Control system is unique in that neither rate gyros nor inertial platform are used for payload de-spin or sun acquisition; direction cosines to solar vector and to earth's magnetic vector are measured by solar cells and two-axis magnetometer; attitude errors and vehicle rates are electronically computed from sensors and used as inputs for control system; analog simulation indicates that limit cycle errors of approximately plus or minus 1 arcsec about solar vector are achievable.
Gyroless solar pointing attitude control system for aerobee sounding rocket
J Spacecraft Rockets
Journal of Spacecraft and Rockets ; 4 , n 11
1967
5 pages
Article (Journal)
English
© Metadata Copyright Elsevier B. V. All rights reserved.