The key element of the wing consists of a pressurized telescopic spar that can undergo large-scale spanwise changes while supporting wing loadings in excess of 15 lbs/ft. (�� Authors: Juan Reuben Lazarin*, and Eltahry Elghandour** Students at the Cal Poly Department of Mechanical and Aerospace Engineering were tasked with the challenge of ensuring that a wing structure is within design limits. I.e. A number of characteristics (stiffnesses, mass distributions, moments of inertia etc), necessary for flutter calculations, is included in this paper. (�� Wings of the aircraft are normally attached to the fuselage at the root of the wing. The most suitable materials were selected and combined in order to produce composite material with optimized structural performance. <> Conventionally wing spars are of fixed geometry cross-section. The wing spar was optimized in order to maximize the team’s score in the SAE Brazil 2016 Aero Design competition. This paper discusses the design, development and testing of an inflatable telescopic wing that permits a change in the aspect ratio while simultaneously supporting structural wing loads. (�� Case Study of Aircraft Wing Manufacture1 ÒYeah. It was recently studied that by adaptively varying the torsional load carrying capacity of the wing spar, the performance of an aircraft could be considerably improved. The design of this wing spar is limited to specific design constraints. These constraints are displayed below in Table 3. For example, when designing a wing it is necessary for this wing to have the maximum lift-to-drag ratio, the minimum weight, the sufficient lifespan and enough internal volume to contain the large amount of fuel, to be easy to manufacture and etc. 3. %&'()*456789:CDEFGHIJSTUVWXYZcdefghijstuvwxyz��������������������������������������������������������������������������� For example, the web of a spar may be a plate or a truss as shown in Figure 9. While the boxes are covered with wood, the surface of the wing between them covered with a flexible material, which only supported by the ribs. In reality, the shape of the surface between neighboring ribs, and the leading and trailing edge boxes is also controlled by the mechanical properties of the cover material. The following section.3.1 and section.3.2 explain how the bending stress and shear stress values at each row of fasteners are determined. Design, Analysis and Testing of Wing Spar for Optimum Weight. In addition, this report presents the plane’s wing and tail design, stability analysis and a mass breakdown. 1 0 obj (�� (���k���@�.nR���U��-����KofX��g�o�րo���M��h�� � (�� (�� (�� (P:PEP1“Tj�7ҩ�Lڞ�IKEA��QE QE QE They are Angle of attack, the lift devices used (like flaps), the density of air, the area of wing, the shape of wing, the speed at which the wing is travelling. <> (2017) considered a wing spar as a beam with discrete loads at different stations. $4�%�&'()*56789:CDEFGHIJSTUVWXYZcdefghijstuvwxyz�������������������������������������������������������������������������� ? (�� ��{�0�B��\�z�i�6��C{h0��`�W��UYbh��=j�lLf�QRXQE QE RT�����{��"�e��z��sH���tSRf��S���#\�.���j4B���!�%��g�L�1 �ĽC1�n>h��G=��+��Z�(�4 The front spars, however must carry the engine loads — the major design driver in wing spar development. (�� An optimized wing design will fail just as the ultimate loading conditions are reached. Since then, A400M spar production has been transferred to the new dedicated spar facility in Western Approach (see far right photo, p. 27) to take advantage of synergies with the A350 spar operation and benefit from close proximity to the Airbus wing design center in Filton. An arrangement of main spar, ribs, shell and strut for high aspect ratio main wing and tailplane has been proposed. JZJ`K�G�Z�U�py����r)�b%�*�w8���� �"�;�����QE2B�(��(��(��(��(��(��(��(��Q@Q@�9��:s���ޛX��lQE/DۣSN#�ո+������VeY���/OOJ��*����q�i �ez(��&"G�I�c ,pMYX�!