Patent application EP17166886A (EP), filed 2017-04-18
Publication number: EP3261000A1
Title: MODELING AND ANALYSIS OF LEADING EDGE RIBS OF AN AIRCRAFT WING
Abstract: [0001]    An apparatus is provided for analysis of a leading edge rib of a fixed leading edge section of an aircraft wing. The apparatus may identify geometric or inertial properties of a plurality of stiffeners (402) of the rib in which respective stiffeners are represented by a collection of geometry within a solid model of the rib, and perform an analysis to predict a failure rate of the leading edge rib under an external load. From the failure rate, the apparatus may determine a structural integrity of the leading edge rib under the external load. Identifying the properties may include, extracting a section cut of the geometry that corresponds to and has one or more properties of the respective stiffener, and identifying the properties of the cross-section and thereby the respective stiffener based on a correlation of the cross-section to a generic profile of a plurality of different cross-sections.
IPC codes: B64C   3/    14            A I
B64C   3/    28            A I
G06F  17/    50            A I
Claims: number: 1
text: An apparatus (1300) for analysis of a leading edge rib (400) of a fixed leading edge section of an aircraft wing, the leading edge rib (400) being composed of a plurality of stiffeners (402), the apparatus (1300) comprising a processor (1302) and a memory (1304) storing executable instructions that, in response to execution by the processor (1302), cause the apparatus (1302) to at least:
number: 2
text: The apparatus of Claim 1, wherein the one or more geometric or inertial properties of the cross-section include at least a cross-section type , dimensional measurements, centroid or moment of inertia of the cross-section; and,
wherein the respective stiffener (402) includes a flange and web, and the cross-section type includes a plus sign, T, I, L, J, C or U-shaped cross-section, and the one or more geometric or inertial properties further include an orientation of the cross-section including at least a left webbed or right webbed orientation.
number: 3
text: The apparatus of Claim 2, wherein the apparatus being caused to identify the one or more geometric or inertial properties of the cross-section includes being caused to:
number: 4
text: The apparatus of Claim 1, wherein the respective stiffener (402) includes at least one flange and a web, and the apparatus is further caused to define offset planes on either side of the midline with respect to a thickness of the web, and the apparatus being caused to identify the one or more geometric or inertial properties of the cross-section includes being caused to identify a location of the at least one flange based on a correlation of the cross-section to the generic profile at the offset planes.
number: 5
text: The apparatus of any one of Claims 1-4, wherein the apparatus being caused to identify the one or more geometric or inertial properties of the plurality of stiffeners (402) includes being caused to:
number: 6
text: The apparatus of Claim 5, wherein the respective stiffener (402) includes at least a flange and web, and the apparatus being caused to identify the nearest outer node nodes of the respective nodes and elements includes the nearest outer node being an outermost common node of elements of the finite element model that represent the flange and web, the outermost common node representing a point of intersection therebetween.
number: 7
text: A method for analysis of a leading edge rib of a fixed leading edge section of an aircraft wing, the leading edge rib being composed of a plurality of stiffeners (402), the method comprising:
number: 8
text: The method of Claim 7, wherein the one or more geometric or inertial properties of the cross-section include at least a cross-section type , dimensional measurements, centroid or moment of inertia of the cross-section.
number: 9
text: The method of Claim 8, wherein the respective stiffener includes a flange and web, and the cross-section type includes a plus sign, T, I, L, J, C or U-shaped cross-section, and the one or more geometric or inertial properties further include an orientation of the cross-section including at least a left webbed or right webbed orientation.
number: 10
text: The method of Claim 7, wherein identifying the one or more geometric or inertial properties of the cross-section includes:
number: 11
text: The method of Claims 7 or 8, wherein the respective stiffener includes at least one flange and a web, and the method further comprises defining offset planes on either side of the midline with respect to a thickness of the web, and identifying the one or more geometric or inertial properties of the cross-section includes identifying a location of the at least one flange based on a correlation of the cross-section to the generic profile at the offset planes.
number: 12
text: The method of any one of Claims 7-11, wherein identifying the one or more geometric or inertial properties of the plurality of stiffeners (402) includes:
number: 13
text: The method of Claim 12, wherein extracting the collection of geometry and identifying the one or more geometric or inertial properties includes:
number: 14
text: The method of any one of Claims 7-13, wherein performing the analysis includes:
number: 15
text: The method of Claim 14, wherein the respective stiffener includes at least a flange and web, and identifying the nearest outer node nodes of the respective nodes and elements includes the nearest outer node being an outermost common node of elements of the finite element model that represent the flange and web, the outermost common node representing a point of intersection therebetween.
