초록 ▼

The directions of travel of an inner and an outer loop actuator are monitored for movement in opposite directions within selected ranges and the outer loop actuator is disabled under selected conditions. These conditions may include movement of both the inner and outer loop actuators in opposite dir

The directions of travel of an inner and an outer loop actuator are monitored for movement in opposite directions within selected ranges and the outer loop actuator is disabled under selected conditions. These conditions may include movement of both the inner and outer loop actuators in opposite directions, any one of which has been detected moving at a rate greater than a selected rate or to a position outside a selected range. The invention is particularly suited for an aircraft trim actuator shutdown monitor system.

대표청구항 ▼

Apparatus for selectively disabling the trim actuator of an aircraft outer loop axis control channel having an inner loop stability augmentation system (SAS) actuator which in combination with the trim actuator maintains aircraft attitude in an associated control axis, each actuator capable of recip

Apparatus for selectively disabling the trim actuator of an aircraft outer loop axis control channel having an inner loop stability augmentation system (SAS) actuator which in combination with the trim actuator maintains aircraft attitude in an associated control axis, each actuator capable of reciprocating motion within a related range of position values, and each having a position sensor for providing a signal indicative of the actual actuator position value in the range, the rate of change of position and direction of travel of the trim actuator determinating the position and direction of travel of the SAS actuator to provide, in combination, supportive effect on the aircraft attitude in the associated axis, the apparatus comprising: direction indicating means, responsive to each actuator position signal, for providing a trim actuator direction signal indicative of the direction of travel of the trim actuator at a rate of change of position, and for providing a SAS actuator direction signal indicative of the direction of travel of the SAS actuator within a selected range of SAS actuator position values; opposite direction detector means, responsive to said direction indicating means, for providing a trim actuator disable signal in response to the simultaneous presence of said trim actuator direction signal and said SAS actuator direction signal indicating directions of travel having opposing effects on the aircraft attitude in the control axis; and means for disabling operation of the trim actuator in response to the presence of said trim actuator disable signal. A method for monitoring and selectively disabling a trim actuator in an aircraft outer control loop having an inner control loop stability augmentation system (SAS) actuator which in combination with the trim actuator maintains aircraft attitude in an associated control axis during flight, each actuator capable of reciprocating motion within a related range of position values, and each having a position sensor for providing a signal indicative of the actual actuator position value in the range, the rate of change of position and direction of travel of the trim actuator determining the position and direction of travel of the SAS actuator to provide, in combination, supportive effect on the aircraft attitude in the associated axis, and the aircraft having a coupled flight director system (CFD), comprising the steps of: determining the value of the rate of change of position of the trim actuator, defining a selected range of trim actuator position rate values, comparing the determined trim actuator position rate value to said selected range of rate values and establishing in response to a determined rate value magnitude within said selected range of rates, a trim actuator direction state indicative of the direction of travel of the trim actuator, defining a selected range of SAS actuator position values, comparing the magnitude of the SAS actuator position signal value to said selected range of position values and establishing, in response to a position signal value magnitude within said selected range of positions, a SAS actuator direction state indicative of the direction of travel of the SAS actuator within said selected range of SAS actuator position values. detecting the simultaneous presence of said trim actuator direction state and said SAS actuator direction state indicating directions of travel having opposing effects on the aircraft attitude in the control axis, and providing a trim actuator disable signal in response thereto, disabling operation of the trim actuator in response to the presence of said trim actuator disable signal.