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1
Majumdar, A., K. Mak, C. Lettington i P. Nalder. "A causal factors analysis of helicopter accidents in New Zealand 1996-2005 and the United Kingdom 1986-2005". Aeronautical Journal 113, nr 1148 (październik 2009): 647–60. http://dx.doi.org/10.1017/s0001924000003316.
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Abstract Helicopter accidents cause many fatalities, and their avoidance is a major area of work for Civil Aviation safety authorities around the World. This paper uses helicopter accident data from the United Kingdom between 1986 and 2005 for 566 accidents and from New Zealand between 1996 and 2006 for 230 accidents to analyse helicopter accidents according to five categories of causes: airworthiness failure (engine); airworthiness failure (non-engine), operational failure, maintenance failure and mixed failure (i.e. operational and airworthiness combined). Factors associated with accidents, e.g. the engine types and weights of the helicopters involved; the nature of the operations and the phase of flight of the helicopter are also analysed. Operational failures were further analysed by Human Factors Analysis and Classification Scheme (HFACS) and airworthiness failures by a logical scheme of helicopter components. The results indicate that operational failures, especially due to unsafe acts, are the major cause of accidents in both countries followed by airworthiness causes. Light single piston helicopters are by far the major group associated with accidents in both countries, with few accidents for twin turbine helicopters. The majority of accidents were in non-public operations with few in public operations and in both countries, the cruise/flight/circuit phase has the largest number of accidents. Further analyses indicated statistically significant associations: type of helicopter and the cause of accidents; type of helicopter and the phase of flight; cause of accidents and nature of flights; cause of accidents and phase of flights; training flights and inadequate supervision; landing and procedural error and cruise and attention failure.
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Štrbac, Alexander, Daniel Heinrich Greiwe, Frauke Hoffmann, Marion Cormier i Thorsten Lutz. "Piloted Simulation of the Rotorcraft Wind Turbine Wake Interaction during Hover and Transit Flights". Energies 15, nr 5 (28.02.2022): 1790. http://dx.doi.org/10.3390/en15051790.
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Helicopters are used for offshore wind farms for maintenance and support flights. The number of helicopter operations is increasing with the expansion of offshore wind energy, which stresses the point that the current German regulations have not yet been validated through scientific analysis. A collaborative research project between DLR, the Technical University of Munich, the University of Stuttgart and the University of Tübingen has been conducted to examine the sizes of the flight corridors on offshore wind farms and the lateral safety clearance for helicopter hoist operations at offshore wind turbines. This paper details the results of piloted helicopter simulations in a realistic offshore wind farm scenario. The far-wake of rotating wind turbines and the near-wake of non-rotating wind turbines have been simulated with high-fidelity computational fluid dynamics under realistic turbulent inflow conditions. The resulting flow fields have been processed by superposition during piloted simulations in the research flight simulator AVES to examine the flight corridors in transit flights and the lateral safety clearance in hovering flights. The results suggest a sufficient size for the flight corridor and sufficient lateral safety clearance at the offshore wind turbines in the considered scenarios.
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Trethewey, Diane. "Development of an index for quick comparison of helicopter costs and benefits". International Journal of Wildland Fire 16, nr 4 (2007): 444. http://dx.doi.org/10.1071/wf06108.
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A helicopter comparison index was developed to incorporate cost and benefit information for individual helicopters for large wildland fire suppression operations. The costs and benefits for individual helicopters are unique. Costs consist of daily availability and hourly flight rates. Benefits depend on the payload, which depends on the altitude and temperature of operation, weight of the helicopter, equipment on board, crew, and fuel. Because of the complexity of calculating payload, previous methods for deploying helicopters classified helicopters into three types according to their typical payload. The least expensive helicopter of the desired type was deployed. Because this classification system produces a broad range of benefits within each helicopter type, this method may not deploy the most efficient helicopter. The helicopter comparison index can be calculated at representative altitudes and temperatures before it is needed. As the work is done beforehand, the helicopters can be compared quickly when they are needed. The helicopter comparison index allows helicopters to be compared based on the efficiency of the individual helicopters rather than just their cost of operation. Evaluation of Type I helicopters shows that using the helicopter comparison index instead cost of operation has savings potential of 20 to 45 percent.
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de Voogt, Alex, i Keyashia Nero. "Technical Failures in Helicopters: Non-Powerplant-Related Accidents". Safety 9, nr 1 (22.02.2023): 10. http://dx.doi.org/10.3390/safety9010010.
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Technical failures in helicopters are a main concern for helicopter safety. The prominence of mechanical failures differs for specific helicopter operations. This analysis used 151 General Aviation accident reports from the National Transportation Safety Board online database from an 11-year time period. The information in each report was collated, including the list of findings for each accident. Possible relations between causes and specific flight operations were analyzed by looking at significant differences between expected and actual values within the dataset of categorical data. It is found that the proportion of fatal accidents in this category of accidents is low (16.6%) compared with the percentage of fatal helicopter accidents in general, as well as those of specific helicopter operations. Instructional flights appear significantly more likely to be associated with maintenance-related causes. Causes related to fatigue of aircraft parts are more often associated with ferry and positional flights, as well as helicopters with turbo-shaft engines. Future research is recommended for these specific associations to further mitigate the number of accidents with non-powerplant failures.
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Rowe, S. J., D. Howson i G. Turner. "A turbulence criterion for safe helicopter operations to offshore installations". Aeronautical Journal 110, nr 1113 (listopad 2006): 749–58. http://dx.doi.org/10.1017/s0001924000001615.
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Abstract This paper describes the development of a wind turbulence criterion for the safe operation of helicopters to offshore installations. The development of the criterion was recommended following a review of the environmental effects around offshore platform helidecks. Currently, criteria exist for ambient temperature and for vertical wind component in the vicinity of helidecks, but a questionnaire-based survey of helicopter pilots revealed that the principal safety hazard and source of highest workload is turbulence around offshore installations. The new turbulence criterion will plug a long-standing gap in the guidance on offshore helideck design. The paper describes how the criterion has been developed using piloted flight simulation in a research flight simulator together with data from wind tunnel tests on offshore platforms. Initial validation has been successfully performed, and extended to include correlation with the large database of helicopter operational flight data records being collected through the UK North Sea Helicopter Operations Monitoring Programme (HOMP). The turbulence criterion will be used, together with existing criteria on vertical wind component and temperature, in the assessment of new offshore installation designs, or proposed modifications to existing designs, to determine wind conditions where turbulence is likely to be excessive for safe helicopter operations. These will be used to estimate helideck operability and thereby inform the installation topsides design process, and will provide input to the setting and maintenance of helicopter operational limitations for individual installations. The work will lead to improved safety through better prediction of safe operating envelopes and helideck operability at the design stage. In addition, development of the work is expected to enable the wind environment around offshore installations to be mapped and monitored in-service using helicopter flight data records. The new turbulence criterion has been included in updated guidance on helideck design, and offshore installation designers are now required to inform helicopter operators about wind conditions which result in violations of the turbulence criterion on their offshore installations (as is currently the case for the temperature and vertical wind component criteria).
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Babenko, Grigory, Vadim Efimov, Mikhail Kiselev i Maksim Shkurin. "Results of the Study of the Influence of External Cargo Parameters on the Helicopter Controllability". Aerospace 9, nr 5 (21.04.2022): 229. http://dx.doi.org/10.3390/aerospace9050229.
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Helicopters are widely used for air transportation and aerial work with cargo on external cables, one of the most challenging and dangerous uses. The main reason for the flight complication is the change in the controllability characteristics of the helicopter because of the presence of cargo. As of today, flight tests are mainly conducted to determine the feasibility of aerial transportation and aerial work involving external cargo. In addition, they are conducted to determine safe flight regimes when performing such operations. From a flight safety perspective, it is always desirable to know the changes in the control parameters before flight tests are performed. A proposal was made to use theoretical methods, including numerical simulations, to solve these problems. At present, work is progressing to isolate the effects of different cargoes on the external cable suspension and its direct effects on the static and dynamic characteristics of the helicopter’s control and stability. The effect of cargo mass and sail weight on the control efficiency is expressed by the helicopter’s angular acceleration, which is gained by deviating the cyclic pitch handle—a static control and stability indicator. When considering dynamic control and stability, the influence of the length of the external suspension cable on the transition time was investigated. The results obtained were refined for inclusion in all flight manuals for Mi-8 helicopters concerning flights with cargoes attached to the external suspension cables, the size and weight of the suspension cables as well as the methods of instruction and for preparing the crew for flights with upgraded cargo, including instruction via flight simulators.
