Guided missile using fluidic sensing and steering

Details Guided missile using fluidic sensing and steering Guided missile using fluidic sensing and steering

1974-10-08

1976-09-07

Pendegrass, Verlin R.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

244 322, F42B 1518

Patent

active

039790851

ABSTRACT:
A missile using fluidic sensors for determination of net aerodynamic force nd moment on the missile. The force and moment thus determined are processed and summed by fluidic amplifiers and integrators to provide control signals for fluidic thrusters or other steerers for the missile. The sensors are diametrically opposed pairs of pressure taps located axially and circumferentially in the missile skin. Net aerodynamic force on the missile is taken as the algebraic sum from all the sensors in a linear fluidic summer, and net aerodynamic moment is taken from the proportional sum of the sensors in accordance with their position along the axis of the missile. This proportional sum is made in a fluidic vortex summer.

REFERENCES:
patent: 2951659 (1960-09-01), Yoler
patent: 3113520 (1963-12-01), Geissler et al.
patent: 3374966 (1968-03-01), Howard
patent: 3502285 (1970-03-01), Gambill

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