Blow off panel for controlling hydrodynamic ram

• US 4,828,206 A
• Filed: 06/26/1987
• Issued: 05/09/1989
• Est. Priority Date: 06/26/1987
• Status: Expired due to Term

• Current Assignee: Grumman Aerospace Corporation Bethpage NY 11714
• Original Assignee: Grumman Aerospace Corporation (Northrop Grumman Corporation)
• Inventors: Bruno, Joseph W., Cacho-Negrete, Carlos
• Primary Examiner(s): Barefoot, Galen
• Assistant Examiner(s): Corl, Rodney
• Application Number:
  US07/067,736
• Time in Patent Office: 683 Days
• Field of Search: 244/121, 244/132, 89/36.02, 89/36.11, 220/900, 428/102, 428/103, 428/912
• US Class Current: 244/132
• CPC Class Codes: B64C 1/06 Frames; Stringers; Longerons ; Fuselage sections
• CPC Class Codes: B64C 2001/0072 from composite materials
• CPC Class Codes: B64C 3/26 Construction, shape, or attachment of separate skins, e.g. panels
• CPC Class Codes: B64C 3/34 Tanks constructed integrally with wings, e.g. for fuel or water
• CPC Class Codes: Y02T 50/40 Weight reduction
• CPC Class Codes: Y10S 220/90 Rupture proof
• CPC Class Codes: Y10T 428/24041 Discontinuous or differential coating, impregnation, or bond

Abstract

A wing structure for controlling hydrodynamic ram and which includes a substructure having a plurality of individual cells each with a respective boundary, a composite skin disposed on the substructure, and perforations disposed through the composite skin which define a plurality of sections in the composite skin such that each section of the plurality of sections of the composite skin is disposed within the confines of each respective boundary of each of the plurality of individual cells of the substructure so that each section of the plurality of sections of the composite skin forms a blow off panel for relieving pressure created by hydrodynamic ram in a respective individual cell of the plurality of individual cells of the substructure.

Claims

1. A wing structure for controlling hydrodynamic ram, comprising:

(a) a substructure having a plurality of individual cells each with a respective boundary;

(b) a composite skin disposed on said substructure; and

(c) first means disposed through said composite skin and defining a plurality of sections in said composite skin such that each section of said plurality of sections of said composite skin is disposed within the confines of said each respective boundary of each of said plurality of individual cells of said substructure so that said each section of said plurality of sections of said composite skin forms a blow off panel for relieving pressure created by hydrodynamic ram in a respective individual cell of said plurality of individual cells of said substructure, said first means including first perforations along which said blow off panel can tear off; and

(d) second means disposed in said composite skin for preventing said composite skin fram cracking from said first perforations and for preventing the growth of running cracks created by penetration damage.

2. A wing structure as defined in claim 1;

further comprising stitches disposed in said perforations for arresting the growth of delamination in said composite skin created by impact damage.

3. A wing structure as defined in claim 2, wherein said blow off panels have corners at which said stitches touch so that said blow off panels tear off more cleanly and completely.

4. A wing structure as defined in claim 3, wherein said stitches are a composite.

5. A wing structure as defined in claim 4, wherein said composite stitches are kevlar/epoxy.

6. A wing structure as defined in claim 5, wherein said kevlar/epoxy composite stitches and said composite skin are cocured.

7. A wing structure as defined in claim 1, wherein said second means includes a composite.

8. A wing structure as defined in claim 6, wherein said composite is fiberglass/epoxy.

9. A wing structure as defined in claim 1;

further comprising third means for mounting said composite skin to said substructure.

10. A wing structure as defined in claim 9, wherein said composite skin contains second perforations for receiving said third means.

11. A wing structure as defined in claim 10;

further comprising fourth means disposed in said composite skin for preventing said composite skin from cracking from said second perforations.

12. A wing structure as defined in claim 11, wherein said fourth means includes a composite.

13. A wing structure as defined in claim 12, wherein said composite is fiberglass/epoxy.