Abstract: An aircraft includes an aircraft body defining a longitudinal direction, a vertical direction and a transverse direction, and at least two propulsion devices rotatable about a respective associated axis of rotation to generate a respective associated thrust vector, wherein a first number of propulsion devices are arranged along a first straight line, which is parallel to the transverse direction, and a second number of propulsion devices are arranged along a second straight line which is parallel to the transverse direction, the first straight line being spaced apart from the second straight line, and the center of mass of the aircraft being positioned between the first straight line and the second straight line.

Abstract: The invention relates to a propulsion device for an aircraft, comprising a blade (2) which can be rotated about an axis of rotation (51) of the propulsion device along a circular path (52) and is mounted for pivoting about a blade bearing axis parallel to the axis of rotation; a pitch mechanism having a coupling device (31) and a bearing device (33); and an offset device (4) to which the blade is coupled, the offset device defining an eccentric bearing axis (41) which is mounted at an adjustable offset distance. The coupling device is coupled to the blade at a coupling point (32) which is positioned in such a way that the plane that comprises the blade bearing axis and the coupling point and the tangential plane to the circular path through the blade bearing axis include a certain, non-vanishing angle (w?) when the offset distance is set to zero.

Abstract: The invention relates to an aircraft designed as a compound helicopter with an aircraft fuselage, a main rotor arranged on the aircraft fuselage, and cyclogyro rotors which protrude laterally from the aircraft fuselage and which comprise an outer end surface. An improved torque compensation is achieved in that the cyclogyro rotors are connected to the aircraft fuselage by means of a suspension device which holds the cyclogyro rotors at the outer border of the rotors, and each cyclogyro rotor can be controlled individually and independently of the other. A torque compensation function of the main rotor can be carried out by the cyclogyro rotors.

Abstract: The invention relates to an aircraft designed as a compound helicopter with an aircraft fuselage, a main rotor arranged on the aircraft fuselage, and cyclogyro rotors which protrude laterally from the aircraft fuselage and which comprise an outer end surface. An improved torque compensation is achieved in that the cyclogyro rotors are connected to the aircraft fuselage by means of a suspension device which holds the cyclogyro rotors at the outer border of the rotors, and each cyclogyro rotor can be controlled individually and independently of the other. A torque compensation function of the main rotor can be carried out by the cyclogyro rotors.