From 92cca121f959c6616e3da431c1e2d23c4fa5e886 Mon Sep 17 00:00:00 2001 From: hardythe1 Date: Tue, 7 Apr 2015 15:58:05 +0530 Subject: added books --- .../Chapter14.ipynb | 226 +++++++++++++++++++++ 1 file changed, 226 insertions(+) create mode 100755 Aircraft_Structures_for_Engineering_Students/Chapter14.ipynb (limited to 'Aircraft_Structures_for_Engineering_Students/Chapter14.ipynb') diff --git a/Aircraft_Structures_for_Engineering_Students/Chapter14.ipynb b/Aircraft_Structures_for_Engineering_Students/Chapter14.ipynb new file mode 100755 index 00000000..f9eb3f9d --- /dev/null +++ b/Aircraft_Structures_for_Engineering_Students/Chapter14.ipynb @@ -0,0 +1,226 @@ +{ + "metadata": { + "name": "", + "signature": "sha256:b89c31a3eb13c71dc64b90ec9c5fad56707d91451229ae687a102dc5e6c2ee23" + }, + "nbformat": 3, + "nbformat_minor": 0, + "worksheets": [ + { + "cells": [ + { + "cell_type": "heading", + "level": 1, + "metadata": {}, + "source": [ + "Chapter 14: Airframe loads" + ] + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 14.1 Pg.No.407" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "from __future__ import division\n", + "import math\n", + "\n", + "W=45 #weight of aircraft (kN)\n", + "m=45/9.8 #mass of aircraft(k-kg)\n", + "a=3*9.8 #deceleration due to cable (ms^-2)\n", + "m1=4.5/9.8 #weight of aircraft after AA in Diagram (k-kg)\n", + "v0=25 #touch down speed (m/s)\n", + "alpha=10 #center line angle with ground (degree)\n", + "\n", + "T=m*a/math.cos(math.radians(alpha))\n", + "print \"tension in cable = %3.1f kN\\n\"%(T)\n", + "\n", + "R=W+T*math.sin(math.radians(alpha))\n", + "print \"load on each undercarriage strut = %2.1f kN\\n\"%(R/2/math.cos(math.radians(20)))\n", + "\n", + "N=T+m1*9.8*math.sin(math.radians(alpha))-m1*a*math.cos(math.radians(alpha))\n", + "S=m1*a*math.sin(math.radians(alpha))+m1*9.8*math.cos(math.radians(alpha))\n", + "print \"N and S forces are shown in Fig 14.4 N=%2.2f kN S=%2.2f kN\\n\"%(N,S)\n", + "\n", + "s=v0**2/2/a\n", + "print \"length of deck covered = %2.2f m\\n\"%(s)" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "tension in cable = 137.1 kN\n", + "\n", + "load on each undercarriage strut = 36.6 kN\n", + "\n", + "N and S forces are shown in Fig 14.4 N=124.57 kN S=6.78 kN\n", + "\n", + "length of deck covered = 10.63 m\n", + "\n" + ] + } + ], + "prompt_number": 10 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 14.2 Pg.No.409" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "from __future__ import division\n", + "import math\n", + "\n", + "g=9.8\n", + "W=250 #weight of aircraft(kN)\n", + "m=250/g #mass of aircraft (K-kg)\n", + "I_CG=5.65*10**8 #inertia about center of mass(N.s^2.mm)\n", + "v0=3.7 #vertical velocity of undercarriage(m/s)\n", + "R_h=400 #horizontal reaction (kN)\n", + "R_v=1200 #vertical reaction (kN)\n", + "l=1 # nose wheel distance from ground (m)\n", + "d=2.5 # distance of CG from ground (m)\n", + "\n", + "#horizontal equilibrium\n", + "ax=R_h/m\n", + "\n", + "#vertical equilibrium\n", + "ay=(R_v-W)/m\n", + "\n", + "\n", + "alpha=(R_v*l+R_h*d)*10**6/I_CG\n", + "print \"angular acceleration of aircraft = %2.1f rad/s^2 \\n\"%(alpha)\n", + "\n", + "#v=v0+ay*t\n", + "t=v0/ay\n", + "print \"time taken for vertical velocity to become zero = %1.3f s\\n\"%(t)\n", + "\n", + "#w=w0+a*t\n", + "w=a*t\n", + "print \"angular velocity of aircraft = %1.2f rad/s \\n\"%(w)" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "angular acceleration of aircraft = 3.9 rad/s^2 \n", + "\n", + "time taken for vertical velocity to become zero = 0.099 s\n", + "\n", + "angular velocity of aircraft = 0.39 rad/s \n", + "\n" + ] + } + ], + "prompt_number": 20 + }, + { + "cell_type": "heading", + "level": 2, + "metadata": {}, + "source": [ + "Example 14.3 Pg.No.414" + ] + }, + { + "cell_type": "code", + "collapsed": false, + "input": [ + "from __future__ import division\n", + "import math\n", + "\n", + "W=8000 #weight of aircraft (N)\n", + "n=4.5 # wing loading\n", + "S=14.5 #wing area (m^2)\n", + "V=60 #speed (m/s)\n", + "rho=1.223 #density (kg/m^3)\n", + "alpha=13.75 #from Fig 14.8 (a)\n", + "C_Mcg=0.075 #from Fig 14.8 (a)\n", + "c=1.35 #mean chord (m)\n", + "\n", + "\n", + "L=n*W\n", + "C_L=L/(0.5*rho*V**2*S)\n", + "print \"lift coefficient of aircraft = %1.3f \\n\"%(C_L)\n", + "\n", + "#from Fig 14.8 (b)\n", + "l=4.18*math.cos(math.radians(alpha-2))+0.31*math.sin(math.radians(alpha-2))\n", + "print \"length of tail arm = %1.3f m \\n\"%(l)\n", + "\n", + "\n", + "C_L=C_L-c/l*C_Mcg\n", + "print \"lift coefficient =%1.3f \\n\"%(C_L)\n", + "\n", + "alpha=13.3\n", + "l=4.18*math.cos(math.radians(alpha-2))+0.31*math.sin(math.radians(alpha-2))\n", + "print \"Now tail arm length = %2.3f m\\n\"%(l)\n", + "\n", + "L=0.5*rho*V**2*S*C_L\n", + "print \"Lift = %5.1f N\\n\"%(L)\n", + "\n", + "P=n*W-35000\n", + "print \"Tail Load = %5.1f N\\n\"%(P)\n", + "\n", + "D=0.5*rho*V**2*S*0.0875\n", + "print \"Drag = %5.1f N\\n\"%(D)\n", + "print \"Forward inertia force = %5.1f N\\n\"%(D) #eqn 14.13" + ], + "language": "python", + "metadata": {}, + "outputs": [ + { + "output_type": "stream", + "stream": "stdout", + "text": [ + "lift coefficient of aircraft = 1.128 \n", + "\n", + "length of tail arm = 4.156 m \n", + "\n", + "lift coefficient =1.103 \n", + "\n", + "Now tail arm length = 4.160 m\n", + "\n", + "Lift = 35222.3 N\n", + "\n", + "Tail Load = 1000.0 N\n", + "\n", + "Drag = 2793.0 N\n", + "\n", + "Forward inertia force = 2793.0 N\n", + "\n" + ] + } + ], + "prompt_number": 31 + }, + { + "cell_type": "code", + "collapsed": false, + "input": [], + "language": "python", + "metadata": {}, + "outputs": [] + } + ], + "metadata": {} + } + ] +} \ No newline at end of file -- cgit