Carbon Nanotube Infused Launch Vehicle Structures

Metadata Updated: November 12, 2020

For the past 5 years Orbital ATK has been investing in, prototyping, and testing carbon nanotube infused composite structures to evaluate their impact on launch vehicle structural damping. Improvements to structural damping would be revolutionary to launch vehicle design.For any vehicle a significant portion of design, material, and integration efforts center on mitigating the severe dynamic environments seen during flight. This includes launch acoustics, random vibration, sinusoidal vibration, and shock. Acoustics are driven by high frequency pressure fluctuations associated with motor firing or the launch vehicle quickly passing through the atmosphere. This induces responses and stress in structures and components. During launch random vibration from aero-acoustics also induces stresses to hardware (e.g. components, as pieces, move relative to each other) risking failure both due to magnitude and fatigue. Sinusoidal vibration, usually (but not always) related to motor chamber pressure resonance during burn, can couple with a component or structure’s natural frequency –magnifying the vibration and posing significant structural and hardware risk. Lastly, short high magnitude shock events also occur at the ignition of each motor stage and at each stage’s pyrotechnic separation event. Shock poses significant technical risk and is a common driver for launch vehicle design requirements.Testing to date by the Orbital ATK Launch Vehicle Division (LVD) has shown that by infusing CNT into composite we can improve the structural damping by a factor of 2x. Improved damping attenuates launch dynamic environments which leads to cascading benefits if CNT’s are infused into all primary and secondary structures. The improved damping lowers transient dynamic loads in primary structures and reduces secondary structure dynamic response. This allows reduction of primary and secondary structural mass. Moreover shock and random vibration are reduced into components which may allow for the elimination of hardware isolation systems. With no isolation required on hundreds of components (including the payload), a significant amount of “parasitic mass” can be eliminated. The significant reduction in part quantity and design complexity produces cascading material, design, test, and integration cost savings and expedites program schedules. A case study on Orbital ATK launch vehicles shows elimination of parasitic mass enabled through CNT utilization could increase payload mass to orbit by >10% and reduce launch vehicle cost by >15%. Dynamic loads and environments into the spacecraft are also decreased—enabling reduction in payload structural mass, associated propellant mass, and reduce spacecraft test environments.CNT infused launch vehicle structures are at a tipping point enabling breakthrough improvement in structural damping. CNT’s efficacy improving damping has been shown at a coupon level in a lab environment (TRL 4). A two phased approach will mature this technology further. Phase I advances TRL to level 5 by building subsystem level prototypes and executing flight-like testing. CNT infused composites will be prototyped and tested in two independent configurations: CNT sheets interstitially layered in pre-impregnated (pre-preg) composite, and chopped CNT’s dispersed into composite. Phase II advances TRL to level 6 by building full-scale flight structures and completing end to end testing (ground and/or flight tests). Flight structures include a CNT sounding rocket interstage and a palletized CNT lattice bulkhead for a major launch vehicle. Orbital ATK is the prime contractor for the NASA Sounding Rocket Operations Contract (NSROC) program. Zero-cost rideshare opportunities to fly the CNT interstage will be pursued on best effort basis through the NSROC program. Results of this two-phased approach will demonstrate the safety, robustness, and cascading benefits of CN

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Public: This dataset is intended for public access and use. License: No license information was provided. If this work was prepared by an officer or employee of the United States government as part of that person's official duties it is considered a U.S. Government Work.

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Metadata Created Date November 12, 2020
Metadata Updated Date November 12, 2020

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Harvested from NASA Data.json

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Resource Type Dataset
Metadata Created Date November 12, 2020
Metadata Updated Date November 12, 2020
Publisher Space Technology Mission Directorate
Unique Identifier Unknown
Identifier TECHPORT_94199
Data First Published 2019-07-01
Data Last Modified 2020-01-29
Public Access Level public
Bureau Code 026:00
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Harvest Source Id 58f92550-7a01-4f00-b1b2-8dc953bd598f
Harvest Source Title NASA Data.json
Homepage URL
Program Code 026:027
Source Datajson Identifier True
Source Hash d734faa451527b735f350491e9ef8d2896347e41
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