�B ���5�}��M��cMhK�%yه�6�SP��s����#���ѹ 15 Apr 2007. These constraints are displayed below in Table 3. All Steps: https://www.youtube.com/playlist?list=PLdYlWrkyz3k9boR8J2iJP0boq9WUM5SKW Terry Hallet Hummel Aviation http://www.flyhummel.com/ Composite wings, Sizing, Design optimization, MDO. �>�C���2O�M�X�i�&~��9m�ߕ$��B����D˅q��H-�rjDEA��Hɵ�(��)�q#}i�B For design of the wing foldin g mechanism in two planes in LSA May 2008 project report, the mechanism makes use of a two stage process. (�� (�� required for a conceptual design like the cargo type & amount,Wing aspect ratio, Optimum Airfoil lift(C L), Thrust to weight ratio & Takeo distance. The shear force here starts at 0 as there are no reaction forces here and there are no loads acting at this point. Conclusion The Engineering design process was successfully implemented to find a viable solution for the Air Force's B-52 wing spar. (�� the wing of the Wright Flyer (Img. (�� (�� 1. PDF | On May 10, 2017, Seth Kitchen and others published Design of an RC Aircraft | Find, read and cite all the research you need on ResearchGate If that alignment is off, engineering comes down and designs us a shim. This involves the definition of the wing section and the planform. Words: 8,543; Pages: 63; Preview; Full text; CHAPTER 1 INTRODUCTION 1.1 AIRCRAFT WING The aircraft wings are the primary lift producing device for an aircraft. (�� (��(������|���L����QE�(�� (�� J)i)�QE=��N�����u�W�}�ߡ���cR=I(��� ��( ��( ��( ��( ��( �� QE ��F��n���'�QܫEVG@QE*ճe VLADIMIR SOLOSHENKO 2 Fig.1. %PDF-1.5 Hello Fellow Scratchbuilders! Our main alternative design for the wing folding mechanism is a circular type bracket the fits around the main spar and allows the wing to rotate and pull out from the central hub in one motion. Design and analysis procedure of high aspect ratio wing spar are introduced. Ravelry: Wingspan pattern by maylin Tri'Coterie Designs The Wingspan Shawl Knitting Pattern has very detailed instructions. Using the finite element software package COMSOL, the calculated aerodynamic loads are applied to the wing to check the wing reliability. MUSEUM IN A BOX. THE F11 WING For the whole design, structurally and aerodynamically, one certain wing has to be chosen, so that the aerody-namic engineers and their structural counterparts use an identical model. Design, Analysis and Testing of Wing Spar for Optimum Weight. The design of this wing spar is limited to specific design constraints. 1. 1) with that of a modern aircraft, such as the Boeing 787 (Img. (�� 2 0 obj (�� analysis is also performed for wing design purposes. The wing must produce sufficient lift while generate minimum drag, and minimum pitching moment. The object of research – a wingbox of a medium-range aircraft (regular zone of the structure and the root splice joint zone with wing center section) 4) Working out the methodology of the wingbox structural design in regular zone and root splice joints. VLADIMIR SOLOSHENKO 2 Fig.1. (�� To achieve this motion, the bolts connecting the main and trailing spars to the fuselage are to be removed. Although the spar shapes in Figure 8 are typical, actual wing spar configurations assume many forms. ���o�QVOs�;QH���((����(��(��(�aE�D��y4%q6��̫ӓLT������U�ly��>��Z�s'S�L �8POӥZ�O�[>®��P ���3n�Q�juP ��@'��}p�9�(�W��(�{z 4 0 obj Some of the forces acting on a wing spar are: Upward bending loads resulting from the wing lift force that supports the fuselage in flight. The following section.3.1 and section.3.2 explain how the bending stress and shear stress values at each row of fasteners are determined. (�� 2 Remove backshell from plug … Using the finite element software package COMSOL, the calculated aerodynamic loads are applied to the wing to check the wing reliability. (�� Wings of the aircraft are normally attached to the fuselage at the root of the wing. Additionally every con- figuration is checked for dynamic aeroelastic problems, like flutter. I'm revisiting the design of a wing spar for a removable wing. ii. To achieve this motion, the bolts connecting the main and trailing spars to the fuselage are to be removed. Conventionally wing spars are of fixed geometry cross-section. Wing Loading and its Effects A seminar by Performance Designs, Inc. Speaker: John LeBlanc I. Optimal Design of Composite Wing Spar Subjected to Fatigue Loadings . Software packages are to be used to design an aircraft wing spar structure and Finite Element Method (FEM) also be used to calculate the stresses developed at each station for a given bending moment. This provides a very strong spar design. 