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Bursala, A., O. Tcherednikov, V. Golub i Y. Trygub. "ON DEVELOPMENT OF AVIATION EQUIPMENT’SRELIABILITY MODELS (ON THE EXAMPLE OF HELICOPTERS)". Наукові праці Державного науково-дослідного інституту випробувань і сертифікації озброєння та військової техніки, nr 4 (19.08.2020): 8–16. http://dx.doi.org/10.37701/dndivsovt.4.2020.02.
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On the example of helicopters, the topical issues of systematization and mathematical processing of statistical information taking from fault log sheetsto assess the level of reliability and flight safety of state aviation equipment are considered.
The reliability of all helicopter systems must meet the pressing needs of defense capabilities and support the capabilities of the state aviation of Ukraine to carry out combat missions at the current level. Improving preparedness for assigned tasks will facilitate participation in combined operations with peacekeeping and NATO forces. The considered model of the system of aviation equipment on the example of helicopters consists of interdependent, jointly functioning, united by a single purpose of five subsystems of the corresponding type of specialty: “helicopter and engine”, “aircraft armament”,“aircraftequipment”, “avionics equipment”,“navigation and target acquisition system”.
Realization and methodical approaches to the development of complex failuremodels of the elements of “helicopter and engine” system by types of helicopters are substantiated. The paper proposes to address on the example of helicopters the lines of approach the problem of assessing the real level of operational reliability and flight safety of aircraft to maintain their serviceable condition.
When putting military aviation assets into operation according to the technical condition, using statistical models of reliability and flight safety, the important task of increasing resource indicators is solved, which requires improving the system of collecting, processing and analyzing information from fault log sheets.
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Page, Juliet, Amanda Rapoza i Eric Jacobs. "Development of Fly Neighborly helicopter model specific operational noise abatement guidance from acoustic flight test data". INTER-NOISE and NOISE-CON Congress and Conference Proceedings 263, nr 1 (1.08.2021): 5671–77. http://dx.doi.org/10.3397/in-2021-3210.
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Improved helicopter noise abatement guidance has been developed based on acoustic test data acquired by NASA, FAA and Volpe in support of the Helicopter Association International (HAI)'s Fly Neighborly Program. This higher fidelity material was developed to supplement previous training programs based on pilot and operator feedback. The manner of presentation allows pilots to readily interpret the directional noise emission of their vehicle at different operating conditions. Flight path, airspeed, approach descent rate, and deceleration rate can be assessed to optimize flight patterns both during the pre-flight planning stage and in real time during flight operations in response to local conditions and events. The resultant sound directivity would be displayed as colored noise exposure contours overlaid onto a map of the area in the vicinity of the helicopter. New Fly Neighborly training modules have been developed utilizing directional operational noise plots based on Volpe's Advanced Acoustic Model (AAM) modeling with empirical sound sphere data from dedicated US Government helicopter flight tests. This paper will describe the acoustic analyses and will present the updated noise guidance for the AS350, AS365, AW139, Bell 205, Bell 206, Bell 407, R-44, R-66 and S-76D helicopters.
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Hart, J. "MANAGING HELICOPTER RISK". APPEA Journal 45, nr 1 (2005): 657. http://dx.doi.org/10.1071/aj04049.
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Annually, a million hours are flown by helicopters for the international petroleum industry. About 90% of this flying is offshore, and involves around 10 million passengers. Each year some 25–35 accidents are recorded, an average of 22 passengers and crew lose their lives, and a higher number are injured. Some 45% of these accidents stem from technical causes, a similar number are pilot related, and the remainder are linked to other causes. Helicopter accident rates are 10 times higher than those of airline travel.Strategies to tackle both technical failures and pilot related accidents have emerged, although application of these strategies around the world is inconsistent.One way in which helicopter technical issues have been addressed is by the introduction of Health and Usage Monitoring (HUMS) equipment. To tackle the pilot related accidents, lessons have been drawn from the airline industry’s use of Flight Data Management (FDM) programs, which allow pilots to learn from deviations from pre-defined normal parameters during routine flying. The helicopter version of FDM is the Helicopter Operations Monitoring Program (HOMP). Another important training tool is flight simulator training to allow simulated emergencies to be flown and practiced.Petroleum companies have the opportunity through their own aviation policy and standards to stipulate flight crew experience and training, the technical specifications for their contracted helicopters and the application of advanced safety programs, such as HUMS, and HOMP. Compliance and continuous improvement in line with these standards can be verified and facilitated through operational and technical audit. Only with such active involvement can helicopter risk be managed downwards.
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Żugaj, Marcin, Mohammed Edawdi, Grzegorz Iwański, Sebastian Topczewski, Przemysław Bibik i Piotr Fabiański. "An Unmanned Helicopter Energy Consumption Analysis". Energies 16, nr 4 (20.02.2023): 2067. http://dx.doi.org/10.3390/en16042067.
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The number of operations incorporating E-VTOL aircrafts is increasing each year, and the optimization of the energy consumption of such vehicles is a major problem. In this paper, a small-scale ARCHER helicopter’s energy consumption is analyzed, wherein different flight conditions, main rotor revolutions, and flight control system settings are considered. The helicopter dynamic model was developed in the FLIGHTLAB environment and was then validated based on flight test data. The model used for the calculation of energy consumption was developed using the electric and dynamic characteristics of the main rotor, electric motor, and transmission system. The main part of this work concerns the analysis of electric energy consumption during the vehicle’s flight via the use of an automatic flight control system (AFCS) that ensures repeatable flight conditions. The AFCS was designed such that it includes both path and attitude control to provide hover and cruise control modes. The helicopter’s energy consumption was analyzed during different phases of flight, when executing maneuvers, and using different main rotor angular velocities to perform - a given task. The results show that the level of energy consumption significantly depends on the helicopter’s main rotor revolutions, flight speed, and the maneuvers performed. The proposed methodology can be used in prospective energy-efficient mission planning and UAV helicopter design.
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Zhang, Chi, Cheng Dong Xu, Xin Pei i Chun Sheng Hu. "Information Acquisition of Maintenance, Repair and Overhaul/Operations System for Helicopters". Applied Mechanics and Materials 220-223 (listopad 2012): 2150–55. http://dx.doi.org/10.4028/www.scientific.net/amm.220-223.2150.
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The helicopter Maintenance, Repair and Overhaul/Operations (MRO) system enables the best sharing of the maintenance resources and maintenance ability in a wide area, so as to promote the specialization of the helicopter maintenance organizations. Information acquisition is an important and difficult part of the helicopter MRO system. This paper systematically analyzes the condition monitoring methods which are used to monitor the rotational speed, temperature, pressure, vibration and flight parameter in different parts of a helicopter, and then it puts forward some improved ways for information acquisition. Considering the helicopter’s features, the process of information acquisition is illustrated. In addition, this paper presents the basic requirements of data sampling, and it also shows a detailed discussion on data format and data transmission in the helicopter MRO system. At the end of the paper, a system mode and architecture of helicopter MRO system are proposed.
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Jin, Zibo, Lu Nie, Daochun Li, Zhan Tu i Jinwu Xiang. "An Autonomous Control Framework of Unmanned Helicopter Operations for Low-Altitude Flight in Mountainous Terrains". Drones 6, nr 6 (17.06.2022): 150. http://dx.doi.org/10.3390/drones6060150.
