翼身融合民机典型PRSEUS受压壁板屈曲及渐进损伤分析

doi:10.7527/S1000-6893.2019.23185

Abstract

Abstract: Due to the excellent loading advantage of stability under compression and damage arrest/crack arrest, the Pultruded Rod Stitched Efficient Unitized Structure (PRSEUS), put forward by NASA and the Boeing Company, has become the major solution to solve low efficiency and poor stability problems caused by non-circular fuselage cross section in civil aircraft. This paper carries out linear/nonlinear buckling and progressive damage analysis for representative compressed PRSEUS panel structure. The methods of modeling the geometric relationship of the support configuration and offset reference surface of skin, tears-trap, stringer flange, frame flange integrated stitched supporting configuration are put forward, improving the accuracy of the finite element model of PRSEUS compressed panel. A mesh convergence analysis method that takes buckling eigenvalue, nonlinear buckling load and other factors into account is proposed to improve the computational efficiency of PRSEUS compressed panel buckling analysis. Three initial imperfection introduction methods including the minimum buckling eigenvalue, geometrical node offset, and combination of the minimum buckling eigenvalue and geometrical node offset are presented to improve the calculation accuracy of the finite element model of PRSEUS compressed panel. Finally, the nonlinear buckling progressive damage analyses of representative PRSEUS compressed panel based on the damage constitutive relation between fiber and matrix are completed. By comparing the experimental results, the nonlinear buckling progressive damage evolution analysis methods for PRSEUS structure are presented. This paper provides the methods and technical support for the stability/damage analysis and design of the PRSEUS structure in blended-wing-body civil aircraft.

Key words: blended-wing-body civil aircraft, PRSEUS structure, nonlinear buckling, mesh convergence, progressive damage

CLC Number:

ZHANG Yongjie, WU Yingying, ZHU Shengli, WANG Bintuan, TAN Zhaoguang, YUAN Changsheng. Buckling and progressive damage analysis of representative compressed PRSEUS panel in blended-wing-body civil aircraft[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2019, 40(9): 623185-623185.