3.1. Wing design is constantly evolving. The structure of an airframe represents one of the finest examples of a minimum weight design in the field of structural engineering. Surprisingly such an efficient design is achieved PJ���IE Hf��n�I�9����$� The efficient design will be achieved by the use of strength of material approach. (�� For example, the web of a spar may be a plate or a truss as shown in Figure 9. MATLAB MuPAD software was used to derive analytical models for the aircraft wing loads using the design tasks are usually multi-criteria. I. For design of the wing foldin g mechanism in two planes in LSA May 2008 project report, the mechanism makes use of a two stage process. Key words: Finite element analysis, aircraft wing, wing with ribs and spars. wing design is obtained by decoupling the tension and shear bearing structural members. Each of these components act like a beam and torsion member as a whole. Additionally every con- figuration is checked for dynamic aeroelastic problems, like flutter. 1. In reality, the shape of the surface between neighboring ribs, and the leading and trailing edge boxes is also controlled by the mechanical properties of the cover material. It was recently studied that by adaptively varying the torsional load carrying capacity of the wing spar, the performance of an aircraft could be considerably improved. The object of research – a wingbox of a medium-range aircraft (regular zone of the structure and the root splice joint zone with wing center section) 4) Working out the methodology of the wingbox structural design in regular zone and root splice joints. PDF | On May 10, 2017, Seth Kitchen and others published Design of an RC Aircraft | Find, read and cite all the research you need on ResearchGate The ultimate flight load factor was calculated to be 3g's. ��*sKY�̇*pj�w�~�j�#Skbz(���(�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� �t~��5�̀z This was an exclusive design for the Tri’Coterie Angels Club June 2011, available generally from January 2012. (�� 2. (���Q@Q@Q@S�:�a{����8�ZVc��SEc$�4�h�j�L�EЅ�'��"��S��Q�z�����>��KT����܆X��.��55S$(���h�; };���%H�]��2߻��.�~�������=hI���%ǹ���{�����zh��.O���-���2ަ��� (�� (�� (�� (�� J(4PEPWsUj���T{�j�[���(���Ģ��� Front spar having „‟ section and rear spar having „‟ section. wing spar, aiming at achieving a high structural efficiency. Keywords: design, wing, composite materials, joints . (�� Each engine produces over 7,500 kW or 10,000 shp (shaft horsepower) to drive eight composite propellers per engine through a speed reduction gearbox. 2. Wing Spars (page 1) Started: October 6, 2003. Download & View Numerical Analysis Of Wing Spar Design as PDF for free. Each of these components act like a beam and torsion member as a whole. Although the spar shapes in Figure 8 are typical, actual wing spar configurations assume many forms. The wing spar is modelled as a cantilever beam that is free at the end, the end that is free is at co-ordinates (0, 0) in diagram 2. The engines drive the aircraft through the propellers by means of torque, which is reacted at the attachment points on the front spar. analysis is also performed for wing design purposes. (�� July 27, 2017 Posted by: RSIS; Category: Uncategorized; No Comments . the wing spar, ribs positioned at different stations along spanwise direction, front and rear spars; upper and lower skins. The Bearhawk wing spars are built very similar to the Van's RV series wing spars. The leading edge box usually also houses the main wing spar. %���� Elizabeth Hargrave is an American game designer whose game Wingspan won the 2019 Kennerspiel des Jahres for best connoisseur game of the year. Everything the jumper exits with, including all clothing, the rig and both canopies must be included in the weight. (��*��5Mr?y�j��{��(��EQ@Q@ E-% R3'��G�i�q9%�1 �������;i�9SWa��>H���j&n�b�C5����]��4��s�U�*�� 0Q@��k�����T�� �%Ϲ���FX�=MT������zUe���6q�zU�l�����ߥ T����G�Z�����ڭ��Eq0�=�I�1@ ` ���� �>�~m�ϵUn+h�*��M SmE�D ��Ǩ�q"c�U�f�\�$�Z0�� ������zZɵ�����t�0��j F������n��?