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Diffstat (limited to 'wing_scripts/my_progress.m')
| -rw-r--r-- | wing_scripts/my_progress.m | 459 |
1 files changed, 0 insertions, 459 deletions
diff --git a/wing_scripts/my_progress.m b/wing_scripts/my_progress.m deleted file mode 100644 index e87ef23..0000000 --- a/wing_scripts/my_progress.m +++ /dev/null @@ -1,459 +0,0 @@ -%wing shear flow -clear all; -close all; - -Vx = 1; Vz = 1; My = 1; %test loads will be applied individually - - -%Ixz = -Ixz; - -%define webs - -%% web cell 1 - -%upper webs -numStringers = numTopStringers; -stringerGap = upperStringerGap; -webThickness = t_upper; -tempStringers = topStringers; - -for i=1:(numStringers+1) - web(i).xStart = sparCaps(1).posX + stringerGap*(i-1); - web(i).xEnd = sparCaps(1).posX + stringerGap*(i); - web(i).thickness = webThickness; - web(i).zStart = get_z(web(i).xStart/chord,1)*chord; - web(i).zEnd = get_z(web(i).xEnd/chord,1)*chord; - if i==1 - web(i).dp_area = sparCaps(1).area; - web(i).dP_X = 0; - web(i).dP_Z = 0; - web(i).qPrime_X = 0; - web(i).qPrime_Z = 0; - else - web(i).dp_area = tempStringers(i-1).area; - dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ; - web(i).dP_X = get_dp(dx,dz,Vx,0,Ix,Iz,Ixz,web(i).dp_area); %just Vx - web(i).dP_Z = get_dp(dx,dz,0,Vz,Ix,Iz,Ixz,web(i).dp_area); %just Vz - web(i).qPrime_X = web(i-1).qPrime_X - web(i).dP_X; - web(i).qPrime_Z = web(i-1).qPrime_Z - web(i).dP_Z; - end - tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil function - triangle1 = abs( (web(i).xStart - sparCaps(1).posX)*web(i).zStart/2); - triangle2 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2); - web(i).Area = tempInt + triangle1 - triangle2; - web(i).ds = get_ds(web(i).xStart/chord,web(i).xEnd/chord,1)*chord; - web(i).dS_over_t = web(i).ds / web(i).thickness; - - web(i).q_dS_over_t_X = web(i).qPrime_X * web(i).dS_over_t; - web(i).q_dS_over_t_Z = web(i).qPrime_Z * web(i).dS_over_t; - web(i).two_A_qprime_X = 2*web(i).Area*web(i).qPrime_X; - web(i).two_A_qprime_Z = 2*web(i).Area*web(i).qPrime_Z; - web(i).qp_dx_X = web(i).qPrime_X *(web(i).xEnd-web(i).xStart); - web(i).qp_dx_Z = web(i).qPrime_Z *(web(i).xEnd-web(i).xStart); - web(i).qp_dz_X = web(i).qPrime_X *(web(i).zEnd-web(i).zStart); - web(i).qp_dz_Z = web(i).qPrime_Z *(web(i).zEnd-web(i).zStart); -end -webTop = web; -web = []; - -%rear spar -i=1; -web(i).xStart = sparCaps(3).posX; -web(i).xEnd = sparCaps(4).posX; -web(i).thickness = t_rearSpar; -web(i).zStart = sparCaps(3).posZ; -web(i).zEnd = sparCaps(4).posZ; -web(i).dp_area = sparCaps(3).area; -dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ; -web(i).dP_X = get_dp(dx,dz,Vx,0,Ix,Iz,Ixz,web(i).dp_area); -web(i).dP_Z = get_dp(dx,dz,0,Vz,Ix,Iz,Ixz,web(i).dp_area); -web(i).qPrime_X = webTop(numTopStringers+1).qPrime_X - web(i).dP_X; -web(i).qPrime_Z = webTop(numTopStringers+1).qPrime_Z - web(i).dP_Z; - -web(i).Area = (sparCaps(3).posX-sparCaps(1).posX)*sparCaps(3).posZ/2 + ... - abs((sparCaps(3).posX-sparCaps(1).posX)*sparCaps(4).posZ/2); -web(i).ds = abs(sparCaps(3).posZ - sparCaps(4).posZ); -web(i).dS_over_t = web(i).ds / web(i).thickness; - -web(i).q_dS_over_t_X = web(i).qPrime_X * web(i).dS_over_t; -web(i).q_dS_over_t_Z = web(i).qPrime_Z * web(i).dS_over_t; -web(i).two_A_qprime_X = 2*web(i).Area*web(i).qPrime_X; -web(i).two_A_qprime_Z = 2*web(i).Area*web(i).qPrime_Z; -web(i).qp_dx_X = web(i).qPrime_X *(web(i).xEnd-web(i).xStart); -web(i).qp_dx_Z = web(i).qPrime_Z *(web(i).xEnd-web(i).xStart); -web(i).qp_dz_X = web(i).qPrime_X *(web(i).zEnd-web(i).zStart); -web(i).qp_dz_Z = web(i).qPrime_Z *(web(i).zEnd-web(i).zStart); - -webRearSpar = web; -web = []; - - -%lower webs -numStringers = numBottomStringers; -stringerGap = lowerStringerGap; -webThickness = t_lower; -tempStringers = bottomStringers; - -for i=1:(numStringers+1) - web(i).xStart = sparCaps(4).posX - stringerGap*(i-1); - web(i).xEnd = sparCaps(4).posX - stringerGap*(i); - web(i).thickness = webThickness; - web(i).zStart = get_z(web(i).xStart/chord,0)*chord; - web(i).zEnd = get_z(web(i).xEnd/chord,0)*chord; - dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ; - if i==1 - web(i).dp_area = sparCaps(4).area; - web(i).dP_X = get_dp(dx,dz,Vx,0,Ix,Iz,Ixz,web(i).dp_area); - web(i).dP_Z = get_dp(dx,dz,0,Vz,Ix,Iz,Ixz,web(i).dp_area); - web(i).qPrime_X = webRearSpar.qPrime_X - web(i).dP_X; - web(i).qPrime_Z = webRearSpar.qPrime_Z - web(i).dP_Z; - else - web(i).dp_area = tempStringers(i-1).area; - web(i).dP_X = get_dp(dx,dz, Vx,0,Ix,Iz,Ixz,web(i).dp_area); - web(i).dP_Z = get_dp(dx,dz, 0,Vz,Ix,Iz,Ixz,web(i).dp_area); - web(i).qPrime_X = web(i-1).qPrime_X - web(i).dP_X; - web(i).qPrime_Z = web(i-1).qPrime_Z - web(i).dP_Z; - end - - tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil function - triangle2 = abs((web(i).xStart - sparCaps(1).posX)*web(i).zStart/2); - triangle1 = abs((web(i).xEnd - sparCaps(1).posX)*web(i).zEnd/2); - web(i).Area = tempInt + triangle1 - triangle2; - web(i).ds = get_ds(web(i).xStart/chord,web(i).xEnd/chord,0)*chord; - web(i).dS_over_t = web(i).ds / web(i).thickness; - - web(i).q_dS_over_t_X = web(i).qPrime_X * web(i).dS_over_t; - web(i).q_dS_over_t_Z = web(i).qPrime_Z * web(i).dS_over_t; - web(i).two_A_qprime_X = 2*web(i).Area*web(i).qPrime_X; - web(i).two_A_qprime_Z = 2*web(i).Area*web(i).qPrime_Z; - web(i).qp_dx_X = web(i).qPrime_X*(web(i).xEnd-web(i).xStart); - web(i).qp_dx_Z = web(i).qPrime_Z*(web(i).xEnd-web(i).xStart); - web(i).qp_dz_X = web(i).qPrime_X*(web(i).zEnd-web(i).zStart); - web(i).qp_dz_Z = web(i).qPrime_Z*(web(i).zEnd-web(i).zStart); - - %web(i).radCurv = ... Example: get_curve(web(i).xStart,web(i).xEnd,1) -end -webBottom = web; -web = []; - -%front Spar -i=1; -web(i).xStart = sparCaps(2).posX; -web(i).xEnd = sparCaps(1).posX; -web(i).thickness = t_frontSpar; -web(i).zStart = sparCaps(2).posZ; -web(i).zEnd = sparCaps(1).posZ; -web(i).dp_area = sparCaps(2).area; -dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ; -web(i).dP_X = get_dp(dx,dz,Vx,0,Ix,Iz,Ixz,web(i).dp_area); -web(i).dP_Z = get_dp(dx,dz,0,Vz,Ix,Iz,Ixz,web(i).dp_area); -web(i).qPrime_X = webBottom(numBottomStringers+1).qPrime_X - web(i).dP_X; -web(i).qPrime_Z = webBottom(numBottomStringers+1).qPrime_Z - web(i).dP_Z; -web(i).Area = 0; -web(i).ds = abs(sparCaps(2).posZ - sparCaps(1).posZ); -web(i).dS_over_t = web(i).ds / web(i).thickness; - -web(i).q_dS_over_t_X = web(i).qPrime_X * web(i).dS_over_t; -web(i).q_dS_over_t_Z = web(i).qPrime_Z * web(i).dS_over_t; -web(i).two_A_qprime_X = 2*web(i).Area*web(i).qPrime_X; -web(i).two_A_qprime_Z = 2*web(i).Area*web(i).qPrime_Z; -web(i).qp_dx_X = web(i).qPrime_X *(web(i).xEnd-web(i).xStart); -web(i).qp_dx_Z = web(i).qPrime_Z *(web(i).xEnd-web(i).xStart); -web(i).qp_dz_X = web(i).qPrime_X *(web(i).zEnd-web(i).zStart); -web(i).qp_dz_Z = web(i).qPrime_Z *(web(i).zEnd-web(i).zStart); - -webFrontSpar = web; -web = []; - - - - -%% web cell 2 - -%lower nose webs -numStringers = numNoseBottomStringers; -stringerGap = lowerNoseStringerGap; -webThickness = t_lower_front; -tempStringers = noseBottomStringers; - -for i=1:(numStringers+1) - web(i).xStart = sparCaps(2).posX - stringerGap*(i-1); - web(i).xEnd = sparCaps(2).posX - stringerGap*(i); - web(i).thickness = webThickness; - web(i).zStart = get_z(web(i).xStart/chord,0)*chord; - web(i).zEnd = get_z(web(i).xEnd/chord,0)*chord; - dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ; - - if i==1 - web(i).dp_area = sparCaps(2).area; - web(i).dP_X = 0; - web(i).dP_Z = 0; - web(i).qPrime_X = 0; - web(i).qPrime_Z = 0; - else - web(i).dp_area = tempStringers(i-1).area; - web(i).dP_X = get_dp(dx,dz,Vx,0,Ix,Iz,Ixz,web(i).dp_area); - web(i).dP_Z = get_dp(dx,dz,0,Vz,Ix,Iz,Ixz,web(i).dp_area); - web(i).qPrime_X = web(i-1).qPrime_X - web(i).dP_X; - web(i).qPrime_Z = web(i-1).qPrime_Z - web(i).dP_Z; - end - tempInt = get_int(web(i).xEnd/chord,web(i).xStart/chord,0)*chord^2; %integral of airfoil function - triangle1 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2); - triangle2 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2); - web(i).Area = tempInt + triangle1 - triangle2; - web(i).ds = get_ds(web(i).xStart/chord,web(i).xEnd/chord,0)*chord; - web(i).dS_over_t = web(i).ds / web(i).thickness; - - web(i).q_dS_over_t_X = web(i).qPrime_X * web(i).dS_over_t; - web(i).q_dS_over_t_Z = web(i).qPrime_Z * web(i).dS_over_t; - web(i).two_A_qprime_X = 2*web(i).Area*web(i).qPrime_X; - web(i).two_A_qprime_Z = 2*web(i).Area*web(i).qPrime_Z; - web(i).qp_dx_X = web(i).qPrime_X *(web(i).xEnd-web(i).xStart); - web(i).qp_dx_Z = web(i).qPrime_Z *(web(i).xEnd-web(i).xStart); - web(i).qp_dz_X = web(i).qPrime_X *(web(i).zEnd-web(i).zStart); - web(i).qp_dz_Z = web(i).qPrime_Z *(web(i).zEnd-web(i).zStart); - - %web(i).radCurv = ... Example: get_curve(web(i).xStart,web(i).xEnd,1) -end -webLowerNose = web; -web = []; - -%upper nose webs -numStringers = numNoseTopStringers; -stringerGap = upperNoseStringerGap; -webThickness = t_upper_front; -tempStringers = noseTopStringers; - -for i=1:(numStringers+1) - web(i).xStart = stringerGap*(i-1); - web(i).xEnd = stringerGap*(i); - web(i).thickness = webThickness; - web(i).zStart = get_z(web(i).xStart/chord,1)*chord; - web(i).zEnd = get_z(web(i).xEnd/chord,1)*chord; - dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ; - if i==1 - web(i).dp_area = 0; - web(i).dP_X = 0; - web(i).dP_Z = 0; - web(i).qPrime_X = webLowerNose(numNoseBottomStringers+1).qPrime_X - web(i).dP_X; - web(i).qPrime_Z = webLowerNose(numNoseBottomStringers+1).qPrime_Z - web(i).dP_Z; - else - web(i).dp_area = tempStringers(i-1).area; - web(i).dP_X = get_dp(dx,dz,Vx,0,Ix,Iz,Ixz,web(i).dp_area); - web(i).dP_Z = get_dp(dx,dz,0,Vz,Ix,Iz,Ixz,web(i).dp_area); - web(i).qPrime_X = web(i-1).qPrime_X - web(i).dP_X; - web(i).qPrime_Z = web(i-1).qPrime_Z - web(i).dP_Z; - end - tempInt = get_int(web(i).xStart/chord,web(i).xEnd/chord,1)*chord^2; %integral of airfoil function - triangle2 = abs((web(i).xStart - sparCaps(2).posX)*web(i).zStart/2); - triangle1 = abs((web(i).xEnd - sparCaps(2).posX)*web(i).zEnd/2); - web(i).Area = tempInt + triangle1 - triangle2; - web(i).ds = get_ds(web(i).xStart/chord,web(i).xEnd/chord,1)*chord; - web(i).dS_over_t = web(i).ds / web(i).thickness; - - web(i).q_dS_over_t_X = web(i).qPrime_X * web(i).dS_over_t; - web(i).q_dS_over_t_Z = web(i).qPrime_Z * web(i).dS_over_t; - web(i).two_A_qprime_X = 2*web(i).Area*web(i).qPrime_X; - web(i).two_A_qprime_Z = 2*web(i).Area*web(i).qPrime_Z; - web(i).qp_dx_X = web(i).qPrime_X *(web(i).xEnd-web(i).xStart); - web(i).qp_dx_Z = web(i).qPrime_Z *(web(i).xEnd-web(i).xStart); - web(i).qp_dz_X = web(i).qPrime_X *(web(i).zEnd-web(i).zStart); - web(i).qp_dz_Z = web(i).qPrime_Z *(web(i).zEnd-web(i).zStart); - -end -webUpperNose = web; -web = []; - - -%front Spar -i=1; -web(i).xStart = sparCaps(1).posX; -web(i).xEnd = sparCaps(2).posX; -web(i).thickness = t_frontSpar; -web(i).zStart = sparCaps(1).posZ; -web(i).zEnd = sparCaps(2).posZ; -web(i).dp_area = sparCaps(1).area; -dx = web(i).xStart-centroid.posX; dz = web(i).zStart-centroid.posZ; - -web(i).dP_X = get_dp(dx,dz,Vx,0,Ix,Iz,Ixz,web(i).dp_area); -web(i).dP_Z = get_dp(dx,dz,0,Vz,Ix,Iz,Ixz,web(i).dp_area); -web(i).qPrime_X = webUpperNose(numNoseTopStringers+1).qPrime_X - web(i).dP_X; -web(i).qPrime_Z = webUpperNose(numNoseTopStringers+1).qPrime_Z - web(i).dP_Z; -web(i).Area = 0; -web(i).ds = abs(sparCaps(1).posZ - sparCaps(2).posZ); -web(i).dS_over_t = web(i).ds / web(i).thickness; -web(i).q_dS_over_t_X = web(i).qPrime_X * web(i).dS_over_t; -web(i).q_dS_over_t_Z = web(i).qPrime_Z * web(i).dS_over_t; -web(i).two_A_qprime_X = 2*web(i).Area*web(i).qPrime_X; -web(i).two_A_qprime_Z = 2*web(i).Area*web(i).qPrime_Z; -web(i).qp_dx_X = web(i).qPrime_X *(web(i).xEnd-web(i).xStart); -web(i).qp_dx_Z = web(i).qPrime_Z *(web(i).xEnd-web(i).xStart); -web(i).qp_dz_X = web(i).qPrime_X *(web(i).zEnd-web(i).zStart); -web(i).qp_dz_Z = web(i).qPrime_Z *(web(i).zEnd-web(i).zStart); - -webFrontSparCell2 = web; -web = []; - - -%check that q'*dx sums up to Vx - -Fx = sum([webTop.qp_dx_X])+webRearSpar.qp_dx_X+ sum([webBottom.qp_dx_X])+webFrontSpar.qp_dx_X; %cell 1 -Fx = Fx + sum([webLowerNose.qp_dx_X])+ sum([webUpperNose.qp_dx_X]); %cell 2 -Fx -Fz = sum([webTop.qp_dz_X])+webRearSpar.qp_dz_X+ sum([webBottom.qp_dz_X])+webFrontSpar.qp_dz_X; %cell 1 -Fz = Fz + sum([webLowerNose.qp_dz_X])+ sum([webUpperNose.qp_dz_X]); %cell 2 -Fz - -%check that q'*dz sums up to Vz - - -Fx = sum([webTop.qp_dx_Z])+webRearSpar.qp_dx_Z+ sum([webBottom.qp_dx_Z])+webFrontSpar.qp_dx_Z; %cell 1 -Fx = Fx + sum([webLowerNose.qp_dx_Z])+ sum([webUpperNose.qp_dx_Z]); %cell 2 -Fx -Fz = sum([webTop.qp_dz_Z])+webRearSpar.qp_dz_Z+ sum([webBottom.qp_dz_Z])+webFrontSpar.qp_dz_Z; %cell 1 -Fz = Fz + sum([webLowerNose.qp_dz_Z])+ sum([webUpperNose.qp_dz_Z]); %cell 2 -Fz - -%% - -% sum up the ds/t and q*ds/t to solve 2 equations, 2 unknowns - -% [A]*[q1s q2s] = B - -A11 = sum([webTop.dS_over_t])+webRearSpar.dS_over_t+ sum([webBottom.dS_over_t])+webFrontSpar.dS_over_t; -A22 = sum([webLowerNose.dS_over_t])+ sum([webUpperNose.dS_over_t])+webFrontSparCell2.dS_over_t; -A12 = -webFrontSpar.dS_over_t; -A21 = -webFrontSparCell2.dS_over_t; - -B1_X = sum([webTop.q_dS_over_t_X])+webRearSpar.q_dS_over_t_X+ sum([webBottom.q_dS_over_t_X])+webFrontSpar.q_dS_over_t_X; -B2_X = sum([webLowerNose.q_dS_over_t_X])+ sum([webUpperNose.q_dS_over_t_X])+webFrontSparCell2.q_dS_over_t_X; -B1_Z = sum([webTop.q_dS_over_t_Z])+webRearSpar.q_dS_over_t_Z+ sum([webBottom.q_dS_over_t_Z])+webFrontSpar.q_dS_over_t_Z; -B2_Z = sum([webLowerNose.q_dS_over_t_Z])+ sum([webUpperNose.q_dS_over_t_Z])+webFrontSparCell2.q_dS_over_t_Z; - -Amat = [A11 A12; A21 A22]; -Bmat_X = -[B1_X;B2_X]; -Bmat_Z = -[B1_Z;B2_Z]; - -qs_X = inv(Amat)*Bmat_X; -qs_Z = inv(Amat)*Bmat_Z; - - - -sum_2_a_q_X = sum([webTop.two_A_qprime_X])+webRearSpar.two_A_qprime_X+ sum([webBottom.two_A_qprime_X]); %cell 1 qprimes -sum_2_a_q_X = sum_2_a_q_X + sum([webLowerNose.two_A_qprime_X])+ sum([webUpperNose.two_A_qprime_X]); %cell 2 qprimes -sum_2_a_q_X = sum_2_a_q_X + 2*qs_X(1)*(sum([webTop.Area])+webRearSpar.Area+ sum([webBottom.Area])); -sum_2_a_q_X = sum_2_a_q_X + 2*qs_X(2)*(sum([webLowerNose.Area])+ sum([webUpperNose.Area])); - -sum_2_a_q_Z = sum([webTop.two_A_qprime_Z])+webRearSpar.two_A_qprime_Z+ sum([webBottom.two_A_qprime_Z]); %cell 1 qprimes -sum_2_a_q_Z = sum_2_a_q_Z + sum([webLowerNose.two_A_qprime_Z])+ sum([webUpperNose.two_A_qprime_Z]); %cell 2 qprimes -sum_2_a_q_Z = sum_2_a_q_Z + 2*qs_Z(1)*(sum([webTop.Area])+webRearSpar.Area+ sum([webBottom.Area])); -sum_2_a_q_Z = sum_2_a_q_Z + 2*qs_Z(2)*(sum([webLowerNose.Area])+ sum([webUpperNose.Area])); - -%shear center -sc.posX = sum_2_a_q_Z / Vz + frontSpar*chord; -sc.posZ = - sum_2_a_q_X / Vx; - - -% now consider the torque representing shifting the load from the quarter -% chord to the SC (need to check signs on these moments) - -torque_Z = Vz*(sc.posX - 0.25*chord); -torque_X = -Vx*sc.posZ; - - -Area1 = sum([webTop.Area]) + webRearSpar.Area + sum([webBottom.Area]); -%check area -Area1_check = get_int(frontSpar,backSpar,1)*chord^2 + get_int(frontSpar,backSpar,0)*chord^2; - -Area2 = sum([webLowerNose.Area]) + sum([webUpperNose.Area]); -Area2_check = get_int(0,frontSpar,1)*chord^2 + get_int(0,frontSpar,0)*chord^2; - - -%for twist equation (see excel spreadsheet example) - -q1t_over_q2t = (A22/Area2 + webFrontSpar.dS_over_t/Area1)/(A11/Area1 + webFrontSpar.dS_over_t/Area2); - -q2t = torque_X/(2*Area1*q1t_over_q2t + 2*Area2); -q1t = q2t*q1t_over_q2t; -qt_X = [q1t;q2t]; - -q2t = torque_Z/(2*Area1*q1t_over_q2t + 2*Area2); -q1t = q2t*q1t_over_q2t; -qt_Z = [q1t;q2t]; - - - -% --- - add up all shear flows: qtot = (qPrime + qs) + qt - - - - -%--- insert force balance to check total shear flows --- - -% --- -- - - -%end - -sc - - -%plotting airfoil cross-section - -xChord = 0:.01:1; -xChord = xChord*chord; -upperSurface = zeros(1,length(xChord)); -lowerSurface = zeros(1,length(xChord)); - -for i=1:length(xChord) - upperSurface(i) = get_z(xChord(i)/chord,1)*chord; - lowerSurface(i) = get_z(xChord(i)/chord,0)*chord; -end - -figure; hold on; axis equal; grid on; -%plot(xChord,z_camber,'-') -plot(xChord,upperSurface,'-k','linewidth',2) -plot(xChord,lowerSurface,'-k','linewidth',2) -plot([0 1],[0 0],'--k','linewidth',1) - - -for i = 1:length(webTop) - vecX = [frontSpar*chord webTop(i).xStart webTop(i).xEnd]; - vecZ = [0 webTop(i).zStart webTop(i).zEnd]; - fill(vecX,vecZ,[0.9 0.9 0.9]) -end - -for i = 1:length(webBottom) - vecX = [frontSpar*chord webBottom(i).xStart webBottom(i).xEnd]; - vecZ = [0 webBottom(i).zStart webBottom(i).zEnd]; - fill(vecX,vecZ,[0.9 0.9 0.9]) -end - -for i = 1:length(webUpperNose) - vecX = [frontSpar*chord webUpperNose(i).xStart webUpperNose(i).xEnd]; - vecZ = [0 webUpperNose(i).zStart webUpperNose(i).zEnd]; - fill(vecX,vecZ,[0.7 0.9 1.0]) -end - -for i = 1:length(webLowerNose) - vecX = [frontSpar*chord webLowerNose(i).xStart webLowerNose(i).xEnd]; - vecZ = [0 webLowerNose(i).zStart webLowerNose(i).zEnd]; - fill(vecX,vecZ,[0.7 0.9 1.0]) -end - - vecX = [frontSpar*chord sparCaps(3).posX sparCaps(4).posX]; - vecZ = [0 sparCaps(3).posZ sparCaps(4).posZ]; - fill(vecX,vecZ,[0.9 0.9 0.9]) - - -sparCapSize = 18; -stringerSize = 18; -plot([sparCaps(1).posX sparCaps(2).posX],[sparCaps(1).posZ sparCaps(2).posZ],'-k','linewidth',2) -plot([sparCaps(3).posX sparCaps(4).posX],[sparCaps(3).posZ sparCaps(4).posZ],'-k','linewidth',2) -plot([sparCaps.posX],[sparCaps.posZ],'.b','markersize',sparCapSize) -plot([topStringers.posX],[topStringers.posZ],'.r','markersize',stringerSize) -plot([bottomStringers.posX],[bottomStringers.posZ],'.r','markersize',stringerSize) -plot([noseTopStringers.posX],[noseTopStringers.posZ],'.r','markersize',stringerSize) -plot([noseBottomStringers.posX],[noseBottomStringers.posZ],'.r','markersize',stringerSize) -plot(centroid.posX,centroid.posZ,'.k','markerSize',18) -plot(sc.posX,sc.posZ,'.g','markersize',18) |