Dual rack and pinion rotational inerter system and method for damping movement of a flight control surface of an aircraft

An aircraft, comprising:

• a flight control surface pivotably coupled to a support structure;
• one or more actuators configured to actuate the flight control surface;
• and
• at least one dual rack and pinion rotational inerter system for damping movement of the flight control surface of the aircraft, the at least one dual rack and pinion rotational inerter system comprising:
• a flexible holding structure disposed between the flight control surface and the support structure of the aircraft;
• a plurality of rod bearings inserted into interior corners of the flexible holding structure;
• a dual rack and pinion assembly clamped by and between the flexible holding structure, the dual rack and pinion assembly comprising a first rack, a second rack, and a pinion engaged to and between the first rack and the second rack;
• a first terminal coupled to the first rack and coupled to the flight control surface, via a pivot element, and a second terminal coupled to the second rack, and coupled to the support structure;
• a pair of inertia wheels comprising a first inertia wheel adjacent to a first side of the flexible holding structure, and a second inertial wheel adjacent to a second side of the flexible holding structure;
• and
• an axle element inserted through the first inertial wheel, the flexible holding structure, the pinion, and the second inertial wheel, coupling a rotational movement of the pair of inertia wheels and the pinion,
• wherein rotation of the flight control surface causes translational movement, via the pivot element, of the first rack relative to the second rack, along a longitudinal inerter axis, which causes the rotational movement of the pinion and the pair of inertia wheels, such that the rotational movement of the pinion is resisted by the pair of inertia wheels, resulting in the dual rack and pinion rotational inerter system damping movement of the flight control surface.

A method for damping movement of a flight control surface of an aircraft, the method comprising the steps of:

• installing at least one dual rack and pinion rotational inerter system between the flight control surface and a support structure of the aircraft;
• the at least one dual rack and pinion rotational inerter system comprising:
• a flexible holding structure having a plurality of rod bearings inserted into interior corners of the flexible holding structure;
• a dual rack and pinion assembly clamped by and between the flexible holding structure, the dual rack and pinion assembly comprising a first rack, a second rack, and a pinion engaged to and between the first rack and the second rack;
• a first terminal coupled to the first rack and coupled to the flight control surface, via a pivot element, and a second terminal coupled to the second rack, and coupled to the support structure;
• a pair of inertia wheels comprising a first inertia wheel adjacent to a first side of the flexible holding structure, and a second inertial wheel adjacent to a second side of the flexible holding structure;
• and
• an axle element inserted through the first inertial wheel, the flexible holding structure, the pinion, and the second inertial wheel, and the axle element coupling a rotational movement of the pair of inertia wheels and the pinion,
• rotating the flight control surface using one or more actuators;
• using the at least one dual rack and pinion rotational inerter to axially accelerate and pull in a translational movement along a longitudinal inerter axis, the first rack relative to the second rack, and to cause the rotational movement of the pinion and the pair of inertia wheels, such that the rotational movement of the pinion is resisted by the pair of inertia wheels and there is no incidental motion;
• and
• damping movement of the flight control surface, using the at least one dual rack and pinion rotational inerter.