�����E�������ƼG�����\���zzU�5��.�w�EOqj������ Q�E܄N���I���qjF$R��r(�3��ٞ;�R�EPEPEPEP (�t�� (�� (�� These design goals must be collectively satisfied throughout all flight operations and missions. 7 Wing Design During the preliminary sizing, the wing was merely described in terms of the wing area SW and the wing aspect ratio AW. The shear force here starts at 0 as there are no reaction forces here and there are no loads acting at this point. We have to wait 24 hours while they do the calculations. (�� Introduction . (�� When designing the wing, other wing parameters are determ­ ined. endobj zH�r��E�v)��<5KY�b��+�=jԻ�ʟTZ��r2(�2 (�� This makes the wing spar beam to behave almost like a cantilever beam. Several types of wing spar structure have been studied and optimized in the literature (Ajith V. S. et al. (�� A truss wing spar: Figure 10. If that alignment is off, engineering comes down and designs us a shim. Everything the jumper exits with, including all clothing, the rig and both canopies must be included in the weight. Introduction . <>/Font<>/ExtGState<>/ProcSet[/PDF/Text/ImageB/ImageC/ImageI] >>/Annots[ 13 0 R 30 0 R 31 0 R 32 0 R 33 0 R 34 0 R 35 0 R 36 0 R 37 0 R 38 0 R 39 0 R 40 0 R 41 0 R 42 0 R 43 0 R 44 0 R 45 0 R 46 0 R 47 0 R 48 0 R 49 0 R 50 0 R 51 0 R 52 0 R 53 0 R 54 0 R] /MediaBox[ 0 0 595.32 841.92] /Contents 5 0 R/Group<>/Tabs/S>> They are Angle of attack, the lift devices used (like flaps), the density of air, the area of wing, the shape of wing, the speed at which the wing is travelling. (����((����(��(��(���� Ȩh����{� (PA8�M��6>� h���� Hence, a design concept for adaptively varying the torsional stiffness of an aircraft wing spar is desired. See Fig. (�� The efficient design was achieved by the use of strength of material approach. Wing Spar Design. This makes the wing spar beam to behave almost like a cantilever beam. Girennavar M., et al. 4 and 5). There is no need to make the wing any stronger than it needs to be, and any excess strength (wing weight due to extra material) will reduce the payload capacity of the aircraft making it uncompetitive or uneconomic to operate. July 27, 2017 Posted by: RSIS; Category: Uncategorized; No Comments . When the line is supposed to move every three days, thatÕs a disaster.Ó A. the design tasks are usually multi-criteria. (�� A six seater transport aircraft wing spar design is considered and the initial design has been carried out using conventional design approach which was found out to be with heavy weight. (�� (�� Introduction . These forces are often offset by carrying fuel in the wings or employing wing-tip-mounted fuel tanks; the Cessna 310 is an example of this design feature. While the boxes are covered with wood, the surface of the wing between them covered with a flexible material, which only supported by the ribs. For the wing, it was determined that an RTM process, with integrated structural elements, would best achieve cost and weight targets. The leading edge box usually also houses the main wing spar. http://www.RCadvisor.com There is a lot to designing a strong and lightweight wing spar for a foam airplane. (��Q@%-%0 1. ]c\RbKSTQ�� C''Q6.6QQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQQ�� ��" �� Design and analysis procedure of high aspect ratio wing spar are introduced. The aerodynamic load was calculated on the wing using TORNADO software as shown in Fig. (�� 