Proceedings of the Vertical Flight Society 76th Annual Forum最新文献

{"title":"Future Vertical Lift Digital Backbone, Navigating Technology and Implementation Details","authors":"H. Tiedeman, Branden Sletteland, Max G. Taylor, Collins Aerospace","doi":"10.4050/f-0076-2020-16431","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16431","url":null,"abstract":"\u0000 The current US DoD has recognized that their asymmetric advantage is eroding1. Adversaries have had over 25 years to counter the US playbook and weapon systems (Ref. [1]). The US Army Future Vertical Lift (FVL) programs have identified several key tenets that their airborne weapon systems need to ensure they maintain asymmetric advantage. \u0000(1) New and upgraded mission capabilities of their airborne platforms need to get to the field faster (Ref. [2]). One of the current roadblocks to achieving this is the extensive full-system regression testing that ends up being required when there are mission system changes (Ref. [3]). \u0000(2) More competition is needed to help generate \"quicker, better, faster\" capabilities (Ref. [4]). \"Vendor lock\" inherent in current system designs hinders the speed at which technology advances (Ref. [4, 5]). \u0000(3) Improved portability of mission capability across the FVL and enduring fleet (Ref. [6, 7]). The ability to more easily reuse technology will help maintain advantage by eliminating the time needed to develop platform specific solutions (Ref. [4, 6]). \u0000The request for Modular Open System Architecture (MOSA) solutions has been a practice to try to address the items above (Ref. [8]). Most air vehicle and mission system providers are today providing MOSA solutions but the required benefits have not yet been fully realized. MOSA standards as they exist today do a very good job of identifying electronics hardware and software architectures. However, they fall short on physical aircraft integration and consistency in architecture among aircraft systems. Minimizing aircraft wiring and structural modifications, increasing speed to fielding, and portability among multiple systems types are all part of integrating highly MOSA compliant solutions. \u0000The US Army FVL programs have required a \"digital backbone\" (Ref. [7, 9, 10]) to address these integration issues and ensure that they can maintain asymmetric advantage. Unique requirements affecting the digital backbone include:\u0000- Power and power distribution (Ref. [9]) \u0000- Thermal management (Ref. [9, 11]) \u0000- Packaging and installation (Ref. [9]) \u0000- Air Vehicle data distribution (Ref. [9]) \u0000- Mission System data distribution (Ref. [9]) \u0000- Isolation of air vehicle and mission system (Ref. [9]) \u0000This paper will provide an introduction to the envisioned digital backbone for US Army, Future Vertical Lift aircraft. The paper will also offer discussion of digital backbone impacts on aircraft and avionics size, weight, power and cost, as well as technology considerations to address interoperability, safety, security, qualification, and accommodations for new, as well as, legacy avionics technology. \u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"41 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116615562","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":"Low AOB Component Loads Derivation to Implement MH-60R HUMS","authors":"S. Moon, D. Liebschutz, Navair","doi":"10.4050/f-0076-2020-16349","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16349","url":null,"abstract":"\u0000 Presently the fatigue lives of MH-60R dynamic components and airframe are based on a usage spectrum developed using pilot surveys. In order to better define the usage spectrum and to extend component and airframe fatigue life, the Health & Usage Spectrum (HUMS) System was installed on the U.S. Navy MH- 60R Rotorcraft. So far 207 aircraft are equipped with the HUMS systems and 121,334 flight hours of good data have been recorded. The regime recognition programs recognize 315 maneuvers, but are consolidated to 94 maneuvers of MH-60R usage spectrum, for which the component measured loads are available. To better define usage spectrum in detail and compute realistic component fatigue life, an additional maneuver of low Angle Of Bank (AOB) from 10 to 25 degrees was added, but the measured component loads were not available at this AOB to implement HUMS. Thus, measured flight loads data of level flight and AOB turns at 30, 45, and 60 degrees were utilized to derive component loads at 20 degrees by spline cubic interpolation technique. The cubic interpolation technique was applied to measured minimum, average, and maximum loads of variation at 10, 30, 45, and 60 degrees to interpolate load at 20 degree. This technique was applied to interpolate loads for pitch control rod, swash-plate, drag damper, shaft bending moments, blade cuff stresses, and flap deflections. The spline interpolation loads correlated with measured available loads of pitch control rod and blade stresses. The probabilistic fleet usage spectrum of various severities was developed using the HUMS recorded data of 121, 334 hours from 