From 41f1f72e9502f5c3de6ca16b303803dfcf1df594 Mon Sep 17 00:00:00 2001 From: Thomas Stephen Lee Date: Fri, 4 Sep 2015 22:04:10 +0530 Subject: add/remove/update books --- .../Chapter14.ipynb | 226 --------------------- 1 file changed, 226 deletions(-) delete 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 deleted file mode 100755 index f9eb3f9d..00000000 --- a/Aircraft_Structures_for_Engineering_Students/Chapter14.ipynb +++ /dev/null @@ -1,226 +0,0 @@ -{ - "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