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Littérature scientifique sur le sujet « Experimental flight »

Auteur : Grafiati

Publié le 1 février 2025

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Articles de revues sur le sujet "Experimental flight"

Gururajan, Srikanth, et Ye Bai. « Autonomous “Figure-8” Flights of a Quadcopter : Experimental Datasets ». Data 4, n^o 1 (9 mars 2019) : 39. http://dx.doi.org/10.3390/data4010039.

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This article describes the data acquired from multiple flights of a custom-built quadcopter. The Quadcopter was programmed to fly a pre-defined “Figure-8” flight path, at a constant altitude. The data set includes flights with a varying number of waypoints (10 and 15 waypoints in each lobe of the “Figure-8”) and at two different velocities (1.5 and 2.5 m/s). The data also contains information on the output of the flight controller in terms of the Pulse Width Modulation (PWM) signals to each of the four Electronic Speed Controllers (ESC) driving the motors, the recorded outputs of the Inertial Measurement Unit (linear accelerations ax, ay, az and angular velocities p, q, r), GPS data (Latitude, Longitude, altitude, Horizontal Dilution of Precision (HDOP) and Vertical Dilution of Precision (VDOP). The data are included as Supplemental Material.

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Caprace, Denis-Gabriel, Camille Gontier, Mohammad Iranmanesh, Mehdi Scoubeau et Vladimir Pletser. « Experimental Characterization of Weightlessness During Glider Parabolic Flights ». Microgravity Science and Technology 32, n^o 6 (10 octobre 2020) : 1121–32. http://dx.doi.org/10.1007/s12217-020-09836-6.

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Abstract Access to earthbound weightlessness is critical to many branches of applied sciences. Besides, several space systems require microgravity testing before their launch. Existing solutions (drop towers, parabolic flights, sounding rockets) offer variable durations and qualities of microgravity environment, but their cost and lead times make them unpractical for small actors such as universities or start-up companies. This leads to a growing interest for alternative microgravity platforms. Here, we study the use of gliders to perform parabolic flights at a lower cost, and we propose a systematic quantification of glider’s 0-g flight capabilities. Results of our flight test campaign show that gliders offer up to 5.5s of weightlessness, with excursions below 0.1g, and a satisfactory level of repeatability. Besides, the recordings do not suffer from the increased level of vibrations generated by piston engines, typical of light-aircraft-based alternatives. Operational considerations associated with glider parabolic flights are also discussed. Finally, we conclude that a microgravity platform based on gliders would be suitable especially for compact experiments and equipment in order to support accelerated design and development, or to produce preliminary experimental results.

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Beh, Helen C., et Peter McLaughlin. « Effect of Long Flights on the Cognitive Performance of Air Crew ». Perceptual and Motor Skills 84, n^o 1 (février 1997) : 319–22. http://dx.doi.org/10.2466/pms.1997.84.1.319.

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The cognitive performance of groups of subjects was tested after flights lasting between 7.5–9.5 hours to the north, east and west of Sydney ( ns = 10, 12, and 12) and compared with the performance of a ground-based control group ( n = 12). Analysis showed an impairment in performance of the flight groups following the flights. The analysis suggests that part of the performance change following transzonal flights may result from stress induced during the flight rather than adjustment to new time zones.

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Pang, Liping, Pei Li, Xiaodong Cao et Xiaoru Wanyan. « Experimental study of the changes in thermal expectation during simulated flights in a civil aircraft cabin mockup ». Indoor and Built Environment 29, n^o 9 (18 mai 2020) : 1277–88. http://dx.doi.org/10.1177/1420326x20925113.

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Aircraft cabin thermal environment is a key issue on flight selection by passengers, especially for long-haul flights. Currently, there have been some studies on the passengers’ thermal comfort in civil aircraft cabins. However, information is still limited on the changes in passenger thermal expectation with flight time. In this study, an aircraft cabin mockup was built, and three experiments involving human subjects were carried out in order to study the in-flight thermal environment in winter, summer and autumn, respectively. The cabin temperatures during the experiments were controlled according to the thermal neutral temperature model derived from our previous study on actual flights. The thermal neutral temperature model was checked by experimental results. The changes in thermal expectation were investigated based on physical measurement and questionnaire survey. In each experiment, the changes in the mean thermal sensation votes of passengers were less than 1, while the cabin temperature increased by 2.8°C, 1.8°C and 2°C from the beginning to the end during the three experiments, respectively. With the increase in the simulated flight time, passengers gradually expected a slightly higher cabin temperature. This trend would become very obvious when the simulated flight time was longer than 2 h.

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Shao, Quan, Mengxue Shao, Yunpeng Bin, Pei Zhu et Yan Zhou. « Flight Recovery Method of Regional Multiairport Based on Risk Control Model ». Mathematical Problems in Engineering 2020 (29 avril 2020) : 1–18. http://dx.doi.org/10.1155/2020/7105381.

