Emergency landing stability system for aircraft

Patent metadata

Field	Value
Publication number	US-10583918-B2
Application number	US-201916395613-A
Country	US
Kind code	B2
Filing date	Apr 26, 2019
Priority date	Apr 19, 2016
Publication date	Mar 10, 2020
Grant date	Mar 10, 2020

Abstract

An aircraft emergency landing stability system includes an aircraft, including a fuselage and landing gear, and a blister projecting downwardly from a fuselage-underside surface of the fuselage proximate to a nose of the fuselage. The blister locates a secondary contact surface of the aircraft forward of a center of gravity of the aircraft to mitigate a nose-down pitching moment of the aircraft created in response to contact with a landing surface during an emergency landing.

First claim

What is claimed is:

1. An aircraft emergency landing stability system comprising:
an aircraft having a center of gravity and comprising a fuselage and landing gear, said fuselage comprising a nose and a fuselage-underside surface; and
a blister projecting downwardly from said fuselage-underside surface of said fuselage proximate to said nose of said fuselage; and wherein:
said blister is located forward of said center of gravity of said aircraft; and
during an emergency landing, an initial contact surface of said aircraft is located on said fuselage-underside surface of said fuselage, aft of said center of gravity of said aircraft, and said blister locates a secondary contact surface of said aircraft on said blister, forward of said center of gravity of said aircraft, so that said blister contacts a landing surface to mitigate a nose-down pitching moment of said aircraft, created in response to contact of said fuselage-underside surface with said landing surface.

2. The system of claim 1 wherein, during said emergency landing, said blister locates said secondary contact surface a sufficient distance forward of said center of gravity such that a reaction force passes forward of said center of gravity.

3. The system of claim 1 wherein:
said landing gear comprises a nose landing gear, and
said blister accommodates said nose landing gear.

4. The system of claim 3 wherein:
said blister comprises a blister-underside surface, and
said blister-underside surface is structurally reinforced to withstand a contact force applied to said blister in response to contact with said landing surface.

5. The system of claim 4 wherein:
said blister comprises at least one blister-underside skin panel, said blister-underside skin panel comprising:
an exterior layer comprising a non-deformable, low friction material; and
an interior layer comprising a deformable, high friction material, and said exterior layer forms at least a portion of said blister-underside surface.

6. The system of claim 1 further comprising a skid deployable from said blister, wherein said secondary contact surface is located on said skid.

7. The system of claim 1 further comprising a ski deployable from said blister, wherein said secondary contact surface is located on said ski.

8. The system of claim 7 wherein said ski comprises a foil shape.

9. The system of claim 1 further comprising:
at least one hydrodynamic drag element; and
at least one tension cable interconnecting said hydrodynamic drag element to said fuselage,
wherein said hydrodynamic drag element comprises a shape configured to produce a hydrodynamic force acting downwardly sufficient to create a nose-up pitching moment.

10. An aircraft having a center of gravity and comprising:
a fuselage comprising a nose and a fuselage-underside surface; and
a blister projecting downwardly from said fuselage-underside surface of said fuselage proximate to said nose of said fuselage; and wherein:
said blister is located forward of said center of gravity of said aircraft;
during an emergency landing, an initial contact surface of said aircraft is located on said fuselage-underside surface of said fuselage, aft of said center of gravity of said aircraft, and said blister contacts a landing surface such that a secondary contact surface of said aircraft is located on said blister, forward of said center of gravity of said aircraft, to mitigate a nose-down pitching moment of said aircraft, created in response to contact of said initial contact surface with said landing surface.

11. The aircraft of claim 10 further comprising a nose landing gear, wherein said blister accommodates said nose landing gear.

12. The aircraft of claim 10 wherein, during said emergency landing, said blister locates said secondary contact surface a sufficient distance forward of said center of gravity of said aircraft such that a reaction force passes forward of said center of gravity of said aircraft so as to create a nose-up pitching moment.

13. The aircraft of claim 10 wherein:
said blister comprises a blister-underside surface, and
said blister-underside surface is structurally reinforced to withstand a contact force applied to said blister in response to contact with said landing surface.

14. The aircraft of claim 13 wherein:
said blister comprises at least one blister-underside skin panel, said blister-underside skin panel comprising:
an exterior layer comprising a non-deformable, low friction material; and
an interior layer comprising a deformable, high friction material, and said exterior layer forms at least a portion of said blister-underside surface.

15. The aircraft of claim 10 further comprising one of a skid deployable from said blister, a ski deployable from said blister, or a drag device deployable from said fuselage.

16. The aircraft of claim 10 further comprising:
at least one hydrodynamic drag element; and
at least one tension cable interconnecting said hydrodynamic drag element to said fuselage,
wherein said hydrodynamic drag element comprises a shape configured to produce a hydrodynamic force acting downwardly sufficient to create a nose-up pitching moment.

17. An aircraft having a center of gravity and comprising:
a fuselage comprising a fuselage-underside surface;
landing gear; and
a landing stability apparatus coupled to said fuselage,
wherein, during an emergency landing, an initial contact surface of said aircraft is located on said fuselage-underside surface of said fuselage, aft of said center of gravity of said aircraft, and said landing stability apparatus locates a secondary contact surface of said aircraft forward of said center of gravity of said aircraft to mitigate a nose-down pitching moment of said fuselage created in response to contact of said initial contact surface with a landing surface.

18. The aircraft of claim 17 wherein said landing stability apparatus comprises at least one skid deployable from said fuselage-underside surface of said fuselage, forward of said center of gravity of said aircraft.

19. The aircraft of claim 17 wherein said landing stability apparatus comprises at least one ski deployable from said fuselage-underside surface of said fuselage, forward of said center of gravity of said aircraft.

20. The aircraft of claim 17 wherein said landing stability apparatus comprises a drag device deployable from said fuselage, aft of said center of gravity of said aircraft.

Assignees

• Boeing Co

Inventors

• Grip Robert E
• Kent Steven R
• Rothaupt Ted K
• Rawdon Blaine K

Classifications

• B64C25/52

  Skis or runners · CPC title

• B64C25/32 Primary

  characterised by elements which contact the ground or similar surface  (arrester hooks B64C25/68) · CPC title

• B64C2001/0045

  Fuselages characterised by special shapes · CPC title

• B64C25/30

  emergency actuated · CPC title

• B64C7/00

  Structures or fairings not otherwise provided for · CPC title