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Record 1 of 56
Identification of a coupled flapping/inflow model for the PUMA helicopter from flight test data
Author and Affiliation:
Du Val, Ronald(Advanced Rotorcraft Technology, Inc., Mountain View, CA, United States)
Bruhis, Ofer(Advanced Rotorcraft Technology, Inc., Mountain View, CA, United States)
Green, John(Advanced Rotorcraft Technology, Inc., Mountain View, CA, United States)
Abstract: A model validation procedure is applied to a coupled flapping/inflow model of a PUMA helicopter blade. The structure of the baseline model is first established. Model structure and flight test data are checked for consistency. Parameters of the model are then identified from the flight test data.
Publication Date: Jan 01, 1989
Document ID:
19900025712
(Acquired Nov 28, 1995)
Accession Number: 90A12767
Subject Category: AIRCRAFT STABILITY AND CONTROL
Document Type: Journal Article
Publication Information: Vertica (ISSN 0360-5450); 13; 3, 19; 267-280
Publisher Information: United Kingdom
Financial Sponsor: NASA; United States
Organization Source: Advanced Rotorcraft Technology, Inc.; Mountain View, CA, United States
Description: 14p; In English
Distribution Limits: Unclassified; Publicly available; Unlimited
Rights: Copyright
NASA Terms: AIRCRAFT MODELS; FLIGHT TESTS; HELICOPTER PERFORMANCE; ROTARY WINGS; ROTOR AERODYNAMICS; SYSTEM IDENTIFICATION; AIRFOIL OSCILLATIONS; COUPLED MODES; FLIGHT SIMULATION; MATHEMATICAL MODELS; PARAMETER IDENTIFICATION
Imprint And Other Notes: Vertica (ISSN 0360-5450), vol. 13, no. 3, 1989, p. 267-280. Research supported by NASA.
Miscellaneous Notes: Research supported by NA
Availability Source: Other Sources
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