A rotorcraft is provided and includes a fuselage. The fuselage includes drag generating portions, a main rotor assembly and an auxiliary propulsor having an expected propulsion efficiency. The auxiliary propulsor is disposed to ingest boundary layer flows and in wake regions associated with the drag generating portions and is provided with a corresponding increase in the expected propulsion efficiency thereof.

A helicopter with a fuselage and a composite tail boom. The composite tail boom has at least a tubular tail boom cone and a composite attachment ring segment that defines a mating face which is connected to the fuselage at an associated connection interface by means of a plurality of tension members that are oriented longitudinally with respect to a longitudinal extension direction of the composite tail boom. The plurality of tension members are distributed over a perimeter of the composite attachment ring segment 7. The composite attachment ring segment has a clamp ring section with a plurality of tension member accommodations. The clamp ring section defines the mating face of the composite attachment ring segment 7. The plurality of tension members is at least partly accommodated in the plurality of tension member accommodations.

A helicopter with a fuselage and a composite tail boom. The composite tail boom has at least a tubular tail boom cone and a composite attachment ring segment that defines a mating face which is connected to the fuselage at an associated connection interface by means of a plurality of tension members that are oriented longitudinally with respect to a longitudinal extension direction of the composite tail boom. The plurality of tension members are distributed over a perimeter of the composite attachment ring segment 7. The composite attachment ring segment has a clamp ring section with a plurality of tension member accommodations. The clamp ring section defines the mating face of the composite attachment ring segment 7. The plurality of tension members is at least partly accommodated in the plurality of tension member accommodations.

In some embodiments, a system and/or method a may include a helicopter transport system. The helicopter transport system may include a support frame. The support frame may be substantially rectangular. The helicopter transport system may include a first pair of wheels. In some embodiments, the first pair of wheels may be positioned on opposing sides of the outer perimeter of the support frame towards a first end of the support frame. The helicopter transport system may include a second pair of wheels. The second pair of wheels may be positioned adjacent one another within the perimeter of the support frame towards a second end of the support frame. The first end of the support frame may be positioned opposite the second end of the support frame. The helicopter transport system may include a lift mechanism coupled to the support frame. The lift mechanism may elevate, during use, a helicopter above the support frame.

The disclosure herein relates to power leveling mechanisms comprising a high frequency controller. The power leveling mechanism receives a power demand signal indicating a power requirement of a vehicle and determines a high frequency component of the power demand signal. The power leveling mechanism also provides a signal to a primary propulsion system and provides, via the high frequency controller, a high bandwidth signal based on the high frequency component to an auxiliary propulsion system.

A steering assembly includes a movable anchor. Movement of the anchor in a first direction is restricted. A first linkage is coupled to the anchor and a second linkage it rotatably coupled to the first linkage. The second linkage is configured to couple to a contactor. A drive mechanism moves the second linkage relative to the first linkage. At least one of moving the second linkage and moving the anchor maneuvers the contactor to a desired position.

A pitching arrangement for a model helicopter includes a securing base, a plurality of servers supported by the securing base, a main connecting shaft linked to the servers, a supporting ring, a control device operatively provided between the servers and axially mounted to the main connecting shaft, and a plurality of connecting rods connecting the servers and the control device through the main connecting shaft, wherein the supporting ring is mounted on the main connecting shaft, wherein the connecting rods are connected to the supporting ring of the main connecting shaft.

A pitching arrangement for a model helicopter includes a securing base, a plurality of servers supported by the securing base, a main connecting shaft linked to the servers, a supporting ring, a control device operatively provided between the servers and axially mounted to the main connecting shaft, and a plurality of connecting rods connecting the servers and the control device through the main connecting shaft, wherein the supporting ring is mounted on the main connecting shaft, wherein the connecting rods are connected to the supporting ring of the main connecting shaft.

A flight control method and system for a rotary wing aircraft. When the longitudinal speed U.sub.X of the aircraft is greater than a first threshold speed V.sub.thresh1, a first mode of operation of the method enables flight to be performed while maintaining track relative to the ground, the flight setpoints of an autopilot being a ground course angle TK.sub.sol, a forward speed Va, a flight path angle P, and a heading Ψ. When the longitudinal speed U.sub.X is less than a second threshold speed V.sub.thresh2, a second mode of operation enables flight to be performed while maintaining heading, the flight setpoints being the longitudinal speed U.sub.X, a lateral speed V.sub.Y, a vertical speed W.sub.Z, and the heading Ψ.

A flight control method and system for a rotary wing aircraft. When the longitudinal speed U.sub.X of the aircraft is greater than a first threshold speed V.sub.thresh1, a first mode of operation of the method enables flight to be performed while maintaining track relative to the ground, the flight setpoints of an autopilot being a ground course angle TK.sub.sol, a forward speed Va, a flight path angle P, and a heading Ψ. When the longitudinal speed U.sub.X is less than a second threshold speed V.sub.thresh2, a second mode of operation enables flight to be performed while maintaining heading, the flight setpoints being the longitudinal speed U.sub.X, a lateral speed V.sub.Y, a vertical speed W.sub.Z, and the heading Ψ.