Aircraft body mounted energy absorbing rub strip

Patent metadata

Field	Value
Publication number	US-9637212-B2
Application number	US-201414249576-A
Country	US
Kind code	B2
Filing date	Apr 10, 2014
Priority date	Apr 10, 2014
Publication date	May 2, 2017
Grant date	May 2, 2017

Abstract

An energy absorbing rub strip having a core material and a fairing positioned over the core material. The core material may be configured to buckle under the application of a predetermined amount of force and the fairing may be configured to be attached to a fuselage of an aircraft. The fairing may be made out of an abrasive-resistant material such as titanium or a nickel-based metal. The core material may be comprised of an aluminum honeycomb. The core material may be comprised of a dual density material. The length of the rub strip may extend beyond potential contact points on the fuselage during landing and takeoff. Upon a ground contact event, the thickness of deformed/buckled core material may be measured to determine if the ground contact event may have caused structural damage to the aircraft.

First claim

What is claimed is:

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.

2. The system of claim 1 , further comprising at least two mounting rails attached to the fairing, wherein the fairing is connected to the fuselage of the aircraft via the mounting rails.

3. The system of claim 2 , the fairing and the at least two mounting rails comprised of titanium.

4. The system of claim 1 , the core material comprised of aluminum honeycomb.

5. The system of claim 1 , the core material comprised of a dual density material.

6. The system of claim 1 , the fairing comprised of an abrasion-resistant material.

7. The system of claim 6 , the fairing comprised of titanium.

8. The system of claim 6 , the fairing comprised of nickel-based metal.

9. A method of using an energy absorbing rub strip on an aircraft fuselage, the method comprising:
positioning an abrasion-resistant fairing around an exterior portion of a core material to form an energy absorbing rub strip, the core material being configured to buckle under an application of a predetermined amount of force;
connecting the energy absorbing rub strip having a length to an exterior portion of a fuselage of an aircraft adjacent a passenger compartment of the aircraft;
determining a potential expected landing contact point by extending a first vector from the landing gear in a landing configuration to the fuselage; and
determining a potential expected takeoff contact point by extending a second vector from the landing gear in a takeoff configuration to the fuselage, the takeoff configuration of the landing gear being different from the landing configuration;
wherein the core material extends from the potential expected landing contact point on the fuselage to the potential expected takeoff contact point on the fuselage and wherein the entire length of the energy absorbing rub strip is positioned between the landing gear of the aircraft and a bulkhead that separates the passenger compartment from a tail of the aircraft.

10. The method of claim 9 , further comprising connecting the energy absorbing rub strip to the fuselage of the aircraft adjacent to a passenger compartment of the aircraft.

11. The method of claim 9 , further comprising:
determining a thickness of core material deformed upon contact with a ground surface; and
determining if contact with the ground surface caused any structural damage to the fuselage based on the thickness of core material deformed.

12. The method of claim 11 , further comprising replacing the abrasion-resistant fairing and the core material with a second abrasion-resistant fairing around an exterior portion of a second core material to form a second energy absorbing rub strip.

13. The method of claim 11 , wherein determining if contact with the ground surface caused any structural damage to the fuselage further comprises determining whether the thickness of core material deformed is greater than or equal to a threshold thickness.

14. An aircraft, the aircraft comprising:
a fuselage;
a passenger compartment within an interior of the fuselage;
a bulkhead separating the passenger compartment from an end of the fuselage with a tail; and
a rub strip having a length attached to an exterior of the fuselage adjacent to a portion of the passenger compartment, the rub strip comprising an abrasion-resistant fairing around an exterior portion of a core material, wherein the entire length of the rub strip is positioned between a landing gear of the aircraft and the bulkhead;
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,
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.

15. The aircraft of claim 14 , the core material being configured to buckle under an application of a predetermined amount of energy.

16. The aircraft of claim 15 , the core material comprising aluminum honeycomb.

17. The aircraft of claim 14 , further comprising the core material comprised of a dual density material.

18. The aircraft of claim 14 , further comprising the abrasion-resistant fairing comprising titanium or a nickel-based metal.

19. The aircraft of claim 14 , wherein a portion of the abrasion-resistant fairing is tapered and the core material does not extend into the tapered portion of the abrasion-resistant fairing.

Assignees

• Boeing Co

Inventors

• Cottet Justin D
• Kepner Roger S
• Drake Michael L

Classifications

• B32B2307/558

  Impact strength, toughness · CPC title

• B32B2311/18

  Titanium · CPC title

• B32B15/015

  the said other metal being copper or nickel or an alloy thereof · CPC title

• B32B2605/18

  Aircraft · CPC title

• B32B2307/722

  Non-uniform density · CPC title