A system and method for adaptively controlling a cooldown cycle of an auxiliary power unit (APU) that is operating and rotating at a rotational speed includes reducing the rotational speed of the APU to a predetermined cooldown speed magnitude that ensures combustor inlet temperature has reached a predetermined temperature value, determining, based on one or more of operational parameters of the APU, when a lean blowout of the APU is either imminent or has occurred, and when a lean blowout is imminent or has occurred, varying one or more parameters associated with the shutdown/cooldown cycle.

The invention relates to a thermoplastic molded part able to constitute a duct of an aerial vehicle or space vehicle, to a method of manufacturing same, and to this duct which comprises said part. For example, provided is a part according to the invention, which has an external surface (2) with symmetry of revolution at least in part, is such that the external surface comprises a multitude of integrally molded depressions (6) which are connected to one another in pairs by crests (7), and that: each of the depressions has a largest transverse dimension D between the adjacently paired crests of between 3 mm and 10 mm, measured in a direction d perpendicular to the crests delimiting each depression, and each of the crests has an apex of transverse width L measured in said direction d, where L<D.

An auxetic bi-stable structure that comprises an auxetic curved shell movable between a first and a second stable position, and a rigid element. At least part of the surface of the auxetic curved shell is joined to the rigid element such that the curved shell is movable with respect to the rigid element between the first and second stable positions.

An aircraft tailcone comprising a tailcone fuselage, a turbomachine, for example an APU, housed inside the tailcone, a ram air intake on the tailcone fuselage for the ingestion of ram air towards the interior of the turbomachine compartment, an inlet flap operable reciprocately from an open position in which ingestion of ram air is allowed, and a closed position in which ram air ingestion is prevented. The ram air intake extends annularly along a perimeter of the tailcone fuselage, and the inlet flap is configured such in its closed position that a surface of the inlet flap is substantially flush with the tailcone fuselage.

A method and apparatus are presented. An active flow control system comprises a flow control valve, a manifold, and a temperature control system. The flow control valve is configured to control a flow of air into the manifold. The manifold is operatively connected to a number of actuators. The temperature control system is configured to heat at least a portion of the flow of air.

A Laminar Inducing Apparatus (LIA) inducing laminar airflow to a turbine engine or a propulsion fan. The LIA produces turbulent-free airflow with a light aerospace structure that can replace single purpose structure in the wing or empennage. Laminar airflow to the propulsion fan or the turbine engine is ensured in a greater number of flight conditions and angles of attack. Active control of flight can be enhanced by the manipulating the turbulent boundary surface as a flight control surface. LIA simply reduces the risk of FOD or bird strike damage. In addition to the engineered, laminar benefits, LIA provides greater safety from ground ingested FOD and more silent vertical take-off and landing. In summary, LIA ensures laminar airflow and acoustic attenuation to a propulsion fan or a turbine engine for a greater number of flight conditions, angles of attack, and from ground ingested FOD during vertical takeoff and landing.

A sealing device for covering an aperture in a wing part of an aircraft. The sealing device has a cover plate covering at least a part of the aperture and having an outer surface delimited by a cover plate edge, and at least one holding device coupled with the cover plate. The at least one holding device having a resilient element, the at least one holding device resiliently holds the cover plate in a distance to an actuation element. The distance is variable in a first direction substantially perpendicular to the outer surface. The at least one holding device holds the cover plate in a substantially fixed spatial alignment in a second direction perpendicular to the first direction. The resilient element urges the cover plate towards the actuation element in a mounted state of the sealing device.

An air intake assembly for an aircraft includes an auxiliary power unit intake that is defined by a skin of the aircraft. The auxiliary power unit intake is in fluid communication with an auxiliary power unit. The air intake assembly also includes a translatable scoop that defines a stowed condition and a fully deployed condition. The translatable scoop directs air exterior to the aircraft into the auxiliary power unit intake when in the fully deployed condition and does not direct the air exterior to the aircraft into the auxiliary power unit intake when in the stowed condition.

A system to predict a startup condition of an auxiliary power unit (APU) of an aircraft includes a machine learning device configured to receive data including sensor data of the aircraft and weather forecast data of a destination airport. The machine learning device is also configured to process the data to generate a prediction regarding the startup condition and to generate a message based on the prediction. The message indicates that an alternate startup procedure of the APU is to be performed after the aircraft has landed at the destination airport to avoid an error condition associated with a primary startup procedure of the APU.

A health monitoring system including an array of microphones, a data collection system, and analytic software used to detect health status, pending malfunctions, or faults of several disparate, engine subsystems. The system can be used to monitor health of the main engines, the engine nacelles, and auxiliary power units (APU) on the aircraft.