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Steven Izzo 2/7/2008 Structures Buckling Analysis Function for Stages with help from Brandon White

Steven Izzo 2/7/2008 Structures Buckling Analysis Function for Stages with help from Brandon White. Inputs Masses Nose Cone, Avionics, Payload, Fuel, Oxidizer, Tanks, Engine Dimensions Length, Diameter, Thickness Material Same values used in tank code by Steven Hiu Function Features

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Steven Izzo 2/7/2008 Structures Buckling Analysis Function for Stages with help from Brandon White

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  1. Steven Izzo2/7/2008StructuresBuckling Analysis Function for Stageswith help from Brandon White AAE 450 Spring 2008

  2. Inputs • Masses • Nose Cone, Avionics, Payload, Fuel, Oxidizer, Tanks, Engine • Dimensions • Length, Diameter, Thickness • Material • Same values used in tank code by Steven Hiu Function Features • Euler Buckling Load • Applied Load 2G’s • Add up masses Outputs • Required number of support rings • Total mass for next stage/skirt AAE 450 Spring 2008 Structures

  3. Results • Ran for several cases based on model analysis code • Little to no extra support needed for buckling. Future Work • Incorporate with other structures codes. • Mass, Sizing, Load/Stress, Cost AAE 450 Spring 2008 Structures

  4. Code pg.1 %Buckling Analysis Function for Stages %Created by Steve Izzo with help from Brandon White %Inputs: % mat- material for each stage tank section % d- diameter % t- thickness % L- length % m_ox- mass of oxidizer % m_fuel- mas of fuel % m_tank_ox- oxidizer tank mass % m_tank_fuel- fuel tank mass % m_engine- engine mass % m_above- total mass of above tank section %Outputs: % num_rings- number of required support rings required for structure % m_total- total mass of structure to be inputted for lower skirts and stages AAE 450 Spring 2008 Structures

  5. Code pg.2 function [num_rings,m_total] = stress1(mat,d,t,L,m_ox,m_fuel,m_tank_ox,m_tank_fuel,m_engine,m_above) %get material data %same data used as tank function by Steven Hiu if mat== 'S' %Steel 17-4PH E= 196.5E9; %Young's Modulus, Pa elseif mat== 'A' %Aluminum 7075 E= 67.9E9; elseif mat== 'T' %Titanium Ti-5Al-2.55Sn E= 109E9; elseif mat== 'C' %Carbon Fiber Composite E= 150E9; end %calculate critical buckling load I= .25*pi*(d*.5)^4-.25*pi*(d*.5-t)^4; num_rings=1; load_cr= pi^2*E*I/((L/num_rings)^2); AAE 450 Spring 2008

  6. Code pg.3 %calculate applied load gload= 2*9.80665; %assume acceleration is 2g's load_ap=gload*m_above; %compare stresses, add appropriate number of rings while load_ap> load_cr; num_rings= num_rings+1; load_cr= pi^2*E*I/((L/num_rings)^2); end num_rings= num_rings-1; %total up masses for next skirt/stage m_total= m_above+m_ox+m_fuel+m_tank_ox+m_tank_fuel+m_engine; return AAE 450 Spring 2008

  7. Sources • Bedford, A, Fowler, W, Liechti, K. Statics and Mechanics of Materials, Prentice Hall, Englewood Cliffs, NJ, 2002. • Function “Tanks.m” by Steven Hiu AAE 450 Spring 2008

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