Classifications

• • G—PHYSICS
  • G06—COMPUTING OR CALCULATING; COUNTING
  • G06F—ELECTRIC DIGITAL DATA PROCESSING
  • G06F30/00—Computer-aided design [CAD]
  • G06F30/10—Geometric CAD
  • G06F30/15—Vehicle, aircraft or watercraft design
• • G—PHYSICS
  • G06—COMPUTING OR CALCULATING; COUNTING
  • G06F—ELECTRIC DIGITAL DATA PROCESSING
  • G06F30/00—Computer-aided design [CAD]
• • G—PHYSICS
  • G06—COMPUTING OR CALCULATING; COUNTING
  • G06F—ELECTRIC DIGITAL DATA PROCESSING
  • G06F30/00—Computer-aided design [CAD]
  • G06F30/10—Geometric CAD
• • G—PHYSICS
  • G06—COMPUTING OR CALCULATING; COUNTING
  • G06F—ELECTRIC DIGITAL DATA PROCESSING
  • G06F2113/00—Details relating to the application field
  • G06F2113/26—Composites
• • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
  • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
  • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
  • Y02T50/00—Aeronautics or air transport
  • Y02T50/40—Weight reduction

Definitions

• a composite structure such as skin or a stiffener may be constructed by stacking up plies of resin-infused carbon fiber tape or fabric on a mandrel, forming an air-tight envelope over the ply stack-up, and curing the stack-up.
• Weight reduction in an aircraft is highly desirable, as it reduces aircraft operating costs.
• the weight of composite aircraft parts may be reduced by using composite material where needed.
• Skin may be formed from an outer ply. Pad-ups on the skin may be used to increase thickness at locations where fasteners will be installed or extra strength is needed.
• the skin In a complex structure such as a composite fuselage, the skin may have an overall nominal thickness, which is padded up to various degrees over arbitrary areas for strength or gage.
• a ply stack-up may have a step-like geometry. Prior to curing, edges of the ply stack-up are sharp. During curing, pre-impregnated resin flows through the stack-up, forming ramps off the edges, which transition from one ply to the next.
• a complex structure such as a fuselage may have tens of thousands of edges.
• the geometric model may be used to determine material properties (e.g., stresses, strains, and displacement) for the composite parts, generate tape laying sequences, and create automated NC part programs.
• material properties e.g., stresses, strains, and displacement
• a composite part including a ply stack-up and resin is modeled.
• the modeling includes performing a convolution on a representation of the stack-up to approximate smoothed ramps between different plies of the stack-up.
• an apparatus comprises a computer programmed to model a composite part including a ply stack-up and resin.
• the modeling includes performing a convolution on a representation of the stack-up to approximate smoothed ramps between different plies of the stack-up.
• an article comprises non-transitory computer memory programmed with data for causing a computer to model a composite part including a ply stack-up and resin.
• the modeling includes performing a convolution on a representation of the stack-up to approximate smoothed ramps between different plies of the stack-up.
• One aspect of the present disclosure relates to a method of modeling a composite part including a ply stack-up and resin.
• the method includes using a computer to perform a convolution on a representation of the stack-up to
• the method also includes contouring the representation of the stack-up prior to the convolution.
• the method also includes contouring the representation of the stack-up after the convolution.
• the representation of the stack-up is contoured with a surface that is modeled procedurally.
• a top ply of the representation corresponds to a mold line ply of the stack-up.
• a top ply of the representation corresponds to an intermediate ply of the stack-up.
• the representation identifies thickness of the stack-up at discrete points on a defining surface of the stack-up.
• the representation identifies thousands of edges.
• the convolution is performed with a kernel that is volume-conserving.
• the convolution is performed with a B-spline convolution kernel.
• distance of knots from a center of the kernel corresponds to how the resin flows from edges of the stack-up.
• the convolution is performed as
• the convolution is performed with a kernel that is chosen according to characteristics of the resin.
• the part is a fuselage part of a commercial aircraft.
• the method also includes using a result of the convolution to define geodesies for tape laying for the composite part.
• the method also includes using a result of the convolution to develop a tool side surface for the composite part.
• the method also includes using a result of the
• Another aspect of the present disclosure relates to an apparatus that includes a computer programmed to model a composite part including a ply stack-up and resin.
• the modeling includes performing a spline convolution on a representation of the stack-up to approximate smoothed ramps between different plies of the stack-up.
• the convolution is performed with a B-spline convolution kernel having a knot structure that represents how the resin flows from edges of the stack-up.
• Yet another aspect of the present disclosure relates to an article that includes non-transitory computer memory programmed with data for causing a computer to model a composite part including a ply stack-up and resin.
