Browse Topic: Collaboration and partnering
The vertical flight industry is on its way to a transformative era, with autonomous technologies set to alter aerial vehicle operations. While it seems certain that fully autonomous helicopters will eventually be deployed for a variety of missions, some high-stakes situations—like medical evacuations (MEDEVAC)—will for the foreseeable future demand human participation in the form of Emergency Medical Care-giving Crew. This study describes the testbed built to run and investigate hypothetical future situations in which a helicopter is autonomously piloted while a human medic with no aviation training, subjected to aviation and medical emergencies, manages patient care onboard. A total of 22 participants, with emergency medical technician certification, nursing or a medical board certification, were invited to run and evaluate the use of AI pilot (AP) in different scenarios of medical evacuation under the following emergencies: medical, empty fuel tank, pressure sensor miscalibration, and engine failure. A comprehensive evaluation of both objective and subjective performance metrics revealed that novice medical professionals could effectively execute medical evacuation operations in conjunction with an AI pilot, even during unforeseen circumstances. The analysis of response times unveiled distinct perspectives on how medics perceive and manage various emergency situations when an AP functions as a collaborative and effective team member.
Research into the feasibility of a scaled rim-drive propulsion product to enable ultra-heavy vertical lift (UHVL) is ongoing at the University of South Carolina in partnership with KRyanCreative, LLC, a start-up aerospace small business. The research team is advancing a superconductive design concept for a rotor system that delivers significant performance gains and flight envelope expansion disruptive to the vertical lift transportation sector. The team has conceived a novel electric tip-driven ducted propulsor to guide architectural and engineering investigations that improve hover and acoustic performance over current practice without penalty to weight and cost. This paper summarizes the data and assumptions that emerge from the systems engineering process of requirements decomposition for product realization. Requirements are categorized as to whether they are explicit (programs of record) or implied (comparable business case or as an alternative to a program of record). Risk reduction enroute to technical feasibility is addressed with a methodology that applies predictive analytics aided by artificial intelligence that will accelerate prototype fabrication by 2030 and fast track market incentives for multiple aviation technologies.
Huma, a reconfigurable lift compounded single main rotor (SMR) helicopter, developed by the UMD Graduate Design Team, is capable of exceptional flight time, able to loiter 185-km away from its takeoff point for over 13 hours before needing to return.
ABSTRACT Updates to the military rotorcraft handling qualities specification are currently being considered that address the high-speed flight regime envisioned for the Future Vertical Lift platform of the US Army. A team that features industry and academia have developed and evaluated a set of Mission Task Elements (MTEs) that have been defined to address VTOL high-speed handling qualities. Following the mission-oriented approach upon which ADS-33E-PRF is based, the MTEs were designed to meet different levels of precision and aggressiveness. The attitude capture and hold MTEs that are the subject of this paper were defined to be precision, non-aggressive tasks that build upon fixed wing analogs. The MTE objectives, descriptions, and performance criteria were assessed and refined via several checkout piloted simulation sessions. Formal evaluations were then conducted by Army test pilots at four simulator facilities, each featuring a unique high-speed platform including a generic winged compound helicopter, two tiltrotor configurations, and a compound helicopter with coaxial rotors. To aid in the MTE evaluation process, baseline VTOL configurations were varied to achieve different handling qualities levels. Quantitative measures based on task performance and qualitative measures based on pilot ratings, comments and debrief questionnaires were used to assess MTE effectiveness. The piloted simulation results demonstrated that the attitude capture and hold MTEs provided an effective means to discern precision, non-aggressive handling qualities in high speed flight.
ABSTRACT Updates to the military rotorcraft handling qualities specification are currently being considered that address the high-speed flight regime envisioned for the Future Vertical Lift (FVL) platform of the US Army. The US Army's National Rotorcraft Technology Center (NRTC) project "Rotorcraft Handling Qualities Requirements for Future Configurations and Missions" is a U.S. Government and Industry co-funded three year research project. A Sikorsky-led project team that features industry and academia have developed and evaluated a set of Mission Task Elements (MTEs) that are defined to address rotorcraft high-speed handling qualities. Following the mission-oriented approach upon which ADS-33E-PRF is based, the MTEs were designed to meet different levels of precision and aggressiveness. Break Turn MTE was defined for non precision, aggressive applications in order to provide a suitable coverage of aggressive air combat maneuvers in future ADS-33. The MTE objectives, descriptions, and performance criteria were systemically developed via a series of piloted simulation sessions at each team's simulation facility. Formal evaluations were then conducted by US Army test pilots at four simulator facilities, each featuring a unique high-speed platform including an X2 Technology™ compound helicopter, two tiltrotor configurations, and a generic winged compound helicopter. To enhance the MTE evaluation process, baseline control law (CLAW) configurations were varied to achieve different handling qualities levels. Quantitative measures based on task performance and qualitative measures based on pilot ratings, comments and debrief questionnaires were used to assess MTE effectiveness. The piloted simulation results demonstrated that the Break Turn MTE provided an effective means to discern non-precision, aggressive handling qualities in high speed flight.
