A flying passenger rotor lifted vehicle that is capable of taking off and landing vertically, that is relatively light-weight, has responsive control, and increased safety against failure of propulsion/thrust systems. The flying vehicle can include a body having a tail section, a central thrust unit arranged along the longitudinal axis of the vehicle, at a distance from the rotation axis of the main rotor, a mounting support on either side of the body, and a side thrust unit mounted to each mounting support. The central thrust unit includes a fan which provides air flow with a flow component perpendicular to a virtual vertical midplane of the vehicle. Each of the side thrust units includes a fan which provides air flow with a flow component parallel to the virtual vertical midplane. At least one of the thrust units has controllable air deflection to deflect the corresponding output air flow in a controllable manner.

A flying passenger rotor lifted vehicle that is capable of taking off and landing vertically, that is relatively light-weight, has responsive control, and increased safety against failure of propulsion/thrust systems. The flying vehicle can include a body having a tail section, a central thrust unit arranged along the longitudinal axis of the vehicle, at a distance from the rotation axis of the main rotor, a mounting support on either side of the body, and a side thrust unit mounted to each mounting support. The central thrust unit includes a fan which provides air flow with a flow component perpendicular to a virtual vertical midplane of the vehicle. Each of the side thrust units includes a fan which provides air flow with a flow component parallel to the virtual vertical midplane. At least one of the thrust units has controllable air deflection to deflect the corresponding output air flow in a controllable manner.

An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

An exemplary aircraft includes a turbine engine having a gas generator spool and a power spool, the power spool operational to drive a rotor, a first generator coupled to the gas generator spool, and a controller operable to increase a load on the gas generator spool when the gas generator spool is on a speed limit thereby increasing a speed limit margin in order to increase power available from the turbine engine.

According to an aspect, a method of assembling a mandrel includes assembling a plurality of members via interlocking features arranged at opposing edges of each member of the plurality of members to form a compartment, the assembled members having a collective outer surface that conforms to an inner surface of the spar. A support member is inserted into the compartment formed radially inward from the assembled members, the support member making contact with a portion of each member of the plurality of members.

According to an aspect, a method of assembling a mandrel includes assembling a plurality of members via interlocking features arranged at opposing edges of each member of the plurality of members to form a compartment, the assembled members having a collective outer surface that conforms to an inner surface of the spar. A support member is inserted into the compartment formed radially inward from the assembled members, the support member making contact with a portion of each member of the plurality of members.

A method and a system for providing a rotorcraft with assistance in taking off from a slope. The rotorcraft includes at least one lift rotor provided with a plurality of blades, control devices for controlling the pitches of the blades, and landing gear provided with at least three ground contact members. The method comprises a step of measuring a piece of information relating to the forces to which each ground contact member is subjected during a landing phase for landing on the slope, a step of measuring at least one piece of information relating to the pitches of the blades during the landing phase, and a control step for controlling the pitches of the blades during the takeoff phase during which the rotorcraft takes off after the landing as a function of the measurements taken during the landing in order to enable a takeoff to be performed that is safe and simplified.

A method and a system for providing a rotorcraft with assistance in taking off from a slope. The rotorcraft includes at least one lift rotor provided with a plurality of blades, control devices for controlling the pitches of the blades, and landing gear provided with at least three ground contact members. The method comprises a step of measuring a piece of information relating to the forces to which each ground contact member is subjected during a landing phase for landing on the slope, a step of measuring at least one piece of information relating to the pitches of the blades during the landing phase, and a control step for controlling the pitches of the blades during the takeoff phase during which the rotorcraft takes off after the landing as a function of the measurements taken during the landing in order to enable a takeoff to be performed that is safe and simplified.

In one embodiment of the present disclosure, there is provided an aircraft gearbox including a gear and a gear shrouding for providing lubrication to the gear. The gear shrouding is disposed around the gear, has an inner surface facing the gear and an opposing outer surface facing away from the gear, and includes a channel formed along at least a portion of the gear shrouding between the inner surface and the outer surface of the gear shrouding, an input orifice extending to the channel, wherein the input orifice is at a first position on the channel, and an output orifice extending to the channel, wherein the output orifice is at a second position on the channel different from the first position. In another embodiment, the gear shrouding further includes a second output orifice at a third position on the channel different from the first and second positions.

The present invention includes a system and method for slowing the rotation of a rotor using, for example, rotor brake system for a rotorcraft comprising: one or more generators connected to a main rotor gearbox; an electric distributed anti-torque system mounted on a tail boom of the rotorcraft comprising two or more electric motors connected to the one or more generators, wherein the two or more electric motors are connected to one or more blades; and wherein a rotation of the rotor is slowed by placing a drive load on the main rotor gearbox with the one or more generators to bleed the mechanical power from rotor into electrical power via the two or more electric motors, wherein the electric distributed anti-torque system generates thrust in opposing directions.