Guided missile with variable rate of spin - has tail unit with angle of incidence adjustable to vary spinning speed and spring loaded

摘要

The missile has a tail unit assuming a position forming an angle of incidence so as to cause it to spin abouts its lengthwise axis. During flight, a mechanism alters the angle so as to decrease the speed of spinning. There can be four tail units, two with an incidence angle variable between 6 deg. and 0 deg., while the others are fixed at roughly 6 deg. The variable incidence tail units pivot in sheaths which are initially locked at 6 deg. by bolts, and they are spring-loaded towards the zero position.