ABSTRACT At the end of 2014, the Group for Aeronautical Research and Technology in EURope (GARTEUR) launched an action group (named AG22) in order to address both experimentally and numerically the issue of rotor wake interacting with obstacles. Within this group, several different experiments were set up and the results were provided to all the partners in order to compare and improve their numerical methods aimed at capturing interaction effects. In the present paper, we numerically investigate the experimental database provided by Politecnico di Milano (Polimi). A low fidelity method based on free wake approach and also CFD computations with different level of modeling are compared to experimental data. It shows that free wake approach is perfectly suitable to predict interaction effects on the rotor loads as long as there is no wake re-ingestion by the rotor. In other cases, the use of CFD is mandatory. However, computational cost can greatly be reduced using some approximation (no fuselage, immersed boundary method approach for the building, wall slip boundary condition on the ground) without significant loss in the rotor loads accuracy. Moreover, such approximation still gives acceptable results with regards to the effects of the rotor wake on the building itself and across the flowfield.
ABSTRACT Updates to the military rotorcraft handling qualities specification are currently being considered that address the high-speed flight regime envisioned for the Future Vertical Lift (FVL) platform of the US Army. The US Army's National Rotorcraft Technology Center (NRTC) project "Rotorcraft Handling Qualities Requirements for Future Configurations and Missions" was a U.S. Government and Industry co-funded three-year research project. A project team that features industry and academia have developed and evaluated a set of Mission Task Elements (MTEs) that are defined to address rotorcraft high-speed handling qualities. The High Speed Acceleration/Deceleration MTE was designed to provide suitable coverage in ADS-33 for handling qualities in Low/High Speed Transitional flight regimes (e.g. rotor-borne to wing-borne flight). The MTE objectives, descriptions, and performance criteria were developed via a series of piloted simulation sessions at each of the four teams' simulation facility. Formal evaluations were then conducted by US Army and contractor test pilots at the four simulator facilities, each featuring a unique high-speed platform, including two tiltrotor configurations, an X2 Technology compound helicopter, and a generic winged compound helicopter. To enhance the MTE evaluation process, baseline control law (CLAW) configurations were varied to achieve different handling qualities levels. Quantitative measures based on task performance and qualitative measures based on pilot ratings, comments and debrief questionnaires were used to assess MTE effectiveness. The piloted simulation results demonstrated that the High Speed Acceleration/ Deceleration MTE provided a suitable and effective means to evaluate Transitional handling qualities between low and high speed flight, although some refinements may still be warranted.
As military organizations internationally assess life extension and replacement actions for current legacy helicopter fleets and next generation rotorcraft are under development, novel rotor system technologies are required to fulfill challenging low-speed and high-speed flight envelopes and mission requirements. Proposed by the Department of National Defense (DND) and in collaboration with the National Research Council of Canada (NRC), a TTCP AER CP13A.1 Collaborative Project (CP) has been initiated supporting multi-nation development of numerical methods for optimizing and designing next generation main rotor blades. Four NRC laboratories collaborated to assemble a data set comprising design, performance, aerodynamics, structures, dynamics, and flight sciences elements. Acquired through research and testing, this information provides reference, technical, and engineering knowledge to support aero-structural model definition, model output validation, and the numerical optimization process development.
