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Determination of shuttle orbiter center of gravity from flight measurementsFlight measurements of pitch, yaw, and roll rates and the resultant rotationally induced linear accelerations during three orbital maneuvers on Shuttle mission space transportation system (STS) 61-C were used to calculate the actual orbiter center-of-gravity location. The calculation technique reduces error due to lack of absolute calibration of the accelerometer measurements and compensates for accelerometer temperature bias and for the effects of gravity gradient. Accuracy of the technique was found to be limited by the nonrandom and asymmetrical distribution of orbiter structural vibration at the accelerometer mounting location. Fourier analysis of the vibration was performed to obtain the power spectral density profiles which show magnitudes in excess of 10(exp 4) ug (sup 2)/Hz for the actual vibration and over 500 ug (sup 2)/Hz for the filtered accelerometer measurements. The data from this analysis provide a characterization of the Shuttle acceleration environment which may be useful in future studies related to accelerometer system application and zero-g investigations or processes.
Document ID
19910006745
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Hinson, E. W. (ST Systems Corp. Hampton, VA., United States)
Nicholson, J. Y. (Vigyan Research Associates, Inc., Hampton VA., United States)
Blanchard, R. C. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
January 1, 1991
Subject Category
Spacecraft Design, Testing And Performance
Report/Patent Number
NAS 1.15:102627
NASA-TM-102627
Accession Number
91N16058
Funding Number(s)
PROJECT: RTOP 506-40-91-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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