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Low-altitude flight in mountainous terrains is a difficult flight task applied in both military and civilian fields. The helicopter has to maintain low altitude to realize search and rescue, reconnaissance, penetration, and strike operations. It contains complex environment perception, multilevel decision making, and multi-objective flight control; thus, flight is currently mainly conducted by human pilots. In this work, a control framework is implemented to realize autonomous flight for unmanned helicopter operations in an unknown mountainous environment. The identification of targets and threats is introduced using a deep neural network. A 3D vector field histogram method is adopted for local terrain avoidance based on airborne Lidar sensors. In particular, we propose an intuitive direct-viewing method to judge and change the visibilities of the helicopter. On this basis, a finite state machine is built for decision making of the autonomous flight. A highly realistic simulation environment is established to verify the proposed control framework. The simulation results demonstrate that the helicopter can autonomously complete flight missions including a fast approach, threat avoidance, cover concealment, and circuitous flight operations similar to human pilots. The proposed control framework provides an effective solution for complex flight tasks and expands the flight control technologies for high-level unmanned helicopter operations.
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Zhou, Tejun, Jiazheng Lu, Chuanping Wu i Shilong Lan. "Numerical Calculation and Analysis of Water Dump Distribution Out of the Belly Tanks of Firefighting Helicopters". Safety 8, nr 4 (3.10.2022): 69. http://dx.doi.org/10.3390/safety8040069.
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Helicopters are more and more widely used for water dumping in fire extinguishing operations nowadays. Increasing attention is being paid to improving helicopter firefighting efficiency. Water distribution onto the ground from the helicopter tank is a key reference target to evaluate firefighting efficiency. Numerical simulations and calculations were carried out concerning water dumping out of the belly tank of a helicopter using the VOF (Volume of Fluent Model) model and mesh adaptation in ANSYS Fluent, and the effects of two parameters, the height of the tank above the ground and the wind speed, on the wake flow and water distribution were discussed. The results showed that for forward flight, the higher the forward flight speed, the less the average water depth on the ground. Similar results were obtained for flight height. The average water depth was one order of magnitude less than in the cases of the corresponding hovering helicopter for a given wind speed. As for hovering flight, the higher the wind speed, the less the average water depth on the ground. The simulation results were basically consistent with the conclusions of water dump tests of fire-fighting equipment carried by helicopters. For example, when the helicopter flew at a forward flight speed of 15 m/s and the tank bottom was 30 m above the ground, the area covered by the dumped water would be 337.5 m2, and the average water depth accumulated per square meter would be 0.3 cm. This result was close to the 0.34 cm obtained under Hayden Biggs’s test condition with a forward flight speed of 70 km/h and a height above the ground of 24 m.
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EDWARDS, FREDERICK G., i PETER V. W. LOOMIS. "Civil Helicopter Flight Operations Using Differential GPS". Navigation 32, nr 3 (wrzesień 1985): 233–53. http://dx.doi.org/10.1002/j.2161-4296.1985.tb00907.x.
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Voskuijl, M., G. D. Padfield, D. J. Walker, B. J. Manimala i A. W. Gubbels. "Simulation of automatic helicopter deck landings using nature inspired flight control". Aeronautical Journal 114, nr 1151 (styczeń 2010): 25–34. http://dx.doi.org/10.1017/s000192400000350x.
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Abstract Research studies have indicated that the optical flow parameter, time to close tau, is the basis of purposeful control in the animal world, and used by both fixed wing and helicopter pilots during manoeuvring. This parameter is defined as the instantaneous time to close a gap (spatial or force) at the current closing rate. A novel automatic flight control strategy has been developed that makes use of optical flow theory and in particular, the parameter tau. This strategy has been applied to two distinct problems; (1) the landing of a helicopter on a ship and (2) the lateral repositioning of a helicopter. The first is a challenging case because the landing of a helicopter on a ship is one of the most dangerous of all helicopter flight operations. Furthermore, helicopters are often subject to torque oscillations during rapid collective control, which increases pilot workload significantly when operating with low power margins and/or whilst performing tasks that require accurate heave control. The second case demonstrates the generality of the technique. Both automatic manoeuvres were simulated successfully within desired limits, with the novel control strategy creating a ‘natural’, smooth, tau motion.
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Forrest, J. S., C. H. Kaaria i I. Owen. "Evaluating ship superstructure aerodynamics for maritime helicopter operations through CFD and flight simulation". Aeronautical Journal 120, nr 1232 (4.07.2016): 1578–603. http://dx.doi.org/10.1017/aer.2016.76.
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ABSTRACTThe unsteady air flow over and around the helicopter landing deck of a naval vessel is known to cause high pilot workload and to limit the helicopter's operational envelope for launch and recovery. Previous research has suggested that modifications to the ship's hangar edges can beneficially modify the flow over the deck. This paper examines the effectiveness of five hangar-edge modifications using computational fluid dynamics–generated airwakes and flight mechanics modelling, as well as piloted flight trials in a motion-base simulator. Results are presented, in terms of unsteady helicopter loads and pilot workload ratings, for modifications to the windward vertical rear edge of the hangar and with an oblique wind. The results demonstrate that while the airwake can be altered by superstructure modifications, the integrated effect of the altered airwake on the entire helicopter does not necessarily give the desired result; indeed of the five modifications tested, two were seen to be beneficial while three caused an increase in pilot workload compared with the unmodified hangar. Overall, the paper shows that the airwake can be modified by superstructure design changes, and that the effect on the helicopter can be measured through modelling and simulation. It is also demonstrated that making judgements on the severity of the airwake based on the aerodynamic flow field alone can be misleading. The benefit of these simulation tools is that they can be used during the ship design process to evaluate the effect of the superstructure aerodynamics, rather than wait until after the ship is built.
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Cao, Yihua, Yihao Qin, Wenyuan Tan i Guozhi Li. "Numerical Simulation of Fully Coupled Flow-Field and Operational Limitation Envelopes of Helicopter-Ship Combinations". Journal of Marine Science and Engineering 10, nr 10 (8.10.2022): 1455. http://dx.doi.org/10.3390/jmse10101455.
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Landing a helicopter to the ship flight deck is most demanding even for the most experienced pilots and modeling and simulation of the ship-helicopter dynamic interface is a substantially challenging technical problem. In this paper, a coupling numerical method was developed to simulate the fully coupled ship-helicopter flow-field under complete wind-over-deck conditions. The steady actuator disk model based on the momentum source approach and the resolved blade method based on the moving overset mesh method were employed to model the rotor. Two different ship-helicopter combinations were studied. The helicopter flight mechanics model was established and then the influences of coupled airwake on the helicopter were analyzed. Finally, based on the derived rejection criterion of safe landing and the developed numerical method, the flight envelopes for these two ship-helicopter combinations were predicted. The steady actuator disk model was found to be effective in the study of helicopter operations in the shipboard environment. The calculated flight envelopes indicate that an appropriate wind direction angle is beneficial to increasing the allowable maximum wind speed and the operating boundary is affected by the rotation direction of the main rotor.
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Fazlin Khuzaima, Retno Wibawanti, Agus Sugiharto, Wawan Mulyawan, M. Ilyas i Dewi S. Soemarko. "Relationship between Total Flight Hours and Individual Factors with Low Back Pain in Indonesian Military Helicopter Pilots". Indonesian Journal of Community and Occupational Medicine 3, nr 1 (26.07.2023): 9–16. http://dx.doi.org/10.53773/ijcom.v3i1.89.9-16.
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Introduction: Helicopter pilots are potentially at risk of Low Back Pain (LBP) and are twice as likely as fighter pilots to experience it. Helicopter pilots’ LBP is caused by a combination of risk factors: engine and rotor vibration, ergonomic risks due to cockpit design, static seating position due to operations, and individual factors. These factors are incorporated into cumulative aviation risk exposure, which can be measured by total flight hours. The prevalence of LBP in Caucasians is high, at 50.5%-92%. However, there has not been any research on Indonesian military helicopter pilots who have a different posture from Caucasians.Objective: To determine the prevalence of LBP, to analyze the relationship between total flight hours and individual factors (age, height, BMI, exercise habits, and smoking habits) with LBP in Indonesian military helicopter pilots.Methods: The study was conducted at the Indonesian Army and Indonesian Air Force with total sampling method as many as 124 people. An explanation was carried out followed by filling in the consent to become a research subject, filling in personal data, anamnesis, Numeric Rating Scale (NRS), physical examination, neurological examination, and total flight hour data.Results: There were 124 subjects, consisting of 37.9% pilots and 62.1% copilots, 87.9% of pilots operate large helicopters, have average total flight hours of 450 hours, age of 30 years, the height of 172.66 cm, low intensity exercise habits of 61.3%, and smokers as much as 45.2%. A total of 57 people (46%) experienced LBP. Statistical results showed that total flight hours had an association with LBP (p = 0.035) where each 1 unit increase in total flight hours had a 1.02 times greater chance of LBP.Conclusion: The prevalence of LBP is 46% and there is an association between total flying hours and LBP in Indonesian military helicopter pilots.
