Aspects relate to systems and methods for folding wings on an aircraft. An exemplary system includes a blended wing body, where the blended wing body includes a main body and at least a wing, a hinge located on the at least a wing and configured to allow folding of the at least a wing, an actuation system configured to fold the at least a wing, and a controller configured to control the at least an actuation system.

Technology for operating an engine smoothly is provided. In an aircraft propulsion system, a controller causes at least a first engine among the plurality of engines to be stopped and causes a second engine, which has not been stopped, to be operated when an aircraft is flying in a prescribed flight mode and causes the first engine to be operated and causes the second engine to be stopped when a detector detects that the temperature related to the first engine is less than or equal to a first prescribed temperature.

Provided is an abnormality detection device for a rotary wing unit. The rotary wing unit includes a plurality of rotary wings that is coaxially disposed. The abnormality detection device includes a controller configured to acquire at least one of a correlation at the time of normal operation between operation parameters related to the rotary wings and a correlation at the time of abnormal operation between the operation parameters and detect abnormality of the rotary wing unit, based on a correlation at the time of actual operation between the operation parameters and at least one of the correlation at the time of normal operation and the correlation at the time of abnormal operation.

A monitoring system for monitoring a kinematic coupling between an actuator and an element controlled by the latter includes a first sensor to detect the operative movement of the actuator. A second sensor is designed to detect the actual movement of the controlled element. A computer unit, based on the operative movement of the actuator, determines an anticipated movement of the controlled element and compares this anticipated movement with the actual movement of the controlled element. An error message is emitted when a value of the deviation between the anticipated movement and the actual movement exceeds a predefined threshold value.

A device may receive equipment information, associated with a first equipment, including information associated with anomalies identified based on operational information collected during operation of the first equipment, and messages generated during the operation of the first equipment. The device may receive maintenance information, associated with the first equipment, that identifies one or more part failures associated with one or more equipment parts. The device may identify associations between the one or more part failures and the first equipment information. The device may receive equipment information, associated with a second equipment, including information associated with anomalies identified based on operational information collected during operation of the second equipment, and messages generated during the operation of the second equipment. The device may generate and provide a prediction, associated with a future failure of an equipment part of the second equipment, based on the second equipment information and the associations.

An automated aircraft recovery system is disclosed. In various embodiments, the system includes an interface configured to receive sensor data; and a control mechanism configured to: perform automatically a recovery action that is determined based at least in part on the sensor data. In various embodiments, the control mechanism may determine an expected state of an aircraft, determine whether a state of the aircraft matches the expected state, and in the event the state of the aircraft does not match the expected state, perform the recovery action.

A system, method and device for monitoring an aircraft, including activity taking place within an aircraft and conditions of the aircraft, where one or more a percepting component such as a camera, microphone, or other sensor, is situated at a location within the aircraft from which information may be ascertained. Preferably the component is disguised within the surfaces or instrumentation of the aircraft. The percepting component is connected with a communication mechanism to transmit communications from the system resident within the aircraft to a grounds portion of the system through a communication link, such as a satellite communication link. The system may process the information corresponding with the aircraft condition or activity and generate alerts when a trigger is met or exceeded. The system components on the aircraft may monitor conditions and activity without using or interfering with the aircraft instrumentation, the system using only the aircraft power.

An overall efficiency of an actuator system can be monitored to determine the health of the actuator system. A ratio between the output power of the actuator system and the input power of the actuator system is monitored over time. Degradation of the efficiency of the actuator system may be observed and corrective action taken before failure of the actuator system.

Flight guidance systems and methods that provide an airport selection in response to an EO condition in a single engine plane. The airport selection takes into consideration factors such as optimal approach type, runway length, weather, terrain, remaining battery time, and the like. Additionally, various also generate and display a visual indication of a remaining glide range when the EO condition is happening; the remaining glide range determination is based, at least in part, on terrain.

A torque measurement system determines torque on a shaft by monitoring angular deflection of the shaft under load using phase shift measurements. Calibration of the system uses a defined offset that is determined using a reference operating condition. The offset calibration value is determined for a rotorcraft using the following steps: defining a reference operational condition in which the shaft is rotating, estimating the torque at the reference condition based on aerodynamic knowledge of the rotors coupled to the shaft, operating the shaft at the reference operational condition, capturing sensor data to determine the phase difference at the operational condition, and associating the phase difference and an estimated torque as a calibration value to enable calculation of torque in the torque measurement system.