bluuebunny/crossref_metadata_2025 huggingface dataset:
Unlocking Potential
Authors: Lalar Sachin , Kumar Tajinder , Kumar Rajinder , Kumar Shubham
Published: October 2024

The aim of this chapter is to improve accessibility for students with disabilities by extensively examining the growing role of Artificial Intelligence in altering special education. The chapter begins with a review of the challenges faced by students with disabilities and highlights the critical need for individualized and flexible learning strategies. It then gives the reader an overview of assistive technologies as they are now, emphasizing their inherent drawbacks and laying the groundwork for future research into AI as a powerful tool to solve them. The chapter demonstrates AI-supported techniques and collaborative technologies that promote an inclusive classroom environment via the perspective of inclusive learning environments. The discussion about the application of AI in special education provides useful insights, highlighting the significance of cooperation between educators, technologists.In order to envisage future developments in AI technology and their possible effects on law and policy, the chapter concludes with a look at current patterns and future directions.
The Impact of Personalized Messages and Designs on Consumer Experiences and Marketing Communications in Technology
Authors: Bozkurt Serap , Uğursoy Ahu Samav , Meral Seden Pınar
Published: October 2024

Personalization entails adapting messages, designs, products, or services to individual needs and preferences, a process executed using data such as personal preferences, past behaviors, demographic characteristics, or online activities. This approach aims to enhance brand loyalty, consumer satisfaction, and profitability by providing more engaging experiences. Widely used in fields like e-commerce, digital marketing, media, and entertainment, personalization extensively leverages new technologies. The study, focusing on personalized products and messages tailored to consumer preferences and needs, underscores the critical role of technology in personalization, emphasizing that digital tools like data analytics and artificial intelligence enable better understanding of consumers and facilitate interaction with them. Advanced digital capabilities enable brands to offer unique experiences, thereby increasing loyalty and satisfaction, and improving marketing performance. As the importance of personalization grows, brands are expected to become more innovative.
An Exploration of Machine Learning in Art and Design
Authors: Dursun Rumeysa Zeynep Araçlı , Bakan Uğur
Published: October 2024

The paper delves into the profound impact of Artificial Intelligence (AI) on various creative domains, emphasizing its transformative potential in reshaping human-computer interaction. It explores AI's evolution from traditional programming to Machine Learning (ML), highlighting ML's pivotal role in facilitating tasks traditionally reserved for human intelligence. The text elucidates how ML algorithms, such as Generative Adversarial Networks (GANs) and Neural Style Transfer, have revolutionized artistic creation by enabling computers to generate visually captivating artworks autonomously. Furthermore, it discusses the democratizing effect of AI in art and design, making creative tools and techniques more accessible to individuals from diverse backgrounds. While acknowledging AI's ethical implications and challenges, such as bias and interpretability concerns, the paper advocates for interdisciplinary collaboration to address these issues responsibly.
Adapting HR Practices for a Transhumanist Future
Authors: Yamijala Suryanarayana Murthy Suryanarayana , Chodisetty R. S. Ch. Murthy , Chakravorty Chandresh
Published: October 2024

As transhumanist technologies modify human traits, HRM must adapt to new problems and opportunities. This empirical study examines HR policy-making and transhumanist workplace enhancements. The research uses HR professional surveys and case studies from several industries to highlight the limitations of standard techniques in staffing, deploying, and retaining talent. Research suggests ethical principles, inclusivity, and effects on employee performance, health, and workplace attitudes. Very beneficial from a Human Resources viewpoint to understand how complicated transhumanism concerns may be understood in the future and propose policy solutions for more intelligent decision making..
Wearable Technologies Leading to Employee Performance and Productivity
Authors: Saxena Manisha , Avanesh Neetha Mary , Niranjan L. R. , Mohanty Priyakrushna
Published: October 2024

This work seeks to reach four specific objectives in order to fill the research void on wearable technologies and how they influence employee performance and wellbeing. Firstly, it investigates how wearable technologies impact employee performance by examining their effect on productivity, effectiveness, and overall job success. Secondly, the study explores the impact of wearable technologies on mental health and wellbeing. Furthermore, it aims to evaluate the relationship between mental health and employee productivity, highlighting the clear impact of mental wellness on performance outcomes. Ultimately, the article explores the role of mental health as a mediator in the link between wearable technologies and employee performance. The article offers a detailed analysis of the complex links between wearable technologies, mental health, well-being, and employee performance, contributing to the fields of organizational behavior and human resource management.
Workplace Wearable Technologies and Their Usage in Worker Productivity, Safety, and Health
Authors: Shukla Gargi Pant , Panday Priyanka , Pant Satish Chandra
Published: October 2024