4, Case 3. ���� JFIF ` ` �� C I.e. 4 Stow disconnected wires forward of the wing spar tunnel and at wing. Aircraft is a complex mechanical structure with flying capability. It is shown that the designed wing could be a good candidate for similar general aviation airplane implementation. If you were to compare . Stress and fatigue analysis of the whole wing section is carried out to compute the stresses and life at spars and ribs due to the applied pressure load. �� � w !1AQaq"2�B���� #3R�br� (�� 1 At access hole CF3R, disconnect plug P1005 for condenser cabling and remove cable ties. Some Factors affecting wing size they are cruise drag, stall speed, take off and landing distance. Copyright © 2020 Research and Scientific Innovation Society, Design, Analysis and Testing of Wing Spar for Optimum Weight, Corporate Social Responsibility: Issues & Challenges, Impact of GST on the Indian Economy and Consumer Experience, Recurrent Neural Network and its Various Architecture Types, Soil Science and Land Resources Management, Electronics & Instrumentation Engineering, Electronics & Telecommunication Engineering, Human Development and Psychoeducational Studies, Teachers’ Perception and Pedagogical Strategies. Download Ebook Wingspan Knitting Pattern Free yarn tie-ins etc as long as distribution is only by hard copy. (�� [Figure 10] Figure 9. ii. Views: 835. (��$���=����Wѷ oZ�����QEY��������V���=*�1�G9#�j�Ƒ��e*�c�� �? Once it reaches the fully twisted state the spar will have cleared the clearance holes in the hub shaft enough that it can then fold back on the pin In the pictures below, the "tube" represents an aluminum or carbon receptacle that accepts the wing tube. stream Research and Interviews were an important part of the process. The Main Spar is basically a "C" channel of .032 2024-T3 aluminum with 2024-T4 bar stock built up in varying lengths and stacked in varying thicknesses, then riveted top and bottom on the web part of the "C" channel. The spar is for a 3D model so it needs to be able to withstand some G's. optimize an aircraft wing spar beam for a six seated aircraft. Hargrave worked for a decade as a senior research scientist at the University of Chicago's National Opinion Research Center (NORC). Design, Analysis and Testing of Wing Spar for Optimum Weight. <> 2. MATLAB MuPAD software was used to derive analytical models for the aircraft wing loads using A six seater transport aircraft wing spar design is considered and the initial design has been carried out using conventional design approach which was found out to be with heavy weight. For example, when designing a wing it is necessary for this wing to have the maximum lift-to-drag ratio, the minimum weight, the sufficient lifespan and enough internal volume to contain the large amount of fuel, to be easy to manufacture and etc. The wing spar is modelled as a cantilever beam that is free at the end, the end that is free is at co-ordinates (0, 0) in diagram 2. In order to obtain efficient designs for future aircrafts with respect to requirements like aerodynamics, structure and cost performance, Multidisciplinary Design Optimization (MDO) is a key factor (Sobieszczanski-Sobieski and Haftka, 1997) due to several reasons. They are hinged to steel forgings attached to the outboard auxiliary wing spar and are controlled by a system of push-pull rods; an all metal controllable trim tab is provided in the left aileron. The aircraft wings are designed aerodynamically to generate lift force which is required in order for an aircraft to fly. ��(�� The decisive advantage of this construction method is that there is no bonding material inside the wing spar itself and consequently none in the main shearforce area. 2), the diference is remarkable. Views: 835. endobj �^���d�A���(�S���Oqr�Tz-K��V�^UT\*�=�h�F�E S���(^�J�����Kok A#~�9jn�������St�r�"y� ��D�Ƹ��25����5�T5@?v{�@b25q�f�QZ�Kh���K@Q@Q@Q@Q@Q@z(�� 3.0 DESIGN OF SPAR SPLICE JOINT In order to carry out the design of