Safety professionals receive data from internal and external sources, then manually determine whether the issue constitutes a safety hazard. Many reports are received, and each report is reviewed, then investigated further, using a tedious, labor intensive, and possibly error prone process. In the course of reaching a decision, human bias is inevitable - any two humans could reach different conclusions, and the same individual human could draw different conclusions on different days. As technology has advanced, numerous approaches have been pursued, attempting to reduce human bias and improve both efficiency and effectiveness of the process. In recent years, moderate success was achieved, which provided accuracy rates near 85% but continued refinement did not achieve acceptable results. In early 2023, the challenge was given to a new team, and within a few months, state-of-the-art Artificial Intelligence/Machine Learning data analytics techniques were utilized to aid in safety data analysis efforts, which resulted in high accuracy and efficiency, with reduced human bias.
The integration of automation and autonomy into modern aircraft has significant potential to simplify many piloting tasks. On the other hand, poor integration of automation and autonomy systems with the human crew has sometimes led to unintended consequences. With the goal of improving human-machine integration in piloting tasks, Bell Textron has conducted several autonomy demonstrations in both the simulator and aircraft. The team assessed automated terminal operations, enhanced station keeping, and maneuver tactile limit cueing in a flight simulator. Additionally, the V-280 technology demonstrator conducted autonomous flight profiles to explore these systems in an airborne environment. To mature autonomy systems for integration on future platforms, a Bell 429 was converted into the Aircraft Laboratory for Future Autonomy, completing its first flight last year with fly-by-wire controls at the evaluation pilot station. The influence of Bell autonomy demonstrations on the evolution of Optimally Crewed Vehicles is presented. These efforts have evolved the concept of a digital co-pilot capable of assisting the human crew when called upon, while also acting to enhance aircraft safety through warnings and automated control input, when appropriate.
Full vehicle CREATE-AV™ Helios model has been developed for SB>1 Defiant®, a Joint-Multi-Role Technology Demonstrator (JMRTD) designed by the Sikorsky-Boeing team utilizing compound design with coaxial rotor and propulsor. The full vehicle model includes coupling with RCAS for elastic blade deformation as well as full vehicle trim in steady level flight condition. The purpose of current study is to assess performance prediction capability of the developed Helios modeling approach for such a complex non-traditional design by correlating with flight test data. To minimize uncertainty in flight test data reduction, correlations were made with the data that were directly measured or requiring minimal derivation. The Helios model showed generally very good correlation in power, component forces, rotor and propulsor efficiencies for wide range of flight test conditions. The model also showed very good correlation in performance sensitivity to trim state and rotor RPM, which demonstrates the modeling approach can be used to find optimal flight trim condition. Significance of geometric details and its aerodynamic interference such as shaft modeling has been demonstrated. Impact of measurement uncertainty to data correlation was also demonstrated.
ABSTRACT
Under the Rotorcraft Structural Integrity Program (RSIP) Pilot Demonstration effort, the requirements defined in MILSTD-3063 were applied to a Future Vertical Lift (FVL) representative, model performance specification objective aircraft to demonstrate a standardized RSIP process. This paper covers application of the MIL-STD-3063 approach on SB>1 DEFIANTTM airframe structural components and presents the evolution of the resulting RSIP Master Plan. Elements of the resulting Master Plan are discussed in detail. The Master Plan is the basis for collaborative establishment of structural integrity with an efficient and effective airworthiness substantiation footprint. The discussion includes case studies of the application of logic flow to requirements in MIL-STD-3063 for the determination of specific, relevant action items to airframe structural demonstration components. Execution of this pilot effort led to lessons learned and highlighted feedback to inform the ongoing development of the MIL-STD-3063 process, through ongoing collaboration between the SB>1 DEFIANTTM team and the U.S. Army.
Over the last decade or more there has been a concerted push to move from on condition to predictive maintenance to improve rotorcraft availability and cost competitiveness of sustainment (Ref. 1-2). The US Army, along with industry partners, have been working on the development of prognostics for complete rotorcraft coverage. It has been identified that accurately capturing maintenance actions is needed to improve the accuracy of prognostics for better component health state awareness. Further to achieve the Army's vision for Zero Maintenance rotorcraft and meet the Maintenance Free Operating Period (MFOP) (Ref. 3) requirements for the Future Vertical Lift (FVL) program, it's essential to have an automated configuration management system. To help meet these objectives, the Army and Honeywell are working on the Rotorcraft Automated Component Tracking (RACT) Science and Technology (S&T) development program. This paper discusses the research being conducted to enable the Army's RACT concept done by the Honeywell team and the CCDC AvMC. It identifies the current state of RACT technologies and challenges of integrating such technologies into the rotorcraft environment.