The rise of wearable technologies has infiltrated the workplace, holding the promise to revolutionize worker productivity, safety, and health. This research delves into the various types of wearable devices used in different industries, analyzing their potential to significantly impact these key areas. Smart watches and AR glasses can enhance worker efficiency by providing real-time data access, streamlining workflows, and reducing errors. However, concerns regarding worker privacy, data security, and potential misuse of collected data necessitate careful implementation strategies. The constant monitoring aspect of wearables can also lead to employee discomfort and negatively impact morale. This research aims to balance the undeniable benefits of wearable technologies and their potential drawbacks. By exploring practical applications, ethical considerations, and employee acceptance strategies, it seeks to pave the way for the responsible integration of wearables in the workplace, ultimately optimizing worker productivity, safety, and well-being.
From Data Entry to Data-Driven Decisions
Authors: Pandey Anand , Singh Dharam Pal , Arora Shaina , Batta Kamal
Published: October 2024

Human resources change with AI. Automation, fewer administrative duties, data-driven decision-making, and better applicant and employee experiences occur. AI can speed up hiring with skills analysis and interview scheduling and tailor onboarding with chatbots and role-specific training. AI's capacity to enhance and tailor instruction changes performance management. AI-driven systems that adapt to learners' needs may improve learning. AI chatbots that automate regular tasks and give 24/7 support may improve employee relations by freeing up HR specialists to concentrate on strategy. However, responsibly employing AI to eliminate discrimination, data privacy problems, and employee concerns about change and job displacement is tough. AI will boost HR empathy, judgment, and strategy. Good AI governance and data management are essential. HR departments may increase productivity and efficiency by overcoming AI's challenges. This improves future collaboration.
A Maneuvering Flight Noise Model for Helicopter Mission Planning
Authors:   NASA Langley Research Center, Greenwood Eric ,   Wyle, May Benjamin , Rau Robert , Hobbs Christopher
Published: October 2024

A new model for estimating the noise radiation during maneuvering flight is developed in this paper. The model applies the Quasi-Static Acoustic Mapping (Q-SAM) method to a database of acoustic spheres generated using the Fundamental Rotorcraft Acoustics Modeling from Experiments (FRAME) technique. A method is developed to generate a realistic flight trajectory from a limited set of waypoints and is used to calculate the quasi-static operating condition and corresponding acoustic sphere for the vehicle throughout the maneuver. By using a previously computed database of acoustic spheres, the acoustic impact of proposed helicopter operations can be rapidly predicted for use in mission-planning. The resulting FRAME-QS model is applied to near-horizon noise measurements collected for the Bell 430 helicopter undergoing transient pitch up and roll maneuvers, with good agreement between the measured data and the FRAME-QS model.
Numerical Optimization for Rotor Blade-tip Planform with Low HSI Noise Characteristics in Forward Flight
Authors:   Nanjing University of Aeronautics and Astronautics Nanjing, Zhu Zheng , Zhao QiJun
Published: October 2024

Based on CFD/FW-H_pds methods and hybrid optimization technique, an optimization design procedure for rotor planform with low HSI noise characteristics is established. In this solver, based on the moving-embedded grid methodology, a CFD simulation method for the aerodynamic characteristics of rotor is developed by solving the compressible Reynolds-averaged Navier-Stokes (RANS) equations. Among the optimization process, the high-qualified blade grids are generated by a high-efficient parameterized method. Additionally, the high-speed impulsive (HSI) noise characteristics generated by transonic helicopter rotor are analyzed through a robust prediction method based on FW-H_pds equations (Ffowcs Williams-Hawkings equations with penetrable data surface). Aiming at the minimization of the noise level in forward flight, optimization analyses based on the rotor blade with double-swept and tapered tip have been accomplished with the aerodynamic performance as constraints. The genetic algorithm and surrogated model based on Latin Hypercube Sampling (LHS) design and Radial Basis Function (RBF) are combined as a hybrid optimization technique. Compared with rectangular blades, it shows that the noise level of rotor with optimized blade-tip shape can be decreased obviously at the present calculating condition. For the rotor with optimized blade-tip, the HSI noise level can be reduced effectively due to its weaker transonic "delocalization" phenomenon in the region of blade-tip.
Efficient Three-Dimensional Solution for Unstructured Grids Using Hamiltonian Paths and Strand Grids
Authors:   University of Maryland, Govindarajan Bharath ,   University of Wyoming, Sitaraman Jay , Jung Yong , Baeder James
Published: October 2024

An approach for achieving line-structures in purely unstructured grids is presented in two-dimensions and three-dimensions. The method entails the identification of Hamiltonian paths created by quadrilateral subdivision of unstructured meshes to represent two distinct surface coordinate directions, and strand grids to represent the wall normal direction. High-order stencil-based discretization and approximate factorization methods are used to construct line-implicit inversion operators along the loops and strands. Efficient solvers are then formulated that exploit these structures to the predict aerodynamic flow over bodies. Steady subsonic and transonic flow over an airfoil, wing, sphere and the Robin helicopter fuselage are predicted using the developed solver and compared against known results to validate the proposed methodology. Various mesh smoothing techniques and their effects on the solution convergence histories using multiple reconstruction schemes are explored. Domain decomposition techniques using message passing interface are developed to allow for the execution of the mesh generator and solver on parallel systems to contain the computational cost. Efficiency comparisons of the Hamiltonian solver against establish structured solvers are performed for representative cases and it is shown that the developed methodology achieves the convergence and accuracy of structured solvers.
A Variational Approach to Multipoint Aerodynamic Optimization of Conventional and Coaxial Helicopter Rotors
Authors:   Duke University, Giovanetti Eli , Hall Kenneth
Published: October 2024