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In the regional multiairport system, the contradiction between the limited operating resources and the large flight flow is serious, and the flight delays can easily lead to the occurrence of unsafe events. This paper investigates the abnormal flight recovery method in regional multiairport system based on risk control. The focus is to reschedule arrival-departure flights in real time with minimized delay time and risk probability. In this study, the risk about terminal area control and scene operation was considered in the analysis of the risk control model (RCM), which includes six key risk points: airspace control, flight conflict, ground service, apron support, ground control, and taxiing conflict. The mathematical model on flight recovery was constructed to solve minimized delay time and risk probability with MSINS (multistart algorithm with intelligent neighborhood selection). The data of a typical regional multiairport system in China were selected for experimental verification in order to compare the RCM with the traditional recovery model (TRM). The experimental results show that first, there are some hidden dangers in the traditional recovery methods of flight delay. Flight conflict and apron support are the risk points that need to be controlled most in the multiairport system. Secondly, for the effective solution with the shortest delay time, the RCM can reduce the overall operation risk of the system, but the flight delay time is a little longer. For the effective solution with the lowest risk probability, RCM can reduce the risk of system operation and the delay time of flights at the same time. Therefore, RCM can improve the security level of the system during abnormal flight recovery and ensure or even improve the recovery efficiency.

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Muravyov, I. S. « Method of training pilots of the latest-generation aircraft to interact with crews of other aircraft ». Civil Aviation High Technologies 26, n^o 5 (30 octobre 2023) : 42–52. http://dx.doi.org/10.26467/2079-0619-2023-26-5-42-52.

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Training pilots of latest-generation aircraft to interact with other crews in flight is complicated by the high level of cockpit automation and information overload of crews, on the one hand, and by the responsibility of pilots for decisions made regarding air traffic, on the other hand. Since the unified methodology for training pilots to interact with other crews in the same airspace is not available, the development of qualitative training is required. To address this issue, a method, based on a preliminary calculation of the amount of information which is necessary to process by a pilot when training depending on the type of this information for the efficient formation of a conceptual model of air traffic in flight, has been developed. The method of forming a conceptual model of air traffic is based on the application of a mathematical model of “random walk with absorption”. The method consists of three phases. In the first flight phase, a pilot should operate a training flight en route. In the first flight of the second training phase, a trainee evaluates the tendency for the approach (separation) of the assessed aircraft to the trainee aircraft. In the second flight of the second phase, the assessed aircraft position is determined by the crew position and altitude reports, in the third flight – by the crew position, heading and altitude reports. In the third training phase, when operating three flights primarily en route, a trainee is supposed to evaluate the air situation according to all the parameters reported by crews operating in the same airspace. After flights of the second and third training phases, the pilot is meant to analyze and evaluate the air situation while operating a flight comprehensively by the number of aircraft in the flight area, their position and the sequence of their motion. The experimental results made it possible to determine that participants in the experimental group were 24% more efficient in evaluating the air situation and interacting with other crews in flight in the same flight area compared to the control group pilots. Processing of the experimental results showed that when employing the proposed training method, the reliability of the latest-generation aircraft crew interaction at the automatic piloting mode was statistically significantly increased.

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Otsuka, Yasutami, Akihiko Onozawa, Azusa Kikukawa et Yoshinori Miyamoto. « Effects of Flight Workload on Urinary Catecholamine Responses in Experienced Military Pilots ». Perceptual and Motor Skills 105, n^o 2 (octobre 2007) : 563–71. http://dx.doi.org/10.2466/pms.105.2.563-571.

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This study investigated the flight responses induced by strenuous aerobatic demonstration flight and an air-to-air combat maneuvering flight in experienced pilots. Subjects were 54 military male pilots on a volunteer basis: 8 T-4 pilots ( M = 35.8 yr., SD = 4.9), 15 F-4 pilots ( M = 32.6 yr., SD = 5.1), 13 F-15 pilots ( M = 33.8 yr., SD = 1.0), and 18 F-2 pilots ( M = 33.7 yr., SD = 3.9). Samples of urine were collected approximately 30 min. before and 20 min. after the flights. The postflight adrenaline in all pilots was significantly higher than at preflight, while a significant increase in noradrenaline at postflight was not observed. The post-/preflight ratio of adrenaline in all pilots was relatively similar and high. These findings might be regarded as a result of autonomic nervous system response to the flight workload of military pilots. Especially is increment in sympathetic activity considered to play an important part in psychological adaptation to flight.

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Hwang, Jinsoo, Seong Ok Lyu et Sun-Bai Cho. « In-Flight Casinos, Is It Really a Nonsensical Idea ? An Exploratory Approach Using Different Choice Experiments ». Sustainability 11, n^o 11 (29 mai 2019) : 3038. http://dx.doi.org/10.3390/su11113038.

