N231-026 TITLE: Friction Drilling Fasteners for Composite Structures
OUSD (R&E) CRITICAL TECHNOLOGY AREA(S): General Warfighting Requirements (GWR)
OBJECTIVE: Develop an innovative friction drilling process that can effectively and precisely fasten together composite structures while preventing induced damage.
DESCRIPTION: This SBIR topic seeks development of an innovative process to fasten composite materials without destroying the integrity of the material. A process such as friction drilling has the potential both to fasten and bond carbon fiber- or glass-based composite material with polymer reinforcement. The Navy uses fiber reinforced polymer (FRP) composites in many military aircraft. Composite materials are in primary load-bearing structures and secondary nonload-bearing structures and skins. The size and complexity of composite components are constantly increasing as the desire for reduced weight drives the replacement of metallic components with low-density FRP. Fatigue and overload conditions require thorough tests and analyses to qualify connections to composite parts for airworthiness. Additionally, nondestructive inspections (NDI) are a crucial requirement for using these connections.
There may be several dozen fastener locations on a single aircraft component requiring a robust and rapid connection process for composites. Hole drilling techniques for FRP material originated from traditional metalworking; however, the unique material properties of FRPs present difficulties in the drilling of a simple fastener hole. Additionally, fastener holes often require precision countersinks. The highly abrasive nature of carbon, glass, and aramid fibers reduces the tool life of traditional tungsten carbide drill bits. This problem necessitates their frequent changing and affects the hole diameter as the material abrades the drill bit. 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 techniques. A friction drilling process may produce a more robust connection.
An alternative method to secure composite parts to other parts involves the use of adhesives. The adhesives require high levels of cleanliness, fixturing tools, curing/wait times, and multiple personnel for assembling non-rigid, large parts. Production must wait for the adhesive to cure and for the removal of the fixturing tools. The shear, and out-of-plane, loads that adhesives transfer from component to component are complex. Adhesives are generally much weaker than fasteners. A process such as friction drilling appears to offer an alternative to adhesives in many applications.
The Navy has a need to address the following technical challenges to qualify a process such as friction drilling:
(a) precision fastener locking with robust bushing collars,
(b) no breakout plies on the exit side,
(c) no delamination from edge of hole or into the part,
(d) no splintering allowed at entrance/exit of hole,
(e) no fatigue or ultimate strength damage from pilot holes,
(f) applied or induced heat must not damage the composite material,
(g) automate the process for bushing collar formation consistency and resilience,
(h) modeling and simulation of the process including temperature profile,
(i) modeling and simulation of the progressive damage for fatigue and overload analyses,
(j) demonstration of equivalent or better fatigue properties than the current processes,
(k) demonstration of ultimate load capabilities equivalent or better than the current processes.
PHASE I: Develop an innovative approach for a friction drilling fastener 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 bonded composite materials. The Phase I effort will include the development of prototype plans for Phase II.
PHASE II: Show that the strength quality can be at least equal to what is currently achievable with traditional drilling or adhesive bonding with similarly produced composite materials. Validate the associated material strength properties around the friction drill bonded region through fatigue and overload testing. Fully develop a prototype friction machining tool, demonstrate the precision fastener capability developed in Phase I, and expand the capability for rapid assembly.
PHASE III DUAL USE APPLICATIONS: Demonstrate fatigue properties and ultimate load capabilities equal to or better than the current processes to transition this technology to applicable platforms.
This SBIR topic will greatly assist the recreational marine industry, the aerospace industry, the wind turbine industry, and any other industry that uses composite materials.