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Haviland, Stephen, Dmitry N. Bershadsky i Eric N. Johnson. "Rapid Automatic Slung Load Operations with Unmanned Helicopters". Journal of the American Helicopter Society 64, nr 4 (1.10.2019): 1–11. http://dx.doi.org/10.4050/jahs.64.042009.
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Slung load operations often involve following conservative flight paths to prevent unwanted swing of the load. However, doing so often limits the maneuvering capability of the system and increases the time to complete trajectories. This work investigates methods to rapidly move a slung load with a helicopter with the intent to deliver it quickly and precisely to a fixed point. Inspired by prior work utilizing differential flatness, which is a property of certain systems that allow for advantageous controllers to be developed for nonlinear systems, the controller developed does not require instrumentation of the load or the ability to estimate the state of the load but does not preclude it. A feedforward and feedback controller was developed that modifies the helicopter commands based on the desired load path. The controller is simplified by neglecting selected higher order terms and modeling the load as a point-mass. An adaptive dynamic inversion controller is used to control the helicopter. A fixed downward-facing camera is used to provide estimates of load position for the feedback controller. Simulation and flight-test results are shown using a Yamaha R-MAX helicopter to validate the proposed method.
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Asher, M., D. Toshkova i N. Lieven. "Automatic regime detection for Rotor Track and Balance using vibration only sensor data". Aeronautical Journal 124, nr 1275 (8.04.2020): 617–34. http://dx.doi.org/10.1017/aer.2020.17.
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ABSTRACTRotor Track and Balance (RTB) is an important part of regular helicopter maintenance. The ability to perform this service assessment during normal operations, rather than with a series of explicit RTB flights, would greatly reduce the time the vehicle is non-operational and the maintenance costs associated with these flights and adjustments. This paper presents a novel methodology for identifying the RTB-related flight regimes, using a minimal number of vibration signals and comparing these to repeatable and stable characteristic vibration profiles. The technique is stable, with an 81% success in correct identification of the flight regime, when applied to a whole flight with a number of unknown regime events. The method can be run in real time, making it an effective way of identifying periods of flight that are suitable for RTB measurements. A new technique for visually representing any real-time flight signal, such as vibration, is also presented.
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Balzarek, Christoph, Steffen Kalow, Johannes Riemenschneider i Andres Rivero. "Manufacturing and Testing of a Variable Chord Extension for Helicopter Rotor Blades". Actuators 11, nr 2 (9.02.2022): 53. http://dx.doi.org/10.3390/act11020053.
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Helicopters are still an indispensable addition to aviation in this day and age. They are characterized by their ability to master both forward flight and hover. These characteristics result in a wide range of possible operations. Key for the design of the rotor blades is a blade design that always represents a compromise between the different flight conditions, which enables safe and efficient flight in the various flight conditions. In order to operate the rotor blade even more efficiently in all flight conditions, a new morphing concept, the so-called linear variable chord extension, has been developed. Here, the blade chord length in the root area is changed with the help of an elastic skin to adapt it to the respective flight condition. The simulations performed for this concept showed a promising increase in overall helicopter performance. The fabrication of the resulting demonstrator as well as the tests in the whirl-tower and wind tunnel are presented in this paper. The results of the tests show that the concept of linear variable chord extension has a positive influence and a great potential for hovering flight.
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Trigos, Miguel A., Antonio Barrientos i Jaime del Cerro. "Systematic Process for Building a Fault Diagnoser Based on Petri Nets Applied to a Helicopter". Mathematical Problems in Engineering 2015 (2015): 1–13. http://dx.doi.org/10.1155/2015/963756.
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This work presents a systematic process for building a Fault Diagnoser (FD), based on Petri Nets (PNs) which has been applied to a small helicopter. This novel tool is able to detect both intermittent and permanent faults. The work carried out is discussed from theoretical and practical point of view. The procedure begins with a division of the whole system into subsystems, which are the devices that have to be modeled by using PN, considering both the normal and fault operations. Subsequently, the models are integrated into a global Petri Net diagnoser (PND) that is able to monitor a whole helicopter and show critical variables to the operator in order to determine the UAV health, preventing accidents in this manner. A Data Acquisition System (DAQ) has been designed for collecting data during the flights and feeding PN diagnoser with them. Several real flights (nominal or under failure) have been carried out to perform the diagnoser setup and verify its performance. A summary of the validation results obtained during real flight tests is also included. An extensive use of this tool will improve preventive maintenance protocols for UAVs (especially helicopters) and allow establishing recommendations in regulations.
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Shin, Sanghyun, Abhishek Vaidya i Inseok Hwang. "Helicopter Cockpit Audio Data Analysis to Infer Flight State Information". Journal of the American Helicopter Society 65, nr 3 (1.07.2020): 1–8. http://dx.doi.org/10.4050/jahs.65.032001.
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In recent years, the National Transportation Safety Board has highlighted the importance of analyzing flight data as one of the effective methods to improve the safety and efficiency of helicopter operations. Since cockpit audio data contain various sounds from engines, alarms, crew conversations, and other sources within a cockpit, analyzing cockpit audio data can help identify the causes of incidents and accidents. Among the various types of the sounds in cockpit audio data, this paper focuses on cockpit alarm and engine sounds as an object of analysis. This paper proposes cockpit audio analysis algorithms, which can detect types and occurrence times of alarm sounds for an abnormal flight and estimate engine-related flight parameters such as an engine torque. This is achieved by the following: for alarm sound analysis, finding the highest correlation with the short time Fourier transform, and the Cumulative Sum Control Chart (CUSUM) using a database of the characteristic features of the alarm; and for engine sound analysis, using data mining and statistical modeling techniques to identify specific frequencies associated with engine operations. The proposed algorithm is successfully applied to a set of simulated audio data, which were generated by the X-plane flight simulator, and real audio data, which were recorded by GoPro cameras in Sikorsky S-76 helicopters to demonstrate its desired performance.
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Ishiki, Takahiro, Kai Washizaki i Makoto Kumon. "Evaluation of Microphone Array for Multirotor Helicopters". Journal of Robotics and Mechatronics 29, nr 1 (20.02.2017): 168–76. http://dx.doi.org/10.20965/jrm.2017.p0168.
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[abstFig src='/00290001/16.jpg' width='300' text='UAV with a microphone array whose performance is evaluated' ] High expectations are placed on the use of unmanned aerial vehicles (UAVs) in such tasks as rescue operations, which require a system that makes use of visual or auditory information to recognize the surrounding environment. As an example of such a system, this study examines the recognition of the environment using a helicopter mounted with a microphone array. Because the rotors of a helicopter generate high noise during operation, it is necessary to reduce the effects of this noise and those from other sources to record the audio signals coming from the ground with onboard microphones. In particular, because of helicopter body control, the rotor speed changes continuously and causes an unsteady rotor noise, which implies that it would be effective to arrange the microphones at a sufficient distance from the rotors. When a large microphone array is employed, however, the array weight may alter the helicopter’s flight characteristics and increase the noise, presenting a dilemma. This paper presents a model of rotor noise that takes into account the effect of the microphone array on the helicopter’s dynamic characteristics and proposes a method of evaluating the optimality of the array configuration, which is necessary for design. The validity of the proposed method is investigated using a multirotor helicopter mounted with a microphone array previously developed by the authors. In addition, an application example for locating sound sources on the ground using this helicopter is presented.
