초록 ▼

A digital longitudinal Aircraft Propulsion Control (APC) system of a multiengine aircraft is provided by engine thrust modulation in response to comparing an input flightpath angle signal .gamma.c from a pilot thumbwheel or an ILS system with a sensed flightpath angle .gamma. to produce an error sig

A digital longitudinal Aircraft Propulsion Control (APC) system of a multiengine aircraft is provided by engine thrust modulation in response to comparing an input flightpath angle signal .gamma.c from a pilot thumbwheel or an ILS system with a sensed flightpath angle .gamma. to produce an error signal .gamma.e that is then integrated (with reasonable limits) to generate a drift correction signal to be added to the error signal .gamma.e after first subtracting a lowpass filtered velocity signal Vel.sub.f for phugoid damping. The output error signal is multiplied by a constant to produce an aircraft thrust control signal ATC of suitable amplitude to drive a throttle servo for all engines, each of which includes its own full-authority digital engine control (FADEC) computer. An alternative APC system omits sensed flightpath angle feedback and instead controls the flightpath angle by feedback of the lowpass filtered velocity signal Vel.sub.f which also inherently provides phugoid damping. The feature of drift compensation is retained.

대표청구항 ▼

[ What is claimed is:] [1.] An emergency control servo system for using thrust modulation for longitudinal control of a multiengine aircraft having a throttle servo for control of all engines in unison, comprisingmeans for independently entering a flightpath angle command to be maintained and produc

[ What is claimed is:] [1.] An emergency control servo system for using thrust modulation for longitudinal control of a multiengine aircraft having a throttle servo for control of all engines in unison, comprisingmeans for independently entering a flightpath angle command to be maintained and producing a flightpath angle command signal .gamma.c,means for continually sensing said aircraft flightpath angle and producing a flightpath angle signal .gamma.,means for producing a flightpath error signal .gamma.e as a fiction of the difference between said flightpath angle command .gamma.c and said sensed aircraft flightpath angle .gamma.,means for forming a limited integral as a function of said error signal andmeans for adding said integral to said error signal for producing an output control signal for said throttle servo, thereby to adjust thrust of said engines to reduce said error signal .gamma.e toward zero.