Office action: search_report, dated 2017-12-27
Rejection reasons: novelty_epc_54
Prior art cited: ref_id: - JAMES AINSWORTH ET AL: "Airframe Wingbox Preliminary Design and Weight Prediction", 69TH ANNUAL CONFERENCE, VIRGINIA BEACH, VIRGINIA, 1 May 2010 (2010-05-01), pages 1 - 41, XP055377257, Retrieved from the Internet <URL:https://hypersizer.com/download.php?type=pdf&file=SAWE2010_Airframe_Wing_Box_Structure_Weight_Predictions.pdf> [retrieved on 20170530]
ref_type: npl
severity: background
ref_id: - LARS KROG ET AL: "Application of topology, sizing and shape optimization methods to optimal design of aircraft components", 1 January 2002 (2002-01-01), pages 1 - 12, XP055377263, Retrieved from the Internet <URL:http://www.southampton.ac.uk/~jps7/Aircraft%20Design%20Resources/manufacturing/airbus%20wing%20rib%20design.pdf> [retrieved on 20170530]
ref_type: npl
severity: background
ref_id: - ANNA ARSENYEVA ET AL: "Efficient and adaptive parametric modeling for shape optimization of a wingbox", YIC GACM 2015 3RD ECCOMAS YOUNG INVESTIGATORS CONFERENCE 6TH GACM COLLOQUIUM, 23 July 2015 (2015-07-23), pages 2 - 6, XP055377546, Retrieved from the Internet <URL:https://www.researchgate.net/profile/Anna_Arsenyeva/publication/280557241_Efficient_and_adaptive_parametric_modeling_for_shape_optimization_of_a_wingbox/links/55b8f84408aec0e5f43bf906.pdf> [retrieved on 20170531]
ref_type: npl
severity: background
ref_id: - HARDEE EDWIN ET AL: "CAD-based design parameterization for shape optimization of elastic solids", ADVANCES IN ENGINEERING SOFTWARE, ELSEVIER SCIENCE, OXFORD, GB, vol. 30, no. 3, 1 March 1999 (1999-03-01), pages 185 - 199, XP002418120, ISSN: 0965-9978, DOI: 10.1016/S0965-9978(98)00065-9
ref_type: npl
severity: background
ref_id: - James Ainsworth ET AL, "Airframe Wingbox Preliminary Design and Weight Prediction", 69th Annual Conference, Virginia Beach, Virginia, (20100501), pages 1 - 41, URL: https://hypersizer.com/download.php?type=pdf&file=SAWE2010_Airframe_Wing_Box_Structure_Weight_Predictions.pdf, (20170530), XP055377257 [X] 1,2,4-9,11-15 * section 4.3, 4.4.1, 4.6.1, 5, 5.1.1, 6.2, 7.1, 7.5;; figures 4.4.2,4.5.1,5.2.1,5.4.1,5.6.1, 6.6.2,10.3.1,10.4.1 * * abstract * * the whole document * [I] 3,10
ref_type: npl
severity: novelty_destroying
ref_id: - Lars Krog ET AL, "Application of topology, sizing and shape optimization methods to optimal design of aircraft components", (20020101), pages 1 - 12, URL: http://www.southampton.ac.uk/~jps7/Aircraft%20Design%20Resources/manufacturing/airbus%20wing%20rib%20design.pdf, (20170530), XP055377263 [X] 1-15 * abstract * * figures 1,3,6,8,9 * * the whole document *
ref_type: npl
severity: novelty_destroying
ref_id: - Anna Arsenyeva ET AL, "Efficient and adaptive parametric modeling for shape optimization of a wingbox", YIC GACM 2015 3rd ECCOMAS Young Investigators Conference 6th GACM Colloquium, (20150723), pages 2 - 6, URL: https://www.researchgate.net/profile/Anna_Arsenyeva/publication/280557241_Efficient_and_adaptive_parametric_modeling_for_shape_optimization_of_a_wingbox/links/55b8f84408aec0e5f43bf906.pdf, (20170531), XP055377546 [X] 1-15 * figures 2,6 * * abstract * * the whole document *
ref_type: npl
severity: novelty_destroying
Final disposition: pending (2017-12-27)