Patent ID: 8967536
Filing Date: 2015-03-03
Classification: B64C,F16F,Y10T

Abstract:
1. A landing gear with a passive vibration absorber for a helicopter, the landing gear comprising: a pair of skids; a forward cross tube; a rearward cross tube; connections between the forward cross tube and skids and between the rearward cross tube and skids, respectively, for mounting the skids to a fuselage of a helicopter; and at least one linear spring-mass system mounted to the landing gear with the masses of the spring-mass system being incorporated in the landing gear, the at least one spring-mass system being tuned, using suitable spring rates and masses, to a main excitation frequency of the helicopter, the main excitation frequency being a product of a rotational speed of a main rotor and a number of main rotor blades, and the at least one spring-mass system being located in the forward cross tube or rearward cross tube, at or near the skids and at or near at least one antinode of the landing gear, the antinode being a point where a vibration amplitude has a local maximum.