N181-028
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TITLE: Precision Machining
of Composite Structures
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TECHNOLOGY AREA(S): Air
Platform, Materials/Processes
ACQUISITION PROGRAM: PMA 261
H-53 Heavy Lift Helicopters
OBJECTIVE: Develop an
innovative machining process that can effectively and precisely machine holes
in composite structures while preventing induced damage.
DESCRIPTION: Fiber reinforced
polymer (FRP) composites are a key enabling material in several U.S. military
aircraft. Composite materials are used in primary load bearing structures, as
well as secondary non-load bearing structures and skins. The size and
complexity of composite components is constantly increasing as the desire for
reduced weight drives the replacement of metallic components with low-density
FRP.
FRP materials are currently being machined using techniques adapted from
traditional metalworking, however the unique material properties of FRPs
present several difficulties in the drilling of a simple fastener hole, of
which there may be several dozen on a single aircraft component. Additionally,
fastener holes often require precision countersinks. The highly abrasive
nature of carbon, glass, and aramid fibers reduces tool life of traditional
tungsten carbide drill bits, necessitating their frequent changing, and also
affecting hole diameter as the drill bit is abraded by the material. The
frictional heat generated by the drill bit can cause severe damage to the
polymer matrix, resulting in a loss of strength that can be extremely difficult
to detect. Lastly, FRP materials are prone to delamination in several
situations due to improper drilling technique.
The Navy needs a tool to create a finished precision fastener hole with
countersink using an innovative precision machining technique. The technique
should provide precise replication of high-quality holes with high placement
accuracy while reducing the amount of consumable tooling required, such as
drill bits, when compared to traditional machining techniques through the same
composite material. This precision fastener hole and countersink machining
process should remove material without inducing damage to, or contamination of,
the actual part. Precision within the specified hole diameter +0.006 in max,
having a surface roughness height rating of 250 or less, and no breakout plies
on the exit side. For thickness greater than 0.100 in, no delamination 0.010
in deep from edge of hole or into the part from hole. No splintering allowed
beyond 0.010 in deep at entrance/exit of hole. For placement, the precision
machining technique does not require a pilot hole be present to maintain
dimensional accuracy. Automation can be leveraged to increase hole and
countersink precision and placement. Careful control of any applied or induced
heat must be demonstrated to not cause damage to the composite material. The
temperature limit at the location of the final diameter size should not exceed
50° F below the glass transition temperature for the composite material during
the machining operation.
PHASE I: Develop an
innovative approach for a precision machining tool to machine fastener holes of
relevant diameter and depth in either a carbon fiber or glass- based composite
material with polymer reinforcement representative of those materials used in
military aircraft today. Demonstrate feasibility of the developed approach for
producing holes in selected composite material and model the temperature
profile of the resulting fastener holes using commercially available analytical
tools. The Phase I effort will include the development of prototype plans for
Phase II.
PHASE II: Fully develop a
prototype precision machining tool; demonstrate the precision fastener hole
capability developed in Phase I; and expand the capability to include
countersink in a laminate that contains both carbon and glass fibers.
Demonstrate the ability to machine a finished precision fastener hole in a 1”
thick composite sandwich structure with relevant face sheet and core
materials. Validate the quality of the hole with traditional Non-Destructive
Inspection (NDI) techniques and show that the quality is at least equivalent to
that which is currently achievable with traditional drilling through similarly
produced composite material. Validate the predicted heat distribution of the
material and the associated material properties around the hole experimentally.
PHASE III DUAL USE
APPLICATIONS: Benchmark the precision machining system to machine and
countersink fastener holes in composite structures for aircraft components.
Transition the technology to provide an efficient and effective tool to produce
countersunk fastener holes in carbon and glass fiber laminate composite
materials used for military air platforms, as well as civilian air vehicle
components and other industrial applications. The technology can be an
effective and efficient machining and cutting tool for various components in
both the military and commercial sectors such as aerospace, automobile, and
marine.
REFERENCES:
1. El-Sonbaty, I., Khashaba,
U. & Machaly, T. “Factors affecting the machinability of GFR/epoxy
composites.” Composite structures 2004, 63, no. 3: 329-338. http://journals.sagepub.com/doi/abs/10.1177/0021998312451609
2. Li, Z. L. Zheng, H. Lim,
G. Chu, P. & Li, L. “Study on UV laser machining quality of carbon fibre
reinforced composites.” Composites Part A: Applied Science and Manufacturing
2010, 41, no. 10: 1403-1408. http://laser.mace.manchester.ac.uk/uploads/tx_neofileshare/2011-10-20_15-46-59_UV_Laser_machining.pdf
3. Piquet, R. Ferret, B.
Lachaud, F. & Swider, P. “Experimental analysis of drilling damage in thin
carbon/epoxy plate using special drills.” Composites Part A: Applied Science
and Manufacturing 2000, 31, no. 10: 1107-1115. http://www.sciencedirect.com/science/article/pii/S1359835X00000695
KEYWORDS: Composite
Structure; Drilling; Temperature Profile; Precision Machining; Heat Distribution;
Fastener Hole
** TOPIC NOTICE **
These Navy Topics are part of the overall DoD 2018.1 SBIR BAA. The DoD issued its 2018.1 BAA SBIR pre-release on November 29, 2017, which opens to receive proposals on January 8, 2018, and closes February 7, 2018 at 8:00 PM ET.
Between November 29, 2017 and January 7, 2018 you may talk directly with the Topic Authors (TPOC) to ask technical questions about the topics. During these dates, their contact information is listed above. For reasons of competitive fairness, direct communication between proposers and topic authors is not allowed starting January 8, 2018 when DoD begins accepting proposals for this BAA.
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