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Most airlines make various efforts to enhance their customers’ levels of in-flight satisfaction while offering alternative services and entertainment. As an innovative service item, some international airlines plan in-flight casino facilities to relieve their customers’ boredom and fatigue emanating from tedious long flights. Using a study sample of casino visitors in Korea, we intend to better understand how potential airline passengers show their willingness to pay for the hypothetical in-flight casino services. We also employ multiple choice experimental techniques to examine preference heterogeneity embedded in the sampled population. Based on study results, several management strategies are discussed for offering tailored in-flight entertainment services to targeted market segments.

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Qin, Kun, Qixin Wang, Binbin Lu, Huabo Sun et Ping Shu. « Flight Anomaly Detection via a Deep Hybrid Model ». Aerospace 9, n^o 6 (19 juin 2022) : 329. http://dx.doi.org/10.3390/aerospace9060329.

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In the civil aviation industry, security risk management has shifted from post-accident investigations and analyses to pre-accident warnings in an attempt to reduce flight risks by identifying currently untracked flight events and their trends and effectively preventing risks before they occur. The use of flight monitoring data for flight anomaly detection is effective in discovering unknown and potential flight incidents. In this paper, we propose a time-feature attention mechanism and construct a deep hybrid model for flight anomaly detection. The hybrid model combines a time-feature attention-based convolutional autoencoder with the HDBSCAN clustering algorithm, where the autoencoder is constructed and trained to extract flight features while the HDBSCAN works as an anomaly detector. Quick access record (QAR) flight data containing information of aircraft landing at Kunming Changshui International and Chengdu Shuangliu International airports are used as the experimental data, and the results show that (1) the time-feature-based convolutional autoencoder proposed in this paper can better extract the flight features and further discover the different landing patterns; (2) in the representation space of the flights, anomalous flight objects are better separated from normal objects to provide a quality database for subsequent anomaly detection; and (3) the discovered flight patterns are consistent with those at the airports, resulting in anomalies that could be interpreted with the corresponding pattern. Moreover, several examples of anomalous flights at each airport are presented to analyze the characteristics of anomalies.

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Califar, Brandon, Agata Zupanska, Jordan A. Callaham, Matthew T. Bamsey, Thomas Graham, Anna-Lisa Paul et Robert J. Ferl. « Shared Metabolic Remodeling Processes Characterize the Transcriptome of Arabidopsis thaliana within Various Suborbital Flight Environments ». Gravitational and Space Research 9, n^o 1 (1 janvier 2021) : 13–29. http://dx.doi.org/10.2478/gsr-2021-0002.

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Abstract The increasing availability of flights on suborbital rockets creates new avenues for the study of spaceflight effects on biological systems, particularly of the transitions between hypergravity and microgravity. This paper presents an initial comparison of the responses of Arabidopsis thaliana to suborbital and atmospheric parabolic flights as an important step toward characterizing these emerging suborbital platforms and their effects on biology. Transcriptomic profiling of the response of the Arabidopsis ecotype Wassilewskija (WS) to the aggregate suborbital spaceflight experiences in Blue Origin New Shepard and Virgin Galactic SpaceShipTwo revealed that the transcriptomic load induced by flight differed between the two flights, yet was biologically related to traditional parabolic flight responses. The sku5 skewing mutant and 14-3-3κ:GFP regulatory protein overexpression lines, flown in the Blue Origin and parabolic flights, respectively, each showed altered intra-platform responses compared to WS. An additional parabolic flight using the F-104 Starfighter showed that the response of 14-3-3κ:GFP to flight was modulated in a similar manner to the WS line. Despite the differing genotypes, experimental workflows, flight profiles, and platforms, differential gene expression linked to remodeling of central metabolic processes was commonly observed in the flight responses. However, the timing and directionality of differentially expressed genes involved in the conserved processes differed among the platforms. The processes included carbon and nitrogen metabolism, branched-chain amino acid degradation, and hypoxic responses. The data presented herein highlight the potential for various suborbital platforms to contribute insights into biological responses to spaceflight, and further suggest that in-flight fixation during suborbital experiments will enhance insights into responses during each phase of flight.

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Thèses sur le sujet "Experimental flight"

Brown, Ainsmar Xavier. « Inflatable wing UAV experimental and analytical flight mechanics ». Thesis, Georgia Institute of Technology, 2011. http://hdl.handle.net/1853/39492.

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The field of man portable UASs (Unmanned Aerial Systems) is currently a key area in improving the fielded warrior's capabilities. Pressurized aerostructures that can perform with similar results of solid structures can potentially change how this objective may be accomplished now and in the future. Construction with high density polymers and other composites is currently part of active inflatable vehicle research. Many shape forming techniques have also been adapted from the airship and balloon manufacturing industry. Additional research includes modeling techniques so that these vehicles may be included in simulation packages. A flight dynamics simulation with reduced-order aeroelastic effects derived with Lagrangian and Eulerian dynamics approaches were developed and optimized to predict the behavior of inflatable flexible structures in small UASs. The models are used to investigate the effects of significant structural deflections (warping) on aerodynamic surfaces. The model also includes compensation for large buoyancy ratios. Existing literature documents the similarity in structural dynamics of rigid beams and inflatable beams before wrinkling. Therefore, wing bending and torsional modes are approximated with the geometrically exact ntrinsic beam equations using NATASHA (Nonlinear Aeroelastic Trim And Stability for HALE Aircraft) code. An approach was also suggested for inclusion of unique phenomena such as wrinkling during flight. A simplified experimental setup will be designed to examine the most significant results observed from the simulation model. These methods may be suitable for specifying limits on flight maneuvers for inflatable UASs.

