A method for sensing a force applied to an aircraft , the method comprising: defining a first velocity vector as a function of a first velocity due to a rotation motion of the aircraft ; defining a second velocity vector as a function of a second velocity due to the rotation motion of the aircraft ; defining an instant axis of rotation of the aircraft as a function of the first velocity vector and the second velocity vector; determining whether a force has been exerted on a first portion of the aircraft ; and outputting an indication that a force has been exerted on the first portion of the aircraft responsive to determining that the force has been exerted on the first portion of the aircraft, wherein the determining whether the force has been exerted on the first portion of the aircraft includes: calculating a distance between the first portion of the aircraft and the instant axis of rotation; calculating a distance between a center of gravity of the aircraft and the instant axis of rotation; determining whether the distance between the first portion of the aircraft and the instant axis of rotation is a minimum of a set of axis of rotation distance values, and whether the distance between the first portion of the aircraft and the instant axis of rotation is less than a gear-axis-distance threshold value; and determining whether the distance between the center of gravity of the aircraft and the instant axis of rotation exceeds the gear-axis-distance threshold value. defining a first velocity vector as a function of a first velocity due to a rotation motion of the aircraft ; defining a second velocity vector as a function of a second velocity due to the rotation motion of the aircraft ; defining an instant axis of rotation of the aircraft as a function of the first velocity vector and the second velocity vector; determining whether a force has been exerted on a first portion of the aircraft ; and outputting an indication that a force has been exerted on the first portion of the aircraft responsive to determining that the force has been exerted on the first portion of the aircraft, wherein the determining whether the force has been exerted on the first portion of the aircraft includes: calculating a distance between the first portion of the aircraft and the instant axis of rotation; calculating a distance between a center of gravity of the aircraft and the instant axis of rotation; determining whether the distance between the first portion of the aircraft and the instant axis of rotation is a minimum of a set of axis of rotation distance values, and whether the distance between the first portion of the aircraft and the instant axis of rotation is less than a gear-axis-distance threshold value; and determining whether the distance between the center of gravity of the aircraft and the instant axis of rotation exceeds the gear-axis-distance threshold value. calculating a distance between the first portion of the aircraft and the instant axis of rotation; calculating a distance between a center of gravity of the aircraft and the instant axis of rotation; determining whether the distance between the first portion of the aircraft and the instant axis of rotation is a minimum of a set of axis of rotation distance values, and whether the distance between the first portion of the aircraft and the instant axis of rotation is less than a gear-axis-distance threshold value; and determining whether the distance between the center of gravity of the aircraft and the instant axis of rotation exceeds the gear-axis-distance threshold value. <EOS>