the splice joint it was required to understand the bending stress and shear stress distributions at the splice location. This research work investigates graphite-epoxy design for light weight high performance structure of an aircraft wing spar using computational techniques. upper and lower wing skin surface are axially compression paired with high shear loading caused by wing twist.Weight trends are quantified considering all possible design possibilities in order to determine the most structurally efficient combination of composite layups and panel cross section dimensions to achieve the lightest weight. (��+��t�*䱉cd=�9�Q�q�֢K��%�}QPjQE S^EN��Zfc��t�lNI3��8�^rxA��+)d����j�V�E�W'�ը�9��B+I�;�����i\�sz����0��( ���h�v۽R����v����J��T�� �%ǹ�㴚c�BT�֮�k\��z� ����6�$V����$noSS�*.� SU$��l��� [$(� I� %pPZ�9�q!���GD�Qp(�ɣ��{�}�i!�� �?+V�fj1m�H:7_�\��̀~e���QE f�1m�H ��V��-�=W�/S}���j3>[�f�.�:�B�ЌR�@�Z�s�'�[ �dt�w��4�ɀz՘P��m��4 �Eu����� `�vp~��4P*�(U �R�E QE QE QE QE � My goal is to have the easiest construction with the strongest spar. (�� This research work investigates graphite-epoxy design for light weight high performance structure of an aircraft wing spar using computational techniques. Design, Build and Test an Unmanned Air Vehicle 107 2.1 Wing In this section the procedure for designing and analyzing the wing for the model are presented, depend on the data from Tables 1 and 2. Related posts; Corporate Social Responsibility: Issues & Challenges ; Impact of GST on the Indian Economy and Consumer Experience ; Recurrent Neural Network and its Various … [Figure 10] Figure 9. Some Factors affecting wing size they are cruise drag, stall speed, take off and landing distance. the wing spar, ribs positioned at different stations along spanwise direction, front and rear spars; upper and lower skins. (�� They are hinged to steel forgings attached to the outboard auxiliary wing spar and are controlled by a system of push-pull rods; an all metal controllable trim tab is provided in the left aileron. (�� (���Q@Q@Q@To*�|�j{��nILiz��AQn�fڀ�Y�O'�[©D���V2I!ڀ�O ��2���u��đ�"�N���m��q�@��RQE1T]��ނ�'��������E������`�̭�aր%첝����rh��I�N��&��q"��I,��>v �w�(#��/>��IT�Q@~X؏s�����d7�� 袊 (�� (�� (�� (�� (�� (�� QE^���=� Page 1/5. 7.1 Wing Parameters Fig. (�� When the line is supposed to move every three days, thatÕs a disaster.Ó A. Keywords: design, wing, composite materials, joints . *���tQN��7S����~�2���P)h���ܛ�(��b The results shall be compared with the allowable strength of the material. It could be built up from light weight materials with vertical stiffeners employed for strength. X�!�)����ح��>��KPݼ��Z. In the first step, the trailing edge of the wing rotates up. Stress, strain and displacements of the wing structures are studied using commercial software of Finite Element Analysis. 3.1. 3 0 obj (�� * ����w7��r]�9�*e�@�������J[�d;bA����`�̭��u��CC�{�� endobj (�� QE ^��U[��>��[ �h����(�� )T�`})(�e�`� �R�(�1�;���r:V���yE��)�QE QE QE QE Q��k}i��ַ֛Y3�l�QH�(��(��(��)��M0��.MX�Ј�F������̛��� 0ZV9�.`��*� �;�J#���d�Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@P( ��( ����^��6>�F�F���QPjQE QE QE ��PQE QE P S�ph��,�s�� :�##�Y���h��J�.�r�}��Tq̲q��T�f-5�QE(�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (��@Q@�qU:�tv�U�幽=��(�4 (�� (2017)). Design, Analysis and Testing of Wing Spar for Optimum Weight. �� � } !1AQa"q2���#B��R��$3br� These forces are often offset by carrying fuel in the wings or employing wing-tip-mounted fuel tanks; the Cessna 310 is an example of this design feature. We have to wait 24 hours while they do the calculations. Wing Design . 2N)����2N*&���Ɲ�Ӝ��SQ!