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Artykuły w czasopismach na temat "Helicopter flight operations"
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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.
Pełny tekst źródłaStreszczenie:
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.
Rozprawy doktorskie na temat "Helicopter flight operations"
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Lentz, Frederick Charles. "Integration of ASW helicopter operations and environment into NPSNET". Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1995. http://handle.dtic.mil/100.2/ADA304302.
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Thesis (M.S. in Computer Science) Naval Postgraduate School, September 1995."September 1995." Thesis advisor(s): Michael J. Zyda, John S. Falby. Includes bibliographical references (p. 107). Also available online.
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Ngo, Tri Dinh. "Constrained Control for Helicopter Shipboard Operations and Moored Ocean Current Turbine Flight Control". Diss., Virginia Tech, 2016. http://hdl.handle.net/10919/71685.
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This dissertation focuses on constrained control of two applications: helicopter and ocean current turbines (OCT).
A major contribution in the helicopter application is a novel model predictive control (MPC) framework for helicopter shipboard operations in high demanding sea-based conditions. A complex helicopter-ship dynamics interface has been developed as a system of implicit nonlinear ordinary differential equations to capture essential characteristics of the nonlinear helicopter dynamics, the ship dynamics, and the ship airwake interactions. Various airwake models such as Control Equivalent Turbulence Inputs (CETI) model and Computation Fluid Dynamics (CFD) data of the airwake are incorporated in the interface to describe a realistic model of the shipborne helicopter. The feasibility of the MPC design is investigated using two case studies: automatic deck landing during the ship quiescent period in sea state 5, and lateral reposition toward the ship in different wind-over-deck conditions. To improve the overall MPC performance, an updating scheme for the internal model of the MPC is proposed using linearization around operating points. A mixed-integer MPC algorithm is also developed for helicopter precision landing on moving decks. The performance of this control structure is evaluated via numerical simulations of the automatic deck landing in adverse conditions such as landing on up-stroke, and down-stroke moving decks with high energy indices. Kino-dynamic motion planning for coordinated maneuvers to satisfy the helicopter-ship rendezvous conditions is implemented via mixed integer quadratic programming.
In the OCT application, the major contribution is that a new idea is leveraged from helicopter blade control by introducing cyclic blade pitch control in OCT. A minimum energy, constrained control method, namely Output Variance Constrained (OVC) control is studied for OCT flight control in the presence of external disturbances. The minimum achievable output variance bounds are also computed and a parametric study of design parameters is conducted to evaluate their influence on the OVC performance. The performance of the OVC control method is evaluated both on the linear and nonlinear OCT models. Furthermore, control design for the OCT with sensor failures is also examined. Lastly, the MPC strategy is also investigated to improve the OCT flight control performance in simultaneous satisfaction of multiple constraints and to avoid blade stall.Ph. D.
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Shafer, Daniel Manfred. "Active and Passive Flow Control over the Flight Deck of Small Naval Vessels". Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/32427.
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Helicopter operations in the vicinity of small naval surface vessels often require excessive pilot workload. Because of the unsteady flow field and large mean velocity gradients, the envelope for flight operations is limited. This experimental investigation uses a 1:144 scale model of the U.S. Navy destroyer DDG-81 to explore the problem. Both active and passive flow control techniques were used to improve the flow field in the helicopterâ s final decent onto the flight deck. Wind tunnel data was collected at a set of grid points over the shipâ s flight deck using a single component hotwire. Results show that the use of porous surfaces decreases the unsteadiness of the flow field. Further improvements are found by injecting air through these porous surfaces, causing a reduction in unsteadiness in the landing region of 6.6% at 0 degrees wind-over-deck (WOD) and 8.3% at 20 degrees WOD. Other passive configurations tested include fences placed around the hangar deck edges which move the unsteady shear layer away from the flight deck. Although these devices cause an increase in unsteadiness downstream of the edge of the fence when compared to the baseline, the reticulated foam fence caused an overall decrease in unsteadiness in the landing region of 12.1% at 20 degrees WOD.Master of Science
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Pereira, Figueira José Márcio. "The use of offline simulation tools to estimate ship-helicopter operating limitations". Thesis, Aix-Marseille, 2017. http://www.theses.fr/2017AIXM0511/document.