1. Nagel, P., & Meschut, G. (2017). Flow drill screwing of fibre-reinforced plastic-metal composites without a pilot hole. Welding in the World, 61(5), 1057-1067. https://doi.org/10.1007/s40194-017-0493-2
2. Alphonse, M., Raja, V. B., Logesh, K., & Nachippan, N. M. (2017, May). Evolution and recent trends in friction drilling technique and the application of thermography. In IOP Conference Series: Materials Science and Engineering (Vol. 197, No. 1, p. 012058). IOP Publishing. https://iopscience.iop.org/article/10.1088/1757-899X/197/1/012058/meta
3. Kumar, B. S., Baskar, N., & Rajaguru, K. (2020). Drilling operation: A review. Materials Today: Proceedings, 21, 926-933. https://doi.org/10.1016/j.matpr.2019.08.160
KEYWORDS: Friction drilling; flow drilling; composites; thermoset; thermoplastic; fatigue
TPOC-1: Alan Timmons
Phone: (301) 342-8139
TPOC-2: Nam Phan
Phone: (301) 342-9359
TPOC-3: Annette Arocho
Phone: (301) 342-9357
TPOC-4: Gabriel Murray
Phone: (301) 342-8166
** TOPIC NOTICE **
The Navy Topic above is an "unofficial" copy from the Navy Topics in the DoD 23.1 SBIR BAA. Please see the official DoD Topic website at www.defensesbirsttr.mil/SBIR-STTR/Opportunities/#announcements for any updates.
The DoD issued its Navy 23.1 SBIR Topics pre-release on January 11, 2023 which opens to receive proposals on February 8, 2023, and closes March 8, 2023 (12:00pm ET).
Direct Contact with Topic Authors: During the pre-release period (January 11, 2023 thru February 7, 2023) proposing firms have an opportunity to directly contact the Technical Point of Contact (TPOC) to ask technical questions about the specific BAA topic. Once DoD begins accepting proposals on February 8, 2023 no further direct contact between proposers and topic authors is allowed unless the Topic Author is responding to a question submitted during the Pre-release period.
SITIS Q&A System: After the pre-release period, and until February 22, 2023, (at 12:00 PM ET), proposers may submit written questions through SITIS (SBIR/STTR Interactive Topic Information System) at www.dodsbirsttr.mil/topics-app/, login and follow instructions. In SITIS, the questioner and respondent remain anonymous but all questions and answers are posted for general viewing.
Topics Search Engine: Visit the DoD Topic Search Tool at www.dodsbirsttr.mil/topics-app/ to find topics by keyword across all DoD Components participating in this BAA.
|1/27/23||Q.||Does Navy want to develop a new “drilling bit” to joint composite materials to themselves? The drilling bit will stay in composites as a fastener something like a self-drilling screw or a self-tapping sheet mental screw.|
|A.||The solution need can be broad and any innovative approach is encouraged.
|1/21/23||Q.||1. According to Reference 2 conclusion, phase I has already been done, except for perhaps (j) and (k). Can you clarify and reiterate the Phase I goal again?
2. Can you define the baseline, i.e., the current processes?
3. Can you define the work material such as CFRP or GFRP/Aluminum assemblies for Phase I?
|A.||1. The USN needs an innovative technology that can structurally restore damaged composites for aircraft. A hybrid structural restoration approach might perform better than friction drilling technology by itself.
2. The current process involves the use of adhesives or fasteners or a combination of both. Medium to high stress regions currently cannot be repaired because of the fatigue loading. Thus the need to research this technology.
3. CFRP (thermoset) is the preferred substrate structure. The bridge for repairing the broken CFRP can be any material for feasibility purposes.
|1/20/23||Q.||1. Is there a target range of material thickness?
2. Is there a target range for hole sizes?
3. Is this for one up multi material stack drilling?
4. If yes to above will there be Al, Ti, and other alloys in the stack?
5. Is it anticipated that chasing the hole with a one shot integrated drill would be done to finish the hole or only a friction drill would be used?
6. Are the bushing collars mentioned part of the formation from friction drilling, drill bushings from a tooling fixture, or something else?
3. It can be.
4. The bridge for repairing a broken composite can be any material for feasibility purposes.
5. The solution need can be broad and any innovative approach is encouraged.
6. The bushings in the topic are associated with the bushings made during the friction drill process; however, the solution need is broader than the methodology for making bushing collars. An innovative approach, including hybrid approaches, are encouraged.