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 3 Ds 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.

A method for manufacturing a real component, enabling at least one acceptance criterion to be displayed by targeting a point on the real component with a pointer of an augmented reality device. The method includes the steps of determining a transfer matrix for converting coordinates of a real point located in a second reference frame into coordinates of a virtual point located in a first reference frame and corresponding to the real point, determining the coordinates in the first reference frame of a virtual point associated with the pointer, using the transfer matrix, determining whether the virtual point associated with the pointer belongs to a criterion area of the virtual component, and, if so, displaying at least one acceptance criterion of the criterion area to which the virtual point associated with the pointer belongs, and addressing the non-conformance according to the acceptance criterion, to make the real component acceptable.

A method for designing the cross-sectional shape of the fuselage of a flying body having the fuselage extending in the roll axial direction, the section being taken on a plane perpendicular to the roll axial direction. This method is provided with: an initial setting step S12 for setting an initial cross-sectional shape, which is the initial cross-sectional shape of the fuselage having a cross-sectional shape that is not truly circular; load application steps S14, S21, S28 for analytically or experimentally preloading the fuselage having the initial cross-sectional shape; and a design shape setting step S17 for acquiring the cross-sectional shape of the preloaded fuselage as the design cross-sectional shape of the fuselage.

Methods and systems relating to the design and testing of systems that include hinged flight control surfaces of aircraft are disclosed. The systems and methods disclosed herein make use of a structural model representing a structural environment of the system in a relatively simple manner. In various embodiments, the structural model comprises one or more actuation branches having a common linear actuation direction, a load mass, and a massless connector representative of a hinge line of the flight control surface. The massless connector is connected to and disposed between the one or more actuation branches and the load mass and is movable along the common linear actuation direction so that linear movement of the massless connector is correlated to rotational movement of the hinged flight control surface.

A method and apparatus for manufacturing a part. The part is designed using a CAD system to generate a CAD part model of the part. Features of the part are identified from the CAD part model of the part. A parametric specification of the part is generated using the features of the part. The parametric specification of the part is saved as a parametric part model. The parametric part model is used to fabricate the part.

A high-fidelity, multi-point, full-mission sonic-boom propagation tool that includes functionality to handle aircraft trajectories and maneuvers, as well as, all relevant noise metrics at multiple points along the supersonic mission. This allows efficient computation of sonic-boom loudness across the entire supersonic mission to allow pilots and aircraft operators to plan the aircraft flight path to manage the sonic boom footprint.

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 implemented by a computer for the real-time simulation of a force and/or of a moment applied to a wing in a fluid flow, wherein the body is previously modelled by at least two scalar and vector point sources of a velocity field, the method including at least one of the steps: assessing at least one element selected among a force and a moment, through a linear function dependent on the main velocity vector, V, of the flow; at least one flow rate, referred to as the scalar mass flow rate, As; and at least one flow rate, referred to as the vector mass flow rate, AR, associated with the sources, on at least one point corresponding to one of the sources.

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.

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.