• the modeling includes performing a spline convolution on a representation of the stack-up to approximate smoothed ramps between different plies of the stack-up.
• FIG. 1 is an illustration of a ply stack-up.
• FIGS. 2A-2C are illustrations of methods of modeling a composite part including a ply stack-up and resin.
• FIGS. 3A-3D are illustrations of a method of modeling a composite part including a ply stack-up and resin.
• FIG. 4 is an illustration of a resin ramp from a first ply to a second ply.
• FIG. 5 is an illustration of a method of using a model of a composite part to improve fabrication of the part.
• FIG. 6 is an illustration of a machine for modeling a composite part including a ply stack-up and resin.
• FIG. 7 is an illustration of an aircraft including parts that may be modeled according to embodiments herein.
• FIG. 1 illustrates a ply stack-up 1 10 prior to curing.
• the stack-up 1 10 includes a plurality of plies of resin-infused fibers (e.g., between 10 and 100 plies).
• the fibers may be applied as tape or fabric.
• the plies may be stacked normal to an outside surface.
• the stack-up 1 10 has a step-like geometry. Pre-cured edges of the stack-up 1 10 are sharp.
• the stack-up 1 10 may be designed from the outer (e.g., aero) surface toward the inner surface.
• the stack-up 1 10 may be manufactured in the opposite direction (the aero surface is last to be deposited).
• the aero surface is last to be deposited.
• those parts may be designed from the outer mold line inwards towards an inner mold line.
• the opposite may be true, especially for large structures such as fuselages, where the plies are built-up from the inner mold line outwards.
• the arrows in FIG. 1 are not always true for all aircraft parts (for instance, wing skins may be designed and built from the outer mold line inward toward the inner mold line). However, the arrows are intended to represent that the outer mold line may be the design surface and the inner mold line may be a tooling surface.
• FIG. 2A illustrates a method of modeling a composite part including a ply stack-up and resin.
• a discrete representation of the ply stack-up (the "discrete correction") is accessed.
• the discrete correction identifies thickness of the ply stack-up at any point on its defining surface (e.g., inner or outer surface).
• a complex structure such as a fuselage may have tens of thousands of edges.
• the discrete correction may be a piecewise constant function.
• the discrete correction may be derived from an engineering definition of the part.
• the engineering definition may define surface geometry including contour and features such as holes, trim locations, and engineering edge of part.
• the engineering definition may also specify ply drops, ply boundaries, stacking sequence and fiber orientations within each ply.
• the engineering definition may define material specifications for the composite part. Software may be designed to produce the discrete representation of the stack-up by counting plies at a large number of points on the defining surface.
• a convolution is performed on the discrete representation of the stack-up.
• the convolution "softens" the edges and approximates a smoothed ramp between different plies of the stack-up. These smoothed ramps represent resin after curing. (During curing, the pre-impregnated resin will flow through the stack-up, forming ramps off the edges, which transition from one ply to the next.)
• the result of the convolution is an empirical approximation of a cured stack-up.
• a stack-up will be contoured prior to curing. For instance, if the tooling surface is curved, the stack-up will be contoured according to the curve of the tooling surface.
• FIGS. 2B and 2C illustrate two different ways in which the empirical
• the contouring may be performed after
• a contour may be defined by a surface model.
• the surface model represents a tool surface (that is, the surface upon which the plies will be stacked up), which gives a contour to the cured part.
• the surface model may represent a mating surface with another part (that is surfaces to which the composite part will be attached), an outer mold line, or any other pre-defined surface.
• the surface may be modeled as a spline. In other embodiments, surface may be modeled as primitives such as cones, spheres, planes, or a combination thereof them.
• the surface may be modeled procedurally. For example, a surface is mapped over a domain, where different portions of the domain are mapped in different ways. For instance, the surface is mapped to a spline or a primitive (e.g., a portion of a cylinder) over one portion of the domain, and the surface is mapped to a fillet having a prescribed radius over the remainder of the domain (e.g., at edges of a member).
• a spline or a primitive e.g., a portion of a cylinder
• FIG. 2B illustrates the first way in which the discrete correction is contoured after convolution.
• a convolution is performed on the discrete representation of the stack-up to approximate smoothed ramps between different plies of the stack-up.
• the empirical approximation produced by the convolution is added to the surface model.
• (u,v) represents the position of a point in a unit square
• S(u,v) represents the empirical approximation that is contoured according to the surface model
• T(u,v) represents the surface model, which may be a mapping from a unit square into 3D space so that points (u,v) in the unit square are mapped to points T(u,v) on the surface;
• Z(u,v) is the convolution of the discrete correction
• N(u,v) is the surface normal
• FIG. 2C illustrates the second way in which the empirical approximation is contoured prior to convolution.