179 rotorcraft with and without low AOB usage. It is evident that fatigue life with 20 AOB split is significantly higher for all dynamic components. Thus, to implement HUMS successfully, it is necessary to compute loads that are not available in the original component fatigue life calculations. Further prorates of gross weigh (GW), velocity and altitude based on the HUMS fleet usage should be implemented to extend component fatigue lives. \u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"13 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115096622","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":"A Motion Primitive Perspective on Rotorcraft Regime Recognition","authors":"Umberto Saetti, Jonathan D. Rogers","doi":"10.4050/f-0076-2020-16266","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16266","url":null,"abstract":"\u0000 An alternative approach to regime recognition that is based on the notion of motion primitives is developed. The algorithm developed is non-causal and leverages the ideas of maneuvers and trims as defined in a motion primitive context. The algorithm functions in three major steps. Given a state and control input time history obtained from flight data, the first step consists of classifying the state and control time history into trim and maneuver segments. The second step leverages the information in the trim state and control vectors to classify each trim segment into a particular trim condition based on conditional (if-else-if) logic. The third step entails the classification of each maneuver segment (flown between two trim segments) as a particular maneuver condition. Importantly, maneuver classification leverages dynamic time warping in order to compensate for rate and time duration variations. Accuracy of the proposed algorithm is evaluated using SH-60B simulated flight data. Operation of the algorithm is also demonstrated using real-world piloted flight test data from a generic utility helicopter.\u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"333 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"115771151","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":"Pupillometric Workload Measurement in the 360 Degree Integrated Cueing Environment (ICE)","authors":"Amanda M Hayes, Christopher J. Aura, Kathryn A. Feltman","doi":"10.4050/f-0076-2020-16421","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16421","url":null,"abstract":"\u0000 This study is a part of an ongoing series of studies examining cueing modalities to circumvent the in-flight effects of degraded visual environments (DVEs) in a rotary wing aircraft. The suite of cueing modalities investigated include visual cueing symbology, auditory cueing, and tactile cueing. This study compared the use of combinations of these cueing modalities to find which resulted in the best performance and the least amount of workload required of the pilot. This specific paper focuses on the analysis of pupillometric data collected through video-based eye-tracking to measure cognitive workload. Results are discussed. \u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"32 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116547830","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":"Influence of Optical and Gravito-Inertial Cues to Height Perception During Supervisory Control","authors":"Martine Godfroy-Cooper, E. Bachelder, J. Miller, Sjsu, Add, AvMC, Francois Denquin, J. Sarrazin, Icna, Dtis, Onera","doi":"10.4050/f-0076-2020-16417","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16417","url":null,"abstract":"\u0000 Future vertical lift (FVL) missions will be characterized by increased agility, degraded visual environments (DVE) and optionally piloted vehicles (OPVs). Increased agility will induce more frequent variations of linear and angular accelerations, while DVE will reduce the structure and quality of the out-the-window (OTW) scene (i.e. optical flow). As helicopters become faster and more agile, pilots are expected to navigate at low altitudes while traveling at high speeds. In nap of the earth (NOE) flights, the perception of self-position and orientation provided by visual, vestibular, and proprioceptive cues can vary from moment to moment due to visibility conditions and body alignment as a response to gravitoinertial forces and internally/externally induced perturbations. As a result, erroneous perceptions of the self and the environment can arise, leading ultimately to spatial disorientation (SD). In OPV conditions, the use of different autopilot modes implies a modification of pilot role from active pilot to systems supervisor. This shift in paradigm, where pilotage is not the primary task, and where feedback from the controls is no more available, is not without consequences. Of importance is the evidence that space perception and its geometric properties can be strongly modulated by the active or passive nature of the displacement in space. An experiment was conducted using the vertical motion simulator (VMS) at the NASA Ames Research Center that examined the contributions of gravitoinertial cueing and visual cueing in a task