Proceedings of the Vertical Flight Society 78th Annual Forum最新文献

{"title":"Impact of Transformative Air Vehicle Operations on Logistic Supply Chains","authors":"K. Stanzione, D. Schrage, Suresh Kannan, Richard Ruff","doi":"10.4050/f-0078-2022-17592","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17592","url":null,"abstract":"\u0000 Global supply chains have reached critical capacity, resulting in escalating prices, long delivery times, and has had a crippling effect on manufacturing, health care, agriculture, and commerce in general. In addition, the cascading effects of the COVID-19 pandemic as well as other intra-supply chain problems have resulted in a 40-year high inflation and degradations in quality of life, employment, GNP, and personal and national security. During the pandemic, shortages in the workforce and all transportation carrier modes forced the acceleration of digitally powered solutions for capacity improvements. At the same time, emerging technologies in autonomy, electrification, fuel cells, and low carbon powerplants are pushing the envelope of OEM development for over-the-road trucks, aircraft, and maritime vessels. These new transportation modes offer clean, low noise, and high safety operations, which promise to move people and goods faster, cleaner, and ultimately more affordably between origin and destination. This paper provides an overview of general logistics issues that can assist VTOL designers and operators in determining critical configuration parameters, location demographics, flight operations, and emerging Aircraft On Ground (AOG) technologies to maximize near-term ROI for transformative VTOL aircraft.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"18 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128712689","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}

{"title":"Preview of an Enterprise Product Architecture (EPA) to Support a Modular Open Systems Approach (MOSA)","authors":"Tom DuBois","doi":"10.4050/f-0078-2022-17624","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17624","url":null,"abstract":"\u0000 The potential for significant MOSA benefits appears unachieved to date. Recently, the requirement to use a MOSA has been made statutory and regulatory (Ref. 1-5). Previous work (Ref. 6) suggested that a customer-controlled component architecture is a necessary activity to achieve MOSA technical and business benefits across multiple programs. This paper extends that premise while previewing the concept of an Enterprise Product Architecture (EPA) for use in an acquisition environment where there is a requirements organization is contractually separated from the development organization. The requirements organization is composed of an enterprise that is responsible for multiple subordinate programs, and each subordinate program is responsible for developing major systems with their suppliers. Industry product line approaches developed the concept of an EPA (Ref. 7). This paper explores how an EPA can be used to set an enterpriselevel MOSA to increase opportunities to achieve expected MOSA benefits in the context of a multi-tiered acquirer with multiple programs using different contracts with different suppliers. This paper is a preview for a more detailed version of this concept planned for a future publication. \u0000\u0000The technical approach previewed in this paper leads to a product line strategy for the enterprise focused on software and data. This paper defines key terms used for the development and application of an Enterprise Product Architecture (EPA). Products to be acquired would be accomplished through the interaction of the subordinate programs and their supplier(s). The development of the EPA begins with the establishment of functional boundaries. Interfaces between functional boundaries will be defined as a result of operational analysis that recognizes how different functional groupings interact to accomplish operational behaviors. Interfaces between functional groupings will be defined at a logical level to enable the incorporation of diverse products to accomplish requirements in the functional grouping. \u0000\u0000This paper previews the use of three independent categories of functional product groupings: Mission, Utility, and Infrastructure. EPA development includes the establishment of functional groupings that enable capabilities to be agnostic of the underlying infrastructure, hence the reason for the separately categorized Infrastructure functional groupings. Utility functional groupings represent a class of applications that provide operational functionality used by more than one Mission functional grouping. The Utility functional groupings facilitate integration and orchestration of Mission functions. Mission functional groupings represent the rest of the non-infrastructure capabilities needed for the programs to accomplish their operations.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"89 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124555474","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}

{"title":"An Investigation of Piloting and Flight Control Strategies on Generic eVTOL Noise","authors":"Bhaskar Mukherjee, K. Brentner, Eric Greenwood, J. Horn, J. Theron","doi":"10.4050/f-0078-2022-17441","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17441","url":null,"abstract":"\u0000 A preliminary investigation of impact of piloting and flight control strategies on maneuver noise is conducted on a generic eVTOL configuration undergoing a 50 knot level-turn maneuver. The piloting strategy involved control of aircraft pitch to change split between rotor lift and wing lift, while the control strategy involved comparing a rotor thrust control with fixed pitch rotors operating with variable rotation rate and a rotor thrust control strategy with variable pitch rotors operating at constant angular velocity. With the rotors operating in the low tip-Mach number f low regime, it was revealed that broadband noise due to airfoil self-noise dominates the noise levels overwhelmingly. The turbulent boundary layer trailing edge noise contributed the most, with blade stall found to result in significant addition to noise levels (nearly 10 dBA). Deterministic noise was found to be sensitive to rotor thrust control strategies, with control biases offering an additional layer of influence over individual rotor tip-Mach number and thrust levels. Individual rotor thrust and trim were found to be important parameters controlling deterministic noise, while combined rotor thrust levels was found to be the important influence over time-averaged broadband noise levels.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"51 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"130106605","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}

