公开(公告)号：US4032757A

公开(公告)日：1977-06-28

申请号：US507514

申请日：1974-09-19

Applicant: Edward Stuart Eccles

Inventor： Edward Stuart Eccles

IPC: B64D31/06 ,  F02C9/00 ,  G05B9/03 ,  G05B23/02 ,  G06F11/16 ,  G06F15/46 ,  G06F11/08

CPC classification number: G06F11/165 ,  B64D31/06 ,  G05B9/03

Abstract: Control apparatus for controlling an aircraft gas-turbine engine, having two control lanes operated in parallel with one another and each of which is capable of performing the function of the control apparatus individually, includes a computer and a monitor unit associated with each lane for performing checks on the integrity of the components of both lanes. Transducers in each lane sense engine parameter values and pass signals in accordance therewith to the computer that sends control signals to a control unit and thence to an actuator for adjusting engine variables in accordance with engine-thrust requirements. The control unit includes a pair of cam-operated switches that respond to difference in the values of the control signal from each lane indicative of a fault in the lanes and that trigger operation of the monitor unit in each lane. The monitor units disengage the control signals of the computers from the actuator and cause each computer to pass to the monitors the results of signal comparisons it has made involving signals values of each lane, so that the monitor units can determine in which lane the fault lies. The monitor units reconnect to the actuator control signals from a lane that is found to be operating correctly.

公开(公告)号：US4038526A

公开(公告)日：1977-07-26

申请号：US640862

申请日：1975-12-15

Applicant: Edward Stuart Eccles ,  David James Moore

Inventor： Edward Stuart Eccles ,  David James Moore

IPC: G06F19/00 ,  G06F15/46 ,  G06F15/06

CPC classification number: B64D31/12 ,  F02C9/42

Abstract: The disclosure of this invention pertains to a system for optimizing fuel consumption in an aircraft having two engines, wherein a computer is programmed to increase the fuel flow to the engine which, consequent upon a fuel flow perturbation, shows itself to be responsible for the greater acceleration of the aircraft. Direction changes resulting from unequal fuel flows to the engines are compensated for by automatic rudder control, and speed changes resulting from the fuel flow changes are compensated for by automatic speed control also acting on fuel flow, all whereby direction and speed of flight are maintained while fuel consumption is minimized.