Rate estimation by mixing two independent rate signals

Details Rate estimation by mixing two independent rate signals Rate estimation by mixing two independent rate signals

1985-01-25

1987-04-21

Jordan, Charles T.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

F42B 1502

Patent

active

046590358

ABSTRACT:
A method of providing an angular rate signal for attitude control in a mile flight control system by linearly mixing a derived rate signal generated from the measured attitude angle and a simulated rate signal generated from the measured nozzle angle. The derived rate is generated from the differentiation of missile attitude data and the simulated rate is generated by simulating the missile attitude dynamics based on the actual nozzle angle. The derived rate, which is filtered to remove the effects of quantization and noise is dominant at low frequencies. The simulated rate, which is filtered to block low frequencies, is dominant at higher frequencies.

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patent: 3794271 (1974-02-01), Barron et al.
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patent: 4111382 (1978-09-01), Kissinger
patent: 4481586 (1984-11-01), Skutecki

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