High efficiency external airbag for crash attenuation

• US 9,487,301 B2
• Filed: 02/23/2011
• Issued: 11/08/2016
• Est. Priority Date: 02/23/2011
• Status: Active Grant

• Current Assignee: Textron Innovations Incorporated (Textron Inc)
• Original Assignee: Textron Innovations Incorporated (Textron Inc)
• Inventors: Hill, Andrew T., Lu, Zi, Lynds, Robert S., Hansen, Andrew R.
• Primary Examiner(s): Sanderson, Joseph W
• Application Number:
  US13/696,970
• Publication Number:
  US 20130062465A1
• Time in Patent Office: 2,085 Days
• Field of Search: 244/107, 244/100.A, 244/139, 280/728.1, 280/729, 280/730.1, 280/743.2, 188/298, 188/377
• US Class Current: 1/1
• CPC Class Codes: B64C 2025/325 specially adapted for helicopters
• CPC Class Codes: B64C 25/52 Skis or runners
• CPC Class Codes: B64D 2201/00 Airbags mounted in aircraft for any use
• CPC Class Codes: B64D 25/00 Emergency apparatus or devices, not otherwise provided for parachutes B64D17/00, B64D19/00; jettisoning of fuel tanks or fuel per se B64D37/00; specially adapted for protection against criminal attack, e.g. anti-hijacking systems B64D45/0015 ; safety belts or body harnesses in general A62B35/00; safety belts or body harnesses for land vehicles B60R22/00; jettisonable parts of fuselage facilitating emergency escape B64C

Abstract

An external airbag for an aircraft includes an inflatable bladder having a top portion and a bottom portion, the top portion being generally adjacent to an exterior of the aircraft. A widthwise panel divides the inflatable bladder into a first cylindrical portion and a second cylindrical portion. The widthwise panel acts to restrict outward bulging of the inflatable bladder. An aperture in the widthwise panel may be used for allowing gas communication between the first cylindrical portion and a second cylindrical portion.

Claims

1. An external airbag for minimizing peak accelerations of an aircraft during a crash landing, the external airbag comprising:

a selectively deployable inflatable bladder having a top portion and a bottom portion, the top portion being generally adjacent to an exterior of the aircraft, the top portion and the bottom portion defining a length and a central axis normal to the aircraft, the inflatable bladder being configured to maintain a selected rectangular shape while absorbing compressive loads along the central axis from the bottom portion contacting a surface;

a widthwise panel dividing the inflatable bladder into a first cylindrical portion and a second cylindrical portion, the widthwise panel being parallel to the central axis of the inflatable bladder and configured to maintain the shape of the inflatable bladder under compression, such that the aircraft experiences approximately linear deceleration during the crash landing; and

a base plate located on the inflatable bladder, the base plate being configured to couple the top portion of the external airbag beneath a fuselage of the aircraft;

wherein the base plate partially defines the shape of the top portion;

wherein the first cylindrical portion is forward of the second cylindrical portion;

wherein the widthwise panel entirely spans across an interior of the inflatable bladder; and

wherein the widthwise panel is configured to prevent fluid communications between the first cylindrical portion and the second cylindrical portion.

2. The external airbag according to claim 1, further comprising:

a lengthwise panel dividing the first cylindrical portion into a first quadrant and a second quadrant, the lengthwise panel also dividing the second cylindrical portion into a third quadrant and a fourth quadrant.

3. The external airbag according to claim 1, wherein the widthwise panel is connected to the top portion and the bottom portion, thereby restricting the top portion and the bottom portion from bulging approximate to where the widthwise panel is connected to the top portion and the bottom portion.

4. The external airbag according to claim 1, wherein the widthwise panel restricts outward bulging in the top portion and the bottom portion, thereby increasing a stroke efficiency of the external airbag.

5. The external airbag according to claim 1, wherein the widthwise panel connects radial side portions of the inflatable bladder, so as to restrict the width of the inflatable bladder.

