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US 8,551,382 B2Granted
Modified blade stiffener and fabrication method therefor
AssigneeThe Boeing Company
InventorsMichael R. Anderson, Darrell D. Jones, Carla D. Murray
Life of this patent
Estimating the term…
Abstract
The disclosure is generally directed to a modified blade stiffener having enhanced mechanical properties. An illustrative embodiment of the modified blade stiffener includes a stiffener-forming material shaped into a pair of coupled blades having first and second ends, a filler cavity provided at the first end of the blades, a blade filler provided in the filler cavity and a pair of blade flanges provided at the second end of the blades.
Claims19
A method of forming a blade stiffener, comprising:
- using a layup charge of stiffener-forming material and a blade-forming assembly having a first tool die, a second tool die, a tool gap between the first tool die and the second tool die, a first forming cavity in the first tool die, and a second forming cavity in the second tool die, wherein using comprises bridging the tool gap with the layup charge to form a blade arm connecting portion;
- placing a blade filler on the blade arm connecting portion at the tool gap;
- pressing, using a forming bar, said blade filler through the tool gap between the first tool die and the second tool die until the blade filler reaches and extends into the first forming cavity and the second forming cavity;
- removing the forming bar;
- and
- pressing said tool dies together such that a first side of the layup charge contacts the first forming cavity in the first tool die and the second forming cavity in the second tool die, and an opposite side of the layup charge contacts the blade filler, and the blade arm connecting portion extends between the first tool die and the second tool die, with the tool gap being substantially eliminated.
3 more elements
A method of forming a blade stiffener for aircraft structure, comprising:
- using a layup charge of stiffener-forming material and a blade-forming assembly having a first tool die, a second tool die, a tool gap between the first tool die and the second tool die, a first forming cavity in the first tool die, and a second forming cavity in the second tool die, wherein using comprises bridging the tool gap with the layup charge to form a blade arm connecting portion;
- placing a blade filler on the blade arm connecting portion the tool gap;
- forming a first blade, a second blade, a first blade flange, a second blade flange, a first blade arm, a second blade arm, and a filler cavity of the blade stiffener by pressing the blade filler through the tool gap between the first tool die and the second tool die until the blade filler reaches and extends into the first forming cavity and the second forming cavity, with the first blade and the first blade arm, being connected to the first blade, engaging the first tool die, and the second blade and second blade arm, being connected to the second blade, engaging the second tool die such that a first side of the layup charge contacts the first forming cavity and the second forming cavity, and an opposite side of said layup charge contacts the blade filler, and the blade arm connecting portion extends between the first tool die and the second tool die;
- leaving the blade filler in the filler cavity;
- pressing the first tool die and the second tool die together to substantially eliminate the tool gap;
- and
- providing a flange filler between the first blade and the second blade.
4 more elements
A method of forming a blade stiffener for aircraft structure, comprising:
- using a layup charge of stiffener-forming material and a blade-forming assembly having a first tool die, a second tool die, a tool gap between the first tool die and the second tool die, a first forming cavity in the first tool die, and a second forming cavity in the second tool die, wherein using comprises bridging the tool gap with the layup charge to form a blade arm connecting portion;
- placing a blade filler on the blade arm connecting portion at the tool gap;
- forming a first blade, a second blade, a first blade flange, a second blade flange, and a filler cavity of the blade stiffener by pressing the blade filler through the tool gap between the first tool die and the second tool die until the blade filler reaches and extends into the first forming cavity and the second forming cavity, with the blade and the first blade flange each engaging the first tool die, and the second blade and the second blade flange each engaging the second tool die such that a first side of the layup charge contacts the first forming cavity and the second forming cavity, and an opposite side of the layup charge contacts the blade filler, and the blade arm connecting portion extends between the first tool die and the second tool die;
- leaving the blade filler in the filler cavity;
- pressing the first tool die and the second tool die together to substantially eliminate the tool gap;
- providing a flange filler between the first blade flange and the second blade flange;
- engaging the first blade and the second blade with a curing tool;
- curing the first blade and the second blade;
- and
- at least one of:
- co-curing, and bonding, at least one of:
- the first blade flange and the second blade flange to a composite structure.
9 more elements
Dependencies are inferred from the claim text.