We present a variational approach to the multipoint aerodynamic design optimization of conventional and coaxial helicopter rotors. The optimal design problem is cast as a variational statement that minimizes the weighted sum of induced and viscous power losses between two flight conditions for prescribed vehicle trim constraints at each flight condition. The resulting nonlinear constrained optimization problem is solved via Newton iteration and may be used to map the Pareto frontier, i.e., the set of rotor designs (radial twist and chord distributions and harmonic blade pitch inputs) for which it is not possible to improve upon the performance in one flight conditions without degrading performance in the other. The two flight conditions can represent different advance ratios (including hover), disk loadings, altitude, or other conditions of interest. For forward flight computations, the rotor control inputs are related to the circulation on the blades (and in the wake) through a lifting-line/vortex-lattice method that accounts for nonlinear sectional lift and drag polars. For hovering flight, the rotor performance is analyzed using Blade Element Momentum Theory. We map the Pareto frontier for both a cruise/cruise and hover/cruise multipoint optimization, and show that significant tradeoffs must be made in designing a rotor to balance performance between two flight conditions, particularly hover and high speed forward flight. We also show that higher harmonic control is capable of reducing rotor power and improving the Pareto frontier, particularly for coaxial rotors. Finally, we present a number of rotor designs that best balance performance between two flight conditions.
Collaborative Investigation of the Aerodynamic Behavior of Airfoils in Reverse Flow
Authors:   Georgia Institute of Technology, Hodara Joachim ,   University of Maryland, Lind Andrew , Smith Marilyn , Jones Anya
Published: October 2024

Two fundamental models of the flow (static and dynamic) over airfoils in the reverse flow region of a helicopter in forward flight are investigated experimentally and computationally at Reynolds numbers of O(10⁵). The first model examines the time-averaged and unsteady flow resulting from a two-dimensional NACA 0012 airfoil held at a static angle of attack. Computational tools successfully predict the presence of three unsteady wake regimes and time-averaged airloads measured experimentally at the University of Maryland (UMD). A second model is investigated by pitching a NACA 0012 airfoil through deep dynamic stall in reverse flow. Both experimental and computational results reveal flow separation at the sharp leading edge for shallow angles of attack, leading to the early formation of a reverse flow dynamic stall vortex. Subsequent flow features in the pitching cycle (trailing edge vortex, secondary dynamic stall vortex) are also captured by the numerical simulation, although the timing and strength of some of these features do not align completely with experiment. This work gives fundamental insight of the aerodynamic behavior of airfoils in reverse flow towards a better understanding of the complex nature of the reverse flow region as well as promising new computational tools to be used in the simulation of this unique flow regime.
Aerodynamics of Micro-Rotors in Confined Environments
Authors:   ISAE Supaero, Jardin Thierry , Prothin Sebastien , Magana Cristian
Published: October 2024

This paper aims at understanding how the aerodynamic performance of a hovering micro-rotor is affected by horizontal and vertical wall proximity. Toward that end, experiments are performed to extract aerodynamic loads and velocity flow fields from strain gauges and high-definition stereoscopic particle image velocimetry measurements respectively. The results show that horizontal wall boundary conditions contribute to enhancing aerodynamic performance while vertical boundary conditions have a negligible impact. Enhancement of aerodynamic performance arises from distinct flow physics that depend on the configuration considered. These results open the path towards the development of micro-air vehicles dedicated to the exploration of highly confined environments.
Fundamental Characterization of Spanwise Loading and Trailed Wake Vortices
Authors:   US Army Aviation Development Directorate - AFDD, Bhagwat Mahendra , Ramasamy Manikandan , Caradonna Francis
Published: October 2024

Rotorcraft flowfields are dominated by the vortices trailing from the blade tips. The formation, evolution and subsequent interaction of these vortices with the following blade(s) is a key to rotor airloads and performance. A fixed-wing wind tunnel test was designed to simulate the aerodynamic environment of a rotor blade tip in hover, using an upstream wing to generate an interacting vortex. Detailed surface pressure and flow field measurements were performed to better understand the relationship between the tip vortex characteristics, such the circulation distribution inside the vortex core, and the loading distribution on the generating wing. The fixed-wing loading distribution differs from a typical loading on a hovering rotor blade in that the maximum bound circulation occurs at the blade root, and not close to the tip; this is similar to a very highly twisted rotor blade, like a tilt-rotor, in hover. The wing-vortex interaction alters the wing loading such that the loading peak moves closer to the tip. The trailed circulation in the wake induced by the vortex interaction may entrain into the interacting vortex. The measurements show that this has a profound impact on the the evolution of both the wing tip vortex and the interacting vortex. These findings can be of significance to engineering models, such as the free vortex wake models typical in rotorcraft comprehensive analyses.
Far-Field Analysis of Hovering Helicopter Rotor
Authors:   ONERA, Pape Arnaud , Verley Simon , Destarac Daniel
Published: October 2024