Since certifying the Bell 505 in December 2016, customers on six continents have received delivery of 250 of these light, single-engine aircraft. In three years the worldwide fleet logged more than 35,000 flight-hours, a testament to the Bell 505's customer experience - not only with the aircraft, but with delivery and service. In getting to the 250th delivery, the paper discusses the efforts taken to meet market demand, provide custom finishing, offer kit integration, and even take on additional envelope expansion. Numerous configurations and kits were made available a short time after initial certification, allowing Bell 505 customers to take full advantage of the aircraft capability in a timely manner. The challenges of meeting market demand and transitioning from low rate production to full rate production requires a team effort and this paper shows how it was done for the 505.
When properly implemented, Manned-Unmanned Teaming (MUM-T) allows for an optimized blending of high-value, manned airborne vehicles with expendable, relatively inexpensive unmanned resources within a coordinated mission. This enables human operators and crew to focus on the most sensitive and complex mission tasks, while limiting their usage and exposure to dangerous environments. The sensor and communication capabilities of even simple unmanned vehicles can enhance the situational awareness and reach of manned vehicle crews; however, controlling, monitoring, and avoiding collisions with these additional vehicles can also quickly increase crew workload in an already overtaxed environment. This paper discusses the challenges associated with bringing MUM-T operations into the maritime environment and offers suggestions for modifications to the teaming structure, operations, and equipment in this setting. The experimental setup and results from the German Army Aviation's MUM-T program1 are compared to maritime requirements and available assets, based on interviews with professional maritime test pilots and relevant operator publications. Expected roles for UAVs in maritime MUM-T operations would include intelligence-gathering, BLOS target designating, and relaying communications. Results of prior research and testing suggest that maritime crews will see little benefit today from MUM-T operations, given their current capabilities and technologies. More sophisticated displays for manned assets, advanced autonomy and robustness for unmanned assets, modified CONOPS, and improved long-range communication methods would be necessary for proper resource management in maritime missions. In particular, teams should require task-based UAV control, weather-proofed and reliable autonomous vehicles, and TLD datalink systems (such as Link 16).
High fidelity code-to-code comparisons have been made between the University of Glasgow HMB3 code and the HPCMP CREATE™-AV Helios code under The Technical Cooperation Program collaboration project, Next Generation Rotor Blade Design. The comparisons are made for two model-scale rotors - Langley baseline (LBL) rotor and Pressure Sensitive Paint (PSP) rotor. Hover and forward flight performance results are compared against test data. For the LBL rotor, hover performance is in a good agreement between the test data and HMB3 results over a full range of CT. However, the comparison between the HMB3 and Helios results at a CT of 0.0084 shows the difference in Figure of Merit (FM) by approximately 2 counts (2.2-3.2%). In forward flight, the HMB3 and Helios performance results overpredict the test data at the low advance ratios but improve the predictions at the high advance ratios. At an advance ratio of 0.31, the code-to-code comparison indicated that the Helios torque was lower by 2.8-3.1% compared with the HMB3 torque. For the PSP rotor, the FM trend computed using the Helios-OVERFLOW code agrees well with the fully-turbulent test data. The Helios-OVERFLOW result shows that the fuselage interaction effect is favorable for rotor performance. For a code-to-code comparison, the HMB3 FM result shows about 3.0 counts (4.0%) lower than the HeliosOVERFLOW result at a CT/σ of 0.091. In forward flight, the HMB3 rotor result agrees well with the test data whereas the Helios rotor result underpredicts by 2-3 counts in CP/σ (3.5-5.7%) at the high advance ratios although it was significantly improved at the low advance ratio. Overall, the code-to-code comparisons are successfully conducted for both the LBL and PSP rotors.
Functional testing of aircraft systems at final assembly has typically been a manually intensive and time consuming process. With the introduction of sophisticated avionics displays, system checkouts require numerous button presses and significant movement of the technicians in and around the aircraft to verify functionality. To accelerate functional testing, the Bell 505 team set out to eliminate most of the tedious steps by developing an easy to use computer assisted tool called "Octopus". In the process, the 505 final assembly team was able to take a fresh look at manual procedures and harvest the experience of "how things have been done" to create a better way. Working closely with the employees involved in the chain of functional testing steps, the automated process was commissioned. The resulting "Octopus" reflects the knowledge and skills of the engineers responsible for creating the functional test procedure and the technician performing the test. Having placed strong emphasis on getting "every voice heard," the Octopus automatically runs through the procedural steps to verify each function of the aircraft avionics system. As a project, the Octopus was able to remove a bottleneck from final assembly and eliminate 20 labor hours in the process.
