Structural Analysis of A310 Wing
Contents Objective:............................. Objective:................................................ ....................................... ........................................ ......................................... ........................... ...... 2 Methodology:.................. Methodology:...................................... ........................................ ........................................ .................................................... ................................ 2 Problem Problem Statement:.............................. Statement:.................................................. ........................................ ....................................... .............................. ........... 2 Assumptions:.................. Assumptions:...................................... ........................................ ........................................ ........................................ ............................. ......... 3 Project Project Flo:.................... Flo:........................................ ........................................ ........................................ ...................................... ............................... ............. 3 !ata "ollection:......................... "ollection:............................................. ....................................... ....................................... ......................................... ....................... # "A! Modeling Section:..................................... Section:........................................................ .................................................. ....................................... ........ $ Analysis:......................... Analysis:............................................. ........................................ ....................................... .................................................... ................................. % F&A Section 'or Structural Structural Analysis:.................................. Analysis:....................................................... ................................... ................. ...% % Problem Problem Speci(cation:......................... Speci(cation:............................................. ....................................... ............................................. ..........................% % Pre)Analysis Pre)Analysis and Start)*p:............................... Start)*p:.................................................. ....................................... .................................. .............. % Setup:................................ Setup:.................................................... ....................................... ....................................... .......................................... ......................++ ++ Future Future ,or-:.................................. or-:...................................................... ........................................ ....................................................... ................................... +2
Objective: he objective o' the project is to demonstrate a "A! model o' a ing structure and importing it to the A/S0S +# or-bench and then applying the necessary boundary conditions hich replicates the condition during the ta-e)o1 o' A3 aircra't normally 'rom any airport.
Methodology: he project o can be summari4ed in three stages. +. !ata "ollection: ,e need lot o' data 'or A3+ ing structure to create appro5imate model 'or aircra't ing. 2. "A! Modeling: ,e need to create "A! model o' ing using Solidor-s. he 'ull model consists o' ribs6'ront and a't spars and the s-in. 7arious design parameters are ta-en 'or Aircra't manual and various assumptions have been made. 3. Model Simulation: ,e ill import model into Ansys in order to place loads across the aircra't ing and identi'y the impact o' various loads on stress intensity 'actor. his F& model ill be optimi4ed and used 'urther 'or various types o' analysis such as thrust and other loads.
Proble Stateent: he ing structure e5perience various types o' loads during each phase o' the ight hich includes ta-e)o16 climb6 cruise6 loiter6 landing6 touch)don. ,e ill try to simpli'y our case study by analy4ing loads during ta-eo1. Since lot o' data is not available in the literature6 assumptions + ere made using A3 ing.
Assu!tions: +. Air'oil used in A3+ is supercritical air'oil so e are using /A"A 8#)2+$ air'oil throughout the ing structure. 2. he rib thic-ness is + mm6 hich is mirror e5tended 'rom its mean position. 3. he diameter o' the 'ront spar is 3 mm and it is placed at .2$ times the chord length at each section 'rom the leading edge. #. he diameter o' rear spar is 2$ mm and it is placed at .9 times the chord length at each section 'rom the leading edge. $. he centre point o' 'ront and rear spar at the tip air'oil is at a distance o' +2.$# m and +3.#8$ m 'rom the re'erence point respectively. 8. he 'ront spar is at 3+ 'rom the re'erence line hile the rear spar is at 23 'rom the re'erence line. + ;
M?&! ?/ @& PA<?A F*F?M&/ OF @& !&B<&& OF6 411023;C$=6 +D$%.
9. he holes are made in the ribs in order to save eight o' the structure. C. he material used 'or the hole structural and modal analysis purpose is aluminium alloy ith density o' 29 -gEm 36 young modulus o' 8C3 MPa6 and poisons ratio o' .3#. %. he boundary conditions applied to the F&A model is that the root section o' the air'oil as ell as the spars is (5ed so that the degree o' 'reedom is restricted in all the si5 directions. +.he loading condition is 'ound using the ma5imum ta-e)o1 eight and ma5imum climb angle hich is alloed 'or this aircra't 'rom any airport.
Project "lo#: o complete this project6 e ill 'ollo the 'olloing ochart to do the project in proper seGuence.
$ata Collection: Aircra't type model ,ing Area ;m 2= ,ing Span ;m= MA" ;m= Aspect
A3+)3 2+% #3.C% $.C% C.C .2C3 ++.C 2C.
