Method of assembling a composite spar removable mandrel

Patent metadata

Field	Value
Publication number	US-11034113-B2
Application number	US-202016774105-A
Country	US
Kind code	B2
Filing date	Jan 28, 2020
Priority date	Jan 29, 2014
Publication date	Jun 15, 2021
Grant date	Jun 15, 2021

Abstract

A method of constructing a mandrel generally complementary to a spar cavity of a spar includes connecting a first component and a second component to form a central space there between and inserting a center component within the central space such that the center component retains the first component and second component in a desired position forming an outer surface of the mandrel which corresponds to an inner surface of the spar cavity.

First claim

What is claimed is:

1. A method of constructing a mandrel including a plurality of components, the mandrel being substantially complementary to a spar cavity of a spar, comprising:
connecting a first component and a second component to form a central space there between; and
inserting a center component within the central space such that the center component retains the first component and second component in a desired position forming an outer surface of the mandrel which corresponds to an inner surface of the spar cavity,
the first component having an exterior surface configured to form an interior leading edge of the spar or an interior trailing edge of the spar, and the second component having an exterior surface configured to form a portion of a lower interior surface of the spar or a portion of an upper interior surface of the spar, and the center component comprising a first end and a first protrusion, the first end and the first protrusion respectively configured to be received by the first component and the second component.

2. The method according to claim 1 , wherein connecting the first component and second component comprises magnetically coupling the first and second components.

3. The method according to claim 1 , wherein connecting the first component and second component comprises interlocking the first and second components using complementary keyway grooves.

4. The method according to claim 1 , wherein inserting the center component further comprises interlocking a portion of the center component with the first and second components.

5. The method according to claim 1 , wherein connecting the first and second components and inserting the component forms a first segment of the mandrel, the method further comprising:
forming a second segment by connecting a third component and a fourth component to form another central space there between;
inserting another center component within the another central space such that the another center component retains the third component and fourth component in a desired position forming another outer surface of the mandrel which corresponds to another inner surface of the spar cavity; and
connecting the formed first segment and second segment of the mandrel.

6. The method according to claim 1 , further comprising forming at least one of the first component, second component, and center component using a plastic material via an additive manufacturing method.

7. The method according to claim 1 , further comprising applying a layer of shrink wrap about the outer surface of the mandrel.

8. The method according to claim 7 , further comprising applying a bagging material about the shrink wrap, the bagging material being configured to apply a pressure to the inner surface of the spar cavity.

9. The method according to claim 1 , further comprising:
constructing a spar about the mandrel, wherein constructing the spar further comprises:
layering multiple plies of material about at least a portion of an exterior of the mandrel;
installing the mandrel in a final curing mold;
applying a pressure to at least one of an interior first surface or an interior second surface of the spar;
removing the mandrel from a center of the layered plies by individually removing the first, second, and center components; and
curing the layered plies.

10. The method according to claim 9 , wherein removing the mandrel includes the sequential steps of:
removing the center component of the mandrel; and
removing each of the first component and second component individually.

11. The method according to claim 9 , wherein the layered plies have varying fiber orientations relative to the mandrel.

12. The method according to claim 9 , wherein the layered plies are cured using a vacuum.

13. The method of claim 1 , wherein at least one of the first component, second component, or center component varies in shape along a length of the spar.

14. The method of claim 1 , further comprising connecting a third component and a fourth component adjacent the first and second components,
the third component having an exterior surface configured to form a portion of the interior leading edge of the spar or a portion of the interior trailing edge of the spar, and the fourth component having an exterior surface configured to form a second portion of the lower interior surface of the spar or a second portion of the upper interior surface of the spar, and the center component further comprising a second end and a second protrusion, the second end and the second protrusion respectively configured to be received by the third component and the fourth component.

15. The method of claim 1 , wherein at least one of the first component, second component, or center component further comprises a plurality of segments disposed over a length of the spar.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Jones Corey D
• Caputo Frank

Classifications

• B29C33/485

  cores or mandrels (collapsible mandrels for shaping tube ends B29C57/02; collapsible mandrels for winding and joining B29C53/824) · CPC title

• B64C2027/4736

  from composite materials · CPC title

• B29D99/0028 Primary

  hollow blades · CPC title

• B29D99/0025

  Producing blades or the like, e.g. blades for turbines, propellers, or wings · CPC title

• B29C70/342

  using isostatic pressure · CPC title