This paper presents the evaluation of the far-field drag analysis and its application to helicopter rotor in hover. This method widely used for fixed-wing configurations has only recently been extended to rotary wing in S. Verley's PhD thesis. Based on these developments, the far-field torque analysis is applied to a realistic rotor case including the blade root area using three different grid topologies: a coarse monoblock grid, a medium multiblock grid and a fine chimera grid. Near-field predictions are obtained through standard integration while Far-field results are obtained using the proposed present approach. Comparisons of near-field and far-field results are presented and discussed. The far-field breakdown is in particular detailed and it is demonstrated how the far-field analysis can be used to locate rotor torque sources.
Highly-efficient Aerodynamic Design of Rotor with High Performance
Authors:   Nanjing University of Aeronautics and Astronautics, Qi Wu , Qi-jun Zhao , Bo Wang , Zhi-zhao Yin
Published: October 2024

To design helicopter rotor efficiently, an adjoint-based and RBF surrogate model coupled method is applied for aerodynamic design of hovering rotor with high aerodynamic performance in a non-inertial reference frame. The OC-O type body-fitted grids are generated around the rotor blade, and the DDM method and "Inverse map" method are utilized for the rapid identification of hole cells and hole boundary donor cells respectively. Based on the embedded grid system, the RANS equations coupled with S-A turbulence model in rotating frame are used as the governing equations, the upwind scheme of Roe with three-order MUSCL interpolation scheme is adopted for spatial discretisation, the LU-SGS implicit method and OpenMP parallel strategy are employed to accelerate the flowfield calculation. On the basis of the highly-efficient and highly-accurate CFD method, the adjoint-based design method is firstly derived to design the rotor airfoil with superior comprehensive performance according to multi-objective and multi-constrained design characteristics for hovering rotor airfoil. The RBF surrogate mode method is then employed to design the twist distributions and planform of the rotor with the aim of highest Figure of Merit for hovering rotor with optimized airfoil. After validating the accuracy of CFD tools by OA209 rotor airfoil and UH-60A hovering rotor, a baseline rectangular rotor with SC1095 airfoil is selected to comprehensively optimize the airfoil, the twist distribution and the planform of the rotor. Through comprehensive optimization, the aerodynamic characteristics of the final optimized rotor is superior and its highest FM value has nearly 14.7% increase when compared with the baseline rotor, which demonstrates the effectiveness and high-efficiency of the adjoint-based and RBF coupled method for the design of a hovering rotor with high performance.
Innovative Integration Approaches
Authors:   AMRDEC AED, Boyett David ,   Intrepid LLC, York Jason ,   GTRI, Edwards Anthony , Dennis Scott , Carter H.
Published: October 2024

The current avionics integration approach is becoming unaffordable partly due to the schedule and cost associated with integrating an avionics system into each configuration of each platform using its native interface. The United States (U.S.) Army's Aviation and Missile Research, Development, and Engineering Center (AMRDEC) Director for Aviation Development tasked the Modular Integrated Survivability (MIS) team to work with the U.S. Army Aviation Engineering Directorate (AED), the Army's airworthiness authority, to explore innovative integration approaches to streamline the integration process while still satisfying airworthiness certification requirements. AED has been engaged since the inception of the MIS Science and Technology (S&T) program. The MIS team, along with AED, has focused on developing the concept of using capability interfaces to communicate with similar avionics systems. The capability interfaces are built by abstracting the native interfaces allowing for a single integration into the platform for an entire suite of avionics systems. To build upon the capability interface approach, the AMRDEC MIS team has aligned its approach with the Future Airborne Capability Environment (FACE™) Technical Standard to enable portability and reuse of the capability interfaces across platforms. The paper discusses the time and cost challenges of the current avionics integration approach. It explores the MIS integration approach of developing and utilizing capability interfaces to integrate entire avionics system suites. The paper also discusses how incorporating the FACE Reference Architecture into the approach promotes software portability and reuse to reduce integration effort. The paper concludes by discussing the synergy realized by combining the MIS capability interface approach with the software portability enabled by the FACE Technical Standard.
Joint Common Architecture Demonstration Lessons Learned - Honeywell Perspective
Authors:   US Army, Boydston Alex ,   Honeywell Aerospace, Cunningham John , Warpinski Matt
Published: October 2024

