An aircraft propulsion system configured to be supported from an aircraft wing having a leading edge and opposing upper and lower surfaces. The aircraft propulsion system broadly comprises an engine having a core, a fan case, and a nacelle including a plurality of access panels, and an attachment assembly for securing the engine to the aircraft wing. The attachment assembly broadly comprises an upper support section including a number of spars and a number of ribs connected between the spars, a lower support section, and an aft section. The attachment assembly aerodynamically melds the nacelle and the aircraft wing together via the upper support section so that air flowing over the engine flows over the aircraft wing along the upper surface and air flowing laterally alongside the nacelle flows under the aircraft wing along the lower surface.

An aircraft includes a fuselage with one or more wings coupled thereto. One or more wheels are also coupled to the fuselage and are configured to allow the aircraft to taxi, take off, and land. A propulsor is used to provide thrust to the fuselage and airflow over the wings. The wings may be fixed in position or may be configured to fold along a line via a hinged system or pivot along an axis. The folding allows the wings to store in a smaller footprint. The fuselage may include one or more safety features. These may include indicator lights configured to illuminate or reflect an amount of light. Additionally, the aircraft may include an occupant safety system with the likes of an airbag and even an anti-lock brake system coupled to the one or more wheels.

A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.

A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.

A tiltrotor aircraft comprising a wing carrying an engine on each wing half, and a fuselage-mounted third engine with a transmission system configured to drive each of the tilting rotors from the third engine. The engines may be any powerplant, including fore example, a reciprocating engine, a turbine engine, or an electric motor. The third engine is preferably controlled for best efficiency and best safety in engine failure cases.

A vertical take-off and landing aircraft including a wing structure including a wing, a rotor operatively supported by the wing, and a hybrid power system configured to drive the rotor, the hybrid power system including a first power system and a second power system, wherein a first energy source for the first power system is different than a second energy source for the second power system.

A vertical take-off and landing aircraft including a wing structure including a wing, a rotor operatively supported by the wing, and a hybrid power system configured to drive the rotor, the hybrid power system including a first power system and a second power system, wherein a first energy source for the first power system is different than a second energy source for the second power system.

A propulsion assembly having a propulsion system including an exhaust nozzle fastened to the nozzle wall on the outside thereof so as to define between them a chamber, and a heat exchanger system ensuring an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall. The heat exchanger system has a pipe portion arranged in the chamber and the exchange of heat energy takes place at this pipe portion. With such an arrangement, the heat energy of the combustion gases is transferred to the fuel for better combustion.

A propulsion assembly having a propulsion system including an exhaust nozzle fastened to the nozzle wall on the outside thereof so as to define between them a chamber, and a heat exchanger system ensuring an exchange of heat energy between the hot combustion gases circulating in the exhaust nozzle and the colder fuel circulating in the supply pipe at least in part by thermal radiation through the nozzle wall. The heat exchanger system has a pipe portion arranged in the chamber and the exchange of heat energy takes place at this pipe portion. With such an arrangement, the heat energy of the combustion gases is transferred to the fuel for better combustion.

An aeronautical car includes a ground-travel system including a drivetrain; an air-travel system including a detachable portion configured to house a propulsion device configured to provide thrust and to be driven by the drivetrain when the detachable portion is connected to the aeronautical car, and at least one flight mechanism configured to provide lift once the aeronautical car is in motion; and a weather manipulation device. The weather manipulation device may be configured to manipulate at least one aspect of a weather condition while the aeronautical car is in the air.