A method of assessing performance of a seat is provided. The method comprises identifying a number of critical seats for testing from a layout of passenger accommodation and building a computer simulation model, following a building block approach, for each identified critical seat. A number of loads are tested on each simulation model. Critical seats are selected for physical testing from simulation model test results according to a specified criteria assessment matrix.

A method for predicting preliminary design load cases using an artificial neural network, the method including obtaining, with a processor, historical data corresponding to an existing structural component, the historical data including finite element modeling analysis data and measured test data for the existing structural component, designing the artificial neural network to include a plurality of neurons to form a numerical model for preliminary design load cases of a new structural component, training, with the processor and the historical data for the existing structural component, the artificial neural network to predict the preliminary design load cases for the new structural component, providing input design parameters for the new structural component to the artificial neural network, and predicting, with the artificial neural network, the preliminary design load cases for the new structural component.

Computer-implemented techniques for simulating underhood conditions for a vehicle and the like are disclosed. The computer-implemented techniques include receiving by a computer processing system digital data of a three dimensional representation of modeling of a fluid source, a fluid sink, and plural fluid nodes, executing a transient thermal model that includes an underhood fluid model, and performing a simulation to simulate fluid flow from the fluid source to the fluid sink through each of the plural fluid nodes.

A system may include a 3D core design engine and a 3D core printing engine. The 3D core design engine may be configured to determine, in a CAD model, an under-core ply of a composite part and a core footprint on the under-core ply specified for an additive 3D core to be manufactured via additive manufacturing for insertion into the composite part, compute a bottom core surface of the additive 3D core from the under-core ply and core footprint, access core design parameters for the additive 3D core; and construct an additive 3D core design in the CAD model based on the computed bottom core surface and the core shape parameters. The 3D core printing engine may be configured to store the additive 3D core design to support subsequent manufacture of the additive 3D core via additive manufacturing.

[Object] To realize an improvement in design accuracy and a reduction in design time in a process of matching an equivalent cross-sectional area of a design shape of a supersonic aircraft to a target equivalent cross-sectional area in a sonic boom reduction method based on an equivalent cross-sectional area.

[Solving Means] The technique includes: setting an initial shape of the airframe and a target equivalent cross-sectional area of the airframe; estimating a near field pressure waveform for the initial shape of the airframe assuming that the supersonic aircraft flies at a cruising speed; evaluating an equivalent cross-sectional area from the estimated near field pressure waveform for the initial shape of the airframe; and setting a Mach plane corresponding to the cruising speed, and setting a design curve on the Mach plane, the design curve corresponding to an initial curve at which the initial shape of the airframe and the Mach plane intersect so that the equivalent cross-sectional area approaches the target equivalent cross-sectional area. Then, the shape of the airframe is designed based on the design curve.

Systems and methods are provided for optimizing designs of composite parts. One embodiment is a method that includes identifying, at a controller, a candidate movement of a ply to a new ply position within a composite part, based on an objective function, loading, at the controller, stacking sequence rules that dictate how fibers are oriented across ply sequences of the composite part, and determining, at the controller, whether the candidate movement complies with the stacking sequence rules.

A method of and a system for propagating a configuration setting of a 3D model to other 3D models, the 3D model and the other 3Ds being part of a same 3D model category. The 5 method comprises dividing the 3D model into a first plurality of surfaces; associating to each one of the first plurality of surfaces, a unique surface identifier. For each one of the other 3D models, the method comprises dividing the one of the other 3D models into a second plurality of surfaces; establishing a correspondence; associating, for each one of the second plurality of surfaces corresponding to one of the first plurality of surfaces. The method also comprises 0 selecting the configuration setting of the 3D model; determining the unique identifier of the 3D model to which the configuration setting is to be applied; and propagating, the configuration setting to the other 3D models.

In a streakline visualization apparatus, a processing unit calculates, by using an expression including a correction value for correcting an error attributable to accelerated motion of a plurality of grid points represented by position information, time differential values of velocities of fluid on the plurality of grid points at each of the plurality of first time points. The processing unit calculates, based on the velocities and the time differential values of the velocities of the fluid on the plurality of grid points at each of the plurality of first time points, positions of a series of a plurality of particles sequentially outputted from a particle generation source as analysis time progresses at each of a plurality of second time points having a second time interval shorter than the first time interval. The processing unit generates display information about a streakline indicating the series of the plurality of particles.

Methods, apparatus, systems, and articles of manufacture are disclosed to generate an aircraft system model using a standardized architecture. An example apparatus includes a model generator to generate an aircraft system model of an aircraft system based on a standardized architecture, a model integrator to integrate the aircraft system model into an integrated aircraft system model, a power sequencer to perform a power sequence test on the integrated aircraft system model, and a report generator to generate a report including a result of the power sequence test.

A system may include a 3D core design engine and a 3D core printing engine. The 3D core design engine may be configured to determine, in a CAD model, an under-core ply of a composite part and a core footprint on the under-core ply specified for an additive 3D core to be manufactured via additive manufacturing for insertion into the composite part, compute a bottom core surface of the additive 3D core from the under-core ply and core footprint, access core design parameters for the additive 3D core; and construct an additive 3D core design in the CAD model based on the computed bottom core surface and the core shape parameters. The 3D core printing engine may be configured to store the additive 3D core design to support subsequent manufacture of the additive 3D core via additive manufacturing.