Removed Problem Statements Completely

1 files changed, 744 insertions, 745 deletions

diff --git a/Satellite_Communication/chapter_3.ipynb b/Satellite_Communication/chapter_3.ipynb
index e87eed02..b87a50b4 100644
--- a/Satellite_Communication/chapter_3.ipynb
+++ b/Satellite_Communication/chapter_3.ipynb
@@ -1,746 +1,745 @@
-{

- "metadata": {

-  "name": ""

- },

- "nbformat": 3,

- "nbformat_minor": 0,

- "worksheets": [

-  {

-   "cells": [

-    {

-     "cell_type": "heading",

-     "level": 1,

-     "metadata": {},

-     "source": [

-      "Chapter 3: Satellite Launch and In-Orbit Operations"

-     ]

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.1, page no-72"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "Az=85      # Azimuth angle of injection point\n",

-      "l=5.2      # latitude of launch site\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "cosi=math.sin(Az*math.pi/180)*math.cos(l*math.pi/180)\n",

-      "i=math.acos(cosi)\n",

-      "i=i*180.0/math.pi\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"Inclination angle attained, i=%.1f\u00b0\"%i)"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "Inclination angle attained, i=7.2\u00b0\n"

-       ]

-      }

-     ],

-     "prompt_number": 1

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.2, page no-73"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "delta_i=7     #orbital plane inclination\n",

-      "V=3000        #velocity of satellite in circularized orbit\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "vp=2*V*math.sin(delta_i*math.pi/(2*180))\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"Velocity thrust to make the inclination 0\u00b0 = %.0f m/s\"%vp)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "Velocity thrust to make the inclination 0\u00b0 = 366 m/s\n"

-       ]

-      }

-     ],

-     "prompt_number": 2

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.3, page no-73"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "\n",

-      "#Variable Declaration\n",

-      "mu=39.8*10**13          # Nm^2/kg\n",

-      "P=7000.0*10**3          # Perigee distance in m\n",

-      "e=0.69                  # eccentricity of eliptical orbit\n",

-      "w=60.0/2                # angle made by line joing centre of earth and perigee with the line of nodes\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "k=(e/math.sqrt(1+e))\n",

-      "k=math.floor(k*100)/100\n",

-      "v=2*(math.sqrt(mu/P))*k*math.sin(w*math.pi/180.0)\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"The velocity thrust required to rotate the perigee point\\n by desired amount is given by, v=%.1f m/s = %.3fkm/s\"%(v,v/1000.0))\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "The velocity thrust required to rotate the perigee point\n",

-        " by desired amount is given by, v=3996.4 m/s = 3.996km/s\n"

-       ]

-      }

-     ],

-     "prompt_number": 3

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.4, page no-74"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "A=15000*10**3            #Original apogee distance\n",

-      "A1=25000*10**3           # Raised opogee distance\n",

-      "P=7000*10**3             # Perigee Distance\n",

-      "mu=39.8*10**13           #Nm**2/kg\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "A_d=A1-A\n",

-      "v=math.sqrt((2*mu/P)-(2*mu/(A+P)))\n",

-      "del_v=A_d*mu/(v*(A+P)**2)\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"required Thrust velocity Delta_v = %.1f m/s\"%del_v)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "required Thrust velocity Delta_v = 933.9 m/s\n"

-       ]

-      }

-     ],

-     "prompt_number": 4

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.5, page no-75"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "A=15000.0*10**3            # Original apogee distance\n",

-      "A1=7000.0*10**3            # Raised opogee distance\n",

-      "P=7000.0*10**3             # Perigee Distance\n",

-      "mu=39.8*10**13             # Nm^2/kg\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "A_d=A-A1\n",

-      "v=math.sqrt((2*mu/P)-(2*mu/(A+P)))\n",

-      "del_v=A_d*mu/(v*(A+P)**2)\n",

-      "\n",

-      "#Result\n",

-      "print(\"required Thrust velocity Delta_v = %.1f m/s\"%del_v)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "required Thrust velocity Delta_v = 747.1 m/s\n"

-       ]

-      }

-     ],

-     "prompt_number": 5

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.6, page no-76"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "#Variable Declaration\n",

-      "A=15000.0*10**3            # Original apogee distance\n",

-      "A1=16000.0*10**3           # Raised opogee distance\n",

-      "P=7000.0*10**3             # Perigee Distance\n",

-      "mu=39.8*10**13           # Nm**2/kg\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "A_d=A1-A\n",