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Sal, Firat. "Effects of the actively morphing root chord and taper on helicopter energy". Aircraft Engineering and Aerospace Technology 92, nr 2 (16.12.2019): 264–70. http://dx.doi.org/10.1108/aeat-08-2019-0165.
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Purpose The purpose of this paper presents the effects of actively morphing root chord and taper on the energy of the flight control system (i.e. FCS). Design/methodology/approach Via regarding previously mentioned purposes, sophisticated and realistic helicopter models are benefitted to examine the energy of the FCS. Findings Helicopters having actively morphing blade root chord length and blade taper consume less control energy than the ones having one of or any of passively morphing blade root chord length and blade taper. Practical implications Actively morphing blade root chord length and blade taper can be used for cheaper helicopter operations. Originality/value The main originality of this paper is applying active morphing strategy on helicopter blade root chord and blade taper. In this paper, it is also found that using active morphing strategy on helicopter blade root chord and blade taper reasons less energy consumption than using either passively morphing blade root chord length plus blade taper or not any. This causes also less fuel consumption and green environment.
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Guchenko, Mykola, Vitalii Shmakov, Anna Yudina, Vikroriya Belska, Jiri Cejka i Ladislav Bartuska. "An Approach to Developing Mathematical Software of On-Board Helicopter Flight Simulator Decision Support System". LOGI – Scientific Journal on Transport and Logistics 13, nr 1 (1.01.2022): 61–72. http://dx.doi.org/10.2478/logi-2022-0006.
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Abstract The work explores methods and develops aids to improve a pilot flight training level using Full Flight Simulators. It examines their didactic advantages over real helicopters by implementing on-board intelligent decision support systems (IDSS). These simulation programs monitor actions of learner, find the best ways to correct errors and generate appropriate instructions. The training is carried out by reference point methods while the helicopter flight dynamics model simulates a flight and helps an instructor in parallel. Sufficiently simple and accurate model of helicopter flight dynamics was selected and tested to assess the proposed methods and aids. Our analysis introduces a functional structure of IDSS as an adaptive control system with a reference model. We further conducted a study on developing models, methods and means of automatic analysis, forecasting, optimization and correction of actions. Combining single-criteria conditional and vector optimization methods, we found out optimal flight parameters. The research findings revealed that the chosen optimization method requires too many system resources for the optimal solution to be found in a short time. The study thereby comes up with applying ANNs to solve this problem.
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de Voogt, Alex, Hilary Kalagher i Andrew Diamond. "Helicopter Pilots Encountering Fog: An Analysis of 109 Accidents from 1992 to 2016". Atmosphere 11, nr 9 (17.09.2020): 994. http://dx.doi.org/10.3390/atmos11090994.
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Helicopters have the ability to make maneuvers or precautionary off-airport landings to avoid flights into instrument meteorological conditions (IMC) such as fog. Flight accidents in which fog was encountered as well as inadvertent and intentional flights into fog were examined to understand their occurrence. A 25-year period in the United States using the National Transportation Safety Board online database was used to collect 109 accident reports of which 73 (67%) were fatal. Pilots flying intentionally into IMC were more likely to be a part of a fatal accident than those who did so inadvertently. Those pilots who were reported as being under pressure when encountering fog conditions were also more likely to be in an accident. The findings confirm a high prevalence and an added danger to intentional flights into IMC. In addition, decision-making under pressure when encountering IMC conditions is now linked to a higher proportion of fatalities, emphasizing that helicopter pilots should be made aware of these specific decision-making circumstances in their operations.
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Ivler, Christina M., J. David Powell, Mark B. Tischler, Jay W. Fletcher i Carl Ott. "Design and Flight Test of a Cable Angle Feedback Flight Control System for the RASCAL JUH-60 Helicopter". Journal of the American Helicopter Society 59, nr 4 (1.10.2014): 1–15. http://dx.doi.org/10.4050/jahs.59.042008.
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The ability of a helicopter to carry externally slung loads makes it very versatile for many civil and military operations. However, the piloted handling qualities of the helicopter are degraded by the presence of the slung load. A control system is developed that uses measurements of the slung load motions as well as conventional fuselage feedback to improve the handling qualities for hover/low-speed operations. Prior research has shown a fundamental trade-off between load damping and piloted handling qualities for a feedback control system with cable angle/rate feedback. A new task-tailored approach proposed and implemented herein uses a method of switching between a load damping mode and a piloted handling qualities mode. These modes provide appropriate load feedback depending on the piloting task and flight regime. This provides improved handling qualities for maneuvering flight and for improved precision load control at hover. A new mission task element for precision load placement is developed (for possible inclusion into ADS-33E-PRF) to test the ability of the cable feedback system to improve load placement task performance. The improvements provided by this control system are demonstrated in a piloted flight test on the JUH-60A RASCAL fly-by-wire helicopter. The average load set-down time was reduced by a factor of two for the 1000-lb load on a 56-ft sling.
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Greenwood, Eric, Fredric H. Schmitz i Richard D. Sickenberger. "A Semiempirical Noise Modeling Method for Helicopter Maneuvering Flight Operations". Journal of the American Helicopter Society 60, nr 2 (1.04.2015): 1–13. http://dx.doi.org/10.4050/jahs.60.022007.
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Qian, Yu, Xiao Jun Xiang i Jun Li Yang. "Study on the Vortex Ring State of Helicopter and Flight Training Operation". Advanced Materials Research 908 (marzec 2014): 245–48. http://dx.doi.org/10.4028/www.scientific.net/amr.908.245.
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Vortex ring state (VRS) is an inherently unsteady aerodynamic phenomenon. For rotor operations in the VRS, an inherent unsteadiness is a characteristic of the flow state, which is reflected by the waves and knots produced on the tip vortex filaments. Operationally, entry into the VRS manifests as rotor thrust fluctuations and also an increase in the average rotor shaft torque, the latter which is necessary to overcome the higher induced aerodynamic losses associated with rotor operations inside its own wake. Arming to the flight safety, the VRS development is discussed, the VRS models are summarized, and the operations for flight out VRS are given at the end of this paper. It is helpful to helicopter flight and training.
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Wang, Zeyang, Jun Huang i Mingxu Yi. "A Stealth–Distance Dynamic Weight Deep Q-Network Algorithm for Three-Dimensional Path Planning of Unmanned Aerial Helicopter". Aerospace 10, nr 8 (15.08.2023): 709. http://dx.doi.org/10.3390/aerospace10080709.
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Unmanned aerial helicopters (UAHs) have been widely used recently for reconnaissance operations and other risky missions. Meanwhile, the threats to UAHs have been becoming more and more serious, mainly from radar and flights. It is essential for a UAH to select a safe flight path, as well as proper flying attitudes, to evade detection operations, and the stealth abilities of the UAH can be helpful for this. In this paper, a stealth–distance dynamic weight Deep Q-Network (SDDW-DQN) algorithm is proposed for path planning in a UAH. Additionally, the dynamic weight is applied in the reward function, which can reflect the priorities of target distance and stealth in different flight states. For the path-planning simulation, the dynamic model of UAHs and the guidance model of flight are put forward, and the stealth model of UAHs, including the radar cross-section (RCS) and the infrared radiation (IR) intensity of UAHs, is established. The simulation results show that the SDDW-DQN algorithm can be helpful in the evasion by UAHs of radar detection and flight operations, and the dynamic weight can contribute to better path-planning results.
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Haworth, Loran A., Nancy Bucher i David Runnings. "Helmet Mounted Display Systems for Helicopter Simulation". Proceedings of the Human Factors Society Annual Meeting 33, nr 2 (październik 1989): 86–90. http://dx.doi.org/10.1177/154193128903300219.
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Simulation scientists continually pursue improved flight simulation technology with the goal of closely replicating the “real world” physical environment. The presentation/display of visual information for flight simulation is one such area enjoying recent technical improvements that are fundamental for conducting simulated operations close to the terrain. Detailed and appropriate visual information is especially critical for Nap-Of-the-Earth (NOE) helicopter flight simulation where the pilot maintains an “eyes-out” orientation to avoid obstructions and terrain. This paper elaborates on the visually-coupled Wide Field Of View Helmet Mounted Display (WFOVHMD) system technology as a viable visual display system for helicopter simulation. In addition the paper discusses research conducted on the NASA-Ames Vertical Motion Simulator that examined one critical research issue for helmet mounted displays.
