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| author | hardythe1 | 2015-04-07 15:58:05 +0530 |
|---|---|---|
| committer | hardythe1 | 2015-04-07 15:58:05 +0530 |
| commit | 92cca121f959c6616e3da431c1e2d23c4fa5e886 (patch) | |
| tree | 205e68d0ce598ac5caca7de839a2934d746cce86 /Aircraft_Structures_for_Engineering_Students/Chapter14.ipynb | |
| parent | b14c13fcc6bb6d01c468805d612acb353ec168ac (diff) | |
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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 |