scholarly journals The Self-Healing Capability of Carbon Fibre Composite Structures Subjected to Hypervelocity Impacts Simulating Orbital Space Debris

2012 ◽  
Vol 2012 ◽  
pp. 1-16 ◽  
Author(s):  
B. Aïssa ◽  
K. Tagziria ◽  
E. Haddad ◽  
W. Jamroz ◽  
J. Loiseau ◽  
...  
Keyword(s):  
Composite Structures ◽  
Space Debris ◽  
Fibre Composite ◽  
Space Station ◽  
Short Review ◽  
Hypervelocity Impact ◽  
The Self ◽  
Space Environment ◽  
Self Healing ◽  
Carbon Fibre Composite

The presence in the space of micrometeoroids and orbital debris, particularly in the lower earth orbit, presents a continuous hazard to orbiting satellites, spacecrafts, and the international space station. Space debris includes all nonfunctional, man-made objects and fragments. As the population of debris continues to grow, the probability of collisions that could lead to potential damage will consequently increase. This work addresses a short review of the space debris “challenge” and reports on our recent results obtained on the application of self-healing composite materials on impacted composite structures used in space. Self healing materials were blends of microcapsules containing mainly various combinations of a 5-ethylidene-2-norbornene (5E2N) and dicyclopentadiene (DCPD) monomers, reacted with ruthenium Grubbs' catalyst. The self healing materials were then mixed with a resin epoxy and single-walled carbon nanotubes (SWNTs) using vacuum centrifuging technique. The obtained nanocomposites were infused into the layers of woven carbon fibers reinforced polymer (CFRP). The CFRP specimens were then subjected to hypervelocity impact conditions—prevailing in the space environment—using a home-made implosion-driven hypervelocity launcher. The different self-healing capabilities were determined and the SWNT contribution was discussed with respect to the experimental parameters.

scholarly journals Multifunctional load-bearing aerostructures with integrated space debris protection

2019 ◽  
Vol 304 ◽  
pp. 07003
Author(s):  
Martin Schubert ◽  
Anthanasios Dafnis
Keyword(s):  
Composite Structures ◽  
High Performance ◽  
Space Debris ◽  
Sandwich Panels ◽  
Thermal Control ◽  
Hypervelocity Impact ◽  
Radiation Shielding ◽  
Impact Testing ◽  
Load Bearing ◽  
Protection Capability

In the project multiSat multifunctional composite structures for satellite application have been developed. Functions such as protection against space debris, radiation shielding and passive thermal control have been integrated into the load-bearing composite spacecraft structure by use of suitable materials and components. Sandwich panels have been studied as representative structural parts of a conventional satellite structure. Measures for increased space debris protection include the substitution of the conventional honeycomb core by 3D-printed aluminum cellular structures and the reinforcement of the sandwich panel by integration of high performance fabrics which effectively break up and catch impacting debris particles. This paper describes the development and design of multifunctional sandwich concepts with increased impact protection capability and presents the experimental results of hypervelocity impact testing with different types of CFRP sandwich panels.

scholarly journals Numerical Analysis of a DMA Epoxy-Carbon Composite Study

2018 ◽  
Vol 9 (4) ◽  
pp. 101-112
Author(s):  
Paweł KOWALECZKO ◽  
Andrzej PANAS ◽  
Mirosław NOWAKOWSKI
Keyword(s):  
Carbon Fibre ◽  
Numerical Simulations ◽  
Composite Structures ◽  
Fibre Composite ◽  
Real Life ◽  
Elastic Response ◽  
Resin Matrix ◽  
Fibre Reinforcement ◽  
Carbon Fibre Composite ◽  
Model Composite

