An aircraft control system may include an engine control subsystem, a flight control subsystem, a processor, and a tangible, non-transitory memory. The tangible, non-transitory memory may be configured to communicate with the processor, and the tangible, non-transitory memory may have instructions stored thereon that, in response to execution by the processor, cause the aircraft control system to perform various operations. The various operations may include controlling, by the processor, the engine control subsystem and controlling, by the processor, the flight control subsystem. That is, a single processor (or a single set of processors) may control both the engine control subsystem and the flight control subsystem.

There is provided a system for controlling at least first and second engines of an aircraft, comprising a common controlling unit configured to convert data representative of a thrust command transmitted by an actuating element controllable by a pilot or by an auto-throttle of the aircraft, into: (a) at least one first command usable by a controller of the first engine for controlling its operation based at least on said first command, and (b) at least one second command usable by a controller of the second engine for controlling its operation based at least on said second command, wherein said common controlling unit is operable to perform said conversion based at least on data representative of a level of operability of each engine, thereby making each engine to either comply with said thrust command or to operate differently from said thrust command, based at least on its level of operability.

Disclosed is a throttle quadrant arrangement having a throttle lever which is independently mechanically connected to different Rotary Variable Differential Transformers (RVDTs). A friction lever selectively creates and releases friction from the throttle lever to enable it to be selectively positioned. The system is configured such that the mechanical connections existing between the throttle lever and the RVDTs are shielded from the friction created by the friction lever.

Disclosed is a throttle quadrant arrangement having a throttle lever which is independently mechanically connected to different Rotary Variable Differential Transformers (RVDTs). A friction lever selectively creates and releases friction from the throttle lever to enable it to be selectively positioned. The system is configured such that the mechanical connections existing between the throttle lever and the RVDTs are shielded from the friction created by the friction lever.

A power generation controller of an aircraft includes a low-temperature start-up control section and a power generation control section. When it is determined that an oil temperature of a hydraulic actuator configured to change an operation position of a speed change element of a hydraulic transmission satisfies a predetermined low-temperature condition when starting up an aircraft engine, the low-temperature start-up control section sets a power generator to a power non-generating state and controls the hydraulic actuator such that the speed change element is positioned at an acceleration side of a median in a speed change range. When it is determined that the oil temperature satisfies a predetermined low-temperature start-up completion condition, the power generation control section sets the power generator to a power generating state and controls the hydraulic actuator in accordance with a rotational frequency of the aircraft engine.

A power generation controller of an aircraft includes a low-temperature start-up control section and a power generation control section. When it is determined that an oil temperature of a hydraulic actuator configured to change an operation position of a speed change element of a hydraulic transmission satisfies a predetermined low-temperature condition when starting up an aircraft engine, the low-temperature start-up control section sets a power generator to a power non-generating state and controls the hydraulic actuator such that the speed change element is positioned at an acceleration side of a median in a speed change range. When it is determined that the oil temperature satisfies a predetermined low-temperature start-up completion condition, the power generation control section sets the power generator to a power generating state and controls the hydraulic actuator in accordance with a rotational frequency of the aircraft engine.

A method of estimating a parameter of a fluid flowing in a passage includes: having a plurality of instruments operable to measure one or more fluid properties flowing in the passage, the plurality of instruments being disposed in the passage and arranged within a common measurement plane; assigning a stream tube to each instrument, each stream tube represents a region of space in the common measurement plane within the passage and each stream tube surrounds one of the plurality of instruments, the stream tubes together correspond to the cross-sectional shape and area of the passage in the common measurement plane; measuring the one or more fluid properties using the instruments to obtain one or more measured values for each stream tube; using the measured value(s) for each stream tube to calculate a derived value for each stream tube; and summing the derived values across all of the stream tubes.

A method of estimating a parameter of a fluid flowing in a passage includes: having a plurality of instruments operable to measure one or more fluid properties flowing in the passage, the plurality of instruments being disposed in the passage and arranged within a common measurement plane; assigning a stream tube to each instrument, each stream tube represents a region of space in the common measurement plane within the passage and each stream tube surrounds one of the plurality of instruments, the stream tubes together correspond to the cross-sectional shape and area of the passage in the common measurement plane; measuring the one or more fluid properties using the instruments to obtain one or more measured values for each stream tube; using the measured value(s) for each stream tube to calculate a derived value for each stream tube; and summing the derived values across all of the stream tubes.

An aircraft control system includes: a motor with a rotating shaft; a pilot control input; a linear actuator connecting the pilot control input to the rotating shaft; a sensor identifying a position of the pilot control input; and a transmitter transmitting the pilot control input position to a controller, the controller adjusting an aircraft performance device based on the received pilot control input position.

An aircraft control system includes: a motor with a rotating shaft; a pilot control input; a linear actuator connecting the pilot control input to the rotating shaft; a sensor identifying a position of the pilot control input; and a transmitter transmitting the pilot control input position to a controller, the controller adjusting an aircraft performance device based on the received pilot control input position.