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 y 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.
Emergency Control Aircraft System Using Thrust Modulation
1997
8 pages
Report
Keine Angabe
Englisch
Aircraft , Government Inventions for Licensing , Patents , Patent applications , Aircraft control , Electronic control , Engine control , Error signals , Feedback control , Air traffic control , Aircraft engines , Damping , Digital systems , Emergencies , Modulation , Multiengine vehicles , Propulsion , Servomechanisms , Thrust
System for realizing emergency control of aircraft by controlling engine thrust and aircraft
Europäisches Patentamt | 2021
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