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Les limitations d’atterrissage des hélicoptères ne sont pas valables dans l'environnement à bord d’un navire. Il n'existe aucune méthodologie approuvée de l'analyse ou de la simulation pour évaluer la compatibilité des hélicoptères-navires et préparer les essais de qualification hélicoptères-navires. Dans ce contexte, le présent travail présente le développement et l'analyse d'une méthodologie hors ligne pour déterminer les limites opérationnelles hélicoptères-navires, SHOLs, en fonction des prédictions d’un modèle de pilote humain. Pour cela, des essais pilotés par des humains sont effectués au simulateur de l’ONERA, Salon de Provence. Sur la base des résultats de ces tests, une méthodologie innovante est validée pour déterminer la limitation de la charge de travail de pilotage, à partir des mesures des déplacements des contrôles d'hélicoptère. En outre, sont validés des modifications innovantes sur un modèle de pilote humain pour pouvoir suivre les trajectoires souhaitées et fournir le même niveau d'activité aux contrôles qu'un véritable pilote. Un ensemble de critères objectifs, correspondant aux marges de sécurité, s'ajoute aux critères subjectifs, correspondant aux limitations de la charge de travail du pilote. Une routine de simulation hors ligne, appelée SholSim, est programmée pour réaliser des simulations avec le modèle pilote et vérifier l'acceptabilité des conditions de vol, selon les critères subjectifs et objectifs. Par conséquent, le présent travail présente la première estimation, dans la littérature, des SHOLs entièrement obtenus à partir d'outils hors ligne, basés uniquement sur les prédictions de modèle piloteHelicopter land-based limitations are not valid in the shipboard environment. There is no analytical or simulated approved methodology for evaluating shipboard helicopter compatibility issues and preparing for at-sea flight tests. In this context, the present work presents the development and analysis of an offline methodology to determine the Ship-Helicopter Operating Limitations, SHOLs, based on pilot model predictions. For this, pilot-in-the-loop simulation trials are performed at the engineering fixed-base simulation facility of ONERA, Salon de Provence. Based on these test results, an innovative methodology is proposed and validated to determine the safe pilot workload limitation, from the measurements of the helicopter control displacements. In addition, it is proposed and validated innovative modifications on a classical pilot model enabling to follow complex predefined desired trajectories and provide the same level of control activity of a real pilot. A set of objective criteria, corresponding to the safety margins, is established in addition to the subjective criteria, corresponding to the safe pilot workload limitations. An offline simulation routine, so-called SholSim, is coded to run all models and verify the acceptability of the flight conditions, according to the subjective and objective criteria. Therefore, the present work presents the first estimation, in the literature, of the SHOLs fully obtained from offline tools, based only on pilot model predictions. The proposed methodology is promising, confirmed by predicting coherent limits when compared to the ones defined by the pilot-in-the-loop simulation trials
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DERE, Ahmet Murat. "Flight regime recognition analysis for the army UH-60A IMDS usage". Thesis, Monterey, California. Naval Postgraduate School, 2006. http://hdl.handle.net/10945/2510.
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Approved for public release; distribution is unlimitedUsage Monitoring requires accurate regime recognition. For each regime, there is a usage assigned for each component. For example, the damage accumulated at a component is higher if the aircraft is undergoing a high G maneuver than in level flight. The objective of this research is to establish regime recognition models using classification algorithms. The data used in the analysis are the parametric data collected by the onboard system and the actual data, consisting of the correct regime collected from the flight cards. This study uses Rpart (with a tree output) and C5.0 (with a ruleset output) to establish two different models. Before model fitting, the data was divided into smaller datasets that represent regime families by subsetting using important flight parameters. Nonnormal tolerance intervals are constructed on the uninteresting values; then these values in the interval are set to zero to be muted (e.g. excluded). These processes help reduce the effect of noise on classification. The final models had correct classification rates over 95%. The number of bad misclassifications were minimized (e.g. the number of bad misclassifications of a level flight regime as a hover regime was minimized), but the models were not as powerful in classifying the low-speed regimes as in classifying high-speed regimes.
