A method of designing an aircraft shape of a supersonic aircraft according to an embodiment of the present invention includes: obtaining an equivalent cross-sectional area distribution of an initial shape at an off-track position of an aircraft; setting a target equivalent cross-sectional area distribution at the off-track position of the aircraft for reducing sonic booms on the basis of the obtained equivalent cross-sectional area distribution; and converting, on the basis of a required additional cross-sectional area distribution that is a difference between the equivalent cross-sectional area distribution and the target equivalent cross-sectional area distribution, a required additional cross-sectional area of a cross-section of the aircraft on an off-track Mach plane that extends through an arbitrary position in an airflow direction into a required additional cross-sectional area of a cross-section of the aircraft on an on-track Mach plane of the aircraft that is located near the off-track Mach plane and adding the required additional cross-sectional area of the cross-section of the aircraft on the on-track Mach plane.

An apparatus is provided for analysis of a repair for a structure by identifying component parts of the structure that have common material properties and geometric constraints, and based thereon determining a generic repair component for the component parts that also have the common material properties and the geometric constraints. A set of loads are extracted from a loads model of the undamaged structure and redistributed in a loads redistribution model at a damaged or defective portion of the component part. The set of redistributed loads indicate loading incurred by the generic repair component under an external load. The apparatus then uses the redistributed loads to perform an analysis to determine a margin of safety of the generic repair component and, in instances in which the margin of safety is positive, outputs the material properties and geometric constraints of the generic repair component to a fabrication system for production thereof.

An optimization analysis method for joining locations of an automotive body obtains optimal locations of additional joining points or joining portions for use in joining parts assemblies together in an automotive body model and includes: a step of obtaining a deformation form in a vibration mode occurring in the automotive body model 31 by frequency response analysis; a step of determining a load condition to be given to the automotive body model in correspondence with the deformation form in the obtained vibration mode; a step of generating an optimization analysis model in which additional joining candidates are set at locations to be candidates for joining parts assemblies together; a step of setting an optimization analysis condition; and a step of giving the determined load condition to the optimization analysis model to perform optimization analysis and obtaining the additional joining candidates satisfying the optimization analysis condition as optimized joining points.

An electromagnetic field analysis method for an anisotropic conductive material involves using an analysis grid having a first side and a second side that are orthogonal to each other to analyze an electromagnetic property of an anisotropic conductive material in which conductivity in a first direction is different from conductivity in a second direction. One or both of the first direction and the second direction are parallel to a direction different from either one of the first side and the second side of the analysis grid. One electromagnetic field component located on the first side and extending along the second side is calculated based on electromagnetic field components that are located on a plurality of the second sides surrounding the one electromagnetic field component and that extend along the second sides.

Systems and methods are provided for composite part design. One embodiment is an apparatus that designs a composite part. The apparatus includes a controller configured to generate a design for the part. The controller subdivides the part into blocks that each comprise a contiguous stack of layers within the part, identifies rules that constrain how layers that have different fiber orientations are stacked within the part, generates a guide for a block that prescribes a fiber orientation for each layer of the block, and identifies sublaminates comprising that are compatible with the guide for the block. The controller subdivides the part into panels, and selects one of the compatible sublaminates for one of the panels of the block, based on compatible sublaminates for neighboring panels. The apparatus also includes a memory configured to store the design for use by an Automated Fiber Placement (AFP) machine constructing the part.

Systems and methods are provided for composite part design. One embodiment is a method for selectively analyzing feasibility of optimizing fiber orientations for layers of a multi-layer composite part subdivided into panels that each comprise a fraction of an area of the composite part. The method includes identifying stacking sequence rules that constrain the composition of sublaminates that comprise consecutively stacked layers utilized during optimization, for each panel of the composite part, analyzing the panel by identifying ply counts that constrain a number of plies at the panel, selecting a number of sublaminates to utilize during optimization of the panel, calculating ply count ranges for a laminate, based on the number of sublaminates and the stacking sequence rules, and determining whether the ply counts for the panel comply with the ply count ranges for the laminates.

Systems and methods are provided for composite part design. One embodiment is a method of creating a library of sublaminates used in optimizing fiber orientations of a multi-layer composite part subdivided along its depth into panels that each comprise a fraction of the area of the composite part. The method includes creating sublaminates that each comprise consecutively stacked layers having a unique sequence of fiber orientations, checking the sublaminates for compliance with stacking sequence rules that constrain how fiber orientations are sequenced, and removing sublaminates that do not comply with the stacking sequence rules. The method further includes generating new sublaminates that each include an additional layer, by, for each of multiple fiber orientations: selecting a sublaminate that was not remove, and generating a new sublaminate by appending an additional layer having the fiber orientation to the selected sublaminate.

An apparatus for modifying aircraft cabin airflow includes a redirector configured to receive an airflow from an inlet of an aircraft cabin. The redirector is configured to downwardly redirect at least a portion of the airflow. In one embodiment, the redirector includes a dividing portion configured to be oriented generally parallel to the airflow received at the redirector from the cabin inlet, and further includes a redirecting portion configured to be oriented in a generally downward direction. In another embodiment, the redirector includes an elongated protrusion configured to be positioned on a ceiling of the aircraft cabin.

In an example, a method of shimming an uncured substructure for assembly is disclosed. The method comprises emitting a signal from an inspection system proximate a mating surface of the substructure, detecting a reflection of the signal with the inspection system, generating a data set based on detecting the reflection of the signal, the data set representing a shape of the mating surface, determining distances between a plurality of points on the mating surface and respective points on an inner surface of a support structure based on the data set, generating filler dimension data based on the distances, wherein the filler dimension data includes a varying thickness, shaping a filler structure with a computer numerical controlled shaping device using the filler dimension data, adhering a first surface of the filler structure to the mating surface of the substructure to form a shimmed substructure subassembly, and curing the shimmed substructure subassembly.

A pressure-resistant hull for a submersible, includes unit hulls, reinforcing ribs, connecting channels, and closure heads. A plurality of unit hulls are provided, and are sequentially strung together spiralling upward or spiralling downward, the closure heads being arranged on the unit hulls at the first position and the last position respectively, an observation window being provided on each unit hull respectively, adjacent two unit hulls in a horizontal direction being respectively connected by means of a reinforcing rib, and at least two connecting channels being provided between adjacent two rings of the unit hulls in the vertical direction. The design method includes using a spiral joining structure to facilitate organic adjustment of the number of unit hulls, thus having better utilization of space and aiding to greatly expand the space. The sensitivity of the limit load to defects is low, increasing axial rigidity, improving the overall pressure-resistive ability.