Abstract: An aircraft (41) including a fuselage (14) having a skin (15) and extending along a longitudinal axis (39) from a front end to a rear end (17) of the aircraft, and an engine (30) including an air intake (31) forming an opening in the skin (15) and an exhaust (32) forming another opening in the skin (15). The engine is in a rear fuselage section, in which the exhaust (32) is situated ahead of the air intake (31) along the longitudinal direction (39).

Abstract: An air intake system comprising an air duct suitable for providing airflow to the inside of an aircraft, preferably to an auxiliary power unit; an inlet arranged at one end of the air duct; a skin surrounding the inlet; a plurality of slots arranged on the skin; a driving arrangement, a flap door connected to the driving arrangement, and a plurality of fins connected to the driving means. The driving arrangement is configured for moving the flap door between at least two positions, the positions being a closed position wherein the flap door closes the inlet, and an opened position wherein the flap door is driven away from the closed position. The driving arrangement is also configured for moving the plurality of fins such that the plurality of fins protrudes through the slots.

Abstract: 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.

Abstract: An aircraft comprising a main engine to provide a supply of bleed air, an APU housing within an APU compartment and having an APU bleed valve, an APU bleed air duct connecting main engine with the APU, and a bleed air heating system for the APU compartment comprising an auxiliary pipeline connecting the APU bleed air duct with the APU compartment, a temperature sensor, an auxiliary pipeline valve to control the discharge of bleed air into the APU compartment, and a temperature controller configured to establish a heating operation mode, when the sensed temperature falls below a minimum temperature threshold value, and a standby operation mode, when the sensed temperature surpasses a maximum temperature threshold value. The temperature controller operates the main engine and the valves to establish these operation modes.

Abstract: An air intake system comprising an air duct suitable for providing airflow to the inside of an aircraft, preferably to an auxiliary power unit; an inlet arranged at one end of the air duct; a skin surrounding the inlet; a plurality of slots arranged on the skin; a driving arrangement, a flap door connected to the driving arrangement, and a plurality of fins connected to the driving means. The driving arrangement is configured for moving the flap door between at least two positions, the positions being a closed position wherein the flap door closes the inlet, and an opened position wherein the flap door is driven away from the closed position. The driving arrangement is also configured for moving the plurality of fins such that the plurality of fins protrudes through the slots.

Abstract: 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.

Abstract: An aircraft comprising a main engine to provide a supply of bleed air, an APU housing within an APU compartment and having an APU bleed valve, an APU bleed air duct connecting main engine with the APU, and a bleed air heating system for the APU compartment comprising an auxiliary pipeline connecting the APU bleed air duct with the APU compartment, a temperature sensor, an auxiliary pipeline valve to control the discharge of bleed air into the APU compartment, and a temperature controller configured to establish a heating operation mode, when the sensed temperature falls below a minimum temperature threshold value, and a standby operation mode, when the sensed temperature surpasses a maximum temperature threshold value. The temperature controller operates the main engine and the valves to establish these operation modes.

Abstract: A start-up system including a control system controlling a partial opening of an air intake valve of a start-up turbine during a first phase of the start-up. The start-up turbine is capable of turning a rotor of the turbomachine for the purpose of the start-up, so as to prevent the rotor from encountering critical frequencies of the turbomachine.

Abstract: The start-up system comprises a control loop, which regulates in real time the opening of a valve of an air feed of a start-up turbine based on the current measured speed of rotation of a rotor of the turbomachine and a predetermined speed value, said start-up turbine being capable of turning the rotor of the turbomachine for the purpose of the start-up.

Abstract: A system for controlling aircraft main engines cooling during starting operations. An aircraft incorporates a main engine and a pneumatic starter for starting the same, and a pneumatic source fluidly communicated with the pneumatic starter to supply pressurized air thereto. A control system is provided with a data chart containing predetermined pressure values of the pneumatic source, and the values correspond to an ambient condition to obtain a desired rotating speed for the main engine for that ambient condition. The control system is configured to control the pneumatic source air pressure output based on the data chart and to rotate the main engine within a predefined rotating speed range during cooling procedure. A controlled reduced rotating speed during main engines cooling or cranking operation is thus provided before starting main engines, in order to mitigate bowed rotor phenomenon.

Abstract: A door system configured to be attached to the fuselage of a tail cone of an aircraft wherein the tail cone comprises an exhaust gas duct of an auxiliary power unit of the aircraft and an opening of the exhaust gas duct located at the rear part of the tail cone. The door system comprises a door which is movable between an open and a closed position, the door being configured such that, in the closed position, it covers the opening of the exhaust gas duct and that the door being shaped such that it follows the aerodynamic shape of the fuselage of the tail cone in its closed position.

Abstract: An Auxiliary Power Unit (“APU”) for an aircraft with reduced weight, but which at the same time meets all fire-related airworthiness standards. The APU comprises a metallic housing having mounts for attaching the housing to an external structure. The APU further comprises at least one temperature sensor suitable for detecting temperature under fire conditions. The temperature sensor is coupled with the mounts for sensing temperature at the housing.

Abstract: An Auxiliary Power Unit (“APU”) for an aircraft with reduced weight, but which at the same time meets all fire-related airworthiness standards. The APU comprises a metallic housing having mounts for attaching the housing to an external structure. The APU further comprises at least one temperature sensor suitable for detecting temperature under fire conditions. The temperature sensor is coupled with the mounts for sensing temperature at the housing.

Abstract: The start-up system comprises a control loop, which regulates in real time the opening of a valve of an air feed of a start-up turbine based on the current measured speed of rotation of a rotor of the turbomachine and a predetermined speed value, said start-up turbine being capable of turning the rotor of the turbomachine for the purpose of the start-up.

Abstract: A start-up system including a control system controlling a partial opening of an air intake valve of a start-up turbine during a first phase of the start-up.