Outstanding Thesis
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Forrest, James Stephen. "Predicting ship-helicopter operating limits using time-accurate CFD ship airwakes and piloted flight simulation". Thesis, University of Liverpool, 2009. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.526869.
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Johnson, Kevin Lee. "Prediction of operational envelope maneuverability effects on rotorcraft design". Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/47601.
Pełny tekst źródłaStreszczenie:
Military helicopter operations require precise maneuverability characteristics for performance to be determined for the entire helicopter flight envelope. Historically, these maneuverability analyses are combinatorial in nature and involve human-interaction, which hinders their integration into conceptual design. A model formulation that includes the necessary quantitative measures and captures the impact of changing requirements real-time is presented. The formulation is shown to offer a more conservative estimate of maneuverability than traditional energy-based formulations through quantitative analysis of a typical pop-up maneuver. Although the control system design is not directly integrated, two control constraint measures are deemed essential in this work: control deflection rate and trajectory divergence rate. Both of these measures are general enough to be applied to any control architecture, while at the same time enable quantitative trades that relate overall vehicle maneuverability to control system requirements. The dimensionality issues stemming from the immense maneuver space are mitigated through systematic development of a maneuver taxonomy that enables the operational envelope to be decomposed into a minimal set of fundamental maneuvers. The taxonomy approach is applied to a helicopter canonical example that requires maneuverability and design to be assessed simultaneously. The end result is a methodology that enables the impact of design choices on maneuverability to be assessed for the entire helicopter operational envelope, while enabling constraints from control system design to be assessed real-time.
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Revor, Mark S. "An analysis of the integrated mechanical diagnostics health and usage management system on rotor track and balance". Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2004. http://library.nps.navy.mil/uhtbin/hyperion/04Jun%5FRevor.pdf.
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Thesis (M.S. in Operations Research)--Naval Postgraduate School, June 2004.Thesis advisor(s): Lyn R. Whitaker, Arnold H. Buss. Includes bibliographical references (p. 77-78). Also available online.
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Unnikrishnan, Suraj. "Adaptive Envelope Protection Methods for Aircraft". Diss., Georgia Institute of Technology, 2006. http://hdl.handle.net/1853/11478.
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Carefree handling refers to the ability of a pilot to operate an aircraft without the need to continuously monitor aircraft operating limits. At the heart of all carefree handling or maneuvering systems, also referred to as envelope protection systems, are algorithms and methods for predicting future limit violations. Recently, envelope protection methods that have gained more acceptance, translate limit proximity information to its equivalent in the control channel. Envelope protection algorithms either use very small prediction horizon or are static methods with no capability to adapt to changes in system configurations. Adaptive approaches maximizing prediction horizon such as dynamic trim, are only applicable to steady-state-response critical limit parameters. In this thesis, a new adaptive envelope protection method is developed that is applicable to steady-state and transient response critical limit parameters. The approach is based upon devising the most aggressive optimal control profile to the limit boundary and using it to compute control limits. Pilot-in-the-loop evaluations of the proposed approach are conducted at the Georgia Tech Carefree Maneuver lab for transient longitudinal hub moment limit protection. Carefree maneuvering is the dual of carefree handling in the realm of autonomous Uninhabited Aerial Vehicles (UAVs). Designing a flight control system to fully and effectively utilize the operational flight envelope is very difficult. With the increasing role and demands for extreme maneuverability there is a need for developing envelope protection methods for autonomous UAVs. In this thesis, a full-authority automatic envelope protection method is proposed for limit protection in UAVs. The approach uses adaptive estimate of limit parameter dynamics and finite-time horizon predictions to detect impending limit boundary violations. Limit violations are prevented by treating the limit boundary as an obstacle and by correcting nominal control/command inputs to track a limit parameter safe-response profile near the limit boundary. The method is evaluated using software-in-the-loop and flight evaluations on the Georgia Tech unmanned rotorcraft platform- GTMax. The thesis also develops and evaluates an extension for calculating control margins based on restricting limit parameter response aggressiveness near the limit boundary.
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Praveen, B. "Study of the ship airwake-helodeck flow field for safe helo operations". Thesis, 2018. http://localhost:8080/xmlui/handle/12345678/7776.
