GB1332911A - Roll stabilised missile - Google Patents

Abstract

1332911 Missiles MESSERSCHMITTBOLKOW-BLOHM GmbH 21 Dec 1970 [23 Dec 1969] 60666/70 Heading F3A [Also in Division G1] A gyroscopic device 5 in a self-propelled remote controlled missile which is non-stabilized by spoilers, has a rotor 13 gimballed in two frames 11, 12 for movement about three axes 14, 17, 24, a stop 16 limiting the angular movement of frame 11 with respect to the frame 12, so that if the missile climbs at an excessive angle (e.g. above 45 degrees) the frame 12 is engaged by stop 16 and precesses 180 degrees about axis 14, aligned with the longitudinal axis of the missile, thus simulating for the missile an inverted rolling position by operating a changeover switch, comprising semicircular contact paths 22, 23 mounted on the missile housing 15 and a sliding contact 21 fixed to the frame 12, any control signal subsequently received by the missile being thus effectively inverted to ensure that guidance failure does not cause the missile to return to the launch point. Alternatively as in Fig. 3 (not shown) a device (25) may lock the frames 11, 12 to the housing after precession of the frame 12 thus causing the missile to perform a continuous roll to thereby nullify any erroneous guidance signal.