{"title":"Computational Analysis of a Quiet Single-Main Rotor Helicopter for Air Taxi Operations","authors":"P. Diaz, D. Perez, Seokkwan Yoon","doi":"10.4050/f-0078-2022-17461","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17461","url":null,"abstract":"\u0000 A computational study has been done on NASA's quiet single-main rotor helicopter concept for urban air mobility using high-fidelity computational fluid dynamics, rotorcraft comprehensive analysis tools, and computational aeroacoustics. High-order accurate schemes, dual-time stepping, and the delayed detached-eddy simulation model have been employed. A loose-coupling approach between the flow solver and the rotorcraft comprehensive code is implemented toinclude vehicle trim and blade motions. Acoustic simulations based on the Ffowcs-Williams and Hawkings equations have been performed to compute the rotor noise. Different blade geometries and tip speeds are analyzed, and performance and acoustics results are compared. The vehicle has been simulated in hover and cruise, with flight conditions representative of an air taxi mission. The quiet single-main rotor helicopter is one of the conceptual designs intended to focus and guide NASA's research activities in support of aircraft development for vertical take-off and landing air taxi operations.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"11 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121672379","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}

{"title":"On the Impact of Flight Control Systems on Kinetosis of Helicopter Passengers","authors":"Süleyman Özkurt, Christian Fischer, H. Bülthoff, W. Fichter","doi":"10.4050/f-0078-2022-17522","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17522","url":null,"abstract":"\u0000 Disorientation, nausea, and vomiting of passengers that result from vehicle vibrations are characterized as kinetosis or motion sickness. It is mainly the low-frequency movements of these vehicles that contribute to the kinetosis of passengers. Frequencies that provoke kinetosis lie within the rigid-body flight characteristics of helicopters, which depend, among other things, on the design parameters of the flight control system. Moreover, the flight control system's reaction to atmospheric turbulence leads to low-frequency vibration that can result in kinetosis of the passengers and decrease the ride comfort of the helicopter. It is necessary to understand which movements of the helicopter cause kinetosis to develop countermeasures. Therefore, an extensive experimental campaign was conducted as part of a national research project. The campaign's results show that kinetosis in helicopters depends on the number of motion degrees of freedom and that the existing assessment method in ISO2631-1 is not able to reflect this correctly. Furthermore, based on the results, it can be assumed that the extent of kinetosis depends on the flight control system since the investigated flight control systems lead to different vibration spectra that expose the passengers. Therefore, consideration of kinetosis and thus ride comfort is recommended for the design procedure of future flight control systems.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"26 4","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114008151","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}

{"title":"Parametric Investigation of Flow over a Rotor-Blown Wing using High-fidelity Simulations","authors":"U. Hebbar, F. Gandhi, O. Sahni","doi":"10.4050/f-0078-2022-17538","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17538","url":null,"abstract":"\u0000 This study models an infinite rotor-wing unit based on the CRC-20 quad-rotor bi-plane at an angle of attack of 8° and rotor modeled using the actuator line method (ALM). Parametric variations to the rotor-wing geometry are considered. These include rotor-wing chordwise separation, rotor-wing vertical offset and rotor-rotor spanwise separation. Large eddy simulation (LES) and delayed detached eddy simulation (DDES) approaches with and without the transition model are used to analyze the baseline configuration. DDES with the transition model is found to compare well with LES and is selected for the parametric study to balance the computational cost. Compared to isolated wing and rotor cases, baseline rotor-wing case shows 5.46% lower power loading, 14.42% higher lift and 4.45% higher L/D ratio. From the parametric study, varying the rotor-wing chordwise spacing did not significantly influence rotor power loading but placing rotor further from the wing improved L/D ratio by 7.64% compared to baseline due to reduction in sectional drag. The rotor-wing vertical offset cases show that placing the rotor below the wing significantly reduces the L/D ratio while placing it above yields similar L/D ratio to baseline but lowers the power loading by 6.69%. Finally, the spanwise rotor-rotor separation cases show that higher separation yields a 5.66% improvement to L/D ratio with no effect on the rotor power loading, again due to reduction in sectional drag.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"2 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"126494118","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}

