The implementation of procedures used to calculate the attitude of a rocket from its transmitted gyroscopic roll, pitch, and yaw signals is discussed. The differences and the angular conversions of the output from various inertial attitude systems are presented. Also, a synopsis of the mathematical analysis used to compute attitude is presented. In addition, analyses and data reduction techniques are developed to determine the attitude of the Ute-Tomahawk rocket A09.209-1, fired 16 April 1973 at White Sands Missile Range, New Mexico.
Attitude Determination Techniques for Rockets with Inertial Measuring Systems
1974
69 pages
Report
Keine Angabe
Englisch
Attitude Control Systems for Sounding Rockets
NTIS | 1967
|Wiley | 2011
|Attitude control systems for sounding rockets
AIAA | 1970
|ATTITUDE CONTROL FOR SPINNING SOUNDING ROCKETS
AIAA | 1967
|Attitude determination of missiles and rockets using a laser system
Tema Archiv | 1977
|