Missile having reduced mass guidance system

Details Missile having reduced mass guidance system Missile having reduced mass guidance system

1984-06-11

1986-07-15

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

102476, F41G 700, F42B 1310

Patent

active

046001662

ABSTRACT:
A guided projectile (11) is provided with a gyroscope (29) having a spherical rotor (41). The rotor (41) is supported at its outer spherical surface by a stator (42) using fluid bearing techniques. The stator (42) is fixed to the projectile's housing (38) so that the gyroscope (29) is operated in a strapdown mode.
The structure of the gyroscope (29) and particularly the stator (42) places very little material along its center axis of the projectile (11). This is particularly useful where the projectile's warhead (17) functions by squirting a stream (25) of metal through a target's armor, and any material in the way of the stream (25) would tend to diminish the lethality of the projectile (11). The spherical configuration of the rotor (41) and the use of the stator (42) as a support bearing also provides a method of supporting the rotor (41) during conditions of high acceleration which are experienced in cannon launch of the projectile (11). Other advantages include light weight, low cost and high reliability.

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patent: 4309005 (1982-01-01), McLean
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