An engine assembly for an aircraft, including an internal combustion engine having a liquid coolant system in fluid communication with a heat exchanger, an exhaust duct in fluid communication with air passages of the heat exchanger, a fan in fluid communication with the exhaust duct for driving a cooling air flow through the air passages of the heat exchanger and into the exhaust duct, and an intermediate duct in fluid communication with an exhaust of the engine and having an outlet positioned within the exhaust duct downstream of the fan and upstream of the outlet of the exhaust duct. The outlet of the intermediate duct is spaced inwardly from a peripheral wall of the exhaust duct. The engine assembly may be configured as an auxiliary power unit. A method of discharging air and exhaust gases in an auxiliary power unit having an internal combustion engine is also discussed.

A high-flying solar unmanned aircraft system capable of extending endurance time is disclosed. The system includes a main aircraft, a separable auxiliary power source and a connection device. The main aircraft includes a first body, a second body, a first wing portion, a second wing portion, a third wing portion, a first propeller and a second propeller. The second wing portion locates between the first body and the second body, and the second wing portion connects the first body and the second body. The connection device connects the main aircraft and the auxiliary power source, and includes a separation device. When the system climbs, the separable auxiliary power source provides additional energy to assist the main aircraft to climb. When reaching a preset altitude, the separation device, by burning out a line of connection bent, is turned on such that the auxiliary power source is separated from the main aircraft.

An exhaust system for an aircraft includes an exhaust duct configured to be inserted within a plurality of leaf springs of an aircraft. The exhaust duct is configured to be in fluid communication with the auxiliary power unit for conveying exhaust from the auxiliary power unit to an exhaust exit, the exhaust duct including at least one exhaust bracket for movably mounting the exhaust duct to an airframe. An alignment system is configured to be operatively connected to the exhaust duct.

Aircraft fuselage apparatus having embedded structural batteries are disclosed. An example apparatus includes a fuselage having a wall. The wall has an outer surface, an inner surface, and a structural battery embedded in the wall between the outer surface and the inner surface.

A toggle release mechanism comprises a platform, a toggle element comprising one or more rolling or sliding elements configured to move along a track between a first, locking position and a second, release position, and a solenoid configured to move the one or more rolling or sliding elements along the track between the first, locking position and the second, release position.

The invention relates to a method for mounting an engine module (1) in a support comprising a first structure (3) and a second structure (2) that is offset relative to the first structure (3), method intended for positioning at least a specified part (4) of the engine module (1) relative to an element (6) of the second structure (2) by means of an isostatic suspension connecting the engine module (1) to said first structure (3) by means of first connecting rods (10a, 10b, 10c, 10d) and to said second structure (2) by means of second connecting rods (10e, 10f), the length of said first and second connecting rods being defined in advance, method wherein the length of at least two (10c, 10f) of said first and second connecting rods is adjusted relative to the previously defined length thereof, in order to position said specified part (4) of the engine module (1) relative to said element (6) of the second structure (2) in said support. The invention also relates to said support comprising adjustable connecting rods, in an installation comprising in particular an auxiliary power unit for an aircraft.

A gas turbine engine includes a gearbox. The gearbox includes a housing at a forward part of a core compartment of a gas turbine engine. A plurality of accessory drives are each configured to rotatably couple the gas turbine engine accessory gearbox to one of a plurality of accessory components.

Various embodiments of the invention can include a portable power system with multiple power generation modes and mode based adjustable drag configuration. Embodiments of the invention include a system with an adjustable inlet ram air inlet, a ram air powered section (e.g. a ram air powered turbine with an adjustable ram air inlet), a fuel powered section, e.g., jet fuel powered auxiliary power unit, which is used when insufficient ram air is present or a power surge requires augmented power generation, and a generator section selectively coupled with the ram air powered section and the fuel powered section.

A vibration isolation device comprises a frame for mounting on an engine casing, an axis to be mounted to an external component to isolate, a resilient member located between the frame and the axis, and a fuse mechanism ensuring that the vibration isolation device presents a first stiffness when loads applied to said vibration isolation device are below a predetermined threshold load, and a second stiffness, lower than the first stiffness, when loads applied to the vibration isolation device are at least equal to the predetermined threshold load. The fuse mechanism constrains the resilient member within a predetermined space when loads applied to the vibration isolation device are below the predetermined threshold load and to release the resilient member so that this latter is capable of deforming beyond said predetermined space when loads applied to the vibration isolation device are at least equal to the predetermined threshold load.

This invention comprises a control device and a communication port device applied to drone, and a drone using such devices. The control device comprises a carrier board and a main control board that is detachably configured on the carrier board, said main control board is electrically connected with the carrier board, and the carrier board is configured with an interface device in which connections between a plurality of kinds of external devices with said carrier board are established. The carrier board is mainly used for connection with other external electronic devices and power distribution, and the main control board is responsible for processing sensor data and delivering control information. The main control board and the carrier board are connected through a single interface to enable a data transmission. The communication port device is configured on the drone flight controller.