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Carvalho, Marco Aurélio. « IPCM Telemetry System : Experimental Results ». International Foundation for Telemetering, 2015. http://hdl.handle.net/10150/596440.

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ITC/USA 2015 Conference Proceedings / The Fifty-First Annual International Telemetering Conference and Technical Exhibition / October 26-29, 2015 / Bally's Hotel & Convention Center, Las Vegas, NV
The aeronautical industries have been suffering financial cutbacks and the market has to face new challenges associated with new companies. Telemetry community has been facing the increase of the electromagnetic spectrum usage for a variety of applications (e.g. 4G), after all telemetry is everywhere. In view of these issues and focused on the inherent requirements of the Flight Test application, the IPEV R&D group proposes the iPCM Telemetry architecture as solution for the existing reliability and bandwidth issues associated with the telemetry link. In this article, as a proof-of-concept of the iPCM architecture, it has been performed an experimental assembly. The results demonstrate the iPCM's ability to regenerate corrupted data providing the required data integrity and reliability, besides the capability to dynamically select the FTI transmitted parameter list to optimize the bandwidth link.

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Wilcox, Michael Schnebly. « Trajectory Generation and Optimization for Experimental Investigation of Flapping Flight ». BYU ScholarsArchive, 2013. https://scholarsarchive.byu.edu/etd/3953.

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Though still in relative infancy, the field of flapping flight has potential to have a far-reaching impact on human life. Nature presents a myriad of examples of successful uses of this locomotion. Human efforts in flapping flight have seen substantial improvement in recent times. Wing kinematics are a key aspect of this study. This study summarizes previous wing trajectory generators and presents a new trajectory generation method built upon previous methods. This includes a novel means of commanding unequal half-stroke durations subject to robotic trajectory continuity requirements. Additionally, previous optimization methods are improved upon. Experimental optimization is performed using the new trajectory generation method and a more traditional means. Methods for quantifying and compensating for sensor time-dependence are also discussed. Results show that the Polar Fourier Series trajectory generator advanced rapidly through the optimization process, especially during the initial phase of experimentation. The Modified Berman and Wang trajectory generator moved through the design space more slowly due to the increased number of kinematic parameters. When optimizing lift only, the trajectory generators produced similar results and kinematic forms. The findings suggest that the objective statement should be modified to reward efficiency while maintaining a certain amount of lift. It is expected that the difference between the capabilities of the two trajectory generators will become more apparent under such conditions.

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Mullen, Gerald John. « Experimental evaluation of the performance and robustness of advanced rotor control schemes ». Thesis, University of Bristol, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.265323.

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Baek, Youn Hyeong. « An experimental review of some aircraft parameter identification techniques ». Thesis, Cranfield University, 1998. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.285023.

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Gibbs, Jason. « Experimental Determination of Lift and Lift Distributions for Wings In Formation Flight ». Thesis, Virginia Tech, 2005. http://hdl.handle.net/10919/31301.

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Experimental methods for the investigation of trailing vortex strengths, total lift, and lift distributions for three-dimensional wings in close proximity flight were developed. With these experiments we model compound aircraft flight either docked tip-to-tip, or flying in formation. There is a distinct lack of experimental formation flight data using three-dimensional wing models for tests. The absence of fixed walls on either end of the wing permits the development of the asymmetric shedding of vortices, and the determination of the asymmetric circulation distribution induced by the proximity of the leading wing. The pair consisted of a swept NACA-0012 non-cambered wing simulating one half of a leading aircraft and a rectangular cambered NACA 63-420 wing simulating the trailing aircraft. Important aspects of the work included theoretical development, experimental setup, data acquisition and processing, and results validation. Experimentally determining the lift for formation flight, in addition to the local flow behavior for a pair of wings, can provide valuable insight for the proposition of flying actual aircraft in formation to increase mission efficiency. To eliminate the need for bulky mounting stings and direct load measurement devices that can potentially interfere with the local flowfield, a minimally invasive velocity probe method is developed. A series of experiments were performed to assist with the development of the method. Velocity and vorticity distributions obtained along a near-field plane were processed to calculate wingtip vortex strengths. Additionally, vortex position instabilities and the shedding of vorticity inboard of the wingtips were observed. To determine the circulation distributions for the trailing wing, the initial method is modified. By processing velocity information acquired in a near-field plane, both the lift and induced drag were calculated for the trailing airfoil. Comparisons are made to directly measured loads and to results reported earlier. Directly measured lift and drag coefficients were found to agree with existing literature.
Master of Science

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Bradley, Roy. « A method for specifying complex real-time systems with application to an experimental variable stability helicopter ». Thesis, University of Glasgow, 1992. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.357497.

