A propulsion unit, for an aircraft, comprising a hollow chassis with an opening at the bottom, a propulsion system comprising an electric motor with a propeller, a fuel cell, a tank and a cooling system, and one platform fastened to the chassis through said opening using fasteners and in which at least one element of the propulsion system is fastened to the platform. An aircraft with such a propulsion unit.

A tilting apparatus for an aircraft, comprising: a tiltable aircraft component which tilts between a first and second position, at least one actuator for adjusting a tilt angle of the tiltable aircraft component, and at least one passive damper connected to the tiltable aircraft component and configured to limit a rate of change of the tilt angle of the tiltable aircraft component. The at least one passive damper is on a load path separate from a load path of the at least one actuator.

A tilting apparatus for an aircraft, comprising: a tiltable aircraft component which tilts between a first and second position, at least one actuator for adjusting a tilt angle of the tiltable aircraft component, and at least one passive damper connected to the tiltable aircraft component and configured to limit a rate of change of the tilt angle of the tiltable aircraft component. The at least one passive damper is on a load path separate from a load path of the at least one actuator.

An aircraft assist system described herein includes an aircraft coupling counterpart attached to a strut of a landing gear of an aircraft, and an assist vehicle. The assist vehicle includes a frame, ground-engaging wheels mounted to the frame, a power source for driving one or more of the ground-engaging wheels, and a vehicle coupling counterpart for engagement with the aircraft coupling counterpart. The aircraft coupling counterpart and the vehicle coupling counterpart define a swivel connection for transferring a propulsive force from the takeoff assist vehicle to the aircraft. The aircraft coupling counterpart is disengageable from the vehicle coupling counterpart by upward movement of the aircraft coupling counterpart relative to the vehicle coupling counterpart.

Aircraft comprises a heater system, a conduit system thermally connected to fuel cell stacks, a pump system, and a controller. The heater system is configured to heat a coolant. The coolant flows through the conduit system. The pump system is configured to circulate the coolant through the conduit system to the fuel cell stacks. The controller is configured to control the heater system to heat the coolant to form a heated coolant. The controller is configured to control the pump system to circulate the heated coolant through the conduit system. The controller is configured to control the conduit system to circulate the heated coolant to a subset of the fuel cell stacks, wherein the heated coolant causes the subset of the fuel cell stacks to reach an operating temperature.

A fluid ice protection system for an aircraft includes a plenum back wall and a fluid delivery network. The plenum back wall is affixed to an interior surface of an inlet cowl of a nacelle of the aircraft to define a plenum between the interior surface and a front surface of the plenum back wall. The nacelle surrounds a rotor assembly of an aircraft propulsion system. The inlet cowl defines a plurality of perforations through a thickness of the inlet cowl. The perforations are fluidly connected to the plenum. The fluid delivery network is coupled to the plenum back wall and configured to supply an anti-ice liquid into the plenum for the anti-ice liquid to penetrate through the perforations onto an exterior surface of the inlet cowl along a leading edge section of the inlet cowl.

A fluid ice protection system for an aircraft includes a plenum back wall and a fluid delivery network. The plenum back wall is affixed to an interior surface of an inlet cowl of a nacelle of the aircraft to define a plenum between the interior surface and a front surface of the plenum back wall. The nacelle surrounds a rotor assembly of an aircraft propulsion system. The inlet cowl defines a plurality of perforations through a thickness of the inlet cowl. The perforations are fluidly connected to the plenum. The fluid delivery network is coupled to the plenum back wall and configured to supply an anti-ice liquid into the plenum for the anti-ice liquid to penetrate through the perforations onto an exterior surface of the inlet cowl along a leading edge section of the inlet cowl.

A thermal management system includes a refrigeration circuit that cools at least a first coolant that circulates around a battery cooling loop. Refrigerant of the refrigeration circuit is cooled at a liquid-cooled condenser and at an air-cooled condenser. In certain examples, the liquid-cooled condenser is cooled by coolant circulating along a propeller arrangement cooling loop. In certain examples, the coolant from the propeller arrangement cooling loop may be combined with coolant from the battery cooling loop.

Embodiments include an aircraft comprising a fuselage; a wing connected to the fuselage; and first and second propulsion systems connected to the wing on opposite sides of the fuselage, wherein at least a portion of each of the first and second propulsion systems and at least a portion of the wing are tiltable between a first position in which the aircraft is in a hover mode and a second position in which the aircraft is in a cruise mode, wherein each of the propulsion systems includes pylon and a rotor assembly comprising a plurality of rotor blades.

Embodiments include an aircraft comprising a fuselage; a wing connected to the fuselage; and first and second propulsion systems connected to the wing on opposite sides of the fuselage, wherein at least a portion of each of the first and second propulsion systems and at least a portion of the wing are tiltable between a first position in which the aircraft is in a hover mode and a second position in which the aircraft is in a cruise mode, wherein each of the propulsion systems includes pylon and a rotor assembly comprising a plurality of rotor blades.