The results of numerical simulations performed for Dynamic Mechanical Analysis (DMA) measurements of thermal and mechanical (or thermomechanical) properties performed on a model composite structure are presented herein. The simulated elastic response of an epoxy-carbon fibre composite specimen was analysed for a case by which the model specimen was subjected to three-point bending with a free support. The epoxy-carbon fibre composite studied as explained herein exhibited extreme differences between the resilient properties of the epoxy resin matrix and the carbon fibre reinforcement. In addition, the carbon fibre reinforcement was both internally and structurally anisotropic. The numerical simulations were performed to demonstrate a qualitative dependence of the DMA measurement results on a certain structure of the investigated specimen and to determine if the DMA results could be qualified as effective or apparent. A macro-mechanical model of the specimen was developed and had the numerical calculations run with COMSOL/M, a FEM modelling software suite. The carbon fibre reinforcement was modelled with an orthotropic structure of laminar or circular inclusions with different characteristic dimensions. Representative material properties were assumed from the results of proprietary experimental investigations and certain reference literature data. The effect of the composite layers’ configuration and their characteristic dimensions on the evaluated model’s elastic modulus value was also studied. The results presented herein suggested a qualitative agreement with the results of the DMA investigations performed on real-life composite structures. They also proved the effectiveness of the developed numerical simulation methodology, shown herein, in the DMA of micro- and macromechanical phenomena

Investigation on Sustained Discharge of Satellite’s Power Harness Due to Plasma from Space Debris Impact

2019 ◽  
Author(s):  
Yuki Mando ◽  
Koji Tanaka ◽  
Takayuki Hirai ◽  
Shirou Kawakita ◽  
Masumi Higashide ◽  
...  
Keyword(s):  
Space Debris ◽  
Internal Resistance ◽  
Low Earth Orbit ◽  
Hypervelocity Impact ◽  
Space Environment ◽  
Earth Orbit ◽  
Large Area ◽  
Solar Arrays ◽  
Sustained Discharge ◽  
Circuit Configuration

Abstract Space debris travels at a velocity of 7-8 km/s in low Earth orbit (LEO) and at 3 km/s in geostationary Earth orbit (GEO). An impact between space debris and spacecraft will result in tremendous damage. In particular, particles less than 1mm in diameter pose a risk of causing permanent sustained discharge (PSD). PSD may affect a satellite’s power system. The effect on solar arrays has been well-studied given their large area, but the effect on the bundle of a satellite’s wire harness (called the power harness) has yet to be clarified, even though the power harness is usually exposed to the space environment without protection. We conducted hypervelocity impact experiments using a two-stage light gas gun, and investigated the risk resulting in PSD from hypervelocity impacts of particles less than 1mm in size. In addition, we compared two kinds of circuit configurations: a more realistic circuit configuration with internal resistance and a circuit configuration without it, so as to investigate whether internal resistance affects the occurrence of PSD. Stainless steel and aluminum oxide projectiles measuring from 0.3 to 1 mm in diameter were gun-accelerated up to 7.16 km/s. Targets entailed a three-layered power harness under a simulated power condition of typical satellites operating in LEO or GEO. As a result, 11 of 28 shots resulted in PSD. With the more realistic circuit configuration we could not confirm any results regarding PSD. We thus found that PSD is less likely to occur in a more realistic circuit configuration.

On the self-piercing riveting of aluminium blanks and carbon fibre composite panels

2011 ◽  
Vol 6 (1) ◽  
pp. 137-144 ◽  
Author(s):  
Giuseppe Di Franco ◽  
Livan Fratini ◽  
Antonino Pasta ◽  
Vincenzo F. Ruisi
Keyword(s):  
Carbon Fibre ◽  
Fibre Composite ◽  
The Self ◽  
Composite Panels ◽  
Carbon Fibre Composite

Numerical Investigation of Dynamically Loaded Bolted Joints in Carbon Fibre Composite Structures