Pełny tekst źródłaKsiążki na temat "Helicopter flight operations"
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Dale, Ryan. Helicopter maneuvers manual: Step-by-step guide to performing all helicopter flight operations. Newcastle, Wash: Aviation Supplies & Academics, Inc., 2011.
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Graham, H. D. Vietnam helicopter crew member stories. [Bloomington, Indiana]: Xlibris Corporation, 2012.
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Center, Ames Research, i United States. National Aeronautics and Space Administration., red. Flight testing and real-time system identification analysis of a UH-60A Black Hawk helicopter with an instrumented external sling load. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1998.
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Get the bloody job done: The Royal Australian Navy Helicopter Flight-Vietnam and the 135th Assault Helicopter Company 1967-1971. St Leonards, NSW: Allen & Unwin, 1998.
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G, Cooper Eric, Society of Automotive Engineers i United States. National Aeronautics and Space Administration., red. Support of helicopter "free-flight" operations in the 1996 olympics: 1996 World Aviation Congress, October 21-24, 1996, Los Angeles, CA. Warrendale, PA: SAE International, 1997.
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N, Swenson Harry, i Ames Research Center, red. Design and flight evaluation of an integrated navigation and near-terrain helicopter guidance system for night-time and adverse weather operations. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.
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G, Cooper Eric, Society of Automotive Engineers i United States. National Aeronautics and Space Administration., red. Support of helicopter "free-flight" operations in the 1996 olympics: 1996 World Aviation Congress, October 21-24, 1996, Los Angeles, CA. Warrendale, PA: SAE International, 1997.
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Kawa, Myron Michael. Program and operational highlights of the armed OH-58D Kiowa Warrior: Presented in the military operations session at the 46th Annual Forum and Technology Display of the American Helicopter Society, "Technology 21, vertical flight for the 21st century, Washington, DC, May, 1990. Alexandria, VA: American Helicopter Society, 1990.
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Yoshikami, Sharon A. Flight operations: Noise tests of eight helicopters. [Washington, DC]: U.S. Dept. of Transportation, Federal Aviation Administration, 1985.
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Visel, James W. Devotions For Boots on the Ground: "Are You There, God? ". USA: WestBow Press, 2011.
Znajdź pełny tekst źródłaCzęści książek na temat "Helicopter flight operations"
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Wipf, Heinz. "Safety Versus Security in Aviation". W The Coupling of Safety and Security, 29–41. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-47229-0_4.
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Abstract The two domains safety and security have traditionally been kept separated in aviation. While the first treats risks associated with aviation activities, the latter safeguards civil aviation against acts of unlawful interference. While national and international guidelines exist in addressing the installation of risk management for organizations having hazardous operations in aviation, an appropriate application of established assessment techniques, both quantitative and qualitative are crucial to both domains. For an incorrect hazard identification and the quantification of an adverse outcome may strongly affect both the level of protection and the investments required to reach it. The empirical example and data shown stem from safety risk assessments in HEMS (helicopter emergency medical service) flight operations. These flight operations use advanced instrument flight procedures in obstacle rich environments under low visibility conditions and are therefore a safety concern on the one hand. On the other hand, one analyzes security, whenever HEMS flights are operated in adverse weather conditions, having as a sole navigation source signals from a global navigation satellite constellation. A traditional safety risk assessment (Wipf in Aviation risk and safety management, Springer, p 108, 1) under these circumstances, considers only factors of human performance under technical failure conditions. A security analysis, however, should treat all forms of jamming, meaconing, and spoofing of the satellite signals and the adverse impact on the performance of the receiver to calculate a valid position. The chapter illustrates to which extent commonalities reign in both domains and where practices go separate ways.
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Kim, Se-Gi, Seung-Hwa Song, Chun-Hyon Chang, Doo-Hyun Kim, Shin Heu i JungGuk Kim. "Design and Implementation of an Operational Flight Program for an Unmanned Helicopter FCC Based on the TMO Scheme". W Software Technologies for Embedded and Ubiquitous Systems, 1–11. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-642-10265-3_1.
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Cook, Matthew, i John P. T. Mo. "Enterprise Approach to Modelling of Risks in the Project Lifecycle of Naval Aviation Asset Ship Integration". W Advances in Transdisciplinary Engineering. IOS Press, 2019. http://dx.doi.org/10.3233/atde190148.
