Patent ID: 9637212
Date: 2017-05-02
CPC Classifications: B32B,B64C,F16F

Claim:
1. An energy absorbing rub strip system, comprising: an aircraft comprising a fuselage; a core material having a length, the core material being configured to buckle under an application of a predetermined amount of force; and a fairing positioned over the core material, the fairing being configured to be attached to a fuselage of the aircraft adjacent a passenger compartment of the aircraft; wherein the core material extends from a potential expected landing contact point on the fuselage to a potential expected takeoff contact point on the fuselage and wherein the entire length of the core material is positioned between a landing gear of the aircraft and a bulkhead that separates the passenger compartment from a tail of the aircraft, wherein the potential expected landing contact point is determined from a first vector extended from the landing gear in a landing configuration to the fuselage and wherein the potential expected takeoff contact point is determined from a second vector extended from the landing gear in a takeoff configuration to the fuselage, the takeoff configuration of the landing gear being different from the landing configuration.