taken load constrained rigid shown 46158 substituting elasticity interesting estimate iered irmation excitation appropriate density source 1ie' minimized U5 show quantify a4uliiz4 even a3u3 involve 7929 9197 sting FREE 46607 etc SHIFT primarily APPENDIX compromise substantial choosing INTERCONNECTED wa set 2'8019 missile 128 bring lid both 1946' tt1o prior mainly interconnected 9954 6748 significantly maximization nodal denoted simulation resifonse third ROD 47711 SUPPORT clamped academic approach self absence aii closely transcendental higher pjaj OO8 31374 lireg dynamic area equation frec aerodynamic stiffnes modelling exist INTRODUCTION azj necessary natural four introduce investigated affected individual simple differentiation FORMULATION ELASTICALLY commonly expected pre a2u2 bangalore many UI numerical considerably tperl act way 129 U4 124 predominating 42059 LOCATION presented symposium 2remain ovld combination axial parameter away MODEL investigate unsteady increase joshi fei imerference tiui1s frjee rod possible 6512 length oscillating understand resemble under frequencie azi earlier differential 2022 7758 determined KJ launchvehicle motion angle comribution 0751 end theory 74068 satisfy m11 particular than Z3 8414 POINTS reduction technology siiffnes follow stra zero aeroelastic ncie resistance modelof practice order following gust anq vibration difference sure strongly respectively 1968the conclusion 2A096 actual m33 flexural generally changed '1j stiffnesse RESULTS IN characteristic 2499 2096 ojfe5t trend 9027 any SOLUTION more a2u september most 'od 6364 2526 slender hat onjunction measurement cantilevered again relevant ''''' much part flight assessing fact seen only l'o structural JOSH aul 119 strong OF approache INERTIA into seven good poao dependent solved translational junction avoidsimultaneousexcitation probably 0022 increasing 1436 come loj l22 paper uniform almost vibrationbulletin value contain displacement twelve f'jt icientify negligible L4 august llx leaving 46765 some function EFFECTS REFERENCES constant respect non uffet location launching pav inside likely negligibly aeroelastically elastic steady necessarily variation substitution IV shift mind Z1 bending 41985 fohow studying know 5vpport behaviour variou lower aracteristic specific LJPADHYA deflection design studie ideally other term AHS turbulence another understandaable view 125 VARIOUS normalized r1f1 launch arameter 4659 stres BOUNDARYCONDITIONS 1986 orthe broken ivei1 choice inadequate well potential concentrated EJ slructure en' stif governing 48079 pres JOSHI beam figure9 decide indicating suitable 5860 dayton mii JONES deciding 118 form give ijl equilibrium figure node being NUMERICAL preset may 36719 different stiffer shqck thu examination marginal number CHEN error now 16971 produce proved identical their scale best aeaod therefore 55239 pressure far suffix also sound related but too over largely induce ooe assume correspond matrix subjected include ha 126 tl1ere ordinate '2r coming based alizing greater tbe such shape unaffected vce A7 example discussed iizl turbulent time cylindrical quantitie shortly comparatively geometry 55589 prone coupling idealized complex trivial represent 871 achieve nertia separation gradual meter HANSON1963 useful alter E1 use secl2 excepting encie suitably conference mentioned typical 3'1576 appropriately observed buffeting mean kit simultaneou significantamount rlu2 iusion range lriao dictated effect fizdui BEA absent merge 127 3'9990 ljpadhya constraint eolo practical a2u3 reduce studied iflatiog presence type note nature supported there keeping signified certain ST1FFNESS directly amount arising CONCLUSIONS 136 116 few pjo reverse should a'nd predominantly applying arriving KI mention 2108 KL resulting n4ghgible coefficient index 198324th eocrgy known aimed fi1i mjj line similarity result solution adversely detail dominantly need tl'i a2i bserved interaction vpled indicated 006 although STIFFNESSES important iteot comparison all j1t1y transverse practically total support inertia itself content pled marginallyaffected continuity altered closenes 2059 prototype revised airflow specify isvalue appendix buffet curvature significant liate 987 jijl VJ 46748m22 attributed designed predict arrive coincide ljaj c27 slope fairly traint 117 contributing homogeneou AIAA sinh 460X satisfied ajzj sufficientseparation consisting 160115 stifines COUPLING substantially ml1 reasonably moment energy system ohio 3494 intermediate shifting bly model static national 'get ith upport explain 560017 similarly gly study affect unchanged case slight observation contradiction 1963 1987 cartesian OO6 008 6168 predominanuy a2ui realm representing yield dimensionalization formulation evident examine guideline nodel 48815 rocket large couple freq relatively KI' attempt boundary deformation force EFFECT become phenomenon deform ia2u ent eilf consideration rodmode propertie operator resuit comparable might tend 49756 iittle vpport corresponding SDM shear TITAN second october cros cou whether noticeabiy three LIN reference prediction saturn two arbitrary each damping frequenciesin nomenclature unaltered it weight full excited 121 close limit A4 block however testing LJ determinant ZI one minimum restraint laboratory considered 42097 tel UPADHYA perhap direction wind will lce A1 cause quite very K1 problem avoid m22 component percent exactly thereby lix dimensionles bringing journal till nes then ger pa1sf segment BEAMS dovm a3u interference iso connected elementary 1622 predominantlysecondsupport pport increased six spacecraft tjx 0'2 NASA 3534 differentiate similar VIBRATION pajm indicate same free L0 HANSON L2L optimum erroneou ofthe here EIJ raised given ensure yet analysi separate rewritten 130 krlo ASME offset between MODAL 6786 though m22i attack influenced atmospheric trial offer doe pattern fully modal determination 115 dividuaj lof body path dimension ing ndia 122 normally AV fourth CONDITIONS 33691 clearly 45458 written limited dimensio'nles AJ versu obtained 6138 response because condition 0928 configuration level 'f1tat vehicle coupled cantilever NOMENCLATURE recalled DOGGE harmonic done frequency sectional spring JJ minima idea ASCE 40688 decrease slightly experimental equal II U3 L1 used 7460 true mji when ground reached reveal solid mode aeronautical base jth change amoun influence A2 freqeuncy rotational JI elastically superscript tated unknown adjusted denote point hand performance flow 6763 small found 7158 UCHIYAMA masse achieving DOGGETJR low pure through while theoretical fluctuation minimize impossible suffixj linear generalized Z2 simplified finally JUNCTION 8416 PETERS 50915 mil purpose 1965 present see cosh 2713 co pose eijm JR TN common difficultie either l1x noticeably e2ii mas general maximum receiued flexible five closer list out to' stage consist EI tunnel en balance scaled ergy at2 conjunction lily manifest 11one contribution sin lessthe ictua around avoided along not ijzih remain circular division drop 123 reduced remained pair high first overall stilfnes' structure