Under the US Army's Science and Technology (S&T) Joint Multi Role (JMR) Program, the Joint Common Architecture (JCA) Demonstration (aka, JCA Demo) project was established to exercise the Future Airborne Capability Environment (FACETM) Standard and tools, validate the JCA concept and reduce risk for follow-on efforts. This was achieved by procuring a software component called the Data Correlation and Fusion Manager (DCFM) along with a Reusable Verification Component (RVC) from multiple vendors, built to the same specification and integrated on multiple undisclosed operating environments (OEs) designed to host FACE conformant Units of Portability (UoPs). Interaction between the software developers and the system integrator was tightly controlled to evaluate whether the information provided was sufficient to define a component that is modular, portable, and interchangeable. A representative acquisition approach was used whereby the interface requirements were provided in the form of a data model. This paper will discuss the experience, significant issues, and lessons learned.
Investigation of Rotor Vibratory Loads of a UH-60A Individual Blade Control System
Authors:   US Army Aviation Development Directorate - AFDD, Yeo Hyeonsoo ,   Science and Technology Corp., Jayaraman Buvana , Jain Rohit
Published: October 2024

Wind tunnel measurements of a full-scale UH-60A Black Hawk main rotor with an individual blade control (IBC) system are compared with calculations obtained using a comprehensive rotorcraft analysis RCAS and a coupled CFD/CSD analysis using Helios. The effects of open-loop 3, 4, and 5/rev IBC on vibratory hub loads, rotor performance, and IBC actuator loads (pitch link loads) are investigated at high-speed, moderate-thrust and high-thrust, moderate-speed conditions. RCAS captures maximum vibratory hub load reduction values well for some cases, but phase is generally not well captured at all. The coupled analysis shows reasonably good correlation with the measured vibratory hub load variations with 3/rev IBC actuation at the high-speed condition. However, vibratory hub load correlation gets worse for 4 and 5/rev IBC actuations. IBC actuations also have a significant influence on rotor performance. Measured data show a maximum 2.2% rotor power reduction (3.9% increase in rotor lift to effective-drag ratio) using 3/rev IBC actuation with 0.9° amplitude at μ = 0.35. In general, the coupled analysis shows good correlation with the measured rotor power variations at both high-speed and high-thrust conditions. Half peak-to-peak IBC actuator load variations are well predicted by the coupled analysis only for the 3/rev IBC actuation at high speed. In general, correlation at the high-speed condition is better than for the high-thrust condition.
A Physics-Based Hydraulic Damper Model for Rotor Structural Loads
Authors:   US Army Research Laboratory, Kang Hao ,   Rensselaer Polytechnic Institute, Reddinger Jean-Pual , Floros Matt
Published: October 2024

A physics-based, fully nonlinear hydraulic damper model was developed within the framework of the Rotorcraft Comprehensive Analysis System (RCAS) in order to facilitate integrated damper and rotorcraft analysis and design. The hydraulic damper governing equations of motion were formulated using flow continuity equations for each hydraulic device within the damper. The developed damper model was evaluated for an integrated rotor-damper solution and was verified against test data from the NASA-Army UH-60A Airloads Program. For these evaluations, the accuracy of blade load predictions using the developed damper was compared against conventional linear and nonlinear (table lookup) damper models. From these comparisons, the developed damper model is shown to better capture the isolated damper dynamics. The assessment help address the previously identified issues and uncertainties and identify trends or dependencies.
Aeromechanics for a High Advance Ratio Coaxial Helicopter
Authors:   University of Maryland, Schmaus Joseph , Chopra Inderjit
Published: October 2024

A comprehensive analysis for evaluating performance and vibratory loads of a coaxial helicopter is developed, and some validations are carried out against existing experimental data. The methodology is extended from baseline UMARC to include interactional rotor wake between the coaxial rotors, modeling of relative phase between rotors and trim strategies for a coaxial helicopter. The simulation is used to define a flight envelope for an experimental rotor being developed by the University of Texas at Austin for testing in the Glenn L. Martin Wind Tunnel. Vertical hub loads and total rotor power are observed to decrease with increasing lift offset while blade root bending moments tend to decrease.
ADS-33 Evaluation of the International CH-47 Chinook
Authors:   The Boeing Company, Colosi Christopher ,   Canadian Department of National Defence, Parsons Matthew , Einthoven Pieter , Kocher Erik , Carrothers Bryan
Published: October 2024

The DAFCS (Digital Automatic Flight Control System) equipped CH‐47 Chinook has been successfully deployed for the US Army and numerous international customers. Several of those international customers contracted with Boeing for ADS‐33 evaluations of the handling qualities of the aircraft including both the predicted and assigned (i.e. the Mission Task Elements) handling qualities. This paper covers the tailoring of ADS‐33 for the Chinook helicopter, the conduct of ADS‐33 testing and the results of the ADS‐33 testing. The primary focus of this paper will be centered on the Canadian long‐range CH147F ADS‐33 evaluation, which was a complete evaluation against all sections of ADS‐33 and was flown in 2012 and 2013. Additional lessons from two other standard‐range international customer evaluations, flown in 2013 and 2014 are also included. All of the configurations featured the DAFCS OFP 3.2 control laws, or a derivative thereof, which was originally developed for the US Army long range configuration. The section on the tailoring of ADS‐33 describes the process by which Boeing tailored ADS‐33E‐PRF for the Chinook and includes recommendations for future releases of ADS‐33. The assessment section describes the test techniques used and conduct of the testing, along with a summary of the results from both the predicted and assigned sections of ADS‐33.
Towards Handling Qualities Evaluations of a Personal Aerial Vehicle in Ground-Based and In-Flight Simulation
Authors:   DLR German Aerospace Center, Schuchardt Bianca
Published: October 2024