-      "v=math.sqrt((2*mu/P)-(2*mu/(A+P)))\n",

-      "v=v*P/A\n",

-      "del_v=A_d*mu/(v*(A+P)**2)\n",

-      "\n",

-      "#Result\n",

-      "print(\"required Thrust velocity Delta_v = %.1f m/s\"%del_v)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "required Thrust velocity Delta_v = 200.1 m/s\n"

-       ]

-      }

-     ],

-     "prompt_number": 6

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.7, page no-77"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "R=6378.0*10**3              # Radius of earth\n",

-      "mu=39.8*10**13              # Nm**2/kg\n",

-      "r1=500.0*10**3              # original orbit from earths surface\n",

-      "r2=800.0*10**3              # orbit to be raised to thisdistance\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "R1=R+r1\n",

-      "R2=R+r2\n",

-      "delta_v=math.sqrt(2*mu*R2/(R1*(R1+R2)))-math.sqrt(mu/R1)\n",

-      "delta_v_dash=math.sqrt(mu/R2)-math.sqrt(2*mu*R1/(R2*(R1+R2)))\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"Two thrusts to be applied are,\\n Delta_v = %.2f m/s \\n Delta_v_dash = %.2f m/s\"%(delta_v,delta_v_dash))\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "Two thrusts to be applied are,\n",

-        " Delta_v = 80.75 m/s \n",

-        " Delta_v_dash = 79.89 m/s\n"

-       ]

-      }

-     ],

-     "prompt_number": 7

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.8, page no-97"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "H=36000.0       # Height of geostationary satellite from the surface of earth\n",

-      "R=6370.0        # Radius of earth in km\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "k=math.acos(R/(R+H))\n",

-      "#k=k*180/%pi\n",

-      "k=math.sin(k)\n",

-      "k=math.ceil(k*1000)/1000\n",

-      "d=2*(H+R)*k\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"Maximum line-of-sight distance is %.2f km\"%d)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "Maximum line-of-sight distance is 83807.86 km\n"

-       ]

-      }

-     ],

-     "prompt_number": 8

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.9, page no-98"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "H=36000.0       # Height of geostationary satellite from the surface of earth\n",

-      "R=6370.0        # Radius of earth in km\n",

-      "theta=20.0      # angular separation between two satellites\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "D=(H+R)\n",

-      "k=math.ceil(math.cos(theta*math.pi/180.0)*100)/100\n",

-      "d=math.sqrt(2*D**2*(1-k))\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"The line-of-sight distance is %.4f km\"%d)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "The line-of-sight distance is 14677.3985 km\n"

-       ]

-      }

-     ],

-     "prompt_number": 9

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.10, page no-98"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "\n",

-      "#Variable Declaration\n",

-      "\n",

-      "#IntelSat-VI location= 37 W\n",

-      "# IntelSat-VII location=74 E\n",

-      "theta=37+74        # angular separation between two satellites\n",

-      "D=42164.0          # circular equilateral geostationary orbit in km\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "k=math.cos(math.pi*theta/180.0)\n",

-      "#printf(\"%f\\n\",k)\n",

-      "k=-0.357952\n",

-      "d=math.sqrt(2*D**2*(1-k))\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"Inter-satellite distance is %.2f km\"%d)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "Inter-satellite distance is 69486.27 km\n"

-       ]

-      }

-     ],

-     "prompt_number": 10

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.11, page no-99"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "\n",

-      "theta_l=30.0          # earth station's location 30\u00b0W longitude\n",

-      "theta_s=50.0          # satellite's location 50\u00b0W longitude\n",

-      "theta_L=60.0          # earth station's location 60\u00b0N latitude\n",

-      "r=42164.0             # orbital radius of the satellite in km\n",

-      "R=6378.0              # Earth's radius in km\n",

-      "\n",

-      "A_dash=math.atan((math.tan(math.pi*(theta_s-theta_l)/180.0))/math.sin(math.pi*60/180.0))\n",

-      "A_dash=A_dash*180/math.pi\n",

-      "A=180+A_dash         #Azimuth angle\n",

-      "\n",

-      "x=(180/math.pi)*math.acos(math.cos(math.pi*(theta_s-theta_l)/180.0)*math.cos(math.pi*theta_L/180))\n",

-      "y=r-math.ceil(R*(math.cos(math.pi*(theta_s-theta_l)/180.0)*math.cos(math.pi*theta_L/180)))\n",