6. The external airbag according to claim 1, further comprising:

a vent configured to release gas from within the inflatable bladder during compression of the inflatable bladder.

7. The external airbag according to claim 1, further comprising:

a gas generator operably associated with the inflatable bladder, the gas generator configured to selectively inflate the inflatable bladder prior to an impact.

8. An external airbag for minimizing peak accelerations of an aircraft during a crash landing, the external airbag comprising:

a selectively deployable inflatable bladder having a top portion and a bottom portion, the top portion being generally adjacent to an exterior of the aircraft, the top portion and the bottom portion defining a length and a central axis normal to the aircraft, the inflatable bladder being configured to maintain a selected shape while absorbing compressive loads along the central axis from the bottom portion contacting a surface;

a widthwise panel having a rectangular shape, the widthwise panel attached to the top portion, the bottom portion, and sides of the inflatable bladder, the widthwise panel being parallel to the central axis of the inflatable bladder and configured to maintain the shape of the inflatable bladder under compression, such that the aircraft experiences approximately linear deceleration during the crash landing;

a base plate located on the inflatable bladder, the base plate being configured to couple the top portion of the external airbag beneath a fuselage of the aircraft;

wherein the base plate spans across the top portion of the inflatable bladder;

wherein the widthwise panel forms a forward cylindrical portion and an aft cylindrical portion;

wherein the widthwise panel is configured to prevent fluid communications; and

wherein the widthwise panel restricts outward deformation of the inflatable bladder and substantially spans across an interior of the inflatable bladder; and

wherein the selected shape is a space efficient rectangular prism shape adjacent the widthwise panel.

9. The external airbag according to claim 8, further comprising:

a lengthwise panel attached to the top portion, the bottom portion, a forward portion, and an aft portion;

wherein the lengthwise panel restricts outward deformation of the inflatable bladder.

10. The external airbag according to claim 8, further comprising:

a vent located on the inflatable bladder.

11. The external airbag according to claim 8, further comprising:

a gas generator operably associated with the inflatable bladder, the gas generator configured to selectively inflate the inflatable bladder prior to an impact.

12. The external airbag according to claim 8, wherein the widthwise panel restricts outward bulging in the top portion and the bottom portion, thereby increasing a stroke efficiency of the external airbag.

13. An external airbag for minimizing peak accelerations of an aircraft during a crash landing, the external airbag comprising:

a selectively deployable inflatable bladder located exterior to the aircraft, the inflatable bladder having a top portion, and a bottom portion, the top portion being generally adjacent to an exterior of the aircraft, the inflatable bladder being configured to maintain a selected shape while absorbing compressive loads along a central axis from the bottom portion contacting a surface;

a diagonal panel located within the inflatable bladder, the diagonal panel being configured to resist a rolling distortion of the inflatable bladder, the diagonal panel extending from the top portion and a forward side of the inflatable bladder to the bottom portion and an aft side of the inflatable bladder to resist deformation of the inflatable bladder due to a forward velocity of the aircraft during the crash landing, such that the aircraft experiences approximately linear deceleration during the crash landing;

a base plate located on the inflatable bladder, the base plate being configured to rigidly couple the top portion of the external airbag beneath a fuselage of the aircraft;

wherein the diagonal panel is configured to prevent fluid communications;

wherein the selected shape resembles a space efficient rectangular prism shape; and

wherein the diagonal panel spans across the entire inflatable bladder.

14. The external airbag according to claim 13, further comprising:

a widthwise panel attached to the top portion, the bottom portion, and sides of the inflatable bladder, the widthwise panel being parallel to the central axis of the inflatable bladder and configured to maintain the shape of the inflatable bladder under compression, such that the aircraft experiences approximately linear deceleration upon during the crash landing; and

wherein the widthwise panel restricts outward deformation of the inflatable bladder.

15. The external airbag according to claim 13, further comprising:

a lengthwise panel attached to the top portion, the bottom portion, a forward portion, and an aft portion;

wherein the lengthwise panel restricts outward deformation of the inflatable bladder.