-sensing guided-wave networks in particular, conventional Damage Index (DI)-based approaches have been the industry standard for decades because of their computational simplicity and ability to do the damage detection and quantification tasks. However, under specific circumstances, like for specific actuator-sensor paths within a network or due to varying operational conditions, DIs can suffer from various drawbacks that make them prone to inaccurate and/or ineffective damage quantification. This study builds on previous work by the authors where DIs were used to train single-output Gaussian Process regression models (SOGPRMs) for robust damage quantification, and the accuracy limit of SOGPRMs was shown to depend on the evolution of the chosen DI formulation with damage size. In this study, multi-output GPRMs (MOGPRMs) are used instead in order to leverage information about damage size from multiple actuator-sensor path DI values. It is shown that the proposed approach can overcome the different shortcomings of DI evolution with damage size in the different path by capturing the correlation between the DI evolution for different paths. The proposed framework is applied for an Al coupon with simulated damage, and the damage size quantification results are compared with those of SOGPRMs. It is shown that the information fusion approach exhibited by MOGPRMs gives more accurate damage size estimations compared to SOGPRMs.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"21 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2021-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116969816","PeriodicalName":null,"FirstCategoryId":null,"ListUrlMain":null,"RegionNum":0,"RegionCategory":"","ArticlePicture":[],"TitleCN":null,"AbstractTextCN":null,"PMCID":"","EPubDate":null,"PubModel":null,"JCR":null,"JCRName":null,"Score":null,"Total":0}

引用次数: 0