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Relevant bibliographies by topics / UH-60A helicopter

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Academic literature on the topic 'UH-60A helicopter'

Author: Grafiati

Published: 4 June 2021

Last updated: 17 February 2022

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Journal articles on the topic "UH-60A helicopter"

1

Lv, Shao Jie, Yi Hua Cao, and Guo Zhi Li. "Helicopter Flying Qualities Sensitivity Analysis with Respect to Aerodynamic Configuration." Applied Mechanics and Materials 401-403 (September 2013): 167–70. http://dx.doi.org/10.4028/www.scientific.net/amm.401-403.167.

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An improved helicopter flight dynamic model suited to evaluate the flying qualities of a single rotor helicopter was built for UH-60A, including trim calculation and stability and controllability derivatives. On this foundation, the open-loop flying qualities of the UH-60A helicopter were studied by using MIL-F-83300. According to the requirement, the change of the UH-60A dynamic response and the control characteristics were computed and compared when some typical aerodynamic configuration parameters were adjusted, the influences of the aerodynamic configuration parameters on flying qualities

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2

Simon, Robert, and Dennis Dunn. "Incorporating Dynamic Field of View Information to Design the Next-Generation Black Hawk Helicopter Cockpit." Proceedings of the Human Factors Society Annual Meeting 33, no. 16 (1989): 1124–28. http://dx.doi.org/10.1177/154193128903301619.

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Changing flight tactics and increased use of Night Vision Goggles (NVGs) has focused attention on the limited Field of View (FOV) of the Army UH-60A Black Hawk Helicopter. To improve the FOV in the next generation Black Hawk, the U.S. Army tasked an independent contractor to investigate the problem and propose alternatives. The study involved a comprehensive review of Army requirement documents, existing FOV studies, and accident data. Close attention was given to dynamic flight characteristics that affect FOV. Also, the study team collected technical data related to military rotary wing desig

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Lee, Ye-Lin, Do-Young Kim, Do-Hyung Kim, Sung-Boo Hong, and Jae-Sang Park. "Vibration Reduction Simulation of UH-60A Helicopter Airframe Using Active Vibration Control System." Journal of the Korean Society for Aeronautical & Space Sciences 48, no. 6 (2020): 443–53. http://dx.doi.org/10.5139/jksas.2020.48.6.443.

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Cao, Yihua, Guozhi Li, and R. A. Hess. "Helicopter flight characteristics in icing conditions." Aeronautical Journal 116, no. 1183 (2012): 963–79. http://dx.doi.org/10.1017/s0001924000007375.

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Abstract A method to predict the effects of rotor icing on the flight characteristics of a UH-60A helicopter is presented. By considering both natural ice shedding and different types of ice accretion due to local temperature variations on the blade surface, an improved rotor icing model was developed. Next, the effects of icing on rotor force, torque and flapping were incorporated in a nonlinear helicopter dynamic model. Based upon icing design envelopes in cumuliform clouds, trim and stability characteristics were studied. Further development of the helicopter state-space model allowed contr

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Cicolani, Luigi S., Allen H. McCoy, Ranjana Sahai, et al. "Flight Test Identification and Simulation of a UH-60A Helicopter and Slung Load." Journal of the American Helicopter Society 46, no. 2 (2001): 140–60. http://dx.doi.org/10.4050/jahs.46.140.

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6

Yeo, Hyeonsoo, Ethan A. Romander, and Thomas R. Norman. "Investigation of Rotor Performance and Loads of a UH-60A Individual Blade Control System." Journal of the American Helicopter Society 56, no. 4 (2011): 1–18. http://dx.doi.org/10.4050/jahs.56.042006.

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Wind tunnel measurements of performance, loads, and vibration of a full-scale UH-60A Black Hawk main rotor with an individual blade control (IBC) system are compared with calculations obtained using the comprehensive helicopter analysis CAMRAD II and a coupled CAMRAD II/OVERFLOW 2 analysis. Measured data show a 5.1% rotor power reduction (8.6% rotor lift to effective-drag ratio increase) using 2/rev IBC actuation with 2.0° amplitude at μ = 0.4. At the optimum IBC phase for rotor performance, IBC actuator force (pitch link force) decreased, and neither flap nor chord bending moments changed sig

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Han, D., and G. N. Barakos. "Variable-speed tail rotors for helicopters with variable-speed main rotors." Aeronautical Journal 121, no. 1238 (2017): 433–48. http://dx.doi.org/10.1017/aer.2017.4.

