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Diffstat (limited to 'Aircraft_Structures_for_Engineering_Students/Chapter14.ipynb')
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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": {}
- }
- ]
-}
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