2009 ◽  
Vol 17 (3) ◽  
pp. 329-346 ◽  
Author(s):  
Garth M. Pearce ◽  
Alastair F. Johnson ◽  
Rodney S. Thomson ◽  
Donald W. Kelly
Keyword(s):  
Carbon Fibre ◽  
Numerical Investigation ◽  
Composite Structures ◽  
Fibre Composite ◽  
Bolted Joints ◽  
Carbon Fibre Composite ◽  
Dynamically Loaded

scholarly journals Robust synthesis of epoxy resin-filled microcapsules for application to self-healing materials

2016 ◽  
Vol 374 (2061) ◽  
pp. 20150083 ◽  
Author(s):  
Patryk A. Bolimowski ◽  
Ian P. Bond ◽  
Duncan F. Wass
Keyword(s):  
Epoxy Resin ◽  
Size Distribution ◽  
Fibre Composite ◽  
Diglycidyl Ether ◽  
High Yield ◽  
Self Healing ◽  
Carbon Fibre Composite ◽  
Scanning Calorimetry ◽  
Water Emulsion ◽  
Oil In Water Emulsion

Mechanically and thermally robust microcapsules containing diglycidyl ether bisphenol A-based epoxy resin and a high-boiling-point organic solvent were synthesized in high yield using in situ polymerization of urea and formaldehyde in an oil-in-water emulsion. Microcapsules were characterized in terms of their size and size distribution, shell surface morphology and thermal resistance to the curing cycles of commercially used epoxy polymers. The size distribution of the capsules and characteristics such as shell thickness can be controlled by the specific parameters of microencapsulation, including concentrations of reagents, stirrer speed and sonication. Selected microcapsules, and separated core and shell materials, were analysed using thermogravimetric analysis and differential scanning calorimetry. It is demonstrated that capsules lose minimal 2.5 wt% at temperatures no higher than 120°C. These microcapsules can be applied to self-healing carbon fibre composite structural materials, with preliminary results showing promising performance.

Fire Condition Effects on the Mechanical Behaviour of Composite Structures

2018 ◽  
Vol 923 ◽  
pp. 13-16 ◽  
Author(s):  
Salvatore Saputo ◽  
Angela Russo ◽  
Antonio Raimondo ◽  
Barbara Iodice ◽  
Mauro Zarrelli
Keyword(s):  
Mechanical Properties ◽  
Mechanical Behaviour ◽  
Composite Structures ◽  
Fibre Composite ◽  
Polymeric Composite ◽  
Mechanical Tests ◽  
Tensile Behaviour ◽  
Main Concern ◽  
Carbon Fibre Composite ◽  
Fire Condition

The fire behaviour of Polymeric composite structures is one of the most critical aerospace research topics. Indeed, the exposure of Polymeric composite structures to high temperatures leads to material decomposition, associated to thermal and mechanical properties degradation. This degradation causes a reduction of the mechanical performances, which can be of main concern for safety reasons. In this paper, the tensile behaviour of Carbon Fibre Composite Polymer specimens, subjected to fire, has been experimentally and numerically investigated. The material properties degradation has been estimated according to an Arrhenius shape function, which relates the mechanical properties of the composite to the temperature. At first, static structural analyses have been carried out to assess the mechanical behaviour of the investigated specimen without fire effects. Then, a coupled thermo-structural analysis allowed evaluating the fire effect on the specimens’ mechanical and the thermal behaviour. In order to preliminary validate the proposed degradation model, the numerical results, in terms of Load versus Displacements curves, have been compared against data obtained from an ad-hoc experimental campaign where fire condition have been suitably replicated during the mechanical tests.

On the self-piercing riveting of aluminium blanks and carbon fibre composite panels

2010 ◽  
Vol 3 (S1) ◽  
pp. 1035-1038 ◽  
Author(s):  
G. Di Franco ◽  
L. Fratini ◽  
A. Pasta ◽  
A. F. Ruisi
Keyword(s):  
Carbon Fibre ◽  
Fibre Composite ◽  
The Self ◽  
Composite Panels ◽  
Carbon Fibre Composite
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