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A strategic capability of contemporary naval ships is the ability to launch and recover embarked aircraft such as helicopters in a maritime environment. Such operations are enormously challenging due to deck motion, limited landing space, visibility, ship’s superstructure, etc. This places extreme pressure on the pilot, ship’s crew and the platforms alike, making such shipboard operations the most dangerous of all helicopter flight missions. Therefore, the design and integration of equipment, systems and aids to ensure such operations are done as safely as is practicably possible, presents ship builders, aircraft manufacturers, engineers and pilots with some extremely demanding and complex problems. Major naval ship design/build programmes that include an aviation capability, will inevitably need to engage resources across multiple disciplines that include, but not limited to; engineering, design, logistics, administration, procurement, legal, alliance partners and the customer to manage project risks from the outset. This research highlights the need for a holistic/Systems Engineering approach that recognises risks across the wider ship programme, that can only be managed/resolved by cross-discipline collaboration. This paper presents a novel methodology to elicit risks qualitatively and models the relative risk profile of an aviation project throughout the ship programme lifecycle. The use of an enterprise model based on the three ‘P’ element methodology (3PE): Product, Process, People within an environment has been developed. Furthermore, the research outlines a continuous management and visualisation approach that enables a process of dynamic analysis to both reduce and/or mitigate residual risks progressively throughout the project lifecycle to acceptable levels.
Streszczenia konferencji na temat "Helicopter flight operations"
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Green, David, Dr Harrison, Dr Bayoumi i Hamid Nouri. "An Innovative Approach for Establishing Power Train Inspection Intervals of Modern Helicopters". W Vertical Flight Society 75th Annual Forum & Technology Display. The Vertical Flight Society, 2019. http://dx.doi.org/10.4050/f-0075-2019-14654.
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Modern transmissions are the product of years of development. The newest materials and software are typically used to design helicopter power trains that are expected to safely endure operations traditionally characterized as representing composite worst-case usage, a level of usage severity that is well above the limits established in the OEM flight manual. In addition, the introduction of Helicopter Flight Data Monitoring programs has systematically constrained the actual usage to a level of severity that is substantially below that allowed by the OEM flight manual. Validation projects have enabled experience to be accumulated with a variety of helicopters and this has demonstrated that many helicopters are currently operating in a way that is best described as involving benign usage. This is partially because the assemblies are so robust and partially because some helicopter usage is systematically constrained to the flight profiles that are actually needed to accomplish the missions. This paper finds that a significant portion of most modern helicopter fleets actually experience benign usage. This finding supports the conclusion that helicopter OEMs can and should provide operators with the option to choose either the traditional inspection intervals for unmonitored operations or choose a set of longer supplemental inspection intervals for helicopters involved in monitored flight operations.
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Chin, Hsiang-Jui, Charles Johnson, Dimitri Mavris i Alexia Payan. "Anomaly Detection in Initial Climb Segments for Helicopter Operations". W Vertical Flight Society 77th Annual Forum & Technology Display. The Vertical Flight Society, 2021. http://dx.doi.org/10.4050/f-0077-2021-16852.
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Helicopters are used in a variety of operations and recent studies show that the number of accidents associated with helicopters is stagnating, if not increasing. Flight data monitoring (FDM) is a useful tool to review the data retrospectively for risk mitigation. Exceedance analyses are typically used in FDM for anomaly detection. However, they typically rely on pre-defined thresholds which might vary depending on the type of operations or vehicles considered. With recent advancements in data mining techniques, many efforts have been put into anomaly detection in the commercial fixed-wing aviation and this provides a new perspective beyond traditional methods. In this research, a sequential approach is proposed to detect anomalies in initial climb segments for helicopter operations. The stepwise methodology contains three elements: trajectory pattern mining, time series length analysis, and shape analysis for identifying different levels of anomalies. To ensure the effectiveness of the methods selected, synthetic and simulated data are used for testing before applying candidate methods to the actual initial climb segments. A specific group of initial climb segments is used to demonstrate the validity of the methods chosen in this study. Our tests show that functional principal component analysis and a convolutional variational autoencoder along with DBSCAN are capable of identifying shape anomalies in flight parameters. Although the detected anomalies might not directly be associated with hazardous events, it is useful to assist helicopter operators in discovering patterns not conforming to the norms.
