Abstract: A system and methods for non-optimal actuator detection are disclosed. A fluid valve controlling a fluid flow to a first actuator is activated, and the fluid valve is controlled to move the first actuator from an initial position to a first position and back to the initial position during a test interval. A measured valve position of the fluid valve is measured during the test interval, and a measured valve travel is calculated based on the measured valve position at an end of the test interval. A health status of the first actuator is determined based on the measured valve travel and an expected valve travel.

Abstract: A system and methods for wraparound signal monitoring are presented. An initial signal is transmitted through a signal path to provide a transmitted signal, and the transmitted signal is transmitted through an inverse signal path to provide an inverse signal. The inverse signal path comprises an inverse of the signal path. The transmitted signal is filtered to provide a filtered signal, and the filtered signal is transmitted through the inverse signal path to provide an inverse filtered signal. The inverse signal, the inverse filtered signal, and the initial signal are compared to provide a signal status.

Abstract: Systems to manage servo controls are disclosed. In some embodiments servo controls may implemented in systems to deflect control surfaces in aircraft.

Abstract: A system and methods for non-optimal actuator detection are disclosed. A fluid valve controlling a fluid flow to a first actuator is activated, and the fluid valve is controlled to move the first actuator from an initial position to a first position and back to the initial position during a test interval. A measured valve position of the fluid valve is measured during the test interval, and a measured valve travel is calculated based on the measured valve position at an end of the test interval. A health status of the first actuator is determined based on the measured valve travel and an expected valve travel.

Abstract: Systems to manage servo controls are disclosed. In some embodiments servo controls may implemented in systems to deflect control surfaces in aircraft.

Abstract: Herein disclosed is an actuator control apparatus, comprising primary control means for producing a control signal used to control an operation of an actuator in accordance with an instruction signal indicative of an operation of the actuator, secondary control means for producing a control signal in accordance with the instruction signal; and switching means for selectively switching one of the primary control means and the secondary control means to the other, and in which the secondary control means is less in the number of functions than the primary control means, and each of components constituting the secondary control means is easier in fault verification than a component constituting the primary control means the most difficult in fault verification among all of components constituting the primary control means.

Abstract: A backup system is provided that has a local electric motor and pump for some or all of hydraulic actuators. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system and the fluid flow to the chambers is controlled by a servo valve. If the hydraulic system fails, the electronic controller detects the failure by observing the signal indicative of the pressure from the pressure sensor, and the controller powers the local hydraulic pump to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve.

Abstract: Herein disclosed is an actuator control apparatus, comprising primary control means for producing a control signal used to control an operation of an actuator in accordance with an instruction signal indicative of an operation of the actuator, secondary control means for producing a control signal in accordance with the instruction signal; and switching means for selectively switching one of the primary control means and the secondary control means to the other, and in which the secondary control means is less in the number of functions than the primary control means, and each of components constituting the secondary control means is easier in fault verification than a component constituting the primary control means the most difficult in fault verification among all of components constituting the primary control means.

Abstract: A backup system is provided that has a local electric motor and pump for some or all of hydraulic actuators. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system and the fluid flow to the chambers is controlled by a servo valve. If the hydraulic system fails, the electronic controller detects the failure by observing the signal indicative of the pressure from the pressure sensor, and the controller powers the local hydraulic pump to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve.

Abstract: A backup system is provided that has a local electric motor and pump for some or all of the hydraulic actuators on an aircraft. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system and the fluid flow to the chambers is controlled by a servo valve. If the hydraulic system fails, the electronic controller detects the failure by observing the signal indicative of the pressure from the pressure sensor, and the controller powers the local hydraulic pump to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve.

Abstract: A backup system is provided that has a local electric motor and pump for some or all of the hydraulic actuators on an aircraft. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system and the fluid flow to the chambers is controlled by a servo valve. If the hydraulic system fails, the electronic controller detects the failure by observing the signal indicative of the pressure from the pressure sensor, and the controller powers the local hydraulic pump to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve.

Abstract: Herein disclosed is an actuator control apparatus, comprising primary control means for producing a control signal used to control an operation of an actuator in accordance with an instruction signal indicative of an operation of the actuator, secondary control means for producing a control signal in accordance with the instruction signal; and switching means for selectively switching one of the primary control means and the secondary control means to the other, and in which the secondary control means is less in the number of functions than the primary control means, and each of components constituting the secondary control means is easier in fault verification than a component constituting the primary control means the most difficult in fault verification among all of components constituting the primary control means.