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公开(公告)号：US10824779B2
公开(公告)日：2020-11-03
申请号：US15471486
申请日：2017-03-28
Applicant: The Boeing Company
Inventor： Vladimir Balabanov , Mostafa Rassaian , Zachary Robert Meves , Yuan-Jye Wu
IPC: G06F17/50 , G06F30/23 , B29C70/38 , B29L31/30 , G06F113/24 , G06F119/18 , G06F113/26
Abstract: A system comprises a model generation system and an analyzer. The model generation system is configured to modify a model of a laminated composite structure to meet a user defined objective and to meet at least one of user defined performance constraints or user defined manufacturing constraints by changing at least one ply characteristic of at least one ply of the model while maintaining ply boundary geometry constraints for each ply of the model. The ply boundary geometry constraints of the model generation system include a number of defined ply boundary geometries each described by a respective mathematical function. The analyzer is configured to return objective values or constraint function values for at least one ply of the model.
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公开(公告)号：US10140388B1
公开(公告)日：2018-11-27
申请号：US14542626
申请日：2014-11-16
Applicant: The Boeing Company
Inventor： Mostafa Rassaian , Vladimir Balabanov , Yuan-Jye Wu , Hong Tat , Olaf Weckner
IPC: G06F17/50
Abstract: A method of generating an optimized design model for a composite laminate may include computing a normalized set of lamination parameters and laminate stiffness matrices of an initial laminate design, and determining, using an optimizer operating on a finite element model, optimum values for the lamination parameters and the laminate thickness. The method may further include adjusting the optimum value of the laminate thickness, and performing an inversion process extracting multiple solutions from the lamination parameters, each solution including a unique set of individual fiber angles for each ply and representing an optimized design model of the composite laminate.
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公开(公告)号：US20160193806A1
公开(公告)日：2016-07-07
申请号：US14588536
申请日：2015-01-02
Applicant: The Boeing Company
Inventor： Vladimir Balabanov , Olaf Weckner , Yuan-Jye Wu , Abdelhai Maysara Saadi , Mostafa Rassaian
CPC classification number: B32B5/12 , B32B5/02 , B32B2250/20 , B32B2307/544 , B32B2307/546 , B32B2605/18 , G06F17/18 , G06F17/50 , G06F17/5009 , G06F17/5018 , Y10T428/24504
Abstract: Composite skin-stringer structures which reduce or eliminate the risk of delamination at the skin-stringer interface. This can be accomplished by arranging ply directions (i.e., the angles of the fiber paths of the ply) in a layup in a way such that for the dominant loading, the skin and stringer will each deform in a way that reduces relative opening (fracture Mode I) and/or sliding (fracture Mode II) and/or scissoring (fracture Mode III) at the skin-stringer interface. This is possible when coupling between specific deformations modes is purposefully activated instead of being suppressed. The ply directions in the stringer are adjusted so that the stringer deforms in a controlled fashion to suppress or “close” cracks that are about to form—before the undesirable modes of failure form—as load is applied.
Abstract translation: 复合皮肤桁架结构，减少或消除皮肤绷带界面分层的风险。 这可以通过以叠层的方式布置帘布层方向（即，帘布层的纤维路径的角度）来实现，使得对于主要负载，皮肤和纵梁将以减少相对开口（断裂）的方式变形 模式I）和/或滑动（断裂模式II）和/或剪切（断裂模式III）。 当特定变形模式之间的耦合有意激活而不是被抑制时，这是可能的。 调节桁条中的帘布层方向，使得桁条以受控的方式变形，以抑制或“关闭”即将形成的裂纹 - 在不期望的失效模式形成之前 - 施加负载。
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Patent Agency Ranking
公开(公告)号：US10183449B2
公开(公告)日：2019-01-22
申请号：US14866597
申请日：2015-09-25
Applicant: The Boeing Company
Inventor： Mostafa Rassaian , Michael A. Epton , Evin J. Cramer , Vladimir Balabanov , Olaf Weckner
IPC: B29C70/30
Abstract: A design process that uses lamination parameter inversion to generate a set of baseline layups having desired stiffness properties. Then the underdetermined Newton's method can be applied to explore solution manifolds describing alternative designs having similar if not identical stiffness properties. The manifold of solutions can be methodically examined to find those with desirable properties. Desirable properties include those that have been traditionally captured by design rules or those that improve manufacturability. Combining lamination parameters as design variables with lamination parameter inversion provides an efficient optimization process for non-traditional laminates.
