Numerical investigation of debris impact on spacecraft structure at hyper-high velocity

Abstract

In this paper, our analysis concentrated on the mechanical behavior of sandwich panel subjected to impact loading. Thus, to improve the resistance of satellite structures from debris collision consequences; we proceed a performance investigation numerically of different materials based on the evaluation of contact force, total energy and kinetic energy generated from the impact of spherical steel debris on sandwich panel. Furthermore, a comparison of deformations and stresses levels in sandwich panel collide by a projectile at hyper-high velocity using finite element with ANSYS code was made. The difference between our models is the type of skins materials which are aluminum and functionally graded material FGM (alumina/ nickel). The impact results a total perforation of sandwich panel with aluminum facesheets creating a fragments; contrary to FGM which the projectile penetrates only the front facesheet and honeycomb core. However, for an effective protection of sandwich panel against debris perforation, the introduction of FGM skins technique is considered as a candidate solution.

Numerical investigation of the dynamic behavior of a Ti/TiB functionally graded material using Split Hopkinson Pressure Bar test

“…The mechanical properties of the material were assumed to vary continuously through the plate thickness between the metal (Ti) and ceramic (TiB) layers according to a power-law distribution of the Vc of the ceramic phase. Numerous researchers, 70–72 assumed that the ceramic Vc (Vc) of FGMs varies through the thickness (h) following a power-law distributionwhere the gradient exponent (n) defines the nature of the required distribution function of constituents. Additionally, in the design of FGMs, the relation between the Vcs of ceramic (Vc) and metal (Vm) must be:

Figure 14.DTTO’s stress-strain curves and constituent volume fractions of functionally graded specimen layers for (a) metal-rich, n = 0.1; (b) linear, n=1.0; and (c) ceramic-rich, n = 10.0 compositions.

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“…The mechanical properties of the material were assumed to vary continuously through the plate thickness between the metal (Ti) and ceramic (TiB) layers according to a powerlaw distribution of the Vc of the ceramic phase. Numerous researchers, [70][71][72] assumed that the ceramic Vc ðV c Þ of FGMs varies through the thickness ðhÞ following a powerlaw distribution…”

Spacecraft real-time thermal simulation using artificial neural networks

“…With the advancement of computer processing capabilities, computational modeling and simulation have been progressively used in the development process of complex systems. In particular for space systems, simulations contribute to reduce costs and time required for development, since they allow the evaluation of functionality and performance without the need to construct physical models and to test scenarios that would not be possible in the laboratory, increasing the reliability of the system [1][2][3][4][5][6]. Simulations are used along all the satellite development phases, from the system conception, through the establishment of mission performance requirements, functional engineering processes, functional validation, software validation, assembly, integration and test (AIT), ground system test, to the final phases for training, operations and maintenance [7,8].…”

In-plane and out-of-plane compressive mechanical properties of Nomex honeycombs and their prediction

“…The hexagonal honeycomb constructed by bees is a wonder of nature: its structure is more powerful than any round or square structure of similar material and can bear external forces from all sides. Even the thinnest material, when made into the shape of a honeycomb, exhibits significant strength and stiffness [1,2]. Various aspects of the performance of metal honeycombs such as aluminium and steel honeycombs have been studied.…”