where the pilot was not in control of the aircraft but was asked to perform altitude monitoring in a simulated UH-60 Black Hawk helicopter with a simulated autopilot (AP) mode. Within the altitude monitoring task, the global optical density (OD), flow rate and visual level of detail (LOD) were manipulated by the introduction of an 18ft vertical drift, upward or downward that simulates a vertical wind shift. Seven pilots were tested in two visual meteorological conditions, good visual environment (GVE) and degraded visual environment (DVE) and two gravitoinertial conditions, where platform motion was either ON or OFF. The results showed that both the good quality of the visual environment and the presence of gravitoinertial cues improved altitude awareness and reduced detection/ reaction times. The improvement of the tracking performance in the visuo-vestibular setting as compared to a visual only setting when the visual cues were poor indicated some level of multisensory integration. Task-dependent limitations of a popular aeronautics metric called DIMSS-PM (Dynamic Interface Modeling and Simulation System Product Metric) and its sub-components were shown, and recommendations for OPV operations were formulated. \u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"15 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"116474216","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":"Modeling of Proprotor / Wing / Flap Interaction for Advanced Vertical Lift Aircraft","authors":"T. Quackenbush, Christine Solomon, D. Wachspress, Michael K. Yu","doi":"10.4050/f-0076-2020-16484","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16484","url":null,"abstract":"\u0000 Recent advanced vertical lift aircraft under development, including several eVTOL configurations, employ tiltwing or tailsitter designs that feature strong proprotor/wing interaction. The operational and flight control requirements of these aircraft typically require the use of flapped wing surfaces to provide high lift in critical low-speed and transition flight conditions. This paper builds on and extends recent assessments of the capabilities of current-generation 'mid-fidelity' design support tools for addressing the complex interactional aerodynamics of such aircraft. The focus here is on the analysis of multiple-component wings operating in proprotor-induced flows, an important step in enabling sizing and design of lifting surfaces for practical tiltwing aircraft. While motivated in part by recent design efforts, the paper does not concern itself with specific new designs, but rather with assessing the readiness of current tools for supporting analysis of such configurations through validation with relevant public domain data sets, identifying both areas of strong predictive capability and challenges requiring additional development work.\u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"284 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"123242178","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":"Bell 525 Relentless - Using Tail Rotor Torque Measurements for Maintenance Credit","authors":"B. Tucker, Ankit Patel, Drew Waller, Bell","doi":"10.4050/f-0076-2020-16267","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16267","url":null,"abstract":"\u0000 In the course of operation, rotorcraft structural components will encounter loading cycles that are often associated with excursions in the main rotor and tail rotor torque. Rotorcraft designs anticipate these load excursions via a design usage spectrum that factors a certain number of such load conditions per flight hour. In general, the usage spectrum assumes worst-case usage regardless of how the helicopter is actually flown. Thus, maintenance intervals are the same regardless of how the helicopter operator uses the aircraft. If a means exists to detect the actual occurrence of these load cycles (per flight hour) and the measured occurrence is less frequent than the assumption in the design usage spectrum, a usage credit could apply. Such a usage credit would reduce maintenance cost by allowing longer intervals between inspections and longer intervals between replacement lives for certain life-limited components. Such a methodology is being sought for the Bell 525, which has a tachometer-based tail rotor torque measurement system. Main rotor torque is also available and is calculated from known engine torque, tail rotor torque, and losses. The torque measurement system has almost two thousand hours of flight test results that show it to be highly accurate. A methodology to use the tail rotor torque measurement and main rotor torque calculation to safely substantiate future usage credits and achieve reduced maintenance cost is put forward. Finally, an application for this sensor technology to detect drive system faults is introduced.