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ABSTRACTVariable tail rotor speed is investigated as a method for reducing tail rotor power, and improving helicopter performance. A helicopter model able to predict the main rotor and tail rotor powers is presented, and the flight test data of the UH-60A helicopter is used for validation. The predictions of the main and tail rotor powers are generally in good agreement with flight tests, which justifies the use of the present method in analysing main and tail rotors. Reducing the main rotor speed can result in lower main rotor power at certain flight conditions. However, it increases the main

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8

Choi, Seongim, Anubhav Datta, and Juan J. Alonso. "Prediction of Helicopter Rotor Loads Using Time-Spectral Computational Fluid Dynamics and an Exact Fluid–Structure Interface." Journal of the American Helicopter Society 56, no. 4 (2011): 1–15. http://dx.doi.org/10.4050/jahs.56.042001.

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The objectives of this paper are to introduce time-spectral computational fluid dynamics (CFD) for the analysis of helicopter rotor flows in level flight and to introduce an exact fluid–structure interface for coupled CFD/computational structural dynamics (CSD) analysis. The accuracy and efficiency of time-spectral CFD are compared with conventional time-marching computations. The exact interface is equipped with an exact delta coupling procedure that bypasses the requirement for sectional airloads. Predicted loads are compared between time-spectral and time-marching CFD using both interfaces

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9

Li, Guozhi, and Yihua Cao. "Numerical Simulation of Helicopter Rotor Performance Degradation in Natural Rain Encounter." International Journal of Aerospace Engineering 2021 (April 28, 2021): 1–15. http://dx.doi.org/10.1155/2021/5533823.

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Sustained flight operation in the rain conditions is still a challenge to a pilot. This problem can be mainly attributed to the aerodynamic performance degradation of aircraft. In this article, in order to quickly understand the influence of rainfall aiming at the engineering application, an approach to predict helicopter rotor performance degradation in heavy rain encounters is presented. Firstly, we develop a computational fluid dynamics- (CFD-) based method of simulation of the blade airfoil under natural rain scenario and different angles of attack in order to obtain a data-driven basis re

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10

Khoshlahjeh, Maryam, and Farhan Gandhi. "Extendable Chord Rotors for Helicopter Envelope Expansion and Performance Improvement." Journal of the American Helicopter Society 59, no. 1 (2014): 1–10. http://dx.doi.org/10.4050/jahs.59.012007.

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This study explores the benefits of rotor chord extension in stall-dominant conditions. Simulations are based on a UH-60A Blackhawk helicopter with an effective chord increase of 20% realized by extending a trailing-edge plate (TEP) through a slit in the trailing edge between 63% and 83% blade span. Since TEP extension changes the baseline SC-1094R8 airfoil profile, two-dimensional aerodynamic coefficients of the modified profile from Navier–Stokes computational fluid dynamics calculations are used, coupled with 12 × 12 dynamic inflow and the Leishman–Beddoes dynamic stall model in the Rotorcr

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Dissertations / Theses on the topic "UH-60A helicopter"

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Marpu, Ritu Priyanka. "Physics based prediction of aeromechanical loads for the UH-60A rotor." Diss., Georgia Institute of Technology, 2013. http://hdl.handle.net/1853/47661.

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Helicopters in forward flight experience complex aerodynamic phenomena to various degrees. In low speed level flight, the vortex wake remains close to the rotor disk and interacts with the rotor blades to give rise to blade vortex interaction phenomena. In high speed flight, compressibility effects dominate leading to the formation of shocks. If the required thrust is high, the combination of high collective pitch and cyclic pitch variations give rise to three-dimensional dynamic stall phenomena. Maneuvers further exacerbate the unsteady airloads and affect rotor and hub design. The strength

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2

Tyson, Peter H. "Simulation validation and flight prediction of UH-60A Black Hawk helicopter/slung load characteristics." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1999. http://handle.dtic.mil/100.2/ADA362524.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, March 1999.<br>"March1999". Thesis advisor(s): E. Roberts Wood, Mark B. Tischler. Includes bibliographical references (p. 279-281). Also available online.

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Fortier, Gregory. "THE APPLICATION OF "CRASHING" A PROJECT NETWORK TO SOLVE THE TIME/COST TRADEOFF IN RECAPITALIZATION OF THE UH-60A HELICOPTER." Master's thesis, University of Central Florida, 2006. http://digital.library.ucf.edu/cdm/ref/collection/ETD/id/3620.

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Since the beginning of project management, people have been asked to perform "more with less" in expeditious time while attempting to balance the inevitable challenge of the time/cost tradeoff. This is especially true within the Department of Defense today in prosecuting the Global War on Terrorism both in Afghanistan and Iraq. An unprecedented and consistent level of Operational Tempo has generated heavy demands on current equipment and has subsequently forced the need to recapitalize several legacy systems until suitable replacements can be implemented. This paper targets the UH-60A:A Recapi

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McCoy, Allen H. "Flight testing and real-time system identification analysis of a UH-60A Black Hawk Helicopter with an instrumented external sling load." Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1997. http://handle.dtic.mil/100.2/ADA343449.

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Thesis (M.S. in Aeronautical Engineering) Naval Postgraduate School, December 1997.<br>"December 1997." Thesis advisor(s): E. Roberts Wood, Mark B. Tischler. Includes bibliographical references (p. 87-88). Also available online.

