Systems and methods for making composite structures

Patent metadata

Field	Value
Publication number	US-11117307-B2
Application number	US-201916255724-A
Country	US
Kind code	B2
Filing date	Jan 23, 2019
Priority date	Jul 29, 2015
Publication date	Sep 14, 2021
Grant date	Sep 14, 2021

Abstract

A system for depositing a composite filler material into a channel of a composite structure includes an end-effector configured to extrude a bead of the filler material into the channel. The filler material can comprise a first group of relatively long fibers, a second group of relatively short fibers and a resin. A drive system is configured to move the end-effector relative to the channel, and a position sensor is configured to detect the position of the bead relative to the channel. A controller is configured to operate the drive system in response to the detected position and to operate the end-effector to heat and compress the filler material so as to orient the longer fibers in a substantially longitudinal direction relative to the channel and the shorter fibers in substantially random directions relative to the channel when the bead is extruded into the channel.

First claim

What is claimed is:

1. A method of in-situ fabricating a composite structure in a channel, the method comprising:
receiving a filler material within a barrel of an end-effector, wherein the filler material comprises a first group of fibers, a second group of fibers, and a resin;
applying a vacuum within the barrel of the end-effector to assist in the receiving of the filler material within the barrel;
operating the end-effector, wherein the operating comprises orienting the first group of fibers in a substantially longitudinal direction relative to the channel when extruded from the end-effector and orienting the second group of fibers in substantially random directions relative to the channel when extruded from the end-effector by rotating a helical extrusion screw within the barrel such that a thread of the screw rotates relative to an interior wall surface of the barrel;
extruding a bead of the oriented filler material from the end-effector into the channel.

2. The method of claim 1 , wherein:
the receiving comprises receiving the filler material at an aft aperture at an aft end of a barrel of the end-effector;
the operating further comprises rotating the helical extrusion screw disposed within the barrel by a motor of the end-effector to compress the filler material within the barrel and heating the filler material in the barrel; and
the extruding comprises passing the oriented filler material through a front aperture at a front end of the barrel.

3. The method of claim 1 , further comprising:
heating the filler material in the barrel, wherein the pulling the vacuum from the end-effector removes gasses generated from the heated filler material within the barrel.

4. The method of claim 1 , further comprising:
detecting a flow rate of the bead from a front aperture; and
adjusting an amount of the vacuum in response to the detected flow rate.

5. The method of claim 1 , further comprising detecting a position of the bead relative to the channel and adjusting an orientation of a front aperture relative to the channel in response to the detected position to align the bead in the channel.

6. The method of claim 2 , further comprising detecting a profile of the bead.

7. The method of claim 6 , further comprising adjusting operation of the motor in response to the detected profile to adjust a compression exerted by the helical extrusion screw on the filler material to conform the detected profile to a desired profile.

8. The method of claim 6 , further comprising adjusting the heating in response to the detected profile to adjust a temperature of the filler material to conform the detected profile to a desired profile.

9. The method of claim 6 , further comprising adjusting a translation speed corresponding to a moving of the end-effector in response to the detected profile to conform the detected profile to a desired profile.

10. The method of claim 6 , further comprising moving a gate across the front aperture to selectively occlude the front aperture to conform the detected profile with a desired profile.

11. The method of claim 2 , wherein the front aperture has a cross-sectional profile corresponding to a cross-sectional profile of the bead.

12. The method of claim 2 , further comprising:
detecting a flow rate of the bead from the front aperture; and
adjusting a rotation speed of the motor in response to the detected flow rate to adjust a compression exerted by the helical extrusion screw on the filler material.

13. The method of claim 2 , further comprising:
detecting a temperature of the filler material in the barrel; and
adjusting the heating in response to the detected temperature.

14. The method of claim 2 , wherein the receiving comprises receiving the filler material from a hopper in fluid communication with the aft aperture.

15. The method of claim 14 , further comprising heating the filler material in the hopper.

16. The method of claim 15 , further comprising:
detecting a flow rate of the bead from the front aperture; and
adjusting the heating of the barrel and the hopper in response to the detected flow rate.

17. The method of claim 15 , wherein:
the filler material in the hopper is heated to a temperature of approximately 140 degrees Fahrenheit; and
the filler material in the barrel is heated to a temperature of approximately 190 degrees Fahrenheit.

18. The method of claim 15 , further comprising:
detecting a first temperature of the filler material in the hopper;
detecting a second temperature of the filler material in the barrel; and
selectively adjusting the heating in response to the detected first and second temperatures.

19. The method of claim 14 , wherein the helical extrusion screw comprises a first screw, and further comprising agitating the filler material by a second screw in the hopper before the filler material passes into the barrel.

20. The method of claim 1 , wherein the channel is of an aircraft stringer and wherein the composite structure is a noodle of the aircraft stringer.

21. The method of claim 1 , further comprising:
moving the end-effector relative to the channel during the extruding to form the composite structure;
detecting a position of the bead relative to the channel; and
selectively adjusting the extruding and the moving in response to the detected position.

22. The method of claim 21 , wherein the end-effector is disposed on an arm of a robot and wherein the moving comprises moving the robot on a carriage relative to the channel.

23. The method of claim 1 , wherein the first group of fibers have a first length and the second group of fibers have a second length shorter than the first length.

24. A method of in-situ fabricating a composite structure, the method comprising:
receiving a material at an end-effector, wherein the material comprises a first group of fibers, a second group of fibers, and a resin;
applying a vacuum within the end-effector to assist in the receiving of the filler material at the end effector;
operating the end-effector, wherein the operating comprises orienting the first group of fibers in a substantially longitudinal direction relative to a channel when extruded from the end-effector and orienting the second group of fibers in substantially random directions when extruded from the end-effector to form an orientated filler material;
extruding a bead of the oriented filler material from the end-effector onto a workpiece;
moving the end-effector relative to the workpiece during the extruding to form the composite structure.

25. The method of claim 24 , wherein first fibers in the first group of fibers have a first length and second fibers in the second group of fibers have a second length that is shorter than the first length.

Assignees

• Boeing Co

Inventors

• Song Weidong
• Perron Daniel J
• Moore Stephen G
• Langabeer Jamie J
• Robbins Jonathan D
• Olberg Jeffrey

Classifications

• B29D99/0005

  Producing noodles, i.e. composite gap fillers, characterised by their construction · CPC title

• B64U20/65

  Composite materials · CPC title

• B29C2948/92609

  Dimensions · CPC title

• B29C2948/92704

  Temperature · CPC title

• B29C66/43441

  with two right angles, e.g. for making T-shaped pieces, H-shaped pieces · CPC title