Ma5. a5i ,eight ;-g= Ma5. a-eo1 eight ;-g= Ma5. anding ,eight ;-g= Ma5. Jero Fuel ,eight ;-g= &stimated Operational &mpty oad ;-g=
+$% +$ +23 ++3 9%888
,eight:
CA$ Modeling Section: he (rst step is to get the air'oil shape in !S Solidor-s. K!esign'oil so'tareL is used to create the air'oil shape by plotting all the co)ordinates in the Solidor-s part design or-bench. he main bene(t o' this so'tare is that all the co)ordinates are the 'unction o' the chord length6 that is ;5Ec6 yEc=. /A"A 8#2+$ air'oil6 ith the chord length o' 2.9C m6 is e5ported to S, part design (le. Since e have one air'oil6 it has to be scaled don accordingly to get reGuired shape o' the ing. As mid ing span is 2+.%$ m6 e divide the air'oil in 22 sections each placed at + m interval. he diameter o' the 'uselage is $.8# m. Some part o' the ing ill be inside 'uselage and it ill be completely (5ed due to its ing bo5 design. he section hich is completely rigid is 2.C2m. From the section placed at distance o' 2.C2 m 'rom the re'erence plane6 the air'oil shape is scaled appropriately to get desired ing pro(le.
he above diagram shos the conceptual s-etch o' ing hich ill be created ith the help o' basic geometry. "alculation o' reGuired values: he 'ormula 'or calculating the distance o' leading edge point hose co)ordinate is ;6 = 'rom re'erence line + using similarities o' the triangle concept is given by6 0Ea+%.8E++.$# ,here6 0 distance o' a point on leading edge hose co)ordinates is ;6 = 'rom the re'erence line +. a distance o' the section 'rom the root chord So distance o' trailing edge point hose co)ordinate is ;6 = 'rom the re'erence line 2 is given by the 'ormula6 J b.tan ;2.+3$= ,here6 J distance o' a point on a trailing edge hose co)ordinate is ;6 = 'rom the re'erence line 2. b distance o' a section 'rom the tip chord up to section %. "alculation o' the local chord length can be done using the 'ormula6 c ++.$# N 2.9$ ) 0) J
"alculation o' local taper ratio is given by ocal taper ratio
local chordlength root chord length
he 'olloing values are 'ound ith the help o' geometry and trigonometry relations: Section /o.
ocal "hord ength c;m=
ocal taper ratio
+ 2 3 # $ 8 9 C % + ++ +2 +3 +# +$ +8 +9 +C +% 2 2+ 22
%.# %.# %.2%#+ C.9$3 C.++8$ 9.$299 8.%3% 8.3$2 $.98+# $.$+89 $.2%# $.9+2 #.C#C$ #.82$9 #.#3 #.+C2 3.%$9# 3.93#9 3.$+2 3.2C%2 3.88# 2.C#38
+ + .%CC9 .%28 .C83# .CC .93C+ .89$$ .8+2% .$C8C .$83+ .$3%# ..$+$9 .#%2 .#8C# .###9 .#2+ .3%93 .3938 .3#%% .3282 .32$+
!istance o' leading edge point 'rom the re'erence line+;m= 0 .+$% .8%#9 +.2C3$ +.C923 2.#8+ 3.#%C 3.83C8 #.229# #.C+8+ $.##% $.%%39 8.$C2$ 9.+9+2 9.98 C.3#CC C.%398 %.$283 +.++$+ +.93% ++.2%29
!istance o' trailing edge point 'rom the re'erence line2;m= J #.C% #.C% #.C% #.C% #.C% #.C% #.C% #.C% #.C% #.$#$% #.+9%% 3.C+3% 3.##9C 3.C+C 2.9+$C 2.3#%C +.%C3C +.8+99 +.2$+9 .CC$9 .+$39 .$3#
?n the ire'rame and sur'ace design or-bench6 the sur'ace 'or the 'olloing sections has been generated accordingly.
&ach section is padded $ mm mirror e5tended so that the air'oil section is converted into the rib section ith a thic-ness o' + mm. he spars and holes are being created in the ing design as per our assumptions respectively. he complete design o' the ing structure ill be as shon belo6
Analysis: "%A Section for Structural Analysis: Proble S!eci&cation: ?n static structural analysis e are interested in the total de'ormation6 7on Misses stress hich is also -non as eGuivalent stress6 shear stress and stress intensity induced in the s-in structure o' the ing. Pre'Analysis and Start'(!: O!en A)S*S Wor+bench ,e are ready to do a simulation in A/S0S ,or-bench. Open A/S0S ,or-bench by going to Start , A)S*S , Wor+bench . o begin6 e need to tell A/S0S hat -ind o' simulation e are doing. ?' you loo- to the le't o' the startup indo6 you ill see the oolbo5 ,indo. a-e a loo- through the di1erent selections. >ecause e are only doing a 'orce loading6 e ill be doing a Static Structural simulation. oad the Static Structural tool bo5 by dragging and dropping it into the Project Schematic. /ame the Project ,ing structure by doubling clic-ing Static Structural ;A/S0S= underneath the project schematic.
-eoetry ?n ,or-bench in the Project Scheatic indo6 go to "ile , .!ort. ?n the .!ort indo that opens6 change the (le type ;ne5t to the File /ame te5t bo5= to Beometry File. Select the donloaded geometry (le and press Open.
-enerate the -eoetry /e5t6 e ill open the (le to generate the geometry. !ouble clic- the imported geometry to open the !esign Modeler. ,hen the !esign Modeler opens6 a pop up indo ill as- us 'or the de'ault units o' measurement 'or the geometry. Select Meter and then press OQ. A'ter you select the units6 you ill notice the -ra!hics indo is empty. ,e ill (5 this soon. First6 clic- on in the Outline indo. ?n the $etails indo6 change Operation 'rom Add Material to Add Fro4en. Finally6 generate the part by clic-ing once you press6 the imported geometry should sho in the -ra!hics indo.