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Ickes, Jacob. "Improved Helicopter Rotor Performance Prediction through Loose and Tight CFD/CSD Coupling." University of Toledo / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1408476196.

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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 unlimited<br>Usage 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 stud

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Books on the topic "UH-60A helicopter"

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Kempski, Piotr. Śmigłowiec wielozadaniowy Sikorsky UH-60A Black Hawk. Dom Wydawniczy Bellona, 2006.

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2

Ballin, Mark G. Validation of a real-time engineering simulation of the UH-60A helicopter. Ames Research Center, 1987.

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3

Oswald, Fred B. Gear tooth stress measurements on the UH-60A helicopter transmission. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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Oswald, Fred B. Gear tooth stress measurements on the UH-60A helicopter transmission. National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1987.

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5

Oswald, Fred B. Gear tooth stress meaurements on the UH-60A helicopter transmission. Lewis Research Center, 1987.

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6

Hamade, Karen S. Modal analysis of UH-60A instrumented rotor blades. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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7

Hamade, Karen S. Modal analysis of UH-60A instrumented rotor blades. Ames Research Center, 1990.

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8

Mitchell, Andrew M. Testing of UH-60A helicopter transmission in NASA Lewis 2240-kW (3000-hp) Facility. Lewis Research Center, 1986.

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9

McCoy, Allen H. Flight testing and real-time system identification analysis of a UH-60A Black Hawk Helicopter with an instrumented external sling load. Naval Postgraduate School, 1997.

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10

Validation of a real-time engineering simulation of the UH-60A helicopter. National Aeronautics and Space Administration, Ames Research Center, 1987.

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Conference papers on the topic "UH-60A helicopter"

1

Kottapalli, Sesi. "Analytical Estimation of UH-60A Helicopter Pilot Vibration with Active Control." In 46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. American Institute of Aeronautics and Astronautics, 2005. http://dx.doi.org/10.2514/6.2005-2248.

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2

Ortiz-Carretero, Jesus, Alejandro Castillo Pardo, Vassilios Pachidis, and Ioannis Goulos. "Assessment of the Effect of Environmental Conditions on Rotorcraft Pollutant Emissions at Mission Level." In ASME Turbo Expo 2017: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/gt2017-63440.

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It is anticipated that the contribution of rotorcraft activities to the environmental impact of civil aviation will increase in the forthcoming future. Due to their versatility and robustness, helicopters are often operated in harsh environments with extreme ambient conditions and dusty air. These severe conditions affect not only the engine operation but also the performance of helicopter rotors. This impact is reflected in the fuel burn and pollutants emitted by the helicopter during a mission. The aim of this paper is to introduce an exhaustive methodology to quantify the influence of the e

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McColl, Chance C., and Massimo Ruzzene. "Analysis of Rotor Load Harmonic Composition and Load Transference Between Frames." In ASME 2013 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/detc2013-12323.

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Loads prediction for helicopters is more complex than that for fixed wing aircraft given that the aerodynamic forces that produce the air vehicle’s lift and moments are generated by rotating components (e.g., the main and tail rotors). This paper examines rotor load content as a function of harmonics of the rotor angular speed. Accurate rotor loads prediction is driven by a clear understanding of the underlying physics of the problem. This understanding is important for several reasons. First, additive effects of multiple load components fed from the rotating frame to the fixed frame influence

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Reports on the topic "UH-60A helicopter"

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Ahroon, William A., Elmaree Gordon, and Frederick T. Brozoski. Impulse Noise Levels of the UH-60A/L Black Hawk Helicopter Cockpit Air Bag System - Enhanced Lateral Air Bags. Defense Technical Information Center, 2002. http://dx.doi.org/10.21236/ada405678.

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Downey, David A., Reginald C. Murrell, and Christopher J. Young. Artificial and Natural Icing Tests of the UH-60A Helicopter Configured with the XM-139 Multiple Mine Dispensing System (VOLCANO). Defense Technical Information Center, 1988. http://dx.doi.org/10.21236/ada205031.

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3

Allen, Luke, Joon Lim, Robert Haehnel, and Ian Dettwiller. Helicopter rotor blade multiple-section optimization with performance. Engineer Research and Development Center (U.S.), 2021. http://dx.doi.org/10.21079/11681/41031.

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This paper presents advancements in a surrogate-based, rotor blade design optimization framework for improved helicopter performance. The framework builds on previous successes by allowing multiple airfoil sections to designed simultaneously to minimize required rotor power in multiple flight conditions. Rotor power in hover and forward flight, at advance ratio 𝜇 = 0.3, are used as objective functions in a multi-objective genetic algorithm. The framework is constructed using Galaxy Simulation Builder with optimization provided through integration with Dakota. Three independent airfoil sections

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