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Kostyleva, Daria [Verfasser]. « Experimental Studies of Proton-Unbound Nuclei via In-Flight Decay Spectroscopy / Daria Kostyleva ». Gießen : Universitätsbibliothek, 2021. http://d-nb.info/1228828970/34.

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Sullivan, Robert Bryan. « The use of vestibular models in flight simulator motion washout systems : an experimental evaluation ». Thesis, Massachusetts Institute of Technology, 1985. http://hdl.handle.net/1721.1/80443.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1985.
Microfiche copy available in Archives and Barker.
Bibliography: leaves 114-115.
by Robert Bryan Sullivan.
M.S.

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Brand, Albert G. « An experimental investigation of the interaction between a model rotor and airframe in forward flight ». Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/12433.

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Livres sur le sujet "Experimental flight"

John, Hansman R., et Langley Research Center, dir. Experimental evaluation of candidate graphical microburst alert displays. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1992.

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Gilyard, Glenn B. In-flight transport performance optimization : An experimental flight research program and an operational scenario. Edwards, Calif : National Aeronautics and Space Administration, Dryden Flight Research Center, 1997.

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NASA Dryden Flight Research Center., dir. In-flight transport performance optimization : An experimental flight research program and an operational scenario. Edwards, Calif : National Aeronautics and Space Administration, Dryden Flight Research Center, 1997.

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Duke, Eugene L. Description of an experimental expert system flight status monitor. Moffett Field, Calif : National Aeronautics and Space Administration, Ames Research Center, 1985.

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1939-, Alexander Charles Melton, Oldson John C, Energy Science Laboratories Inc et George C. Marshall Space Flight Center., dir. Final report on SEDS experiment design definition. San Diego, CA : Energy Science Laboratories, Inc., 1990.

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Jacqueline, Hazard, dir. The lonely sky : The personal story of America's pioneering experimental test pilot. New York : iUniverse, 2009.

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George C. Marshall Space Flight Center., dir. Concept report : Experimental vector magnetograph (EXVM) operational configuation balloon flight assembly. Huntsville, Ala : National Aeronautics and Space Administration, Marshall Space Flight Center, 1993.

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Chapitres de livres sur le sujet "Experimental flight"

Powers, Caitlin, Daniel Mellinger, Aleksandr Kushleyev, Bruce Kothmann et Vijay Kumar. « Influence of Aerodynamics and Proximity Effects in Quadrotor Flight ». Dans Experimental Robotics, 289–302. Heidelberg : Springer International Publishing, 2013. http://dx.doi.org/10.1007/978-3-319-00065-7_21.

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Chazot, Olivier. « Aerospace Flight Modeling and Experimental Testing ». Dans Uncertainty in Engineering, 131–47. Cham : Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-83640-5_9.

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AbstractValidation processes for aerospace flight modeling require to articulate uncertainty quantification methods with the experimental approach. On this note, the specific strategies for the reproduction of re-entry flow conditions in ground-based facilities are reviewed. It shows how it combines high-speed flow physics with the hypersonic wind tunnel capabilities.

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Ji, Jialin, Xin Zhou, Chao Xu et Fei Gao. « CMPCC : Corridor-Based Model Predictive Contouring Control for Aggressive Drone Flight ». Dans Experimental Robotics, 37–46. Cham : Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-71151-1_4.

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Laurence, S. J., S. Karl et K. Hannemann. « Experimental and Numerical Investigation of the HyShot II Flight Experiment ». Dans 29th International Symposium on Shock Waves 1, 307–12. Cham : Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-16835-7_47.

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Benaron, David A., David C. Ho, Stanley Spilman, John P. Van Houten et David K. Stevenson. « Tomographic Time-of-Flight Optical Imaging Device ». Dans Advances in Experimental Medicine and Biology, 207–14. Boston, MA : Springer US, 1994. http://dx.doi.org/10.1007/978-1-4615-1875-4_26.

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Zhanjun, Chen, Fu Zhichao, Lv Jinan et Liu Ziqiang. « Nonlinear Flight Dynamics of Very Flexible Aircraft ». Dans Computational and Experimental Simulations in Engineering, 119–23. Cham : Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-27053-7_12.

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Yates, John T. « Time-of-Flight Detection for Laser-Ionized Neutrals ». Dans Experimental Innovations in Surface Science, 334–36. New York, NY : Springer New York, 1998. http://dx.doi.org/10.1007/978-1-4612-2304-7_103.

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Woods, Amina, Rong Wang, Marc Chevrier, Tim Cornish, Cathy Wolkow et Robert J. Cotter. « Elucidation of Protein Structure and Processing Using Time-of-Flight Mass Spectrometry ». Dans Experimental Mass Spectrometry, 199–242. Boston, MA : Springer US, 1994. http://dx.doi.org/10.1007/978-1-4899-2569-5_6.