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Paszko, Mateusz. "Infrared Signature Suppression Systems in Modern Military Helicopters". Transactions on Aerospace Research 2017, nr 3 (1.09.2017): 63–83. http://dx.doi.org/10.2478/tar-2017-0022.
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Abstract Helicopters play an important role in air-to-ground fire covering and the short-distance air-to-air fights, as well as the anti-tank missions and battlefield force transferring. The detection and survivability of helicopters on a battlefield significantly depends on their infrared emissions level, as well as the methods, equipment and systems used by potential enemy. The automatic detection systems, recognition and identification of flying objects use among other the thermo-detection methods, which rely on detecting the infrared radiation emitted by the tracked object. Furthermore, due to low-altitude and relatively low flight speed, today’s combat assets like missile weapons equipped with infrared guidance systems are one of the most important threats to the helicopters performing combat missions. Especially meaningful in a helicopter aviation is infrared emission by exhaust gases, egressed to the surroundings. Due to high temperature, exhaust gases are a major factor in detectability of a helicopter performing air combat operations. In order to increase the combat effectiveness and survivability of military helicopters, several different types of the infrared suppressor (IRS) have been developed. This paper reviews contemporary developments in this discipline, with particular examples of the infrared signature suppression systems.
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Fang, Shuping, Yu Ru, Yangyang Liu, Chenming Hu, Xuyang Chen i Bin Liu. "Route Planning of Helicopters Spraying Operations in Multiple Forest Areas". Forests 12, nr 12 (29.11.2021): 1658. http://dx.doi.org/10.3390/f12121658.
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It is of great value to research the problem of forest pest and disease control. Currently, helicopters play an important role in dealing with this problem. However, the spraying route planning still depends on the pilot’s driving experience, which leads to low efficiency and less accurate coverage. For this reason, this paper attempts to use intelligent algorithms to plan the pesticide spraying route for helicopters. When the helicopter is conducting spraying operations in multiple forest areas, the routes are divided into two parts: pesticide spraying routes for individual forest areas and dispatch routes between multiple forest areas. First, the shorter spraying route with fewer turnarounds for individual forest areas was determined. Then a two-layer intelligent algorithm, a combination of a genetic algorithm (GA) and ant colony optimization algorithm (ACO), was designed to determine the dispatch route between multiple forest areas, which is referred to as GAACO-GA. The performance was evaluated in self-created multiple forest areas and compared with other two-layer intelligent algorithms. The results show that the GAACO-GA algorithm found the shortest dispatch route (5032.75 m), which was 5.60%, 5.45%, 6.54%, and 4.07% shorter than that of GA-GA algorithm, simulated annealing-GA (SA-GA) algorithm, ACO-GA algorithm, and particle swarm optimization-GA (PSO-GA) algorithm, respectively. A spraying experiment with a helicopter was conducted near Pigzui Mountain, Huai’an City, Jiangsu Province, China. It was found that the flight path obtained from the proposed algorithm was 5.43% shorter than that derived from a manual planning method. The dispatch route length was reduced by 16.93%, the number of turnarounds was reduced by 11 times, and the redundant coverage was reduced by 17.87%. Moreover, helicopter fuel consumption and pesticide consumption decreased by 10.56% and 5.43%, respectively. The proposed algorithm can shorten the application route, reduce the number of turnarounds and the cost of spraying operations, and has the potential for use in spraying operations in smart forestry and agriculture.
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Shaffer, Margaret T., Keith C. Hendy i Lou R. White. "An Empirically Validated Task Analysis (EVTA) of Low Level Army Helicopter Operations". Proceedings of the Human Factors Society Annual Meeting 32, nr 2 (październik 1988): 178–82. http://dx.doi.org/10.1177/154193128803200239.
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A computer-based Empirically Validated Task Analysis (EVTA) of Canadian Forces light observation helicopter operations was conducted from video records of cockpit activity gathered during flight. The task analysis was performed in order to provide data for function analysis and workload prediction studies in support of the Canadian Forces Light Helicopter replacement project. Observable behaviors were categorized according to the type of activity involved and communications were analysed for content, agencies involved, and relevance to the crew's task. The results of this study indicate that data gathered from a controlled test environment can differ considerably from those obtained in operational settings and that miniature video cameras can be useful in obtaining information from environments which hitherto may have been inaccessible to all but operational personnel.
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Oliveira Neto, João Manoel de, Andersson Guimarães Oliveira, João Vitor Lira de Carvalho Firmino, Marcelo Cavalcanti Rodrigues, Antônio Almeida Silva i Laura Hecker de Carvalho. "Development of a smart system for diagnosing the operating conditions of a helicopter prototype via vibrations analysis". Research, Society and Development 10, nr 12 (22.09.2021): e304101220546. http://dx.doi.org/10.33448/rsd-v10i12.20546.
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In the forward flight, wind loads affect the helicopters and cause vibration. This paper analyzes the behavior of a helicopter prototype composed by two blades when subjected to a front wind load, similar to the forwarding flight condition. An Artificial Neural Network (ANN) processes the experimental data in order to identify the pattern of its dynamic behavior. The tests led to Vibration analysis for different wind speeds. Also, the data indicates that vibration amplitude increases when the blades are subjected to the fundamental frequency and its first harmonic on tests conducted without rotor plane tilt (hover flight). On the other hand, the second test performs a 5-degree tilt on the rotor disc. In this test, the vibration amplitude decreased in the fundamental frequency, and the amplitude related to the first harmonic increased. The ANN achieved 100% efficiency in recognizing the flight conditions of the prototype.
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Huliak, O., L. Kinderknekht, V. Minasov, M. Smolyanyi i V. Klimenko. "ACTIONS OF THE ARMY AVIATION DURING THE RAID BY THE AIR ASSAULT FORCES’ UNITS". Collection of scientific works of Odesa Military Academy 2, nr 14 (25.01.2021): 209–13. http://dx.doi.org/10.37129/2313-7509.2020.14.2.209-213.
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The article analyzes the foreign and domestic experience of combat use of Army Aviation Helicopters (AA) in modern wars and local conflicts when conducting raid operations by the units of Air Assault (Airmobile) forces, as well as the experience of transfer of the Air Assault Forces by helicopters in time of action. During a raid, air assault battalion can use combat helicopters. In this case, helicopter ambushes are most expedient to use in the ways of raising the nearest enemy reserves and in case of the enemy's mobile objects to strike suddenly, using various tactical techniques. The use of ambushes will be most effective in the area, which provides the secretive action of helicopters and the selection of enough quantity of fields. The use of Army aviation allows the airborne assault units to be transferred during a raid. Helicopters must fly at extremely low altitudes using terrain masking, individual and group means of EW. Exit of helicopters at the landing field of the air assault force is carried out suddenly and accurately in relation to place and time. AA units are widely used to evacuate units. Transport and combat helicopters provide for the admission on board and transportation of personnel, weapons, documents; conducting intelligence. At the same time combat helicopters perform the task of destroying air defense on the flight route; concealment of AA combat order from possible attacks by enemy helicopters in the air; landing and take-off of transport and combat helicopter. Commanders of air assault units must be aware of the tactics of combat, transport-combat and transport helicopters and their tactical characteristics, which will significantly improve the effectiveness of the raid and be able to apply it during the raid. Keywords: Army aviation helicopters, combat control group, advanced aircraft commander, Air Assault Forces, helicopter units.
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Nascimento, F. A. C., A. Majumdar, W. Y. Ochieng i W. Schuster. "Night-time offshore helicopter operations: a survey of risk levels per phase of flight, flying recency requirement and visual approach technique". Aeronautical Journal 119, nr 1222 (grudzień 2015): 1475–98. http://dx.doi.org/10.1017/s0001924000011362.
