Calculation of strength, rigidity, and stability of the aircraft fuselage frame made of composite materials
| Autor: | Yana A. Vahterova, Yuri A. Utkin, Ying Sun, Sergei I. Ivannikov |
|---|---|
| Rok vydání: | 2021 |
| Předmět: |
finite element model
Materials science composite materials Frame (networking) Aerospace Engineering TL1-4050 Rigidity (psychology) carbon-carbon composite materials 02 engineering and technology 021001 nanoscience & nanotechnology Stability (probability) 020303 mechanical engineering & transports 0203 mechanical engineering Fuselage Control and Systems Engineering stress-strain state Composite material 0210 nano-technology physical and mechanical parameters Motor vehicles. Aeronautics. Astronautics |
| Zdroj: | INCAS Bulletin, Vol 13, Iss S, Pp 77-86 (2021) |
| ISSN: | 2247-4528 2066-8201 |
| DOI: | 10.13111/2066-8201.2021.13.s.8 |
| Popis: | Carbon-carbon composite materials (CCCM) are characterized by high heat resistance and thermostability for which they, in most of their physical and mechanical characteristics, can be attributed to the most promising materials. Approximately 81% of all carbon-carbon composite materials are used for the manufacture of brake rotors for aircraft, 18% – in space rocket technology, and only 1% – for all other areas of application. This study discusses calculations of the strength, rigidity, and stability of a frame made of carbon-carbon composite materials. It is known that the strength of CCCM based on high-strength carbon fibers is higher than the strength of a composite material based on high-modulus carbon fibers obtained at various processing temperatures. The stress-strain behaviour (SSB) of the material is carried out. Among the special properties of CCCM are low porosity, low coefficient of thermal expansion, maintaining a stable structure and properties, as well as product dimensions. |
| Databáze: | OpenAIRE |
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