Inertially decoupled strapdown system

Details Inertially decoupled strapdown system Inertially decoupled strapdown system

1978-10-16

1981-04-21

Blum, Theodore M.

Aeronautics and astronautics

Missile stabilization or trajectory control

Automatic guidance

364453, F41G 700, F42B 1502, G06F 1550

Patent

active

042628610

ABSTRACT:
The invention comprises a novel strapdown gyro inertial system having a single degree of freedom between it and the vehicle upon which it is mounted. An angular transducer having a low friction bearing is mounted on the vehicle along the vehicle roll axis bearing and supports the strapdown gyros and accelerometers that are skewed with respect to the roll axis. The method of determining the total vehicle attitude employs the gyros so that the vehicle rate around each gyro axis is integrated and combined with the vehicle angular roll to obtain the total attitude. The inertial momentum of the sensor block, electrically enhanced or strictly dependent upon its mass, decouples high acceleration inputs along the free axis and thus reduces the dynamic rate sensing requirement along the free axis. Also the novel configuration of the sensors skewed with respect to the free axis, permits easy calibration of gyro scale factors and other inertial parameters which are characteristics of gyroscopes and accelerometers. The calibration is attainable in the factory or in the field.

REFERENCES:
patent: 3312423 (1967-04-01), Welch
patent: 3414899 (1968-12-01), Buell
patent: 3746281 (1973-07-01), Stripling
patent: 3924824 (1975-12-01), Brodie et al.

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