A drive device for an aircraft, comprising - a blade which can be rotated about an axis of rotation of the drive device along a circular path; - a pitch mechanism having a coupling device and a bearing device, - wherein the blade is mounted by the bearing device for pivoting about a blade bearing axis parallel to the axis of rotation of the drive device; - an offset device to which the blade is coupled by the coupling device at a connection point, wherein the offset device defines an eccentric bearing axis which is mounted at an adjustable offset distance parallel to the axis of rotation of the drive device, - such that the coupling device couples the blade to the offset device such that the rotation of the blade along the circular path about the axis of rotation of the drive device effects a pitch movement (α) of the blade when the offset distance is set to a nonzero value; and - wherein the blade bearing axis is shifted toward the axis of rotation of the drive device by a certain distance w gx relative to the plane that extends through the center of mass of the blade and that extends parallel to both the axis of rotation and the chord of the blade, wherein the certain distance w gx is chosen such that the expression R = w gx, 0 ⋅ M ⋅ r 1 − α A 2 8 − I cm + w gx, 0 2 + w gz 2 ⋅ M is approximately zero, wherein M designates the mass of the blade, r designates the distance of the blade bearing axis from the axis of rotation, α A designates the amplitude of the pitch movement (α), l cm designates the mass inertia moment calculated with respect to the center of mass of the blade, and w gz designates the distance of the blade bearing axis with respect to the plane that extends through the center of mass of the blade and is perpendicular to the chord of the blade. - a blade which can be rotated about an axis of rotation of the drive device along a circular path; - a pitch mechanism having a coupling device and a bearing device, - wherein the blade is mounted by the bearing device for pivoting about a blade bearing axis parallel to the axis of rotation of the drive device; - wherein the blade is mounted by the bearing device for pivoting about a blade bearing axis parallel to the axis of rotation of the drive device; - an offset device to which the blade is coupled by the coupling device at a connection point, wherein the offset device defines an eccentric bearing axis which is mounted at an adjustable offset distance parallel to the axis of rotation of the drive device, - such that the coupling device couples the blade to the offset device such that the rotation of the blade along the circular path about the axis of rotation of the drive device effects a pitch movement (α) of the blade when the offset distance is set to a nonzero value; and - wherein the blade bearing axis is shifted toward the axis of rotation of the drive device by a certain distance w gx relative to the plane that extends through the center of mass of the blade and that extends parallel to both the axis of rotation and the chord of the blade, wherein the certain distance w gx is chosen such that the expression R = w gx, 0 ⋅ M ⋅ r 1 − α A 2 8 − I cm + w gx, 0 2 + w gz 2 ⋅ M is approximately zero, wherein M designates the mass of the blade, r designates the distance of the blade bearing axis from the axis of rotation, α A designates the amplitude of the pitch movement (α), l cm designates the mass inertia moment calculated with respect to the center of mass of the blade, and w gz designates the distance of the blade bearing axis with respect to the plane that extends through the center of mass of the blade and is perpendicular to the chord of the blade. - such that the coupling device couples the blade to the offset device such that the rotation of the blade along the circular path about the axis of rotation of the drive device effects a pitch movement (α) of the blade when the offset distance is set to a nonzero value; and - wherein the blade bearing axis is shifted toward the axis of rotation of the drive device by a certain distance w gx relative to the plane that extends through the center of mass of the blade and that extends parallel to both the axis of rotation and the chord of the blade, wherein the certain distance w gx is chosen such that the expression R = w gx, 0 ⋅ M ⋅ r 1 − α A 2 8 − I cm + w gx, 0 2 + w gz 2 ⋅ M is approximately zero, wherein M designates the mass of the blade, r designates the distance of the blade bearing axis from the axis of rotation, α A designates the amplitude of the pitch movement (α), l cm designates the mass inertia moment calculated with respect to the center of mass of the blade, and w gz designates the distance of the blade bearing axis with respect to the plane that extends through the center of mass of the blade and is perpendicular to the chord of the blade. M designates the mass of the blade, r designates the distance of the blade bearing axis from the axis of rotation, α A designates the amplitude of the pitch movement (α), l cm designates the mass inertia moment calculated with respect to the center of mass of the blade, and w gz designates the distance of the blade bearing axis with respect to the plane that extends through the center of mass of the blade and is perpendicular to the chord of the blade.