\u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"76 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"125468732","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":"Compound Rotorcraft Yaw Control Fault Detection","authors":"Jeffrey A. Lewis, Venkatakrishnan H. Iyer, Eric N. Johnson","doi":"10.4050/f-0076-2020-16395","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16395","url":null,"abstract":"\u0000 Emerging vertical flight concepts being proffered for solutions to the Future Vertical Lift (FVL) mission set such as compound high speed rotorcraft can be designed with multiple, coupled control effectors thus creating redundant systems in one or two more axes to generate control forces and moments which allow for a range of trim states. In the FVL mission area future rotorcraft will be asked to fly into high threat environments where potential failure modes can be encountered due to enemy fire or mechanical failure causing reduction of the safe flight envelope. Fault detection creates options to increase the survivability of the crew and passengers allowing an emergency flight envelope to be proposed. One of the more serious potential failures due to enemy fire is a loss of yaw control. Faults in yaw control can be detected in a compound rotorcraft with a vectored thrust ducted propeller (VTDP) or similar anti-torque thruster. An online Kalman filter (KF) for a dimensional yaw moment coeff icient model will be used to estimate vehicle yaw coeff icients. Deviation from the nominal coefficients will be monitored based on the KF statistics in the case of both rudder and tail rotor failure at 60, 40, and 20 ft/s in forward flight. Both frozen zero rudder and ganged sector faults as well as failed tail rotor faults were successfully detected at all airspeeds except the failed tail rotor at 60 ft/s. For the yaw control faults considered, post fault excitation appears airspeed dependent. An online KF estimator for yaw control fault detection could successfully be integrated into the design of a compound rotorcraft with VTDP thereby increasing system safety.\u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"98 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"121304805","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":"Methodology Correlation for Coaxial Rotor and Blade Load Prediction","authors":"Jing-gen Zhao, Mikel Brigley, R. Modarres, H. Xin, Sikorsky","doi":"10.4050/f-0076-2020-16285","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16285","url":null,"abstract":"\u0000 This paper focuses on rotor blade loads analysis and correlation for coaxial rotor applications. Predicted rotor blade loads from two methodologies used in-house at Sikorsky Aircraft were compared with flight test data from a coaxial rotorcraft. The flight conditions for the correlation range from low speed transition flight to high speed cruise flight and a pull-up maneuver. The methodologies being correlated include both a high-fidelity CFD/CSD (Computational Fluid Dynamics coupled with Computational Structural Dynamics) methodology and the Sikorsky-proprietary flight dynamics simulation tool, GENHEL. Detailed blade load correlations were presented at multiple representative flight conditions. In addition, a survey of the prediction accuracies from these tools were carried out to quantify the overall prediction accuracy using critical metrics for both blade structure load sizing and rotor vibrations to support practical design application.\u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"34 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"124561146","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":"Practical Solutions for Embedding Fiber Optic Strain Sensors in Composites","authors":"N. Dew, Sikorsky, Daniel V. Camp, Mark E Robeson","doi":"10.4050/f-0076-2020-16282","DOIUrl":"https://doi.org/10.4050/f-0076-2020-16282","url":null,"abstract":"\u0000 A multidisciplinary team performing under the Aircraft and Aircrew Protection (A&AP) project between Sikorsky and the US Army Combat Capabilities Development Command Aviation & Missile Center (CCDC AvMC) successfully demonstrated the assembly of a full-scale fiber-optic-instrumented composite aircraft structure assembly. Through a building-block progression from test coupons to sub-scale to full-scale assemblies, the team developed practical strategies to maximize fiber optic survival rate and utility. Ultimately, the team defined and implemented five key elements to enable successful fiber optic strain sensor embedment in structural composites: thoughtful arrangement of the fiber optic network, controlled placement of strain sensors and excess fiber in the laminate, accommodation of minimum fiber optic bend radii, encapsulation of the fiber at the egress point from the composite laminate, and protection of the connector termination. These elements allow for a robust strain-sensing network that can be utilized for damage detection and advanced structural health monitoring.\u0000","PeriodicalId":293921,"journal":{"name":"Proceedings of the Vertical Flight Society 76th Annual Forum","volume":"26 1","pages":"0"},"PeriodicalIF":0.0,"publicationDate":"2020-10-05","publicationTypes":"Journal Article","fieldsOfStudy":null,"isOpenAccess":false,"openAccessPdf":"","citationCount":null,"resultStr":null,"platform":"Semanticscholar","paperid":"114619615","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}