Modal analysis of UH-60A instrumented rotor blades

Cover of: Modal analysis of UH-60A instrumented rotor blades |

Published by National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, For sale by the National Technical Information Service in [Washington, D.C.], Springfield, Va .

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  • Rotors (Helicopters) -- Testing.,
  • Rotors (Helicopters) -- Aerodynamics -- Computer simulation.,
  • Aerodynamic loads.,
  • Analogies.,
  • Finite element method.,
  • Mode (Statistics),
  • Rotor aerodynamics.,
  • Rotor blades.

Edition Notes

Book details

StatementKaren S. Hamade and Robert M. Kufeld.
SeriesNASA technical memorandum -- 4239.
ContributionsKufeld, Robert M., Ames Research Center., United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.
The Physical Object
Pagination44 p.
Number of Pages44
ID Numbers
Open LibraryOL16132235M

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Get this from a library. Modal analysis of UHA instrumented rotor blades. [Karen S Hamade; Robert M Kufeld; Ames Research Center.; United States. National Aeronautics and Space Administration. Scientific and Technical Information Division.]. {{Citation | title=Modal analysis of UHA instrumented rotor blades [microform] / Karen S.

Hamade and Robert M. Kufeld | author1=Hamade, Karen S | author2=Kufeld, Robert M | author3=Ames Research Center | author4=United States. National Aeronautics and Space Administration. Vehicle: UHA Black-Hawk, extensive flight test data with pressure instrumented blades Identified 4 critical flight conditions: Vibration Validation Study Level Flight: 1.

High speed µ = 2. Low speed transition µ = 3. High altitude dynamic stall µ = Maneuver: 4. Airloads Correlation of the UHA Rotor inside the by Foot Wind Tunnel Conference Paper (PDF Available) in International Journal of Aerospace Engineering (1) January with 79 Reads.

Full text of "NASA Technical Reports Server (NTRS) Research and technology, " See other formats. An emergency medical service (EMS) and a search and rescue (SAR) mission are used as case studies to simulate the effects of extreme temperatures, high altitude, and compressor degradation on a representative twin-engine medium (TEM) weight helicopter, the Cited by: 2.

Bowen-Davies, G. and Chopra, I., “Correlation of the UHA Slowed Rotor Wind Tunnel Tests Using UMARC,” 69th Annual Forum of the American Helicopter Society, Phoenix, AZ, May Friedman, C., Rand, O. and Chopra, I., “Obstacle Avoidance and Targeted Flight for Rotary Wing MAVs,” 69th Annual Forum of the American Helicopter Society.

Full text of "NASA Technical Reports Server (NTRS) Aeronautical engineering: A continuing bibliography with indexes (supplement )" See other formats.

In: 31st international modal analysis conference on structural dynamics, IMACGarden Grove, pp – doi: /_44 Olson LE, Abrego AI, Barrows DA, Burner AW () Blade deflection measurements of a full-scale UHA rotor by: 6.

This work establishes a validated reference model similar to the UHA for research activities on rotor blade design and analysis of rotor-fuselage coupling mechanisms. The focus is on structural. A new, actively deployable trailing edge flap system is introduced and an experimental investigation is undertaken to determine its effects on the disturbances created during blade–disturbance interactions (BDI), with blade–vortex interaction (BVI) alleviation being the ultimate by: 7.

Passive approach of controlling twist in composite tilt-rotor blades John B. Kosmatka ; Renee C. Lake Proc. SPIESmart Structures and Materials Smart Structures and Integrated Systems, pg (1 May ); doi: / High Load Conditions Measured on a UHA I Maneuvering Flight Kufeld, Robert Bousman, W.

Structural Optimization for Vibratory Loads Reduction of Composite Helicopter Rotor Blades with Advance Geometry Tips Yan, Kuo-An 43, 1 An Aeroelastic Analysis Methodology for Bearingless Main Rotor Helicopters Chopra I.

Typical full-scale helicopter rotor blades have large span to chord ratios on the order of 15– Model scale rotor blades have much smaller aspect ratios for both safety and practical reasons.

Moreover, the planforms can be complex; Fig. 5 is a sketch of several rotor blade shapes. Fig. 5(a) is a UH blade which is used on several by: [15] H.

Yeo and W. J ohnson, Assessment of comprehensive analysis calculation of airloads on helicopter rotors, J. of Aircraft, 42 (5),[16] A. Datta and I. Chopra, Validation of structural and aerodynamic modeling using UHA airloads program data, J.

of the American Helicopter Society, pp.J anuary ple of the Figure of Merit results for the scale UHA rotor and figure b compares the calculations with measurements for the four rotor sets. For the individual tests, the accuracy varied from m = for the full-scale CHB main rotor to m = for the model-scale UHA main Size: 10MB.

Program Executive Office Aviation Layne Merritt () Iris Prueitt () A Automatic Test Equipment (ATE) for Non-Destructive Test/Non-Destructive Inspection/Non- Destructive Evaluation/Non-Destructive Test Evaluation (NDT/NDI/NDE/NDTE) of Composite Rotor Blades A High Integrity, Low Cost Rotor State Measurement System.

Some of the modeling and analysis challenges are 1) aerodynamic interaction between multiple lifting/propulsive devices (e.g., may involve rotors/propellers and each rotor/propeller has blades), 2) complicated load paths of each lifting and propulsive device, 3) aeroelastic effects between the lifting/propulsive devices and supporting.

The UHA-A/L recapitalization and rebuild program will be applied to a number of older aircraft while awaiting introduction of UHM aircraft into the fleet. PROGRAM STATUS • 1QFY UHM multiyear VII award • 2QFY UHM first-unit equipped • 4QFY UHM upgrade first flight • 4QFY UHM upgrade customer test.

The general trend is that even with 3 or 4 blades, the lowest number of blades is favorable for the rotor figure of merit in the range of max hover rotor loading. Boeing (Ref. (17|), gives an opposite trend in comparing 3-and 4-blade rotors having the same solidity of the 4-blade rotor seems to be clearly favorable (Fig.

18). During the s, NASA and the U.S. Army put together a plan for multiple rotor tests with extensive airloads measurements on the envisioned three pillars to this program: a model-scale rotor tested in a wind tunnel, a full-scale rotor tested in flight, and that same rotor tested in the by Foot Wind UHA rotor was selected for the first set of tests, since it.

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Labview Student Edition: Inc National Instruments $ Modal Analysis Of Uha Instrumented Rotor Blades: Nation $ Envío gratis. In Situ Instruments: National Aeronautics And Space Adm Na $ Wind tunnel measurements of the rotor trim, blade airloads, and structural loads of a full-scale UH A Black Hawk main rotor are compared with calculations obtained using the comprehensive rotorcraft analysis CAMRAD II and a coupled CAMRAD II/OVERFLOW 2 analysis.

A speed sweep at constant lift up to an advance ratio of and a thrust sweep. UH Airloads Program Tutorial. NASA Technical Reports Server (NTRS) Bousman, William G. From the fall of to late winter ofNASA Ames and the U.S. Army flew a flight test program using a UHA helicopter with extensive instrumentation on the rotor and blades, including pressure this period, approximately 30 flights were made, and data.

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This book is a compilation of peer-reviewed papers from the Asia-Pacific International Symposium on Aerospace Technology (APISAT ). The symposium is a common endeavour between the four national aerospace societies in China, Australia, Korea and Japan, namely, the Chinese Society of Aeronautics and Astronautics (CSAA), Royal Aeronautical Society Australian Division (RAeS.

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