Calculation of strength, rigidity, and stability of the aircraft fuselage frame made of composite materials

Abstract

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.

Numerical Analysis of Deformation Characteristics of Elastic Inhomogeneous Rotational Shells at Arbitrary Displacements and Rotation Angles

“…To construct the evolutionary problem, the grid analogs of equilibrium equations (20) are replaced by nonstationary equations that have the same form as the shell's equations of motion in a viscous medium [1][2][3]5]. The finite-difference analogs of the equilibrium equations (20) in operator form are represented as (22):…”

“…Thus, the difference approximation of the non-stationary equations ( 23) leads to the iterative process (24) of finding the solution to the original stationary problem (22). The computational algorithm for solving the nonlinear problem in the case of conservative loading is constructed similarly to (23), (24).…”

Optimization Design of Core Ultra-Stable Structure for Space Gravitational Wave Detection Satellite Based on Response Surface Methodology

“…After modeling, the total mass of the finite element model of the spacecraft's ultra-stable structure was 404.1 kg, with the frame assembly weighing 53.6 kg and the mirror assembly weighing 350.5 kg. Modal and static analyses were performed using the finite element analysis software to extract fundamental frequencies and deformation results [17]. Ultimately, the optimization equations were subsequently fitted.…”