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AbstractThe analysis of risks per phases of flight is fundamental for safe helicopter operations, of which night-time offshore oil- and gas-related missions form an important part. The safe execution of such missions also depends on pilots’ recent flying practice and a stable visual approach segment prior to landing. However, the poor quality of the safety data currently available prevents accurate analysis of risk on a per-phase-of-flight basis, establishment of a meaningful flying recency requirement and identification of any preferable visual approach design. To redress these problems, this paper develops a bespoke taxonomy of phases of offshore helicopter flights and uses it as the basis for a questionnaire survey on the phase-specific risk levels experienced by pilots in the night-time, perceived optimal flying recency requirement and preferred visual approach design. With the responses obtained from pilots located in seven countries, extensive statistical hypothesis testing shows that the phases involving visual scan techniques at high speed regimes are problematic, especially the visual segment of instrument approaches. Moreover, the between-night-flights time gaps required for assured flying recency were found considerably shorter than currently standardised across the industry. Finally, no preferred visual approach technique was identified. A number of important implications have been highlighted and should form the basis for future safety interventions.
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Yuan, Weixing, Alanna Wall, Eric Thornhill, Chris Sideroff, Mahmoud Mamou i Richard Lee. "CFD Aided Ship Design and Helicopter Operation". Journal of Marine Science and Engineering 10, nr 9 (15.09.2022): 1304. http://dx.doi.org/10.3390/jmse10091304.
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In support of Canadian industrial and defence ship design and offshore helicopter operations, a series of Ship–Helicopter Operational Limits Analysis and Simulation (SHOLAS) projects are being conducted at the National Research Council Canada (NRC) in collaboration with Defence Research and Development Canada (DRDC). This study presents a brief overview of a Canadian in-house ship airwake simulation capability combining in-house high-fidelity wind-tunnel tests, full-scale sea trials, high-order computational fluid dynamics (CFD) tools, and realistic engineering-oriented flight simulators. This paper reports challenges and lessons learned during the course of the study, discusses the current capabilities and limitations of the CFD tools and the infrastructure required, and evaluates the gaps and barriers in industry adoption by focusing on how they could be overcome based on our current practice. After validating the CFD results of an updated version of a simplified frigate shape (SFS2) and the real-world Canadian Patrol Frigate (CPF), which are in reasonable agreement with the available in-house wind-tunnel and sea-trial data, the developed approach was recently applied to the design of an undisclosed Canadian ship. Among other applications, CFD airwake results were used with confidence as input to produce representative airwake features in industrial high-fidelity piloted flight simulators.
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Padfield, Gareth D. "The making of helicopter flying qualities: a requirements perspective". Aeronautical Journal 102, nr 1018 (grudzień 1998): 409–37. http://dx.doi.org/10.1017/s0001924000027627.
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AbstractIn this review paper, a recurring theme is the interplay between flying qualities as a technical discipline and flying qualities as an operational attribute. This interplay provides the setting for a presentation on the status of helicopter flying quahties, using maritime helicopter operations as the focus, particularly the recovery phase and the helicopter-ship dynamic interface. Poor weather, inducing high sea states and ship motion, along with complex, invisible and disturbing airflow and degraded visibility, make the dynamic interface a particularly demanding environment for both pilot and helicopter.Flying qualities are a product of four elements — the aircraft, the pilot, the task and the environment — and the maritime application serves to give this viewpoint its full perspective. Mission-oriented flying quahties engineering is described within the systems framework of Aeronautical Design Standard 33 (ADS-33), utilising concepts like the mission task element, usable cue environment, response type and dynamic response criteria. The innovative constructs introduced by ADS-33 for flying qualities in degraded visual conditions are given special attention. The paper argues that the requirements for what constitutes safe and easy, or Level 1, flying qualities now exist and are well substantiated. New aircraft can now be designed to achieve these performance and safety standards while existing aircraft can be upgraded with integrated flight management systems featuring advanced control/flying qualities technologies.In this context, the paper also promotes the concept of concurrent requirements capture and preliminary design, to maximise the likelihood that user requirements are achieved and that designs are robust and work first time. The multidisciplinary nature of flying qualities is emphasised, embracing aeromechanics and flight dynamics, controls and displays and human factors. Similarly, the importance of high-fidelity design tools and comprehensive evaluation methods in the concurrent process is stressed.Handling deficiencies can increase the risk of helicopter accidents, particularly in degraded visual conditions or in emergencies where excursions beyond the operational flight envelope can lead to piloting difficulties. These situations are the new challenges for flying qualities engineers, and two areas are discussed here in some detail. First, flight in severely degraded visual conditions, highlighting the importance of understanding the fundamentals of human visual perception in the development of integrated control and display augmentation. Second, handling qualities following tail rotor failures are discussed and results from current research to develop new advice for aircrew are presented. The author takes the view that much more can and needs to be done to assist the pilot in the management of the tension between performance and safety in helicopter operations, through the provision of improved flying qualities.
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Muksin, Muksin, Udisubakti Ciptomulyono, Sutrisno Sutrisno i Sunarta Sunarta. "THE OPERATIONAL READINESS FOR ANTI SUBMARINE INDONESIAN NAVAL BY USING ANTI SUBMARINE HELICOPTER". JOURNAL ASRO 12, nr 01 (18.01.2021): 166. http://dx.doi.org/10.37875/asro.v12i01.394.
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Some of the Indonesian naval effort to see and protect the Indonesian territory is by using Helicopter sea patrol. In the other side, submarines are the most strategic weapons in the world that can provide a deterrence effect which has a very significant impact on the maritime powers of the countries operating them in the era of generation 4.0 war. Operational readiness is very important, there are readiness in building operational readiness for naval defense through budget fulfillment, utilization of existing resources, procurement and naval modernization by paying attention to Life Cycle Cost, and interoperability while still paying attention to paradigm shifts in naval capability. So, the combat readiness is the condition of the Indonesian Navy's defense equipment and its constituent units, resources and personnel, weapon systems and other military technology equipment in a condition that is ready to carry out military operations in an unspecified time, or function consistent with the purpose for which the defense equipment is organized or designed, the management of resources and training personnel in preparation for combat in the face of the threat of modern warfare in a state of constant combat readiness. At this time, training in Anti-Submarine Warfare conducted by Indonesian Navy’s Helicopter is still limited to carrying out flight procedures, communication procedures with the KRI and the command line, because Helicopters have sensors, weapons and command that need to be upgraded and The personnel also have underwater warfare capabilities that need to be upgraded, so there needs to be an increase in the capability of the helicopter and human resources. Technometry will be used to calculate the Heli's current readiness level.
Keywords: Submarine, Anti Submarine Helicopter and operational readiness
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ZELENSKA, Olena, Olga MARCHENKO, Pavlo ONYPCHENKO i Olena KONDRA. "English training of future helicopters to radio exchange". Scientific Bulletin of Flight Academy. Section: Pedagogical Sciences 10 (2021): 160–68. http://dx.doi.org/10.33251/2522-1477-2021-10-160-168.
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The complex nature of the professional activities of helicopter pilots actualizes a systematic approach to determining their readiness to perform their duties when flying in international airspace. At the same time, participation in peacekeeping operations, rescue expeditions, evacuation of the population makes increased demands on the level of their foreign language training in the higher military educational institution of aviation profile. Aviation English training is specific in terms of purpose, content, proficiency criteria and relevant professional and personal indicators and conditions of use. Given the importance of radio exchange in ensuring trouble-free flight activities, the article analyses the process of English-language preparation of future helicopter pilots for radio exchange at the main stages of the training flight. This training should take place with a gradual increase in the complexity of tasks, the advancement of cadets from learning and reproduction of language structures to independent modelling of professional communication situations. It involves the involvement of such resources of the information and educational environment of higher education institutions as regular classrooms with classrooms and / or interactive whiteboards, language classrooms, training cabins of Mi-2, Mi-8, Mi-24 helicopters, located in specialized classrooms. The most successful place to practice radio communication skills is an aviation simulator, which allows you to practice not only the speech response, but also the motor response to control the helicopter. Intelligence computer simulations of helicopter motion are promising, which creates unique opportunities for creating radio exchange learning situations. At the same time, the study of this issue allowed us to conclude that it is inexpedient in teaching cadets to focus only on standard phraseology of radio exchange, as the latter, although it helps to avoid misunderstandings, is not able to describe all possible circumstances and reactions. Therefore, in cases where the standard phraseology does not "offer any typical forms of verbal communication, pilots and air traffic controllers switch to ordinary English", which raises the issue of enriching the English-speaking arsenal of aviation professionals. Key words: aviation English, helicopter pilot, language tasks, flight situation, professional readiness, radio exchange, phraseology.