• the discrete representation of the ply stack-up is combined with the surface model.
• the discrete correction is contoured.
• a convolution is performed on the contoured correction.
• the convolution is applied only to the correction, not to the surface model.
• the tooling surface isn't changed by the applied heat and pressure.
• FIGS. 3A-3D illustrate the method of FIG. 2C.
• a contoured underlying surface 310 e.g., a tooling surface
• a 2D stack-up 320 including three plies is illustrated in FIG. 3B.
• a combined representation 130 of the stack-up 320 on the contoured surface 310 is illustrated in FIG. 3C.
• the stack-up 320 is located on the surface 310, and the edges of the stack-up 320 are sharp.
• the stack-up 320 follows the contour of the underlying surface 310.
• FIG. 3D illustrates the approximation 340 resulting from the convolution on the contoured discrete correction. Resin ramps are formed from the third ply to the second ply, from the second ply to the first ply, and from the first ply to the surface 310.
• FIG. 4 illustrates a resin ramp 410 that transitions from a first ply 420 to a second ply 430.
• the convolution is performed with a kernel.
• the kernel As but one example, the
• convolution may be performed with a B-spline convolution kernel.
• the B-spline kernel is defined by its knots and its order.
• the convolution may be performed as where Z is a piecewise constant function that defines the normal component of a 2D ply stack-up, and M is a B-spline convolution kernel defined by its knots and order.
• knot structure is constructed, and the order is selected.
• the order determines the amount of smoothing.
• the knot structure and order fix the coefficients of the kernel.
• the knot structure affects the modeling of the movement of resin. Roughly speaking, the farther knots are located from the center of the kernel, the more flow that is represented.
• the kernel may be volume-preserving.
• a volume preserving kernel is a kernel that integrates to unity over the entire domain. When it is applied through a convolution operator, the integral of the original object remains unchanged. In the case of a convolution, this means that the volume of the composite part does not change.
• the kernel is not limited to one that is volume-preserving. Using non-volume preserving kernels enables modeling the situation in which compression of material occurs during curing.
• a choice of kernels may be available, and the convolution is performed with a kernel that is chosen according to characteristics of the resin. For example, a selection may be made between a first kernel
• the different kernels may be distinguished by different knot structures, or different types of kernels may be used. Examples of other types of kernels include Gaussian distributions and probability density functions.
• the B-spline is faster than these other kernels, and since the B-spline is dense within space, it can be
• the modeling herein may be used advantageously to improve composite fabrication processes.
• the modeling herein may be used to develop tool side surfaces (block 520). Starting with an exterior surface, plies are continually added and smoothed until a tool side surface is obtained. These tool side surfaces may be used to machine molds.
• modeling of an intermediate layer of a stack-up may be used to improve flat patterning (block 530). For instance, if the empirical
• the modeling may be used to reduce the uncertainty of weight computations.
• the modeling may reduce uncertainty over the amount or resin, length and thickness of the plies (which affects the ply weight), center of gravity, and moments of inertia etc.
• modeling may be used to infer tape laying
• sequencing (block 550).
• the modeling provides smooth surfaces over which geodesies can be computed reliably and accurately. These geodesies form the basis of computations which improve tape laying operations, including sequencing and orientation and steering of tape laying heads.
• a method herein is not limited to modeling the final surface of a composite part.
• a method herein may be used for the modeling of intermediate or partial ply stack-ups. Intermediate ply locations may be useful for providing repair schematics and performing mass property calculations for non- homogeneous ply stacks, both of which require models for cured partial ply stacks. An intermediate ply may be modeled simply by leaving off all plies above that intermediate ply.
• FIG. 6 illustrates a machine 610 including a processor 620, and non-transitory machine-readable memory 630.
• the machine 610 may be a computer.
• a program 640 is stored in the memory 630. When executed in the machine 610, the program 640 performs modeling of one or more composite parts as described herein.
• FIG. 7 illustrates an example of a composite aircraft 700.
• the aircraft 700 includes components and parts thereof that may be modeled according to a method herein.
• the components may include, but are not limited to a fuselage 710, wing assemblies 720, empennage 730, and landing gear assemblies 740.

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• 2011
  • 2011-12-02 US US13/310,665 patent/US8892406B2/en active Active
• 2012
  • 2012-09-20 WO PCT/US2012/056402 patent/WO2013062697A1/en not_active Ceased
  • 2012-09-20 JP JP2014537077A patent/JP6089036B2/ja active Active
  • 2012-09-20 KR KR1020147007608A patent/KR101943678B1/ko active Active
  • 2012-09-20 CN CN201280051944.0A patent/CN103890764B/zh active Active
  • 2012-09-20 EP EP12769573.2A patent/EP2748735A1/en not_active Withdrawn
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