References 55

[1]	LAUGHLIN T, CORMAN J, MAVRIS D. A parametric and physics-based approach to structural weight estimation of the hybrid wing body aircraft[C]//51st AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston,VA:AIAA, 2013:16076-16095.
[2]	DICKEY E D, PRINCEN N, BONET J T, et al. Wind tunnel model design and fabrication of a 5.75% scale blended-wing-body twin jet configuration[C]//54th AIAA Aerospace Sciences Meeting. Reston,VA:AIAA, 2016.
[3]	FLANSBURG B D. Structural loads analysis of a hybrid wing body transport[C]//58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston,VA:AIAA, 2017.
[4]	GERN F H. Conceptual design and structural analysis of an open rotor hybrid wing body aircraft[C]//54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston,VA:AIAA, 2013.
[5]	LAUGHLIN T W, CORMAN J A, MAVRIS D N. A parametric and physics-based approach to structural weight estimation of the hybrid wing body aircraft[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston,VA:AIAA, 2013.
[6]	NICKOL C L. Hybrid wing body configuration scaling study[C]//50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston,VA:AIAA, 2012.
[7]	LIEBECK R. Blended wing body design challenges[C]//AIAA International Air and Space Symposium and Exposition:The Next 100 Years. Reston,VA:AIAA, 2003.
[8]	MUKHOPADHYAY V. Hybrid wing-body pressurized fuselage modeling, analysis, and design for weight reduction[C]//53rd AIAA/ASME/ASCE/AHS/ASCStructures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2012.
[9]	MUKHOPADHYAY V. Hybrid-wing-body vehicle composite fuselage analysis and case study[C]//14th AIAA Aviation Technology, Integration, and Operations Conference. Reston,VA:AIAA, 2014.
[10]	MUKHOPADHYAY V, SOBIESZCZANSKI-SOBIESKI J, KOSAKA I, et al. Analysis design and optimization of non-cylindrical fuselage for blended-wing-body (BWB) vehicle[C]//9th AIAA/ISSMO Symposium on Multidisciplinary Analysis and Optimization. Reston,VA:AIAA, 2002.
[11]	BISHARA M, HORST P, MADHUSOODANAN H,et al. A structural design concept for a multi-shell blended wing body with laminar flow control[J]. Energies, 2018, 11(2):383.
[12]	MUKHOPADHYAY V. Blended-wing-body (BWB) fuselage structural design for weight reduction[C]//46th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2005.
[13]	VELICKI A, THRASH P, JEGLEY D. Airframe development for the hybrid wing body aircraft[C]//47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition. Reston,VA:AIAA, 2009.
[14]	LIEBECK R H, PAGE M A, RAWDON B K. Blended-wing-body subsonic commercial transport[C]//36th Aerospace Sciences Meeting & Exhibit. Reston,VA:AIAA, 1998.
[15]	KAWAI R T. Benefit potential for a cost efficient dual fuel bwb[C]//51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston,VA:AIAA, 2013.
[16]	REIST T A, ZINGG D W. Optimization of the aerodynamic performance of regional and wide-body-class blended wing-body aircraft[C]//33rd AIAA Applied Aerodynamics Conference. Reston,VA:AIAA, 2015.
[17]	RISCH T, COSENTINO G, REGAN C D, et al. X-48b flight-test progress overview[C]//47th AIAA Aerospace Sciences Meeting and Exhibit. Reston,VA:AIAA, 2009.
[18]	VOS R, GEUSKENS F, HOOGREEF M F M. A new structural design concept for blended wing body cabins[C]//53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2012.
[19]	CHO S H, BIL C, ADAMS R. Design and analysis of bwb military cargo centre body structure[C]//AIAA Centennial of Naval Aviation Forum "100 Years of Achievement and Progress". Reston,VA:AIAA, 2011.
[20]	CHO S H, BIL C, BAYANDOR J. Structural design and analysis of a bwb military cargo transport fuselage[C]//46th AIAA Aerospace Sciences Meeting and Exhibit. Reston,VA:AIAA, 2008.
[21]	BRADLEY K R. A sizing methodology for the conceptual design of blended-wing-body transports:NASA/CR-2004-213016[R]. Washington, D. C.:NASA, 2004.
[22]	LIEBECK R. Design of the blended-wing-body subsonic transport[C]//40th AIAA Aerospace Sciences Meeting & Exhibit. Reston,VA:AIAA, 2002.
[23]	YOVANOF N P, VELICKI A, LI V. Advanced structural stability analysis of a noncircular bwb-shaped vehicle[C]//50th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston,VA:AIAA, 2009.
[24]	LI V, LINTON K. Hybrid wing body (hwb) aircraft design and optimization using stitched composites[C]//16th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference. Reston,VA:AIAA, 2015.
[25]	GERN F H. Update on HCDstruct-A tool for hybrid wing body conceptual design and structural optimization[C]//15th AIAA Aviation Technology, Integration, and Operations Conference. Reston,VA:AIAA, 2015.
[26]	WU H T, SHAW P, PRZEKOP A. Analysis of a hybrid wing body center section test article[C]//54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston,VA:AIAA, 2013.
[27]	GERN F H. Finite element based hwb centerbody structural optimization and weight prediction[C]//53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2012.