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Kuo, Brian C., Wen-lin Guan, Pei-chung Chen, Fu-yuen Hsiao i Feng-yu Chang. "Helicopter Lightweight Flight Recorder Image Analysis for Flight Data Monitoring Purpose". W 2018 Aviation Technology, Integration, and Operations Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3051.
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Goulos, Ioannis, Panos Giannakakis, Vassilios Pachidis i Pericles Pilidis. "Mission Performance Simulation of Integrated Helicopter–Engine Systems Using an Aeroelastic Rotor Model". W ASME Turbo Expo 2013: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/gt2013-94798.
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This paper presents an integrated approach, targeting the comprehensive assessment of combined helicopter–engine designs, within designated operations. The developed methodology comprises a series of individual modeling theories, each applicable to a different aspect of helicopter flight dynamics and performance. These relate to rotor blade modal analysis, three-dimensional flight path definition, flight dynamics trim solution, aeroelasticity and engine performance. The individual mathematical models are elaborately integrated within a numerical procedure, solving for the total mission fuel consumption. The overall simulation framework is applied to the performance analysis of the Aérospatiale SA330 helicopter within two generic, twin-engine medium helicopter missions. An extensive comparison with flight test data on main rotor trim controls, power requirements and unsteady blade structural loads is presented. It is shown that, for the typical range of operating conditions encountered by modern twin-engine medium civil helicopters, the effect of operational altitude on fuel consumption is predominantly influenced by the corresponding effects induced on the engine, rather than on airframe–rotor performance. The implications associated with the implicit coupling between aircraft and engine performance, are discussed in the context of mission analysis. The potential to comprehensively evaluate integrated helicopter–engine systems within complete three-dimensional operations, using modeling fidelity designated for main rotor design applications, is demonstrated. The proposed method essentially constitutes an enabler in terms of focusing the rotorcraft design process on designated operation types, rather than on specific sets of flight conditions.
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Lee, Dooyong, Joseph Horn, Nilay Sezer-Uzol i Lyle Long. "Simulation of Pilot Control Activity During Helicopter Shipboard Operations". W AIAA Atmospheric Flight Mechanics Conference and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-5306.
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Payan, Alexia P., Po-Nien Lin, Charles Johnson i Dimitri N. Mavris. "Helicopter Approach Stability Analysis Using Flight Data Records". W 17th AIAA Aviation Technology, Integration, and Operations Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-3437.
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Taymourtash, Neda, Giuseppe Gibertini, Giuseppe Quaranta i Alex Zanotti. "Experimental Investigation of Unsteady Inflow for a Helicopter Model in Shipboard Operations". W Vertical Flight Society 77th Annual Forum & Technology Display. The Vertical Flight Society, 2021. http://dx.doi.org/10.4050/f-0077-2021-16840.
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State-space representation of the dynamic inflow is an essential element in rotorcraft flight mechanics modeling and simulation. Identification of a reliable low-order model which is able to predict the transient response of the inflow as well as the steady part, becomes even more important during the maneuvering flights. The objective of this paper is to exploit an experimental setup, consists of a helicopter model and a simplified ship geometry, to investigate the possible effect of the wake interactions with environmental elements such as ground effect or airwake of the ship, on the time constants associated with the buildup of the inflow states. A series of wind tunnel tests were performed, simulating various flight conditions, including hover and forward flight, inside and outside of the ground effect, and the rotor over the deck of the SFS1 at two different positions with respect to the ship super-structure, with the wind coming from two different directions. After trimming the rotor at each flight condition, a sequence of pitch excitation commands were applied to the collective, lateral and longitudinal cyclic in order to excite the induced flow of the rotor. The frequency analysis of the measured aerodynamic loads shows the variation of the time lag, while rotor is operating in the same trim condition, but different positions with respect to the ground or the flight deck.
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Oltheten, Erik. "Restoring Practical Single Engine IFR to the Marketplace". W Vertical Flight Society 76th Annual Forum & Technology Display. The Vertical Flight Society, 2020. http://dx.doi.org/10.4050/f-0076-2020-16343.
