In-Flight Vibration Environment of the NASA F-15B Flight Test Fixture

Corda, Stephen and Franz, Russell J. and Blanton, James N. and Vachon, M. Jake and DeBoer, James B. (2002) In-Flight Vibration Environment of the NASA F-15B Flight Test Fixture. Technical Report NASA/TM-2002-210719, Research Engineering, NASA Dryden Flight Research Center.

Full text available as: PDF - Requires Adobe Acrobat Reader or other PDF viewer.

Abstract

Flight vibration data are analyzed for the NASA F-15B/Flight Test Fixture II test bed. Understanding the in-flight vibration environment benefits design and integration of experiments on the test bed. The power spectral density (PSD) of accelerometer flight data is analyzed to quantify the in-flight vibration environment from a frequency of 15 Hz to 1325 Hz. These accelerometer data are analyzed for typical flight conditions and maneuvers. The vibration data are compared to flight-qualification random vibration test standards. The PSD levels in the lateral axis generally are greater than in the longitudinal and vertical axes and decrease with increasing frequency. At frequencies less than approximately 40 Hz, the highest PSD levels occur during takeoff and landing. Peaks in the PSD data for the test fixture occur at approximately 65, 85, 105-110, 200, 500, and 1000 Hz. The pitch-pulse and 2-g turn maneuvers produce PSD peaks at 115 Hz. For cruise conditions, the PSD level of the 85-Hz peak is greatest for transonic flight at Mach 0.9. From 400 Hz to 1325 Hz, the takeoff phase has the highest random vibration levels. The flight-measured vibration levels generally are substantially lower than the random vibration test curve.

EPrint Type:	NASA Technical Memorandum
Keywords:	F-15B flight test fixture, Flight test, Power spectral density, Random vibration, Vibration flight data
Subjects:	Aircraft/Project: F-15B (01 - 09) Aeronautics: (05) Aircraft Design, Testing And Performance
ID Code:	35
Deposited On:	01 June 2004
Additional Information:	31 pages.