[28]	QUINLAN J R, GERN F H. Conceptual design and structural optimization of NASA environmentally responsible aviation (era) hybrid wing body aircraft[C]//57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston,VA:AIAA, 2016.
[29]	JOHNSTON P H, JUAREZ P D. Ultrasonic nondestructive evaluation of pultruded rod stitched efficient unitized structure (PRSEUS) during large-scale load testing and rod push-out testing:NASA/TM-2016-218978[R]. Was-hington, D. C.:NASA, 2016.
[30]	HORNE M R, MADARAS E I. Evaluation of acoustic emission SHM of PRSEUS composite pressure cube tests:NASA/TM-2013-217993[R]. Washington, D.C.:NASA, 2013.
[31]	JEGLEY D C. Experimental behavior of fatigued single stiffener PRSEUS specimens:NASA/TM-2009-215955[R]. Washington, D.C.:NASA, 2009.
[32]	WANG J T, GRENOBLE R W, PICKELL R D. Structural integrity testing method for prseus rod-wrap stringer design[C]//53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and MaterialsConference. Reston,VA:AIAA, 2012.
[33]	JEGLEY D C, VELICKI A. Development of the prseus multi-bay pressure box for a hybrid wing body vehicle[C]//56th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference.Reston,VA:AIAA, 2015.
[34]	LOVEJOY A E, POPLAWSKI S. Preliminary design and analysis of an in-plane prseus joint[C]//54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston,VA:AIAA, 2013.
[35]	LOVEJOY A E, LEONE JR F A. T-cap pull-off and bending behavior for stitched structure:NASA/TM-2016-218971[R]. Washington, D.C.:NASA, 2016.
[36]	LOVEJOY A, ROUSE M, LINTON K, et al. Pressure testing of a minimum gauge PRSEUS panel[C]//52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2011.
[37]	JEGLEY D, ROUSE M, PRZEKOP A, et al. Testing of a stitched composite large-scale pressure box[C]//57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2016.
[38]	VELICKI A, JEGLEY D. Prseus structural concept development[C]//52nd Aerospace Sciences Meeting. Reston,VA:AIAA, 2014.
[39]	LOVEJOY A E, LEONE F A. Tension and bending testing of an integral t-cap for stitched composite airframe joints[C]//57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston,VA:AIAA, 2016.
[40]	JEGLEY D C. Behavior of frame-stiffened composite panels with damage[C]//54th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston,VA:AIAA, 2013.
[41]	PRZEKOP A, JEGLEY D C, LOVEJOY A E, et al. Testing and analysis of a composite non-cylindrical aircraft fuselage structure, Part I:Ultimate design loads[C]//57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2016.
[42]	PRZEKOP A, JEGLEY D C, LOVEJOY A E, et al. Testing and analysis of a composite non-cylindrical aircraft fuselage structure, Part Ⅱ:Severe damage[C]//57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2016.
[43]	PRZEKOP A. Repair concepts as design constraints of a stiffened composite prseus panel[C]//53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2012.
[44]	VELICKI A, JEGLEY D. Prseus development for the hybrid wing body aircraft[C]//AIAA Centennial of Naval Aviation Forum "100 Years of Achievement and Progress". Reston,VA:AIAA, 2011.
[45]	PAPAPETROU V S, TAMIJANI A, KIM D. Preliminary wing study of general aviation aircraft with prseus panels[C]//57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. Reston,VA:AIAA, 2016.
[46]	LI V, VELICKI A. Advanced prseus structural concept design and optimization[C]//12th AIAA/ISSMO Multidisciplinary Analysis and Optimization Conference. Reston,VA:AIAA, 2008.
[47]	VELICKI A. Damage arresting composites for shaped vehicles phase 1 final report:NASA/CR-2009-215932[R]. Washington, D. C.:NASA, 2009.
[48]	VELICKI A, THRASH P. Advanced structural concept development using stitched composites[C]//49th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2008.
[49]	YOVANOF N P, JEGLEY D C. Compressive behavior of frame-stiffened composite panels[C]//52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2011.
[50]	VELICKI A, YOVANOF N, BARAJA J, et al. Damage arresting composites for shaped vehicles-phase Ⅱ final report:NASA/CR-2011-216880[R].Washington, D.C.:NASA, 2011.
[51]	LINTON K A, VELICKI A, HOFFMAN K, et al. Prseus panel fabrication final report:NASA/CR-2014-218149[R]. Washington, D.C.:NASA, 2014.
[52]	VELICKI A, YOVANOF N P, BARAJA J, et al. PRSEUS acoustic panel fabrication:NASA/CR-2011-217309[R]. Washington, D.C.:NASA, 2011.
[53]	SANZ-DOUGLASS G J, VENKATARAMAN S. Parametric study of influence of stiffener variables onpost-buckling response of frame stiffened composite panels[C]//57th AIAA/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference. Reston,VA:AIAA, 2016.
[54]	LAPCZYK I, HURTADO J A. Progressive damage modeling in fiber-reinforced materials[J]. Composites Part A:Applied Science and Manufacturing, 2007, 38(11):2333-2341.
[55]	JEGLEY D C. Improving strength of postbuckled panels through stitching[J]. Composite Structures, 2007, 80(2):298-306.

Buckling and progressive damage analysis of representative compressed PRSEUS panel in blended-wing-body civil aircraft

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