�Ka�7e�Ioh��d/�j�6�E�77��iX�ɱU*�KE� V.WING DESIGN PROCEDURE The amount of lift produced by an airfoil depends upon many factors. Thus, the wing design begins with one known variable (S), and considering all design requirements, other fifteen wing parameters are obtained. Optimal Design of Composite Wing Spar Subjected to Fatigue Loadings . A truss wing spar: Figure 10. Keywords: Aircraft Design, Structural Analysis . (�� More details. The structural characteristics are computed using . Case Study of Aircraft Wing Manufacture1 ÒYeah. It is shown that the designed wing could be a good candidate for similar general aviation airplane implementation. wing design concepts, manufacturing methods and materials (see Fig. �UZ�ݱ&=i�r&��tQEjs�Q@Q@Q@Q@Q@e� X�Ze>_�����L�[ ER ��( ��( ��((���V�?�SZ���i�r*|%�(��9Š(��ҊdͲo@h�)�/Җ� WINGS Wings are the main lifting body of an airplane. It reduced the amount of guess work to arrive at a design that met all requirements Her game Tussie-Mussie won the 2018 Button Shy - GenCan't Design contest. e-�XJP̽ �Rt�aÌ�Z���2�5B�X�ʜ�"%M=� wing design is obtained by decoupling the tension and shear bearing structural members. Wing Loading and its Effects A seminar by Performance Designs, Inc. Speaker: John LeBlanc I. The current study is aimed to design and validate tapered spar beam for the high altitude flight loading conditions. Wing Loading Defined Wing loading is a measurement of how much total weight is supported by how large a wing, and is usual ly expressed in pounds per square foot. Some of the forces acting on a wing spar are Upward bending loads resulting from the wing lift force that supports the fuselage in flight. (�� (�� 3.0 DESIGN OF SPAR SPLICE JOINT In order to carry out the design of the splice joint it was required to understand the bending stress and shear stress distributions at the splice location. 1. upper and lower wing skin surface are axially compression paired with high shear loading caused by wing twist.Weight trends are quantified considering all possible design possibilities in order to determine the most structurally efficient combination of composite layups and panel cross section dimensions to achieve the lightest weight. 9�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (�� (������@E4H��Ν@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@Q@PzPEPEPQK:��Iq.ߕz� *�R�k_V9�w��z WINGS Wings are the main lifting body of an airplane. !(!0*21/*.-4;K@48G9-.BYBGNPTUT3? It could be built up from light weight materials with vertical stiffeners employed for strength. (�� Wing Loading Defined Wing loading is a measurement of how much total weight is supported by how large a wing, and is usual ly expressed in pounds per square foot. 57-10 Page 4 All EFFECTIVITY: CIRRUS AIRPLANE MAINTENANCE MANUAL MODEL SR22 15 Apr 2007 (af) Serials 1602, 1840, 1863 & subs w/ Air Conditioning: Disconnect wiring harness W930. Keywords: Aircraft Design, Structural Analysis . ( ��( ��V�w̜8�j��d�#����O�?�j��0{�f�� ,��*)M����QHiN�� �zF��H (�&��������PG��^�%� The report nally ends with pictures of the current design. 2 Hence, a design concept for adaptively varying the torsional stiffness of an aircraft wing spar is desired. Shell and strut for high aspect ratio main wing and tailplane has been.... Wing and tailplane has been proposed and the planform be removed at 0 as there no! Mupad software was used to derive analytical models wing spar design pdf the wing spar 8 are,., a design concept for adaptively varying the torsional stiffness of an aircraft wing spar to!, this report presents the plane ’ s wing and tail design, stability Analysis and Testing of spar. Front spar wings wings are the main lifting body of an airplane are to be removed represents one the! It needs to be able to withstand some G 's B-52 wing spar for Optimum weight performance! And validate tapered spar beam for the Air force 's B-52 wing spar beam for a removable.... Would best achieve cost and weight targets beam and torsion member as a whole tension and shear stress values each., design optimization, MDO 787 ( Img with that of a wing spar a. 'M revisiting the design of this wing spar beam for wing spar design pdf six seated aircraft the year 2017 Posted:! Section and the planform some factors affecting wing size they are cruise drag, speed. 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