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

Acoustic Predictions for the Side-by-Side Air Taxi Rotor in Hover 悬停时并列空中滑行旋翼的声学预测

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16695

J. Sagaga, Seongkyu Lee

{"title":"Acoustic Predictions for the Side-by-Side Air Taxi Rotor in Hover","authors":"J. Sagaga, Seongkyu Lee","doi":"10.4050/f-0077-2021-16695","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16695","url":null,"abstract":"\u0000 In this paper, acoustic predictions are performed for the rotors of NASA’s side-by-side Urban Air Mobility (UAM) aircraft in hover. Investigations of the acoustics are performed on four overlap configurations, 0%, 5%, 15%, and 25%, in hover via high-fidelity Computational Fluid Dynamics (CFD) simulations. CFD simulations are carried out using the HPCMP CREATETM-AV Helios and acoustics calculations are conducted using PSUWOPWOP. Blade airloads and performance of the rotors are computed for this study. Predictions on the rotor airloads and wake geometry are compared for all overlap configurations at a collective pitch angle of 8°. It is shown that the 25% overlap configuration yields a higher overall sound pressure level (OASPL) than for the other overlap configurations, mainly due to stronger blade-vortex-interactions at the entrance and exit locations of the overlap region. It is found that the OASPL difference in hover is above 62 dB at an altitude of 500 ft (152.4 m), which is the UAM aircraft noise guideline suggested by Uber. Additionally, noise for all overlap cases are compared against various background noise levels. Results show that noise from the side-by-side rotor could not be fully concealed by the various background noise at an altitude of 500 ft (152.4 m).\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"109 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":"132201251","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

Model Predictive Approach for Short-Term Collision Avoidance 短期避碰的模型预测方法

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16906

Alexej Dikarew

{"title":"Model Predictive Approach for Short-Term Collision Avoidance","authors":"Alexej Dikarew","doi":"10.4050/f-0077-2021-16906","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16906","url":null,"abstract":"\u0000 Automatic helicopter flight in uncertain surroundings remains a challenging task due to sudden changes in environment, requiring fast response to guarantee safe and collision-free guidance. Increasing numbers of small unmanned aerial vehicles, which are not covered by air traffic control, pose a potential threat to rotorcraft operating in lower airspace. In order to provide collision avoidance in this scenario, the capability of reacting immediately to appearing obstacles and guiding the rotorcraft along feasible evasive trajectories is required. This paper presents an approach to short-term collision avoidance based on model predictive techniques. The proposed method, originally developed for automotive applications, finds optimal control inputs by predicting a set of trajectories utilizing a model resembling the helicopter dynamics. Compared to model predictive control no iterative optimization is adopted, resulting in deterministic execution time. The proposed method is evaluated by closed-loop simulations with a non-linear helicopter model. Additional hardware-in-the-loop simulations are conducted to examine the real-time capability of the approach.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"19 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":"132208621","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: 1

Predicting a Maximum Stress using Machine Learning and Parametric Flight Data 使用机器学习和参数化飞行数据预测最大应力

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16805

Mike G. Sweet, Samuel Forgerson, Chad deMontfort

{"title":"Predicting a Maximum Stress using Machine Learning and Parametric Flight Data","authors":"Mike G. Sweet, Samuel Forgerson, Chad deMontfort","doi":"10.4050/f-0077-2021-16805","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16805","url":null,"abstract":"\u0000 Mercer Engineering Research Center (MERC) developed a neural network-based regression method for predicting maximum stress per flight values at four structural tracking locations on the United States Air Force HH-60G helicopter airframe using Individual Vehicle Health and Usage Monitoring (IVHMS) data. Maximum stress per flight is utilized when evaluating a failure criterion within the HH-60G service life analysis, so an accurate, fleet-wide estimation of maximum stress magnitude and likelihood is critical for accurate service life determinations. The model was trained using parametric flight data time histories (from IVHMS) and stress time histories from a strain survey aircraft. The stress time histories were developed from the strain signals using two different methods depending on the location of strain gauges in the vicinity of the tracking locations. For two of the tracking locations, they were derived from a global finite element model using a collection of strain gauge signals throughout the strain survey aircraft. At the other two tracking locations, the strain time histories were derived from single strain gauges installed in close proximity to the tracking locations. Multiple regression methods and input data configurations were evaluated in order to identify an appropriate regression method that predicts a maximum stress per flight accurately without over-fitting the training data. MERC identified that the relationship between parametric flight data and aircraft component strain can be exploited to a high level of accuracy using machine learning regression tools. Achieving a high level of accuracy required an extensive review of independent and dependent variable data quality and thoughtful consideration of model inputs.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"26 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":"133969543","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: 1

Impact of Handling Qualities on Motor Sizing for Multirotor Aircraft with Urban Air Mobility Missions 具有城市空中机动任务的多旋翼飞机操纵质量对电机尺寸的影响

