Lissandrini, Marco

A machine and process configured to control bleed-off from an airflow and/or reduce a drag of an inlet. The machine may include: a panel that may include a porous section that comprises: a length; a flow side; and a channel side; a channel that surrounds the porous section and contains a carriage adjacent to the panel, wherein the carriage comprises: a flow side; a translation component; a channel side connected to a first rigid link and to a second rigid link; a bleed gap; and a number of pressure taps; a cylinder that comprises: a forward end; an aft end; a piston connected to: a forward rod that extends out of the forward end of the cylinder; and an aft rod that extends out of the aft end of the cylinder; a number of chambers; and a bias device connected to: the aft rod; and the channel.

An apparatus comprises a tank and the tank comprises an inner wall configured to hold liquid, an outer wall surrounding the inner wall, and a gap separating the inner wall and the outer wall. The exemplary apparatus further comprises a flow component configured to, in a first mode, flow fluid into the gap and, in a second mode, flow the fluid out of the gap. A system includes the tank, the flow component, and a reservoir. In the first mode, the flow component is configured to flow the fluid from the reservoir into the gap. In the second mode, the flow component is configured to flow the fluid from the gap into the reservoir. A method comprises flowing the fluid into the gap of the tank and flowing the fluid out of the gap.

A scanner system (100) for parts, the scanner system (100) comprising a plurality of scanners (106) mounted to a measurement head (104), a part support (114), a conveyor mechanism (124) to change a relative location of the part support (114) and the measurement head (104) along a scan path (112) during scanning, and an alignment artifact (108) located along the scan path (112).

A tracking unit 20 configured to connect to a robotic device 200 and move across a surface 101 of an object 100. The tracking unit 20 includes a body 21, one or more distance sensors 30 mounted to a first side of the body 21 and configured to detect a distance from the object 100, and one or more peripheral sensors 40 mounted to a second side of the body 21 and configured to detect a peripheral feature 110. A controller 90 is configured to receive signals from the one or more distance sensors 30 and the one or more peripheral sensors 40. The controller 90 is configured to position the body 21 a fixed distance away from the object 100 and to prevent contact between the body 21 and the peripheral feature 110.

Wing assemblies comprise a slat, wing support structures, and a gap-adjustment assembly configured to permit selective adjustment of the slat relative to the wing support structures. The gap-adjustment assembly comprises a track member and an adjustment member. The track member is pivotally coupled relative to the wing support structures about a track-member axis, the slat is operatively translationally coupled to the track member, and the track member is configured to constrain translation of the slat between a stowed position and a deployed position. The adjustment member is pivotally coupled relative to the wing support structures about an adjustment-member axis and pivotally coupled to the track member about a linkage axis. The adjustment member is configured to permit selective adjustment of a direct distance between the adjustment-member axis and the linkage axis.

Hybrid propulsion systems that utilize liquid natural gas solid oxide fuel cells in a manner practical for use in aircraft that avoid the use of heavy batteries, provide transient response times suitable for use in aircraft, and/or simplify reactant pre-conditioning systems using a compressor and turbine pair operatively coupled to the solid oxide fuel cell. Such hybrid propulsion systems for an aircraft may include a liquid natural gas solid oxide fuel cell, a motor driven by electric power from the solid oxide fuel cell, a gearbox operatively coupled to the motor, and a turbofan engine configured to generate thrust for the aircraft. The turbofan engine may be configured to provide electric power and shaft power and may include a duct fan that is operatively coupled to the motor via the gearbox, with the duct fan being driven by mechanical power from the gearbox and by the motor.

Bleed-air systems comprise a bleed-air turbine configured to receive at least a first portion of bleed air from a jet engine and deliver it to a cabin, a cabin-exhaust compressor operatively coupled to the bleed-air turbine and configured to receive cabin exhaust air from the cabin, and a cabin-exhaust nozzle configured to receive the cabin exhaust air from the cabin-exhaust compressor. Aircraft comprise a fuselage, a wing, a jet engine, and a bleed-air system. Methods comprise expanding at least a first portion of bleed air from a jet engine to drive a cabin-exhaust compressor, compressing cabin exhaust air from a cabin with the cabin-exhaust compressor, and nozzling the cabin exhaust air to environment.

Method of monitoring motion of an aircraft (100) during flight. The method includes determining sensed motion of the aircraft (100) about an axis during the flight and determining predictive motion of the aircraft (100) about the axis during the flight (based on a digital model (200)). An error is determined based on the sensed motion and the predictive motion. An effector (110) on the aircraft (100) is determined that controls the motion of the aircraft about the axis. The error is converted into an amount of necessary movement of the effector (110) to correct the error.

A system and a method include a lower support, an upper support, a first coupler connected to the lower support and the upper support at a first point of contact and a second point of contact, respectively, and a second coupler connected to the lower support and the upper support at a third point of contact and a fourth point of contact, respectively. The first coupler and the second coupler are configured to retain a test article therebetween.

An anti-slip system (10) for skis, in particular for skiing activities, comprises an anti-slip strip (20) comprising a plurality of protruding elements (23) movable relative to the anti-slip strip (20) itself and, moreover, a support panel (30) having a lower face (32) couplable with a base (101) of the ski (100) and an upper face (31) couplable with a main panel (104) of a ski (100), present in which there is a groove (33) adapted to contain the anti-slip strip (20). The groove (33) has a plurality of through holes passing through towards the lower face (32), each of which is adapted to receive a corresponding protruding element (23) of the anti-slip strip (20). The system (10) also comprises a movement means (40) configured to move the anti-slip strip (20) inside the groove (33) between a neutral configuration, in which the protruding elements (23) are arranged outside the holes or only partly inside the holes without protruding from them beyond the lower face (32), and an anti-slip configuration, in which the protruding elements (23) are arranged inside the holes so as to pass through them in a projecting manner relative to the lower face (32) of the support panel (30). The subject matter of the present invention also relates to a method for producing a ski for skiing activities.