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Attempting to pick through bad weather - becoming disoriented in diminished visibility or striking a wire or obstacle at low altitude - remains one of the major causes of fatal helicopter accidents. It is more common than engine failure, more common than mechanical failures, and more common than systems failures. While some feel the answer involves more tools to enable low-flying helicopters to avoid terrain and obstacles, a better solution is to keep helicopters safely away from terrain and obstacles using instrument flight rules (IFR) when weather conditions demand. For single engine helicopters, which form the largest population of helicopters, this means finding cost effective ways to provide them with safe and practical IFR capability. IFR capability is commonplace in airplanes, even among entry-level and training aircraft. An IFR rating is typically the first rating sought after an airplane pilot receives their license. For helicopters, there is currently not a parallel culture of shifting to the safety of IFR operations when weather demands. The reasons are complex, but a significant factor affecting this culture today is that the entryl evel IFR rotorcraft is generally a twin-turbine-engine helicopter. By the time a helicopter pilot gets to this level of machine, he or she is typically well versed in the "alternate" methods of weather avoidance. Unfortunately, even IFR rated helicopter pilots tend to default to a practice of attempting to fly below the weather using visual flight rules (VFR). Increasing the availability of IFR-capable helicopters by restoring practical, low-cost IFR solutions to single engine rotorcraft is the first step in a process intended to change the rotorcraft safety culture. This paper describes a 5-year effort by associations, industry, and regulators to remove the obstacles to certifying low-cost IFR helicopters. By mid-year 2019, two single-engine helicopters were certified for IFR operations, ending an absence of more than 20 years from the marketplace, but these were newly-manufactured aircraft. The remaining challenge is to apply what has been done in order to allow cost-effective retrofits of IFR capability to the existing fleet of VFR helicopters. The hope is that, with the trail now blazed, others will follow, and we will see even more single-engine rotorcraft with IFR capability and fewer weather-related accidents.
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Li, Sicheng, i Seongkyu Lee. "Acoustics Analysis of a Quiet Helicopter for Air Taxi Operations". W Vertical Flight Society 77th Annual Forum & Technology Display. The Vertical Flight Society, 2021. http://dx.doi.org/10.4050/f-0077-2021-16694.
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This paper investigates tonal noise and broadband noise for rotor designs used on urban air mobility vehicles. The rotor aerodynamics in edge-wise forward flight is calculated using the blade element theory, coupled with a dynamic inflow model and the moment-balance trim analysis. Loading noise and thickness noise are obtained using the lifting-line loading distribution and the dual-compact thickness noise model in PSU-WOPWOP.With the forward flight capability developed in UCD-QuietFly, broadband noise is obtained, including trailing-edge noise, trailing-edge bluntness noise, and airfoil stall noise. The air taxi designs, with varied tip speeds and the same mission specifications, are studied for their tonal noise and broadband noise. First, it is found that broadband noise is the dominant noise source for the rotor designs with low tip speeds and fewer blades, while tonal noise is dominant for the high-tip-speed designs. Second, for human hearing, A-weighting maintains the importance of broadband noise while reduces tonal noise significantly. Third, broadband noise is the dominant noise source for the rotor out-of-plane observers, while tonal noise is dominant for the in-plane observers. Fourth, both tonal noise and broadband noise increase proportionally with increasing the forward speed. Finally, low tip speed and more blades are found to be the preferable design features in terms of psychoacoustic metrics.
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Paul, Brent S. "Numerical Analysis of the LCS 2 airwake to understand potential interactions during helipcopter operations". W SNAME 5th World Maritime Technology Conference. SNAME, 2015. http://dx.doi.org/10.5957/wmtc-2015-104.
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The successful integration of aviation capabilities aboard ships is a complex endeavor that must balance ship design with the flight envelope of the helicopter. This can be particularly important when considering air wakes and other flow around the superstructure as it impacts the flight deck. This flow can generate unsteady structures that may interfere with safe helicopter operations. Computational fluid dynamics (CFD) is commonly used to characterize the flow field and assess potential impacts to the flight envelope, which can be used to help define an operating envelope for helicopter operations.