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16791

S. Withrow-Maser, Carlos A. Malpica, K. Nagami

{"title":"Impact of Handling Qualities on Motor Sizing for Multirotor Aircraft with Urban Air Mobility Missions","authors":"S. Withrow-Maser, Carlos A. Malpica, K. Nagami","doi":"10.4050/f-0077-2021-16791","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16791","url":null,"abstract":"\u0000 Control models of three NASA Urban Air Mobility (UAM) reference vehicles (the quadrotor, octocopter, and Lift+Cruise (LPC)) were created and compared to determine the effect of rotor number and disk loading on control margin and design. The heave and yaw axes demand more actuator usage than the roll and pitch axes. Between heave and yaw, heave was the more demanding of the two because of the dependence of heave on the engine speed controller (ESC). When the feedback gains for all three vehicles were optimized to Level 1 handling qualities (HQs) specifications using CONDUIT, the ESC for the octocopter was the most stable and had the highest rise time (time for the rotor to respond to an input), while the LPC ESC was the least stable and had the smallest rise time. Rise time corresponds to the time required for rotor response. When actuator usage was translated to current margin, torque margin, and power margin, heave was the most demanding axis, followed by yaw, roll, and then pitch for all three vehicles. The results emphasize the importance of an accurate motor model within the control system architecture.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"45 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":"132742636","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: 5

Integrated Occupant Safety for Urban Air Mobility Applications 城市空中交通应用的综合乘员安全

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16755

G. Olivares, Domenic L. Barsotti, P. Hooijdonk, L. Gomez, Vincent Robinson, Michiel Unger

引用次数: 0

History of the Vertol Aircraft Corporation, 1956 to 1960 Vertol飞机公司的历史，1956年至1960年

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16811

K. Bartie

{"title":"History of the Vertol Aircraft Corporation, 1956 to 1960 ","authors":"K. Bartie","doi":"10.4050/f-0077-2021-16811","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16811","url":null,"abstract":"\u0000 With an overall company lifespan of only four years, Vertol Aircraft Corporation continued the tandem-rotor helicopter legacy of its predecessor, Piasecki Helicopter Corp., as well as research, development and testing of other V/STOL aircraft and technologies while concurrently designing two medium-lift transport helicopters that are still in worldwide use and/or production today. During this short timeframe, the company finalized production and deliveries of the H-21C Shawnee/V-44 for the US Army and international customers. The company designed and flew the world’s first tilt-wing VTOL, the NACA/Army/Navy/Vertol VZ-2A. Application of T53 and T58 turbine powerplants led to twin-turbine engine trials and flight tests with experimental H-21 variants. With Vertol’s in-theater customer support, the French Army and Navy introduced the H-21 into combat in Algeria which included the early use of armed, troop-carrying helicopters. The design, test and successful US and worldwide demonstrations of the privately-funded Vertol 107 led to development and certification of the 107-II airliner version and follow-on military transports as the Boeing H-46 Sea Knight. The contract to design and build the YHC-1B was won by Vertol in 1959 and led to the enduring Boeing H-47 Chinook.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"147 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":"121719678","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

Rust for Safe and Secure Avionics and Mission System Software 安全可靠的航空电子设备和任务系统软件

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16907

Max G. Taylor, Massimiliano Otto, Josh Ehlinger, Jeff Imig

{"title":"Rust for Safe and Secure Avionics and Mission System Software","authors":"Max G. Taylor, Massimiliano Otto, Josh Ehlinger, Jeff Imig","doi":"10.4050/f-0077-2021-16907","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16907","url":null,"abstract":"\u0000 The development lifecycle of software for aircraft systems is dominated by safety and cybersecurity considerations. Software development processes and tools are being continually updated to improve and optimize these critical considerations. While the processes and tools have received continuous updates, changes to the programming languages employed for developing safe and secure software for aircraft systems have evolved at a much slower pace. \u0000\u0000As of 2017, 63% of Department of Defense (DoD) systems were developed with the C/C++ programming languages (Ref. 1). This is representative of the dominant position that software developed with the C/C++ programming language has in existing aircraft avionics and mission systems. The C language has been around since the 1970s and C++ was first introduced in the late 1980s. These languages are very stable and their extensive supporting ecosystems have helped grow and maintain their expansive use in aerospace and many other domains. The longevity of C/C++ has enabled language, usage, process, and tool tailoring so that the software built with C/C++ can be certified for use in both safety-critical and security-critical environments. \u0000\u0000The C/C++ ecosystems are stable and mature but have properties that make writing software embedded in aircraft avionics very challenging. \u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"62 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":"122105857","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

System Identification of a Thrust-vectoring, Coaxial-rotor-based Gun-launched Micro Air Vehicle in Hover 推力矢量同轴旋翼炮射微型飞行器悬停系统辨识