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Albertani, Roberto, Tatjana Hubel, Sharon M. Swartz, Kenneth S. Breuer et Johnny Evers. « In-Flight Wing-Membrane Strain Measurements on Bats ». Dans Experimental and Applied Mechanics, Volume 6, 437–45. New York, NY : Springer New York, 2011. http://dx.doi.org/10.1007/978-1-4419-9792-0_68.

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Berestov, L., A. Kozlov, V. Melnik, V. Vid, V. Denisov et V. Khabarov. « Intelligent Support of Flight Experimental Design and Analysis ». Dans Applications of Artificial Intelligence in Engineering VI, 319–28. Dordrecht : Springer Netherlands, 1991. http://dx.doi.org/10.1007/978-94-011-3648-8_21.

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Actes de conférences sur le sujet "Experimental flight"

Sydney, Anish, Naipei Bi, Kevin Kimmel et David Haas. « Experimental Investigation of Fan-In-Wing ». Dans Vertical Flight Society 72nd Annual Forum & Technology Display, 1–12. The Vertical Flight Society, 2016. http://dx.doi.org/10.4050/f-0072-2016-11904.

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Fan-in-Wing (FIW) and other embedded fan configurations have the potential to enhance the performance of future vertical take-off and landing aircraft by achieving efficient hover and high-speed forward flight. However, there is a continuing need for research to characterize the fundamental aerodynamics associated with these types of embedded fan systems. To this end, the present work experimentally investigates the aerodynamic performance of a series of generic FIW configurations in the Naval Surface Warfare Center Carderock Division (NSWCCD) 8- by 10-ft Subsonic Wind Tunnel. The goals are to understand how the aerodynamic performance of a FIW in hover is affected by different fan design parameters and also to create a benchmark dataset for model validation. The research is conducted in three phases; isolated fans in hover, FIW configurations in hover, and FIW configurations in transition from hover to forward flight. This paper describes the experimental approach and results obtained from the second phase of testing, which examines a number of different generic FIW configurations. Particular focus is placed on examining the effects of fan rotational frequency, blade pitch angle, number of blades, fan solidity, blade twist, and fan axial position within the wing duct. Furthermore, to better quantify the aerodynamic performance of the fan and the wing as well as the interactions within FIW systems, the model is designed such that the fan performance can be measured independently of the total FIW system performance. The results show that the fan and the wing form a complex and coupled aerodynamic environment that can, at times, be counter-intuitive when compared to results expected from an isolated fan. In general, the results suggest that all of the design variables affect the inflow distribution on the blades and, therefore, the overall aerodynamic performance as well as the stall characteristics of the fan and total FIW system. It is also clear that the future FIW systems must consider an integrated design philosophy that treats the fan and the wing as a coupled aerodynamic system. These results, along with those obtained in Phase I, will ultimately be used as a baseline for comparison with results in Phase III of the study which will examine the generic FIW configuration in transition and forward flight.

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Tanner, Philip, Luther Jenkins, Austin Overmeyer, Chung-Sheng Yao et Scott Bartram. « Experimental Investigation of Rotorcraft Outwash in Ground Effect ». Dans Vertical Flight Society 71st Annual Forum & Technology Display, 1–26. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10281.

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The wake characteristics of a rotorcraft are affected by the proximity of a rotor to the ground surface, especially during hover. Ground effect is encountered when the rotor disk is within a distance of a few rotor radii above the ground surface and results in an increase in thrust for a given power relative to that same power condition with the rotor out of ground effect. Although this phenomenon has been highly documented and observed since the beginning of the helicopter age, there is still a relatively little amount of flowfield data existing to help understand its features. Joint Army and NASA testing was conducted at NASA Langley Research Center using a powered rotorcraft model in hover at various rotor heights and thrust conditions in order to contribute to the complete outwash data set. The measured data included outwash velocities and directions, rotor loads, fuselage loads, and ground pressures. The researchers observed a linear relationship between rotor height and percent download on the fuselage, peak mean outwash velocities occurring at radial stations between 1.7 and 1.8 r/R regardless of rotor height, and the measurement azimuthal dependence of the outwash profile for a model incorporating a fuselage. Comparisons to phase-locked PIV data showed similar contours but a more contracted wake boundary for the PIV data. This paper describes the test setup and presents some of the averaged results.

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Berkebile, Stephen, Radames Colon-Rivera, Jason Fetty, Nikhil Murthy, Kevin Radil et Brian Dykas. « Experimental Evaluation of Transmission Loss-of-Lubrication Technologies ». Dans Vertical Flight Society 74th Annual Forum & Technology Display, 1–15. The Vertical Flight Society, 2018. http://dx.doi.org/10.4050/f-0074-2018-12860.