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公开(公告)号：US20170087779A1
公开(公告)日：2017-03-30
申请号：US14866597
申请日：2015-09-25
Applicant: The Boeing Company
Inventor： Mostafa Rassaian , Michael A. Epton , Evin J. Cramer , Vladimir Balabanov , Olaf Weckner
IPC: B29C70/30
CPC classification number: B29C70/30
Abstract: A design process that uses lamination parameter inversion to generate a set of baseline layups having desired stiffness properties. Then the underdetermined Newton's method can be applied to explore solution manifolds describing alternative designs having similar if not identical stiffness properties. The manifold of solutions can be methodically examined to find those with desirable properties. Desirable properties include those that have been traditionally captured by design rules or those that improve manufacturability. Combining lamination parameters as design variables with lamination parameter inversion provides an efficient optimization process for non-traditional laminates.
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公开(公告)号：US11861273B2
公开(公告)日：2024-01-02
申请号：US16714012
申请日：2019-12-13
Applicant: THE BOEING COMPANY
IPC: G06F30/20 , G06F111/04 , G06F113/26 , G06F111/10
CPC classification number: G06F30/20 , G06F2111/04 , G06F2111/10 , G06F2113/26
Abstract: A method, a computing system and a computer program product are provided to efficiently define a guide that includes one or more defined sets of ordered ply orientations. In the context of a method, a plurality of stacking sequence rules are received. The method defines the guide including the one or more defined sets of ordered ply orientations in accordance with a constrained, linear integer optimization formulation. In this regard, the method defines the guide by dividing the guide into a plurality of blocks and determining a plurality of sublaminate stacks that satisfy the stacking sequence rules and that have a size limited by a size of the blocks. For each of the plurality of blocks, the method determines in accordance with the constrained, linear integer optimization formulation a sublaminate stack from among the plurality of sublaminate stacks that is compatible with a respective block.
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公开(公告)号：US10195817B2
公开(公告)日：2019-02-05
申请号：US14588536
申请日：2015-01-02
Applicant: The Boeing Company
Inventor： Vladimir Balabanov , Olaf Weckner , Yuan-Jye Wu , Abdelhai Maysara Saadi , Mostafa Rassaian
Abstract: Composite skin-stringer structures which reduce or eliminate the risk of delamination at the skin-stringer interface. This can be accomplished by arranging ply directions (i.e., the angles of the fiber paths of the ply) in a layup in a way such that for the dominant loading, the skin and stringer will each deform in a way that reduces relative opening (fracture Mode I) and/or sliding (fracture Mode II) and/or scissoring (fracture Mode III) at the skin-stringer interface. This is possible when coupling between specific deformations modes is purposefully activated instead of being suppressed. The ply directions in the stringer are adjusted so that the stringer deforms in a controlled fashion to suppress or “close” cracks that are about to form—before the undesirable modes of failure form—as load is applied.
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8.发明申请公开(公告)号：US20180285498A1
公开(公告)日：2018-10-04
申请号：US15471486
申请日：2017-03-28
Applicant: The Boeing Company
Inventor： Vladimir Balabanov , Mostafa Rassaian , Zachary Robert Meves , Yuan-Jye Wu
Abstract: A system comprises a model generation system and an analyzer. The model generation system is configured to modify a model of a laminated composite structure to meet a user defined objective and to meet at least one of user defined performance constraints or user defined manufacturing constraints by changing at least one ply characteristic of at least one ply of the model while maintaining ply boundary geometry constraints for each ply of the model. The ply boundary geometry constraints of the model generation system include a number of defined ply boundary geometries each described by a respective mathematical function. The analyzer is configured to return objective values or constraint function values for at least one ply of the model.
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