Disclosed is a method for calculating a fluid-structure interaction response of ceramic matrix composites (CMCs). The method includes: calculating a stress-strain hysteresis curve under loading and unloading of a CMC unit cell model through a multi-scale method; performing an interpolation to calculate a hysteresis loop response under arbitrary loading and unloading through a hysteresis loop under loading and unloading calculated through the unit cell model, and using the hysteresis loop response as a proxy model for a dynamics calculation of a solid domain of a fluid-structure interaction; and calculating a fluid load on a fluid-structure interaction interface through CFD, writing a program to read the fluid load and map the same to a solid node, reading a displacement of the solid node and mapping the same onto the fluid node, where a fluid domain and the solid domain use the same time step.

A method for designing fiber-composite parts in which part performance and manufacturing efficiency can be traded-off against one another to provide an “optimized” design for a desired use case. In some embodiments, the method involves generating an idealized fiber map, wherein the orientation of fibers throughout the prospective part align with the anticipated load conditions throughout the part, and then modifying the idealized fiber map by various fabrication constraints to generate a process-compensated preform map.

First FEA mesh model representing 3-D geometry of a carbon fiber reinforced composite (CFRC) product/part, pre-forming fiber orientation and desired reference fiber direction at a particular location on the product/part are received. First FEA mesh model contains finite elements associated with respective material properties for carbon fibers and binding matrix. Pre-forming fiber orientation includes number of fibers and relative angles amongst the fibers. Pre-forming 2-D shape of a workpiece used for manufacturing the product/part is obtained by conducting a one-step inverse numerical simulation that numerically expands the first to a second FEA mesh model based on numerically-calculated structural behaviors according to respective material properties. Pre-forming fiber orientation is superimposed on the second FEA mesh model with the desired reference fiber direction being preserved. Relative angles amongst all of the fibers on the product/part are determined by correlating the superimposed fiber orientation of the second to the first FEA mesh model.

A method for screening a large design space of compositions with possible application as binders in cermet and powder metallurgy applications allows rapid elimination of large portions of the design space from contention so that resource intensive procedures, such as computationally intensive modeling techniques and experimental testing, can be focused on potential binder compositions with a high likelihood of being used successfully. The method relies on parameters such as surface tension, contact angle, viscosity, a special capillary metric that is used to characterize capillary behavior, and melting point, which are relatively easy to calculate or determine, to screen out large portions of the design space. Exemplary binder compositions are obtained using the method.

A method, apparatus, and system for managing a composite structure. A set of component models is created for a set of components in the composite structure. A set of embedded reinforcement element models is placed within the set of component models for the set of components in the composite structure to form a composite structure model for the composite structure. The set of embedded reinforcement element models is for a set of embedded reinforcements embedded within the set of components in the composite structure. A structural analysis of the composite structure is performed using the composite structure model formed by the set of component models and the set of embedded reinforcement element models, wherein the set of embedded reinforcement element models enables modeling at least one of a deformation or a failure of embedded reinforcements.

The invention discloses a method for predicting a residual strength of a composite material after impact. The method includes: acquiring a first frequency value of a composite material to be tested after impact damage; determining a first frequency change rate according to an initial frequency value and the first frequency value of the composite material to be tested; inputting the first frequency change rate to a pre-constructed residual strength prediction model to predict a first residual strength of the composite material to be tested; the first frequency value and the initial frequency value being obtained by a modal test. Further, residual strength prediction may be performed on the composite material in service, the position and the size of impact damage, the impact energy, the shape and quality of the impact object are not required to be determined, which avoids a rigidity test of the composite material in service.

A composite laminate designing method includes: deriving, on a basis of allowable strains corresponding to fiber orientation angles in a composite laminate having the fiber orientation angles, an allowable load region that represents in three dimensions a combination of an allowable X-direction load in a predetermined x direction in a plane orthogonal to a lamination direction in which layers of the composite laminate are laminated, an allowable Y-direction load in a y direction orthogonal to the x direction in the plane orthogonal to the lamination direction, and an allowable shearing load in a shearing direction in the plane orthogonal to the lamination direction; and determining whether a working load acting on the composite laminate is included within the allowable load region.

Provided is an optimization design method for new composite structure under a high-dimensional random field condition. The method includes the following steps: firstly, establishing a high-dimensional random field model considering spatially dependent uncertainty of material properties and loads considering the complexity of a preparation process and a service environment of a new composite structure, and then establishing an optimization design model of the new composite structure under the influence of the high-dimensional random field according to the high-rigidity and light-weight design requirement; secondly, combining a stochastic isogeometric analysis approach with a stochastic polynomial expansion enhanced Dagum kernel Kriging surrogate model, and efficiently and accurately calculating statistical characteristics of stochastic responses of the new composite structure under the influence of the high-dimensional random field; and finally, rapidly obtaining optimal design parameters of the new composite structure by utilizing a particle swarm optimization algorithm. (FIG. 1)

Conventionally, manufacturing of molded parts using composite materials has led to poor dimensional accuracy and tensile strength due to improper curing thus resulting in rejection or early/premature failure of composite part. Embodiments of the present disclosure provide simulation-based systems and methods for manufacturing/generating molded parts using reinforced composite materials. The optimized cure cycle is computed for a given component without carrying out numerous experiments. The present disclosure implements multiscale method and surrogate modeling in virtual testing for more accurate and faster manufacturing of molded parts. Process parameters for specified qualities (e.g., minimum residual stresses, minimum deformation, etc.) required for a part are determined along with least process manufacturing time. The resulting optimized time dependent cure cycle for each thermal zone of the heated mold is transferred to a master controller (e.g., system) which controls the entire curing processes with the use of feedback control.

A composite material includes stacked reinforced fiber substrates and has a thickness-varying part whose thickness in a stacking direction changes from a large thickness to a small thickness. The reinforced fiber substrate that has the drop-off portion and is positioned between a base substrate and a cover substrate in the stacking direction is set as a cut substrate. Stress analysis is performed on the base substrate, the cut substrate, and the cover substrate to calculate an evaluation value concerning stress on the cut substrate. A reinforced fiber substrate in the thickness-varying part is set at the cut substrate, based on the calculated evaluation value.