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Greenwood, Eric, i Robert Rau. "A Maneuvering Flight Noise Model for Helicopter Mission Planning". Journal of the American Helicopter Society 65, nr 2 (1.04.2020): 1–10. http://dx.doi.org/10.4050/jahs.65.022007.
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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.
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Vascik, Parker D., i R. John Hansman. "Evaluating the Interoperability of Urban Air Mobility Systems and Airports". Transportation Research Record: Journal of the Transportation Research Board 2675, nr 6 (9.02.2021): 1–14. http://dx.doi.org/10.1177/0361198121991501.
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This paper investigates how existing arrival and departure procedures can be directly used or adapted to enable high-volume instrument and visual urban air mobility (UAM) flight operations at major airports in the United States. Viable procedures are restricted to those that enable simultaneous and non-interfering UAM flights with conventional aircraft operations. Air traffic controller workload is proposed as the critical integration barrier to scale UAM operations in visual conditions whereas separation minima, especially for approach procedures, is proposed as the critical barrier in instrument conditions. A systems approach is taken to evaluate potential integration strategies for UAM in which the location of UAM runways or vertipads and flight procedures are presented in a topological framework. The benefits, challenges, and notional application of five integration schemes are discussed. Four promising procedures for UAM are introduced through case studies at three airports. Findings indicate that multiple procedures exist to support high-volume UAM integration at major airports under current regulations with additional controller staffing, especially if UAM aircraft exhibit helicopter-like performance.
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Krueger, Gerald P., Richard N. Armstrong i Ronald R. Cisco. "Aviator performance in week-long extended flight operations in a helicopter simulator". Behavior Research Methods, Instruments, & Computers 17, nr 1 (styczeń 1985): 68–74. http://dx.doi.org/10.3758/bf03200898.
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Memon, Wajih A., Ieuan Owen i Mark D. White. "Motion Fidelity Requirements for Helicopter-Ship Operations in Maritime Rotorcraft Flight Simulators". Journal of Aircraft 56, nr 6 (listopad 2019): 2189–209. http://dx.doi.org/10.2514/1.c035521.
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Żyluk, Andrzej, Mariusz Zieja, Norbert Grzesik, Justyna Tomaszewska, Grzegorz Kozłowski i Michał Jasztal. "Implementation of the Mean Time to Failure Indicator in the Control of the Logistical Support of the Operation Process". Applied Sciences 13, nr 7 (5.04.2023): 4608. http://dx.doi.org/10.3390/app13074608.
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The focus of this paper is to identify a method for defining the needs of logistical operational support based on the mean time to failure (MTTF) factor. The research was based on a helicopter intended for flight training. The MTTF indicator for selected equipment was determined based on failure data from previous flight operations. As the basic operational data for the developed method, the time from the beginning of the operation or the flight time from the last damage and the method of restoring airworthiness were selected. The MTTF and replacement index for the device were determined. The next step was to determine the index, based on selected probability distributions. The results were analyzed and presented in graphical form, and conclusions were drawn. Based on the MTTF index and replacement index, the logistics needs of selected devices were determined. The obtained results were compared with the actual exchanges of devices made in the year in question. The research proved that the MTTF reliability factor and the analysis of trends in value changes could be used to determine the needs for the logistical security of the operation process, particularly in relation to the equipment subject to accidental failures. This is important for maintaining high availability of an aircraft or other technical objects.
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Golub, V., O. Akimov, V. Boyarov, M. Zhdanyuk i R. Kholodnyi. "ASSESSMENT OF THE INFLUENCE OF INDICATORS OF RELIABILITY HELICOPTER SAFETY Ми-8МСБ, Ми-8MT(MTВ) ON SAFETY PERFORMANCE FOR 2017-2021". Наукові праці Державного науково-дослідного інституту випробувань і сертифікації озброєння та військової техніки, nr 12 (5.07.2022): 24–28. http://dx.doi.org/10.37701/dndivsovt.12.2022.03.
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The article offers a complex approach to determination of long-term trends of quantitative indicators of safety of flights of helicopters Mi-8MSB-V and Mi-8MT (MTV) and influence on them of operational reliability.
The integrated approach is to determine the impact of the failure of the functional systems of helicopters on operational reliability and flight safety: average failure rate, mean failure rate, probability of helicopter flight reliability in one hour, Average aircraft accident, probability of absence.
Proposals have been developed to improve the reliability and safety of helicopter flights based on information about the technical condition during military operation, which will allow adjusting the terms of maintenance, repair, extending the service life and provide for areas for upgrading aviation equipment.
In order to take into account objectively the impact of helicopter systems on the reliability and safety of aircraft equipment flights, information on the flight hours of aircraft equipment should be provided, taking into account the level of functional systems upgrade. Recommendations for improving flight safety and reliability of elements of helicopter systems limiting the reliability of aviation equipment are given.
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Wang, Jialiang, Hai Zhao, Yuanguo Bi, Xingchi Chen, Ruofan Zeng i Shiliang Shao. "Quad-Rotor Helicopter Autonomous Navigation Based on Vanishing Point Algorithm". Journal of Applied Mathematics 2014 (2014): 1–12. http://dx.doi.org/10.1155/2014/567057.
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Quad-rotor helicopter is becoming popular increasingly as they can well implement many flight missions in more challenging environments, with lower risk of damaging itself and its surroundings. They are employed in many applications, from military operations to civilian tasks. Quad-rotor helicopter autonomous navigation based on the vanishing point fast estimation (VPFE) algorithm using clustering principle is implemented in this paper. For images collected by the camera of quad-rotor helicopter, the system executes the process of preprocessing of image, deleting noise interference, edge extracting using Canny operator, and extracting straight lines by randomized hough transformation (RHT) method. Then system obtains the position of vanishing point and regards it as destination point and finally controls the autonomous navigation of the quad-rotor helicopter by continuous modification according to the calculated navigation error. The experimental results show that the quad-rotor helicopter can implement the destination navigation well in the indoor environment.
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Minasov, V., L. Kinderknekht i M. Smolyanyi. "ACTIONS OF THE ARMY AVIATION DURING THE RAIDBY THE AIR ASSAULT FORCES’ UNITS". Collection of scientific works of Odesa Military Academy 2, nr 12 (27.12.2019): 66–72. http://dx.doi.org/10.37129/2313-7509.2019.12.2.66-72.
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The article analyzes the foreign and domestic experience of combat use of Army Aviation Helicopters (AA) in modern wars and local conflicts when conducting raid operations by the units of Air Assault (Airmobile) forces, as well as the experience of transfer of the Air Assault Forces by helicopters in time of action. During a raid, air assault battalion can use combat helicopters. In this case, helicopter ambushes are most expedient to use in the ways of raising the nearest enemy reserves and in case of the enemy's mobile objects to strike suddenly, using various tactical techniques. The use of ambushes will be most effective in the area, which provides the secretive action of helicopters and the selection of enough quantity of fields. The use of Army aviation allows the airborne assault units to be transferred during a raid. Helicopters must fly at extremely low altitudes using terrain masking, individual and group means of EW. Exit of helicopters at the landing field of the air assault force is carried out suddenly and accurately in relation to place and time. AA units are widely used to evacuate units. Transport and combat helicopters provide for the admission on board and transportation of personnel, weapons, documents; conducting intelligence. At the same time combat helicopters perform the task of destroying air defense on the flight route; concealment of AA combat order from possible attacks by enemy helicopters in the air; landing and take-off of transport and combat helicopter. Commanders of air assault units must be aware of the tactics of combat, transport-combat and transport helicopters and their tactical characteristics, which will significantly improve the effectiveness of the raid and be able to apply it during the raid.