{"title":"SmartHangars and SAE International Aircraft Charging Standard","authors":"Joshua N. Portlock, R. Watson","doi":"10.4050/f-0078-2022-17591","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17591","url":null,"abstract":"\u0000 Electro.Aero has been supporting the emerging electric aviation industry for nearly a decade, including the development of chargers, electrical management systems, battery management systems and electric propulsion systems to numerous electric aircraft development projects. During that time, it was identified that the industry needed standardization, especially regarding the charging coupler, so the SAE AE-7D committee was founded by Joshua Portlock in 2018 to help standardize electric aircraft charging and energy management. The AS6968 standard for light conductive charging of electric aircraft was the first standard the committee worked on and is now approaching completion through this year. Furthermore, while the charging coupler standard was proving to be of high priority to the industry, there has also been a noticeable trend that typical airport hangars don't have sufficient electrical power to charge the growing power demands of future electric vertical take-off and landing (eVTOL) aircraft. Therefore, SmartHangar technology was developed, whereby the limited grid connectivity is supplemented by solar and stationary battery energy storage systems to help deliver the peak power demands of electric aviation charging, whilst also helping airports and vertiports transition to more self-sufficient sustainable energy. \u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"108 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"128160567","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}

{"title":"Analytical Model Development for Rotors Hovering Above Heaving Surfaces","authors":"J. Milluzzo, J. Tritschler, S. Davids","doi":"10.4050/f-0078-2022-17468","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17468","url":null,"abstract":"\u0000 A potential flow model was developed for rotors hovering in-ground-effect above a heaving surface using a similar methodology to classical, analytical, static ground effect models. Experimental performance measurements for rotors hovering above a surface undergoing single degree-of-freedom heaving motion were used for model validation, and speculative mission trends were generated for a representative naval helicopter. Unlike prior empirical models, the current model was able to capture the effect of rotor hub height, as well as ground motion parameters. A new thrust ratio was proposed that compared the thrust produced in-ground-effect above a heaving surface to that produced above a static surface. Better agreement was found to occur at the higher collective pitch settings and hub heights, with the model predicting the classical thrust ratio within 5% of the measured value for approximately 75% of the test points. The thrust ratio relative to a static surface was found to produce better agreement and approximately 80% of the experimental tests points were predicted within 5% of the measured value.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"77 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131358179","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}

{"title":"The Effect of Lift Position on Helicopter Recovery to a Twin-Island Aircraft Carrier","authors":"N. Watson, R. Lynn, I. Owen, M. White","doi":"10.4050/f-0078-2022-17585","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17585","url":null,"abstract":"\u0000 This paper describes an investigation of the air flow over the flight deck of a twin-island aircraft carrier with the ship's lifts in a raised and lowered position, and the subsequent change in the aerodynamic loads on a helicopter in hover over the deck. The unsteady flow over the flight deck was simulated using Computational Fluid Dynamics for a 40 kt wind from 60◦ off the starboard. The turbulence intensity and velocity flow field produced over the flight deck for each lift configuration was analyzed and compared. An experimental study was conducted in which the mean and unsteady f low over a 1:200 scale model the aircraft carrier submerged in a large recirculating water channel was measured with the lifts in the raised and lowered position. The CFD prediction of the flow over the full-scale aircraft carrier was compared to the experimental velocity data. To analyze the effect of the two airwakes on a helicopter in hover, a technique known as the Virtual AirDyn was used to quantify the unsteady forces and moments acting on the aircraft. Thirty seconds of time-varying velocity data simulated for each lift configuration was integrated with a flight dynamics model of a helicopter representative of a Seahawk SH-60B. The helicopter was fixed in hover positions over the flight deck and subjected to each unsteady airwake. The resultant unsteady aerodynamic loads acting on the aircraft were analyzed to assess the effect of the lift positions on the helicopter in hover. The results show that for the conditions considered, while the lifts' positions do affect the air flow and the aerodynamic loading, there will only be a limited impact on a recovering helicopter.\u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"173 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131521049","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}

{"title":"Advanced Data Analytics for Dynamic Systems Monitoring","authors":"Océane Martin, Ammar Mechouche, E. Mermoz","doi":"10.4050/f-0078-2022-17605","DOIUrl":"https://doi.org/10.4050/f-0078-2022-17605","url":null,"abstract":"\u0000 On the last generation of Airbus Helicopters rotorcrafts such as H175 or H160, dynamic systems data are collected in a systematic manner in order to perform advanced analytics. Main gearbox (MGB) oil temperature and oil pressure are key parameters to assess the overhaul status of the lubrication and cooling systems. This paper describes new ways of monitoring lubrication and cooling systems behavior, taking advantage of big data capabilities and advanced analytics such as machine learning and physical modeling based approaches. \u0000","PeriodicalId":223727,"journal":{"name":"Proceedings of the Vertical Flight Society 78th Annual Forum","volume":"43 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2022-05-10","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"131789209","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}