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A Joint Aircraft Survivability Program (JASP) project was awarded in 2014 in order to accelerate the research and development on military helicopter transmission loss of lubrication survivability. This JASP project, "Helicopter Transmission Loss-of-Lubrication" was a collaboration between the US Army, US Navy, and NASA and completed in 2018. The approach for the effort was to first screen emerging technologies using coupon-level methods, then test those showing the most promise at the component level, and finally to downselect and evaluate these technologies at the system level. Several concepts to reduce heat generation, increase heat rejection, increase material tolerance to higher temperatures, and increase material resistance to damage were evaluated for this effort. Included in this evaluation were: a ceramic material for bearings, four different gear steels, various levels of gear surface roughness, six gear coatings, five lubricant and lubricant additive variations, and gearbox noble gas injection. After gear testing at the component level, isotropic superfinishing and ionic liquid lubricant additive were down selected as the two most suitable technologies for the system level testing. These technologies underwent loss of lubrication testing to failure in an intermediate gearbox from a standard configuration medium lift helicopter. A baseline loss of lubrication test, without these technologies, was also performed for comparison.

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Srivathsan, Shreyas, Pranav Sridhar, Marilyn Smith et Juergen Rauleder. « Experimental and Computational Investigations of Propeller-Wing Interactions ». Dans Vertical Flight Society 80th Annual Forum & Technology Display, 1–27. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1337.

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A joint experimental-computational research campaign is underway to develop physical understanding and a validation-quality database for a model-scale tractor propeller-wing system. Separate load measurements on the wing and propeller accompany wing surface pressure distributions and flow field measurements via stereoscopic particle image velocimetry (SPIV) at discrete wing spanwise locations for a range of static propeller tilt angles. The physical wind tunnel test is modeled using a high-fidelity computational approach (Helios). Computational simulations aid in assessing the influence of the wind tunnel facility effects and test support structure wake interference, as well as in reducing uncertainties in the physical experiments for use in computational validation. The behavior of the induced thrust and lift at a zero-degree wing angle of attack in the axial flow regime (cruise configuration) is correlated with flow field measurements, showing distinct differences between upwash and downwash fields produced by the propeller. Recirculation regions near the wing upper surface are identified for high propeller tilt angles as the propeller wake interacts with the wing boundary layer. Increased propeller tilt angles result in a decreased wing lift and increased propeller thrust in forward flight, resembling a rotor in ground effect. Results indicate ways to improve computational modeling and refine the physical wind tunnel testing. These will be applied to refine the database to further elucidate physical understanding of the propeller-wing interactional aerodynamics.

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BROCKLEHURST, ALAN, et EARL DUQUE. « Experimental and numerical study of the British Experimental Rotor Programme blade ». Dans Flight Simulation Technologies Conference and Exhibit. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-3008.

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Bykova, N. G., L. B. Ibraguimova, O. P. Shatalov, Yu V. Tunik et I. E. Zabelinskii. « Experimental study of nonequilibrium dissociation of molecular oxygen ». Dans Progress in Flight Physics, sous la direction de P. Reijasse, D. Knight, M. Ivanov et I. Lipatov. Les Ulis, France : EDP Sciences, 2013. http://dx.doi.org/10.1051/eucass/201305557.

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TALMADGE, R. « Mobile Experimental Laboratory (MEL) ». Dans 3rd Flight Testing Conference and Technical Display. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-9801.

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Génin, C., R. Stark, O. Haidn, K. Quering et M. Frey. « Experimental and numerical study of dual bell nozzle flow ». Dans Progress in Flight Physics, sous la direction de P. Reijasse, D. Knight, M. Ivanov et I. Lipatov. Les Ulis, France : EDP Sciences, 2013. http://dx.doi.org/10.1051/eucass/201305363.

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Kashkovsky, A. V., P. V. Vashchenkov, T. Bányai et M. S. Ivanov. « Modeling Intermediate eXperimental Vehicle control thruster plume-surface interaction ». Dans Progress in Flight Physics, sous la direction de P. Reijasse, D. Knight, M. Ivanov et I. Lipatov. Les Ulis, France : EDP Sciences, 2013. http://dx.doi.org/10.1051/eucass/201305545.

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Hanakova, Lenka, Viktor Valenta, Aleš Řezníček, Roman Matyas et Vladimir Socha. « Effects of Napping on Pilot Performance : An Experimental Study ». Dans 14th International Conference on Applied Human Factors and Ergonomics (AHFE 2023). AHFE International, 2023. http://dx.doi.org/10.54941/ahfe1003838.

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Several strategies can be employed to combat a sudden onset of fatigue. Napping is widely used as one of these strategies. Commercial airlines allow one pilot on flight deck duty to avail of a short rest period in the pilot seat while the other pilot is responsible for the aircraft control – this technique is called controlled rest. Controlled rest is considered a tool to enhance flight safety; this is based on the premise that reducing fatigue leads to an improved pilot condition in the context of cognitive and motor functions. However, this assumption has not been explored on an experimental level and is not supported by objective data. The aim of this study is to evaluate the effect of control rest on pilot performance. Ten pilots participated in the study. The experiment consisted of four experimental flights in a simulator. Two flights were flown on the first night of the experiment without a controlled rest period and several days later another two night flights were flown with a controlled rest period. Deviations from the instrument landing system guidance during the final approach phase were evaluated in terms of precision and accuracy. The analysis of flight data revealed an improvement in horizontal path tracking for flight with controlled rest; this is further supported by the evaluation of excessive deviations in 3D space. On the other hand, significant performance degradation is observed in the vertical plane for flights with controlled rest.