This paper reports results from a study, conducted in a fixed-base helicopter simulator, to investigate the handling qualities of possible future Personal Aerial Vehicles (PAV) that are supposed to have VTOL capabilities like helicopters. A PAV simula-tion developed in the European project myCopter is used as baseline configuration. In preparation for actual flight tests on DLR's in-flight simulator ACT/FHS an adapted version of the baseline configuration has been integrated into the model-based control environment of the ACT/FHS and evaluated on the ground-based ACT/FHS simulator. The results indicate acceptable to good model following. Finally, a third configuration with a novel steering wheel control concept is evaluated. The steering wheel replaces the conventional center stick. The other control axes are also redefined to resemble a carlike control concept for rotorcraft. The participating pilots gave better usability ratings for the conventional inceptor arrangement. Nevertheless, the detailed pilot ratings show that when the steering wheel is used the overall handling qualities can be im-proved while the subjective workload is reduced.
Achieving Usage Based Maintenance with HUMS Regime Recognition
Authors:   Sikorsky Aircraft Corporation, Beale Raymond ,   Federal Aviation Administration, Swindell Paul , Davis Mark
Published: October 2024

Monitoring of actual aircraft structural usage and loads would enhance rotorcraft safety while enabling reduced operating costs via usage-based maintenance (UBM) credits. While flight regime recognition (RR) algorithms have been demonstrated, they have not been fully validated, and regime-based UBM credits remain elusive due to both technical and certification challenges. This paper describes a viable method, which was developed by Sikorsky Aircraft Corporation under an R&D effort funded by the Federal Aviation Administration Technical Center, for achieving UBM retirement credits for a representative life-limited component based on individual aircraft RR usage statistics calculated from Health and Usage Monitoring System (HUMS) operational fleet data recorded on S-92® rotorcraft. A RR post-processing technique for addressing key technical challenges is described and validation results against flight test data are presented. The RR post-processing method is applied to operational HUMS data resulting in individual aircraft usage statistics across the fleet. Usage statistics are compared to the composite worst case (CWC) usage spectrum by individual tail number to identify the best candidates for UBM life credits. Finally, a UBM component retirement credit is calculated for a specific tail number using reliability factors and validated within a probabilistic framework that assures the goal of six-nines (0.999999) fatigue reliability is maintained.
Gross Weight and Center-of-Gravity Estimation System for the V-22
Authors:   Technical Data Analysis Inc., Thaiss Chris , Caplan Fred
Published: October 2024

An evaluation of a combination Artificial Neural Network and Kalman filter system to estimate gross weight and center of gravity for the V-22 is presented. A sampling of V-22 flight test data is used to develop the estimation models, and typical event-driven recorded flight data is used to test the performance of the estimation method. Estimation results of airplane mode gross weight using the combined methods indicate an improvement over using a neural network method alone. The estimated gross weight is able to follow the recorded data without being subject to large gaps or spikes in the event-driven recorded data, as would be the case using a neural network method alone with this type of data. Results of airplane mode CG, helicopter mode GW, and helicopter mode CG estimation are also presented, but using a neural network only at this time. These estimation results match the recorded data well and will provide a good starting estimation for use in a Kalman filter in future efforts.
Preliminary Assessment of the Effect of Daily Reporting of HUMS Events on Squadron Maintenance and Logistics
Authors:   Naval Surface Warfare Center, Scates Erica ,   Naval Air Systems Command, Molinaro Gino ,   In-Service Support Center, Bullock John , Fuller Brian
Published: October 2024

Department of the Navy engineers created the Condition Based Maintenance (CBM) Action Report (CAR) in response to a recent requirement to supplement the MH-60R/S Integrated Mechanical Diagnostics System (IMDS) ground station with a separate daily reporting application. The goal of the CAR was to alert maintainers to events that require immediate maintenance action, as well as those that may be scheduled within a specified number of flight hours, based on the most up-to-date maintenance documentation and thresholds. The CAR was also intended to reduce maintainer burden by centralizing event reporting and providing actionable guidance related to each event. The purpose of this study was to quantify and assess the initial effect of the CAR on maintenance actions and overall squadron readiness. This effect was evaluated using several metrics, specifically Mission Capable (MC) Rate, Non-Mission Capable due to Maintenance – Unscheduled (NMCMU) Rate, and Unscheduled Maintenance Man-Hours per Flight Hour (UMMF). Baseline values were established using data from the two years prior to the introduction of the CAR (May 2012 through April 2014), while current squadron behavior was quantified using the first six months of data after the introduction of the new reports (June through November 2014). Although the combined results amongst the fleet sample showed increases in MC Rate, NMCMU Rate, and UMMF after the new reports were introduced, the response was not consistent amongst the squadrons. Additionally, individual squadron trends for the three metrics investigated carried over from the two-year baseline to the six-month period under the CAR. Given these findings, it is recommended that this evaluation is continued after the CAR has been in use for a longer period of time.
A Smart Position Sensor for Articulated Rotors
Authors:   Bell Helicopter Textron Inc, Schank Troy , Schulte Kynn
Published: October 2024

