A passive elastic teeter bearing (3c) for an aircraft rotor (3b), including, rotatably arranged on an rotational axis (RA) of said rotor (3b), a teeter beam (3d), configured for attaching the rotor which has rotor blades, with the teeter beam being configured for performing a teetering motion, and having two pairs of first lugs (3j1, 3j2) arranged at opposite ends thereof at a distance with respect to the rotational axis; and a hub piece (3f) located below the teeter beam, the hub piece having two arms (3g1, 3g2) that extend outwardly in a radial direction, each having a second lug (3k) arranged at a distance with respect to said rotational axis. Each second lug is located between the two lugs of a respective pair of first lugs, and respective connecting pins (3n) pass through the first and second lugs on either side of the rotational axis. A pair of elastic bushings (3l1, 3l2) are arranged on each connecting pin between a first one of the first lugs and the second lug and between a second one of said first lugs and the second lug, respectively.

Spring-integrated rotors are disclosed. A disclosed example apparatus includes a bracket defining a first rotational axis and coupled to a motor for rotating the bracket about the first rotational axis, a pivot body defining a second rotational axis extending along a direction different than the first rotational axis, the pivot body coupled to the bracket for rotation about the second rotational axis, and at least one spring device positioned at the bracket, the at least one spring device urging the pivot body toward a central position when the bracket is rotating.

A propeller arrangement for an aircraft, and an aircraft having a propeller arrangement of said type, are specified. The propeller arrangement has a first propeller blade and a second propeller blade, and a propeller mount on which both the first propeller blade and the second propeller blade are mounted. The propeller arrangement furthermore has a drive shaft with a holding unit, and a first connecting unit. The first propeller blade is rotatable about a first axis of rotation and the second propeller blade is rotatable about a second axis of rotation. The propeller mount is pivotable about a pivot axis. The first connecting unit is coupled to the first propeller blade and to the holding unit, such that, in the event of a pivoting of the propeller mount about the pivot axis, the first propeller blade is set in rotational motion about the first axis of rotation.

A propeller arrangement for an aircraft, and an aircraft having a propeller arrangement of said type, are specified. The propeller arrangement has a first propeller blade and a second propeller blade, and a propeller mount on which both the first propeller blade and the second propeller blade are mounted. The propeller arrangement furthermore has a drive shaft with a holding unit, and a first connecting unit. The first propeller blade is rotatable about a first axis of rotation and the second propeller blade is rotatable about a second axis of rotation. The propeller mount is pivotable about a pivot axis. The first connecting unit is coupled to the first propeller blade and to the holding unit, such that, in the event of a pivoting of the propeller mount about the pivot axis, the first propeller blade is set in rotational motion about the first axis of rotation.

A helicopter rotor hub assembly for coupling a pair of helicopter blades to a helicopter mast. It includes a yoke assembly and a pitch assembly. The yoke assembly includes a central section and first and second sections extending respectively on opposite sides of the central section. Each one of the first and second sections has a pair of elongated arms defining inbetween a bearing-receiving interspace. The pitch assembly includes first and second attachment plates extending respectively along the first and second sections of the yoke assembly and first and second pitch bearing assemblies. Each attachment plate is connected to a respective one of the helicopter blades. Each pitch bearing assembly extends in the bearing-receiving interspace of a respective one of the first and second sections of the yoke assembly. Each pitch bearing assembly contacts a respective one of attachment plates to allow a pitch movement of the helicopter blades.

A helicopter rotor hub assembly for coupling a pair of helicopter blades to a helicopter mast. It includes a yoke assembly and a pitch assembly. The yoke assembly includes a central section and first and second sections extending respectively on opposite sides of the central section. Each one of the first and second sections has a pair of elongated arms defining inbetween a bearing-receiving interspace. The pitch assembly includes first and second attachment plates extending respectively along the first and second sections of the yoke assembly and first and second pitch bearing assemblies. Each attachment plate is connected to a respective one of the helicopter blades. Each pitch bearing assembly extends in the bearing-receiving interspace of a respective one of the first and second sections of the yoke assembly. Each pitch bearing assembly contacts a respective one of attachment plates to allow a pitch movement of the helicopter blades.

An electric vertical takeoff and landing aircraft including a teetering propulsor assembly is provided. Teetering propulsor assembly may include a propeller that includes a hub and blades. Hub of propeller may be mechanically connected to a teeter mechanism of propulsor assembly that may be configured to allow the propeller to pivot about a teeter axis relative to the electric aircraft. Thus, teeter mechanism allows for a rotational axis of propeller to move during teetering of propeller. Teeter mechanism may include one or more springs that reduce teetering or prevent teetering of the propulsor at certain rotational speeds of propeller.

An electric vertical takeoff and landing aircraft including a teetering propulsor assembly is provided. Teetering propulsor assembly may include a propeller that includes a hub and blades. Hub of propeller may be mechanically connected to a teeter mechanism of propulsor assembly that may be configured to allow the propeller to pivot about a teeter axis relative to the electric aircraft. Thus, teeter mechanism allows for a rotational axis of propeller to move during teetering of propeller. Teeter mechanism may include one or more springs that reduce teetering or prevent teetering of the propulsor at certain rotational speeds of propeller.

A teeter flap lock for an aircraft may include at least one pair of diametrically positioned teeter flap lock plates extending from a rotor teetering hinge, spaced apart from a rotor mast of the aircraft. A teeter flap lock block is positioned about the rotor mast and is configured to fit between the teeter flap lock plates and the rotor mast. The teeter flap lock block fits between and contacts the teeter flap lock plates in an engaged position, and is movable between the engaged position and a disengaged position relative to the teeter flap lock plates. The teeter flap lock enables flapping of rotors coupled to the rotor mast via the teetering hinge when the teeter flap lock block is in the disengaged position and disables flapping of the rotors when the teeter flap lock block is in the engaged position.

The present invention includes a rotor hub system, comprising: a teetering rotor hub disposed about a mast, the teetering rotor hub comprising: a first and a second yoke; each connected to a set of rotor blades, wherein the second set of rotor blades and the first set of rotor blades are disposed in a common plane, but the first and the second yoke do not come in contact.