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16706

H. Denton, Hao Kang, Moble Benedict, Grant McCurdy

{"title":"System Identification of a Thrust-vectoring, Coaxial-rotor-based Gun-launched Micro Air Vehicle in Hover","authors":"H. Denton, Hao Kang, Moble Benedict, Grant McCurdy","doi":"10.4050/f-0077-2021-16706","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16706","url":null,"abstract":"\u0000 This paper discusses the flight testing and system identification of a compact, re-configurable, rotary-wing micro air vehicle concept capable of sustained hover and could potentially be launched from a 40mm grenade launcher. By launching these energy-constrained platforms to a target area, the mission range could be significantly improved. The vehicles used in the paper has a mass of 345 grams. The vehicle design features coaxial rotors with foldable blades, and a thrust-vectoring mechanism for pitch and roll control. Yaw control was accomplished with a specialized counterrotating motor system composed of two independently controlled motors. A comprehensive set of flight experiments were performed to excite the longitudinal, lateral, directional, and heave modes of the vehicle. A linearized statespace model was derived from the flight test data. The model showed that lateral and longitudinal dynamic modes were decoupled from each other and from the other modes of the vehicle. Due to the axisymmetric nature the vehicle design, the longitudinal and lateral stability and control coefficients and their eigenvalues were nearly identical. All of the aerodynamic damping terms were negative and stabilizing except for the pitch and roll acceleration modes. These two unstable modes necessitated the need for pitch and roll feedback control. The final flight dynamics model was compared against flight test data for each state, and the model shown good agreement with the experimental data.\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":"125862220","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

Feature-Driven Specification of VTOL Air-Taxis with the Use of the Model-Based System Engineering (MBSE) Methodology CUBE 基于模型系统工程(MBSE)方法论CUBE的垂直起降空中出租车特征驱动规范

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16881

Nicolas Jäckel, J. Andert, Abdulsamed Karaduman, C. Granrath, Bernhard Rumpe, L. Wachtmeister

{"title":"Feature-Driven Specification of VTOL Air-Taxis with the Use of the Model-Based System Engineering (MBSE) Methodology CUBE","authors":"Nicolas Jäckel, J. Andert, Abdulsamed Karaduman, C. Granrath, Bernhard Rumpe, L. Wachtmeister","doi":"10.4050/f-0077-2021-16881","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16881","url":null,"abstract":"\u0000 Ground-bound transport systems in major cities are increasingly encountering their limits. Vertical Take-Off and Landing systems, in short VTOL systems, possibly autonomous and electrified, are a promising way to utilize urban space for public transportation. In this context, the application of the Compositional Unified system-Based Engineering (CUBE) methodology, enables the use of Model-Based Systems Engineering (MBSE) to develop suitable VTOLs. This methodology can be used to move from abstract artifacts to concrete architecture and from system to subsystem development. In this paper, the CUBE methodology is presented using a feature-driven specification to demonstrate its general applicability. The model-based description of the System of Interest (SoI, i.e., the VTOL system) from an abstract use case to a technical architecture is exemplified using three features. This methodology approaches the creation of system- and feature-based models with a tailored level of abstraction to better manage complexity.\u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"46 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":"121717517","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: 2

Practical Conceptual Design of Quieter Urban VTOL Aircraft 城市更安静垂直起降飞机的实用概念设计

Proceedings of the Vertical Flight Society 77th Annual Forum Pub Date : 2021-05-10 DOI: 10.4050/f-0077-2021-16739

Christopher J. Silva, W. Johnson

{"title":"Practical Conceptual Design of Quieter Urban VTOL Aircraft","authors":"Christopher J. Silva, W. Johnson","doi":"10.4050/f-0077-2021-16739","DOIUrl":"https://doi.org/10.4050/f-0077-2021-16739","url":null,"abstract":"\u0000 A toolchain and process for conceptual design of VTOL rotorcraft, employing low- and mid-fidelity tools is presented. The approach is capable of providing more quantitatively-credible trades between noise, size, and cost metrics than the methods commonly used for conceptual design. In addition to a general conceptual design tool, the approach employs comprehensive analysis for trim, blade motion, and airloads; these are then used by acoustic analysis software to develop source sound, propagate it, and calculate noise metrics. A key aspect of the approach is flexibility to assess varied aircraft types and different technologies and design features. Vehicles are sized using a representative Urban Air Mobility design mission. Demonstration cases are presented for a single main rotor helicopter, quadrotor, sideby-side helicopter, and lift+cruise aircraft. Noise metrics used for demonstration are the FAA/EASA certification Effective Perceived Noise Levels for takeoff, flyover, and approach. The concept aircraft in this study are shown to achieve reductions in noise relative the initial design points, with changes in mission performance and cost as a consequence. Many of the designs are predicted to be tens of EPNdB quieter in the certification metrics than existing helicopters. \u0000","PeriodicalId":273020,"journal":{"name":"Proceedings of the Vertical Flight Society 77th Annual Forum","volume":"32 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":"124888941","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: 5