Modern articulated rotors utilize an elastomeric bearing on the root of each blade to allow multi-axis articulation through a single component. The bearing forms a spherical joint that makes measuring angular displacements in specific blade axes both coupled and difficult to measure. A smart sensing concept is developed to uncouple and separately measure the blade flapping, feathering, and lead-lag position. The sensor concept projects a magnetic field from the blade root to the rotor hub such that flap, lag and pitch displacements can be derived from a hub mounted pickup array. The device utilizes permanent magnets on the blade root and an array of Anisotropic Magnetoresitive (AMR) sensors on the hub. The sensor array is integrated with other electronic components, including a microprocessor in a printed circuit board, forming a self contained sensing system. The 'smart' sensor is software driven, self checking, and can be networked with other sensors for application flexibility. The sensor accuracy is ensured through a process that develops calibration coefficients that are loaded into system non-volatile memory. The sensor system is designed for initial application on an articulated tail rotor for flight test purposes. Risk reduction testing is conducted in simulated tail rotor environmental conditions including vibration and shock, elevated centrifugal force (CF), temperature extremes and electromagnetic emissions / susceptibility. All development and test results indicate the new sensor technology is valid and ready for use in its initial flight test application.
Rotor Load and Health Monitoring Sensor Technology
Authors:   Sikorsky Aircraft Corporation, Davis Mark ,   LORD Corporation, Smith Matt ,   Hutchinson Aerospace, Sarjeant Roberto ,   KCF Technologies Inc., Loverich Jacob ,   Army Aviation Development Directorate, Bordick Nate , Bouquillon Brian , Allred Charles
Published: October 2024

The Sikorsky Aircraft Corporation and the U.S. Army Aviation Development Directorate - Aviation Applied Technology Directorate jointly sponsored the Capability-Based Operations and Sustainment Technology-Aviation (COST-A) program. The objective of COST-A was to develop and demonstrate an integrated set of high-value diagnostics, prognostics, and system health management technologies for six different rotorcraft systems with a focus on reduced maintenance burden without sacrificing safety. One focus of the COST-A program was the rotor system because of the maintenance associated with life limited, flight critical components that are not directly monitored by existing rotorcraft Health and Usage Monitoring Systems. Operators must rely on numerous inspections to determine condition and ensure airworthiness, resulting in significant maintenance burden, both scheduled and unscheduled. The COST-A program developed and matured a number of prototype rotor sensors and diagnostic algorithms that can measure key global rotor loads, detect and characterize blade impact events, and monitor the health of high-value rotor components. Many of these technologies were developed to include the capability for wireless communication and self-powered operation. This paper focuses on rotor loads and health monitoring technologies and the results from full-scale UH-60 main rotor whirl demonstration tests.
Low-Velocity Impact Monitoring System for a Helicopter Frame by Means of an Artificial Neural Network
Authors:   Politecnico di Milano, Sbarufatti Claudio , Gilioli Andrea , Manes Andrea , Giglio Marco
Published: October 2024

Low-velocity impacts, like those due to stone debris, hailstone and bird strike, are a present issue for helicopter operations. Aim of the paper is to develop a low-velocity impact monitoring system able to provide information regarding the position of a low velocity impact. Impacts have been implemented by means of a dynamometric hammer on sandwich panels representing a helicopter frame. One of the most innovative aspects of the research regards the use of a sensor network composed of strain gauges, which are rarely applied for impact localization purposes. Several experimental impact tests have been carried out and an artificial neural network (ANN) has been trained. The system demonstrates the possibility to apply the sensors on a face of the sandwich panel whilst the impacts take place on the other, still guaranteeing robust impact localization. Furthermore, if proper filtering techniques are applied, the algorithm provides a general response regardless of the material used as the hammer tip.
Data-Informed Structural Diagnostic Framework
Authors:   US Army Research Lab, Haile Mulugeta
Published: October 2024