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Rapports d'organisations sur le sujet "Experimental flight"

Moore, D. G., C. R. Jones, J. E. Mihelic et J. D. Barnes. Experimental flight test vibration measurements and nondestructive inspection on a USCG HC-130H aircraft. Office of Scientific and Technical Information (OSTI), août 1998. http://dx.doi.org/10.2172/656772.

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Gkatis, G., C. Paradela, G. Alaerts, M. Diakaki, J. Heyse, S. Kopecky, G. Noguere, A. Plompen, P. Schillebeeckx et R. Wynants. Results of time-of-flight transmission measurements for natFe at a 50 m station of GELINA. IAEA Nuclear Data Section, juin 2024. http://dx.doi.org/10.61092/iaea.twc4-dgh7.

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Transmission measurements on natural iron samples have been performed at the time-of-flight facility GELINA to validate neutron resonance parameters for Fe isotopes. The measurements were carried out at the 50 m transmission station using a Li-glass scintillator with the accelerator operating at 800 Hz. This report provides the experimental details required to deliver the data to the EXFOR data library which is maintained by the International Network of Nuclear Reaction Data Centres (NRDC). The experimental conditions and data reduction procedures are described. In addition, the full covariance information based on the AGS concept is given such that nuclear reaction model parameters together with their covariances can be derived in a least-squares adjustment to the data.

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Roesler, Stefan. Calculation of Neutron Time-of-Flight and Energy Spectra Behind Thick Shielding of an Electron Accelerator and Comparison to Experimental Data. Office of Scientific and Technical Information (OSTI), mai 2002. http://dx.doi.org/10.2172/799067.

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Akin, David L., Katherine McBryan et Nicholas Limparis. DYMAFLEX : DYnamic Manipulation FLight EXperiment. Fort Belvoir, VA : Defense Technical Information Center, septembre 2013. http://dx.doi.org/10.21236/ada589986.

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Blair, Maxwell, Jason Robinson, William A. McClelland et Jason C. Bowman. A Joined-Wing Flight Experiment. Fort Belvoir, VA : Defense Technical Information Center, février 2008. http://dx.doi.org/10.21236/ada482613.

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Cenkci, Martha J. ZEST Flight Test Experiments, Kauai Test Facility, Hawaii. Fort Belvoir, VA : Defense Technical Information Center, juillet 1991. http://dx.doi.org/10.21236/ada241143.

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Harkins, Thomas E. Understanding Body-Fixed Sensor Output From Projectile Flight Experiments. Fort Belvoir, VA : Defense Technical Information Center, septembre 2003. http://dx.doi.org/10.21236/ada418331.

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Estrade, Alfredo. Time-of-flight experiments for nuclear structure and astrophysics. Office of Scientific and Technical Information (OSTI), décembre 2022. http://dx.doi.org/10.2172/1903697.

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Hicks, Robert J., et David H. Jenkins. High Altitude Balloon Flight Test of the GRAD Experiment. Fort Belvoir, VA : Defense Technical Information Center, avril 1990. http://dx.doi.org/10.21236/ada224398.

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Jones, Landon R., Jared A. Elmore, B. S. Krishnan, Sathishkumar Samiappan, Kristine O. Evans, Morgan B. Pfeiffer, Bradley F. Blackwell et Raymond B. Iglay. Dataset for Controllable factors affecting accuracy and precision of human identification of animals from drone imagery. Mississippi State University, juillet 2023. http://dx.doi.org/10.54718/xblo5500.

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Dataset from the results of an experiment to determine how three controllable factors, flight altitude, camera angle, and time of day, affect human identification and counts of animals from drone images to inform best practices to survey animal communities with drones. We used a drone (unoccupied aircraft system, or UAS) to survey known numbers of eight animal decoy species, representing a range of body sizes and colors, at four GSD (ground sampling distance) values (0.35, 0.70, 1.06, 1.41 cm/pixel) representing equivalent flight altitudes (15.2, 30.5, 45.7, 61.0 m) at two camera angles (45° and 90°) and across a range of times of day (morning to late afternoon). Expert human observers identified and counted animals in drone images to determine how the three controllable factors affected accuracy and precision. Observer precision was high and unaffected by tested factors. However, results for observer accuracy revealed an interaction among all three controllable factors. Increasing flight altitude resulted in decreased accuracy in animal counts overall; however, accuracy was best at midday compared to morning and afternoon hours, when decoy and structure shadows were present or more pronounced. Surprisingly, the 45° camera enhanced accuracy compared to 90°, but only when animals were most difficult to identify and count, such as at higher flight altitudes or during the early morning and late afternoon. We provide recommendations based on our results to design future surveys to improve human accuracy in identifying and counting animals from drone images for monitoring animal populations and communities.

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