Fan controller (1) for a modular power supply having a fan (13). An output (8) is provided for transmitting control signals to the fan (13) for controlling fan speed. A plurality of sensor modules (20) are associated with a respective module (11,6,7) of the modular power supply. Each sensor module (20) includes a temperature detecting circuit comprising a sensor for sensing temperature variations in the respective module (11,6,7), a fan control circuit (30) galvanically isolated from the temperature detecting circuit for outputting a control signal to the output (8) for controlling the fan (13), and an optocoupler (10,9) for transferring an output signal from the temperature detecting circuit (20) to the fan control circuit (30) for generating the control signal.

A system includes a network of a plurality of sensing/control/identification devices distributed throughout a machine, each of the sensing/control/identification devices associated with at least one sub-system component of the machine and operable to communicate through a plurality of electromagnetic signals. Shielding surrounds at least one of the sensing/control/identification devices to contain the electromagnetic signals proximate to the at least one sub-system component. A communication path is integrally formed in a component of the machine to route a portion of the electromagnetic signals through the component and a remote processing unit operable to communicate with the network of the sensing/control/identification devices through the electromagnetic signals, wherein at least a portion of the sensing/control/identification devices comprise a wide band gap semiconductor device and wherein at least a portion of the sensing/control/identification devices comprise an on-chip antenna.

The present disclosure concerns the communication between electronic systems in an aircraft subassembly such as a propulsion unit. This communication is at least partially carried out by light signals transmitted through at least one interior volume of the sub-assembly, this interior volume defining an optical channel. To this end, at least one of these systems includes an emitter arranged to emit a light signal and modulate it depending on data to be transmitted generated by this system, and at least one other of these systems includes at least one receiver capable of receiving this light signal.

A system and a method include an engine having one or more vanes. An actuator is coupled to the one or more vanes. The actuator is configured to move the one or more vanes between different positions. A control unit is coupled to the actuator. The control unit is configured to operate the actuator to move the one or more vanes between the different positions. The control unit is disposed on or within the engine.

A communication adapter of a gas turbine engine of an aircraft includes a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine. The communication adapter also includes a memory system and processing circuitry configured to receive one or more configuration items from the offboard system, confirm an authentication between the communication adapter and the engine control, apply a cryptographic algorithm using one or more parameters received and cryptographic information to decrypt the one or more configuration items, wherein the cryptographic information includes a combination of received cryptographic information and previously stored cryptographic information, and transfer the one or more configuration items to the engine control based on the authentication.

The method can include generating a first duty cycle value for the PWM; monitoring a current value of a parameter; generating a duty cycle limit value for the PWM, including activating more than one duty cycle limit functions based on corresponding activation conditions, the corresponding activation conditions based on the current value of the parameter, each of the more than one duty cycle limit functions generating a corresponding duty cycle limit subvalue when the corresponding activation conditions are met, and setting the duty cycle limit value to a sum of the generated duty cycle limit subvalues; setting a second duty cycle value for the PWM, as the first duty cycle value or as the duty cycle limit if the first duty cycle value exceeds the duty cycle limit; and, applying the PWM at the second duty cycle value to the valve.

A communication adapter of a gas turbine engine of an aircraft includes a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine. The communication adapter also includes a memory system and processing circuitry configured to receive one or more configuration items from the offboard system, apply a cryptographic algorithm using one or more parameters received and cryptographic information to decrypt the one or more configuration items, wherein the cryptographic information includes a combination of received cryptographic information and previously stored cryptographic information, and transfer the one or more configuration items to the engine control after applying the cryptographic algorithm.

A communication adapter of a gas turbine engine of an aircraft includes a communication interface configured to wirelessly communicate with an offboard system and to communicate with an engine control of the gas turbine engine. The communication adapter also includes a memory system and processing circuitry configured to receive an engine control update request from the offboard system, confirm an authentication between the communication adapter and the engine control, transfer one or more configuration items received at the communication adapter from the offboard system to the engine control based on the authentication, and transmit an update completion confirmation of the engine control from the communication adapter to the offboard system based on a confirmation message from the engine control.

A system and a method include an engine having one or more vanes. An actuator is coupled to the one or more vanes. The actuator is configured to move the one or more vanes between different positions. A control unit is coupled to the actuator. The control unit is configured to operate the actuator to move the one or more vanes between the different positions. The control unit is disposed on or within the engine.

A full authority digital engine controller (FADEC) based system is also disclosed. The system includes a processor, and a tangible, non-transitory memory configured to communicate with the processor, the tangible, non-transitory memory having instructions stored thereon that, in response to execution by the processor, cause the FADEC to perform operations. The operations may include measuring a first temperature at a first sensor disposed at a first known location of an engine, measuring a second temperature at a second sensor disposed at a second known location of the engine, and estimating at least one of a stress or a strain of a part or component in the engine based on the first temperature and the second temperature. The system may control fuel flow and/or other engine effectors during a thrust transient to limit the estimated stress or the estimated strain of the component from exceeding a predetermined threshold.