Limiting aircraft vertical acceleration response

Details Limiting aircraft vertical acceleration response Limiting aircraft vertical acceleration response

1985-11-18

1988-11-22

Lall, Parshotam S.

Boots, shoes, and leggings

318584, 244181, G05D 106

Patent

active

047870427

ABSTRACT:
The presently-disclosed invention utilizes sensed pitched rate and sensed vertical acceleration to prevent aberrant pitch rate command outputs as a function of lead compensated sensed acceleration, controlling the vertical acceleration by sensing when a maximum is approached. When the lead compensated acceleration exceeds a first predetermined acceleration factor, the presently-sensed pitch rate replaces the pre-programmed maximum pitch rate factor as the temporary maximum rate, to temporarily prevent additional vertical acceleration due to increasing pitch rate. This apparatus requires no airspeed input and does not interfere with flight performance characteristics during normal flight operations, allowing higher torque servos to be used, and thus improves overall performance.

REFERENCES:
patent: 3510090 (1970-05-01), Falkner et al.
patent: 3510092 (1970-05-01), Hendrick et al.
patent: 3578269 (1971-05-01), Kramer et al.
patent: 3801049 (1974-04-01), Simpson et al.
patent: 4378518 (1983-03-01), Nixon
Burns, "Attitude and Acceleration Peformance in the Flight Control System", 1983, IEEE Aerospace, pp. 8.2.1-8.2.4.

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