Abstract
In this study, epoxy molding compounds are combined with fast-curing epoxy prepregs in thermoset injection molding using a new integrative process. The combination is carried out under the varied parameters of mold temperatures and curing times, which are dominant factors in thermoset processing. The focus of the investigations is the bond strength in the interface resulting from these parameters, as the interface is known as the weak point of hybrid components. To identify causes for possible increases and decreases of the bond strength, additional rheological and thermoanalytical analyses are done under near-process conditions. The influence of prepreg pre-crosslinking, a function of the mold temperature, is also described by means of additional tests in which specific pre-crosslinking of the prepreg is adjusted by the temperature storage and then functionalized in integrative process combination. The aim of the study is to identify and understand initial process limits for the integrative process combination for a potential process window.
Highlights
Increasing environmental regulations to reduce CO2 emissions with rising costs for fossil fuels leads to a necessary improvement of resource efficiency in all transport sectors [1]
The maximum bond strength for both material combinations is reached at a mold temperature of 160°C
The dominant process variables, mold temperature and curing time, and their effects on the resulting bond strength were investigated for a novel integrative process of combining molding compounds and prepregs in thermoset injection molding
Summary
Increasing environmental regulations to reduce CO2 emissions with rising costs for fossil fuels leads to a necessary improvement of resource efficiency in all transport sectors [1]. A weight reduction of 1 kg for an Airbus A340 reduces fuel consumption by 3 t in the calculated 20 years [2]. Assuming the aircraft is operating on the principle of complete combustion, this would correspond to a CO2 reduction of 9.45 t [3]. If this were applied across all aircraft in the Star Alliance fleet, a reduction of 44,100 t CO2 would be possible in 20 years by reducing the weight of each aircraft by 1 kg [4]. Fiberreinforced polymer (FRP) composites have excellent weightspecific mechanical properties, making them well suited to reduce aircraft weight by substituting metallic materials [5]
Sign-in/Register to view highlights & summary 
Published Version (
Free)
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a callMore From: The International Journal of Advanced Manufacturing Technology
Disclaimer: All third-party content on this website/platform is and will remain the property of their respective owners and is provided on "as is" basis without any warranties, express or implied. Use of third-party content does not indicate any affiliation, sponsorship with or endorsement by them. Any references to third-party content is to identify the corresponding services and shall be considered fair use under The CopyrightLaw.
