Apparatus for fabricating highly contoured composite stiffeners with reduced wrinkling

Patent metadata

Field	Value
Publication number	US-9242393-B2
Application number	US-201414324239-A
Country	US
Kind code	B2
Filing date	Jul 7, 2014
Priority date	Sep 23, 2010
Publication date	Jan 26, 2016
Grant date	Jan 26, 2016

Abstract

A mandrel having an out-of-plane curvature and a corresponding in-plane change in mandrel geometry is used to fabricate substantially wrinkle-free, fiber reinforced stiffeners having an out-of-plane curvature.

First claim

What is claimed:

1. Apparatus for forming a substantially wrinkle-free fiber reinforced composite stiffener having an out-of-plane curved section along its length, comprising:
a mandrel on which fiber reinforced composite plies may be formed, the mandrel having a sidewall comprising a first tool face, the sidewall including a first portion along a first length that is less than a total length of the sidewall, the sidewall further including a second portion along a second length that is less than the total length and a third portion along a third length that is less than the total length, the first portion being between the second portion and the third portion, the first portion having an out-of-plane curvature and an in-plane curvature, the second portion having a second curvature different than the in-plane curvature and the out-of-plane curvature, the third portion having the second curvature, the mandrel further having a second tool face along the sidewall and connected to the sidewall at an angle, the second tool face also having the out-of-plane curvature along the first length, and the second tool face further having the second curvature along the second length and the third length.

2. The apparatus of claim 1 , wherein the first and second tool faces extend transverse to each other.

3. The apparatus of claim 2 , wherein the first and second tool faces are contiguous to each other.

4. The apparatus of claim 1 , further comprising:
tooling for compacting composite plies against the first and second tool faces, the tooling including a first curved surface substantially matching the out-of-plane curvature, and a second curved surface substantially matching the in plane change in geometry.

5. Apparatus for fabricating a fiber reinforced, substantially wrinkle-free composite stringer, the apparatus comprising:
a mandrel on which fiber reinforced composite plies may be formed, the mandrel having a sidewall, the sidewall including a first portion along a first length that is less than a total length of the sidewall, the sidewall further including a second portion along a second length that is less than the total length and a third portion along a third length that is less than the total length, the first portion being between the second portion and the third portion, the first portion having an out-of-plane curvature and an in-plane curvature, the second portion having a second curvature different than the in-plane curvature and the out-of-plane curvature, the third portion having the second curvature, the mandrel further having a bottom tool face along the sidewall and connected to the sidewall at an angle, the bottom tool face also having the out-of-plane curvature along the first length, and the bottom tool face further having the second curvature along the second length and the third length.

6. The apparatus of claim 5 , wherein the stringer is hat shaped in cross section and the mandrel includes:
a top face for forming a cap of the stringer, the top face extending at an angle from the sidewall, opposite the bottom tool face relative to the sidewall,
side faces for respectively forming opposite sides of the stringer, wherein the sidewall is one of the side faces, and
a pair of bottom faces for forming oppositely extending flanges of the stringer, wherein the bottom tool face is one of the pair of bottom faces.

7. The apparatus of claim 6 , wherein:
the top face and each of the bottom faces includes a section having the out-of-plane curvature, and
each of the side faces includes a section having the corresponding in-plane change in geometry.

8. The apparatus of claim 5 , wherein:
the mandrel includes a top, sides and a base,
the out-of-plane curvature is defined in the base of the mandrel, and
the corresponding in-plane change in geometry is defined as a widening of the sides of the mandrel.

9. The apparatus of claim 5 , wherein the stringer mandrel includes tool faces for forming a stringer cross section selected from the group consisting of an I, a J, a Z, an L, a C, and a hat.

10. Apparatus for forming a substantially wrinkle-free fiber reinforced composite stringer having an out-of-plane curved section along its length, comprising:
a mandrel on which fiber reinforced composite plies may be formed, the mandrel having a sidewall comprising a first tool face, the sidewall including a first portion along a first length that is less than a total length of the sidewall, the sidewall further including a second portion along a second length that is less than the total length and a third portion along a third length that is less than the total length, the first portion being between the second portion and the third portion, the first portion having an out-of-plane curvature and an in-plane curvature, the second portion having a second curvature different than the in-plane curvature and the out-of-plane curvature, the third portion having the second curvature, the mandrel further having a second tool face along the sidewall and connected to the sidewall at an angle, the second tool face also having the out-of-plane curvature along the first length, and the second tool face further having the second curvature along the second length and the third length; and
a pair of compaction tools for compacting the plies against the first and second tool faces, the compaction tools each including a curved surface substantially matching the out-of-plane curved section of the first tool face, and a curved surface substantially matching the section of the second tool face having the in-plane change in geometry.

Assignees

• Boeing Co

Inventors

• Bland Jamel R

Classifications

• B29C33/76

  Cores (B29C33/02 - B29C33/70, {B29C41/40, B29C53/74, B29C53/82} take precedence) · CPC title

• B29C70/342

  using isostatic pressure · CPC title

• B29C33/38 Primary

  characterised by the material or the manufacturing process (B29C33/44 takes precedence) · CPC title

• B29L2031/3076

  Aircrafts (blades, propellers B29L2031/08) · CPC title

• Y02T50/433

  Cross-Sectional Technologies · mapped topic