Flight 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.
Determination of Shuttle Orbiter Center of Gravity from Flight Measurements
1991
55 pages
Report
No indication
English
Manned Spacecraft , Spacecraft Trajectories & Flight Mechanics , Accelerometers , Aerospace environments , Center of gravity , Gravitational effects , In-flight monitoring , Orbital maneuvers , Roll , Space shuttle orbiters , Space transportation system , Space transportation system flights , Structural vibration , Weightlessness , Yaw , Asymmetry , Bias , Calibrating , Errors , Fourier analysis , Mounting , Position (Location) , Spectra
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