Crack growth in airframe structures may be considered as a nonlinear dynamic process where the crack size at each time step is predicted by a physical damage model such as the Paris-Erdogan equation and updated by a sequence of noisy sensor measurements. The prediction-update implementation is a two stage recursive process that uses a sequential Monte Carlo sampling to obtain a posterior density of crack size at the desired inspection stage. The goal of this paper is to develop a datainformed diagnostic framework that combines the predictions of a physical damage model and evidence from ultrasonic sensor data to provide accurate estimation of crack-size in rotorcraft structures. The data-informed approach obtains the most probable crack-size (MPCS) at each inspection stage using a sequential Monte Carlo method known as Particle Filters. To validate the approach, two Al7075-T6 nested-angle plates were tested using rotorcraft spectrum loads. Results show that the prediction error of the data-informed method, as measured by root mean square deviation from the true value, is less than half of the error of both the Paris-Erdogan and NASGRO models.
Utilizing Additive Manufacturing / 3-D Printing to Optimize Design and Support Solutions for One-Off Spares and Support Product Requirements
Authors:   Bell Helicopter Textron Inc., Reilly Thomas , Przano Dominic
Published: October 2024

Out-of-production aircraft continue to have demand for spare parts that are designed and fabricated with the tooling, processes and materials that were optimized during the high-rate production periods. Similarly, component repair and overhaul support equipment can require broaching, machining, electrical discharge machining (EDM), grinding and polishing and other techniques necessary to achieve reliable functionality of the system. In both cases the low production volume for these parts requires significant non-recurring set-up, tooling, and quality controls costs that affect the per-unit costs and lead times. The maturing technology of additive manufacturing and 3-D printing is now allowing companies to strategize around "growing parts" from a digital database and bypass the design paradigms and production costs inherited from historical manufacturing limitations. Engineers who understand the design freedom of additive manufacturing could leverage the capability and optimize support equipment functionality even further to increase maintainability and safety of usage. As additive materials continue to develop, more and more low-volume spare parts could be converted from traditional, production-driven designs to parts grown-when-needed.
A Numerical Investigation of Ground Effect on a Coaxial Rotor System
Authors:   AVX Aircraft Company, Dreier Mark , Paredes Ashley
Published: October 2024

This paper presents results of a numerical investigation into ground effect on a coaxial rotor system. The rotor system model comprises two n-bladed simply articulated, blade-element rotors with offset flapping hinges, feathering hinges and full-range angle of attack tabular airfoil data. The vortex ring method models the wake of each rotor in axial flow and an image plane represents the ground. A control law adjusts the cooperative and differential collective settings to drive the torques to equal but opposite magnitude while also achieving a desired thrust. The investigation reports the interactions of several important rotor parameters including disk loading, disk separation, solidity, twist rate and height above ground. When possible, the numerical results are compared to data in the open literature.
Coupled Flight Dynamics and CFD Simulations of the Helicopter / Ship Dynamic Interface
Authors:   The Pennsylvania State University, Oruc Ilker ,   CRAFT Tech, Shipman Jeremy ,   NAVAIR, Polsky Susan , Horn Joseph , Erwin James
Published: October 2024

The objective of this study is the development of a virtual dynamic interface simulation using fully coupled Navier-Stokes CFD with a helicopter flight dynamics model. The results show the initial coupling of the codes and development of baseline cases. The long-term goal is to develop more efficient numeric techniques and integrate the simulation on advanced computing hardware with the objective of achieving real-time computations. The unsteady flow over the generic simple frigate shape (SFS2) was calculated using the CRAFT Tech computational fluid dynamics solver, CRUNCH CFD®. The GENHEL-PSU simulation code was integrated with the flow solution, and simulations were performed with a non-linear dynamic inversion control law to hold hover or follow a prescribed trajectory. An Actuator Disk Model with Gaussian distribution of source terms stacked vertically around the rotor disk is developed and sensitivity studies were performed for cases with the vehicle fuselage dynamics frozen. Free flight simulations were then performed, with full rotorcraft flight dynamics regulated by the NLDI controller and coupled with the CFD flow solutions. The time history results include: the helicopter hovering in an open domain both in and out of ground effect, the helicopter hovering over the SFS2 ship deck, and the helicopter performing an approach to the SFS2 ship deck. Results compare responses with no CFD coupling, using a one-way coupled CFD airwake, and using fully coupled simulations. Fully coupled simulations are shown to be feasible, to exhibit reasonable physical behavior, and to capture expected aerodynamic coupling effects.
Measured and Predicted Response of a Submerged Towed Sonar Array to Maneuvering Input
Authors:   United States Naval Academy, Loomis Jean , Falls Jaye , Mouring Sarah
Published: October 2024

There exists a necessity to increase helicopter pilot's safety during mine countermeasure operations. Models have been developed for scenarios involving a cable that is fully submerged in either air or water, but there has been very little testing when the cable is partially submerged. This change in fluid type along the length of the cable has a significant impact on the stability and drag forces that has not yet been extensively studied. A series of experimental investigations examining speed, acceleration, length of cable and path of motion were paired with predictions from a simulation for the purpose of developing a predictive tool. It was determined that the simulation accurately predicted the depth of the body and its position behind the tow point; however, the simulation did not accurately predict the lateral motion of the body. Additionally, these tests further characterized the stability of the body, indicating that acceleration is a governing factor in the operability of the towed sonar.