Hybrid Ceramic Matrix Composite/Polymer Matrix Composite (CMC-PMC) Skin Materials
Navy STTR 2018.A - Topic N18A-T024
ONR - Mr. Steve Sullivan - firstname.lastname@example.org
Opens: January 8, 2018 - Closes: February 7, 2018 (8:00 PM ET)
AREA(S): Air Platform, Materials/Processes
PROGRAM: Research Topic – Potential future use for PEOU&W platforms.
Develop a hybrid multifunctional composite material that is an improvement upon
the thermal and chemical stability, and surface durability of traditional carbon
fiber reinforced polymer (CFRP) composites.
Carbon fiber reinforced polymer (CFRP) composites (also known as polymer matrix
composites (PMC)) are a type of strong and lightweight composite material that
is commonly used in the aerospace, automotive, and civil engineering fields.
For example, the Boeing 787 aircraft fuselage, wing, and other key airframe
components are made from CFRP composite material. However, these materials
have two inherent drawbacks that limit the breadth of usefulness in naval
applications: (1) The operating temperature is not high enough in terms of the
thermal durability of the material in structural applications. For example,
the most common matrix materials for CFRP composites are epoxy and
bismaleimides (BMI), whose glass transition temperatures are about 75°C and
260°C, respectively. Such polymer matrices do not perform as desired in higher
temperatures due to thermal softening and other degradation effects. Cracks
and fracture phenomenon may develop as well after long duration exposures to
higher temperatures or exhaust impingement. (2) Chemical stability is not
sufficient for long lifespans. Especially for aerospace applications, the
lifespan for CFRP material is limited under UV light radiation and harsh weather
conditions (e.g., the salty and high moisture atmosphere in Naval operations).
These weaknesses constrain CFRP composite applications to certain limited
I: Define and determine the feasibility of a multifunctional composite material
system and an associated manufacturing process. Target the durability
properties of interest (e.g., thermal, EMI, etc.). Develop a Phase II plan.
II: Develop and demonstrate a prototype of concept with a coupon-sized sample
for mechanical, thermal, and chemical testing. Demonstrate the prototype’s
material property maintained under simulated aforementioned environmental
conditions (temperature, humidity, pH).
III DUAL USE APPLICATIONS: A material state awareness system of this nature
could be installed in many DoD or commercial platforms such as UAV’s and
commercial airframes. The contractor will need to identify a skin/component
target to integrate the material solution; and demonstrate that the material
system is fully functional and capable of surviving the ship or aircraft
operational environment and determine the system’s compatibility with legacy
and future applications.
Soutis, C. “Carbon fiber reinforced plastics in aircraft applications.” Mater.
Sci. Eng., A, 412:171 (2005).
Hollaway, L.C. “The evolution of and the way forward for advanced polymer
composites in the civil infrastructure.” Construct. Build. Mater., 17:365
Parry, Daniel (POC). “Navy Develops High Impact, High Integrity Polymer for
Air, Sea, and Domestic Applications” Naval Research Laboratory News Releases
Parry, Daniel (POC). “NRL Licenses New Polymer Resin for Commercial
Applications.” Naval Research Laboratory News Releases 2015. http://www.nrl.navy.mil/media/news-releases/2015/nrl-licenses-new-polymer-resin-for-commercial-applications
Polymers; Ceramics; PMC; CMC; Skin; Materials