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.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen


    Exportieren, teilen und zitieren



    Space Shuttle Orbiter Trimmed Center-of-Gravity Extension Study

    W. I. Scallion / W. P. Phillips | NTIS | 1985


    Space Shuttle orbiter trimmed center-of-gravity extension study

    Scallion, W. I. / Phillips, W. P. | NTRS | 1985



    Recent aerothermodynamic flight measurements during Shuttle Orbiter re-entry

    Bertin, John J. / Bouslog, Stanley A. / Wang, Kuo-Chi et al. | AIAA | 1996


    Space shuttle orbiter test flight series

    Garrett, D. / Gordon, R. / Jackson, R. B. | NTRS | 1977