Connect the -eoetry /e5t6 e need to connect the geometry to our current project. "lose the !esign Modeler and return to the project schematic. First clic- ;and hold= on the imported
geometry bo5 !rag and drop on. ,hen you are (nished6 a line should connect the to bo5es shoing that you have success'ully lin-ed them. /o that the geometry is imported and generated6 e are ready to mesh the geometry.
Mesh ?nitial Setup "lose the !esign Modeler i' you havenRt already6 and open A/S0S Mechanical by double clic-ing ,hen A/S0S Mechanical opens6 notice that there is a Guestion marne5t to Beometry in the Project Outline ) this means that there is something missing in this section. &5pand Beometry6 e5pand Part and select Outer Sur'ace. /otice that hic-ness is highlighted as it does not have a value speci(ed. ,e ill speci'y a thic-ness so the geometry ill mesh correctly. For the Outer Sur'ace6 enter +e)2 ne5t to hic-ness.
/ody Siing For this geometry6 e ill be using a body si4ing. "lic- on Mesh in the Project Outline indo to open up the Meshing Menu in the menu bar. o create a ne si4ing6 go to Mesh "ontrol Si4ing. /e5t6 e need to select the geometry that the si4ing ill a1ect. ,e ant to select the entire geometry.
Ma!!ed "ace Meshing o apply a mapped 'ace meshing6 (rst clic- on Mesh in the Outline indo. his ill bring up the Meshing Menu >ar at the top o' the screen. /e5t6 select Mesh "ontrol Mapped Face Meshing. Select the 2 'aces o' the mesh by holding don the le't mouse button and dragging over the entire geometry. ?n the !etails indo6 clicBeometry Apply ) it should say 2 'aces are selected.
%dge Siing ?n the Meshing Menu6 clic- Meshing "ontrol Si4ing. "lic- the edge selection (lter. Select the # curved edges on the outside o' the geometry that ma-e up the shape o' the /A"A 8#2+$ Air'oil as the picture shos:
?n the details indo6 select Beometry Apply6 and select ype /umber o' !ivisions. "hange the /umber o' !ivisions to 2. Also6 change >ehavior @ard. /e5t6 create another &dge Si4ing6 and this time6 select the 2 edges at the very 'ront and very bac- o' the air'oil that run along the ingspan6 as the picture shos:
Again6 in the !etails indo change the settings such that ype /umber o' !ivisions and >ehavior @ard. his time6 change the /umber o' !ivisions to #. Benerate the mesh by selecting Mesh Benerate Mesh
Setu!: A'ter setting up analysis type to structural and importing part into Ansys or-bench6 e ill setup simulation. Fi5ed Support: /e5t6 e ill apply the boundary conditions to the geometry. ?n the graphics indo6 clic- the positive J)A5is on the compass to loo- at one side o' the air'oil. Pressure oad: ,e ant to apply a +8C /Em 2 upard 'orce on the ing. Select oads Force to initiali4e a pressure load. he pressure load is determined by the calculating the load 'actor 'rom the Arccosine o' +9. he ma5imum climb angle 'or A3 'rom any airport is +9. 1
n
( ) +.#$8%
Arccosin e 17
he ma5imum ta-e)o1 eight o' A3+)3 < is around +$6 -g From the basic aerodynamics6 i't 'orce load 'actor T eight o' an aircra't. As e are interested to calculate the structural parameters during ta-e)o1 and climbing phase6 li't must be greater than eight o' an aircra't. hus the total li't 'orce reGuired to climb through +96 the aircra't should be able to generate the li't 'orce +$8C.$ -/. his is the total li't hich has to be generated by the sets o' its ing.
hus the 'orce developed by each ing is 9C#.3 -/. his 'orce is converted into the pressure load6 hich is in the 'orm o' uni'ormly distributed load by dividing this 'orce by the semi ing area o' +%.$ m 2. here'ore6 the total pressure load applied 'rom the bottom o' the sur'ace is 9+82.$8 Pa. ,hen the sur'aces have been selected6 press Beometry Apply in the !etails indo. /e5t6 select !e(ne >y "omponents. !e(ne the 0 "omponent as 9+82.$8 Pa. ,e are no ready to set up the solution and solve.
"uture Wor+: he stress intensity 'actors calculated are based on various assumptions due to inadeGuate data. Assumptions: +. he ing pro(le o' A3+ is similar to A3. he ing pro(le 'or A3+ ill be calculated using 'ormulas given in the report. he current ing data is 'or A3 ing. 2. he pro(le o' A3+ hich include design o' ing spar and ribs is similar to A3. Actual ing design o' A3+ ill be used 'or ne design 3. he pressure load due to li't has been considered. ocali4ed 'orce ill be reGuired 'or 'urther or- on determining stress on rivets.
eferences: +. ;M?&! ?/ @& PA<?A F*F?M&/ OF @& !&B<&& OF6 411023;C$=6 +D$%.