As imbedded as it is in technology, the history of flight is also chock full of people stories. The history of the helicopter, one of the most versatile flying machines ever designed, abounds in such stories. This text looks at the development of Intercity Airlines Company's SG Mark VI by a unique team based for a time in Montreal, Quebec. Bernard W. Sznycer and Selma G. Gottlieb conceived one of the most advanced and innovative helicopter of its day. Designed to minimize vibrations and facilitate production, the SG Mark VI first flew in July 1947. Canada's Department of Transport awarded a Certificate of Airworthiness to a second prototype, in April 1951. The SG Mark VI was the first helicopter designed within the British Commonwealth of Nations to be so honored. Sadly, by then, American helicopters all but dominated the civilian and military markets. The SG Mark VI was abandoned during the winter of 1953-54 and both Sznycer and Gottlieb returned to the United States.
The Army's Future Attack Reconnaissance Aircraft (FARA) program is much bigger than the two ambitious high speed helicopters that Bell and Sikorsky will now get more than $1 billion to build. At least five other major moving pieces must come together on time to turn the final aircraft, whoever makes it, into a working weapon: - a new Improved Turbine Engine built by GE; - helicopter-launched mini-drones called Air Launched Effects (ALE); - a new Long-Range Precision Munition (LRPM), with the Israeli Spike-NLOS as the initial version; - an Integrated Missile Launcher (IML) to launch both the missile and the drones; - and the underlying electronic framework of standards and interfaces to plug it all together, the Modular Open Systems Architecture (MOSA). *Recently, FARA has added a 20mm Gatling Gun being developed by The Advanced Rotorcraft Armament and Protection System (ARAPS) program team at the U.S. Army Combat Capabilities Development Center (CCDC) Armaments Center The Army is "not just focused on the air vehicle, but focused on the weapon system," said Brig. Gen. Walter Rugen, Future Vertical Lift director at Army Futures Command, in a call this morning with reporters. [1] While some have questioned the viability of fielding the FARA in ten years, e.g. by 2028, others have offered reasons on why the plan for a next-gen recon aircraft needs to be accelerated. Who knows how much money will be available to the Army for sustaining its aviation fleet as budget walls close in over the next several years? Trilliondollar deficits have a way of impinging on defense budgets. What is proposed, though, is that the Army compress its development schedule for a new armed recon rotorcraft so that our soldiers begin to be better equipped against the likes of Russia and China somewhere around 2025, rather than after 2030. A whole lot can happen in ten years. We don't need another Army development program to be overtaken by events. (2) However, since the FARA will likely be in service for a half-century or more, it makes sense to conduct rigorous analysis up front to ensure that what is fielded has the capabilities to provide the most value for the warfighter and the taxpayer. Prior to spending billions of dollars and decades producing the FARA aircraft, it is prudent to spend the time to determine what the right solutions should be. Many projects fail when the initial requirements are not well thought out and the ramifications are not clearly understood. To solve the tension between these conflicting desires, designers need to iterate the design sensitivities with operational analysis to show the pros and cons of each attribute, alone and in concert, but ultimately the Army must prioritize its requirements and potentially make hard trade-off decisions.(3) The major objective of this paper is provide a methodology for the necessary understanding of the push and pull of technology readiness and application through trade studies and operational analysis early to avoid disappointments and to minimize FARA slippages and cost increases. This will be accomplished by reviewing Lessons Learned from the AHIP/OH-58D Kiowa Warrior and the LHX/RAH-66 Comanche development programs. While the authors were directly involved in these programs as Army Aviation engineers, managers and senior executives, the major emphasis for this paper will be to address how the government-industry teams brought these programs successfully through initial development. Fortunately, for the AHIP/OH-58D Kiowa Warrior Development Program there are excellent documentation of the government-industry team participation in References 4 and 5. While the authors strongly endorse the lessons learned in these documents, they will have a few of their own. For the LHX/RAH66 Comanche Development Program there is considerably less documentation; however, the authors will provide Army and their lessons learned. It is hoped that this paper and the referenced documents will be read, and the lessons learned by both government and industry involved in the FARA development program.
Items per page:
50
1 – 50 of 550