The Spinning Rocket Attitude Control (SPINRAC) system for guidance of exoatmospheric sounding rockets is described. The main objective for this system is the impact dispersion reduction making it possible to launch apogees of about 1000 km at launch sites with small impact areas. The SPINRAC main features are the low gas consumption and short guidance time, both contributing to higher apogee altitudes. Typically 20 degrees of repointing and damping of 10 degrees half cone angle is performed in less than 20 s. The SPINRAC is easily adaptable to other applications. The standard system, its components and the first flights are described.
SPINRAC System: Control of Exoatmospheric Vehicles
1991
5 pages
Report
No indication
English
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