US 4,787,042 A · Limiting aircraft vertical acceleration response

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.

Claims3

Dependent claims

An autopilot pitch command apparatus having a specified maximum pitch rate control output comprising:

a. first means for receiving a sensed vertical acceleration signal;
b. second means for receiving a sensed pitch rate signal;
c. third means, coupled to said first means, for lead compensating said sensed vertical acceleration signal;
and
d. fourth means, coupled to said second means, and to said third means, for detecting when said lead compensated acceleration signal exceeds the absolute value of a first predetermined factor, and for requiring said autopilot pitch command apparatus to limit as a function of said detection, said pitch control output to said presently-sensed pitch rate as a maximum.

2 more elements

Dependencies are inferred from the claim text.

Limiting aircraft vertical acceleration response

Life of this patent

Limiting aircraft vertical acceleration response

Life of this patent

Abstract

Claims3