-      "z=R*math.sin(math.pi*x/180)\n",

-      "E=(math.atan(y/z)*180/math.pi)-x\n",

-      "print(\"Azimuth  angle =%.1f\u00b0\\n Elevation angle =%.1f\u00b0\"%(A,E))\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "Azimuth  angle =202.8\u00b0\n",

-        " Elevation angle =19.8\u00b0\n"

-       ]

-      }

-     ],

-     "prompt_number": 11

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.12, page no-100"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "theta_l=60.0           #earth station's location 60\u00b0W longitude\n",

-      "theta_s=105.0          #satellite's location 105\u00b0W longitude\n",

-      "theta_L=30.0           #earth station's location 30\u00b0N latitude\n",

-      "\n",

-      "theta_l1=90.0           #earth station's location 90\u00b0W longitude\n",

-      "theta_s1=105.0          #satellite's location 105\u00b0W longitude\n",

-      "theta_L1=45.0           #earth station's location 45\u00b0N latitude\n",

-      "\n",

-      "c=3*10**8             # speed of light\n",

-      "r=42164.0             # orbital radius of the satellite in km\n",

-      "R=6378.0              # Earth's radius in km\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "\n",

-      "x=(180/math.pi)*math.acos(math.cos(math.pi*(theta_s-theta_l)/180)*math.cos(math.pi*theta_L/180))\n",

-      "y=r-math.ceil(R*(math.cos(math.pi*(theta_s-theta_l)/180)*math.cos(math.pi*theta_L/180)))\n",

-      "z=R*math.sin(math.pi*x/180)\n",

-      "E=(math.atan(y/z)*180/math.pi)-x\n",

-      "\n",

-      "x1=(180/math.pi)*math.acos(math.cos(math.pi*(theta_s1-theta_l1)/180)*math.cos(math.pi*theta_L1/180))\n",

-      "y1=r-math.ceil(R*(math.cos(math.pi*(theta_s1-theta_l1)/180)*math.cos(math.pi*theta_L1/180)))\n",

-      "z1=R*math.sin(math.pi*x1/180)\n",

-      "E1=(math.atan(y1/z1)*180/math.pi)-x1\n",

-      "E1=math.floor(E1)\n",

-      "\n",

-      "#calculation of slant range dx\n",

-      "k=(R/r)*math.cos(math.pi*E/180)\n",

-      "k=(180/math.pi)*math.asin(k)\n",

-      "k=k+E\n",

-      "k=math.sin(math.pi*k/180)\n",

-      "k=math.ceil(k*1000)/1000\n",

-      "#k=k+E\n",

-      "#k=sin(k)\n",

-      "dx=(R)**2+(r)**2-(2*r*R*k)\n",

-      "dx=math.sqrt(dx)\n",

-      "\n",

-      "\n",

-      "#calculation of slant range dy\n",

-      "k1=(R/r)*math.cos(math.pi*E1/180)\n",

-      "k1=(180/math.pi)*math.asin(k1)\n",

-      "k1=k1+E1\n",

-      "k1=math.floor(k1)\n",

-      "k1=math.sin(math.pi*k1/180)\n",

-      "k1=math.ceil(k1*1000)/1000\n",

-      "dy=(R)**2+(r)**2-(2*r*R*k1)\n",

-      "dy=math.sqrt(dy)\n",

-      "\n",

-      "tr=dy+dx\n",

-      "delay=tr*10**6/c\n",

-      "x=50\n",

-      "td=delay+x\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"Elevation angle, Ex =%.1f\u00b0\"%E)\n",

-      "print(\"\\n Elevation angle, Ey =%.1f\u00b0\"%math.floor(E1))\n",

-      "print(\"\\n Slant range dx of the earth station X is dx=%.2fkm\"%dx)\n",

-      "print(\"\\n Slant range dy of the earth station Y is dy=%.1fkm\"%dy)\n",

-      "print(\"\\n Therefore, total range to be covered is %.2fkm\"%tr)\n",

-      "print(\"\\n propagation delay=%.2fms\"%delay)\n",

-      "print(\"\\n\\n Time required too transmit 500 kbs of information at \\n a transmisssion speed of 10Mbps is given by 500000/10^7=%.0fms\"%(500000000.0/10**7))\n",

-      "print(\"\\n\\n Total Delay= %.2fms\"%td)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "Elevation angle, Ex =30.3\u00b0\n",

-        "\n",

-        " Elevation angle, Ey =36.0\u00b0\n",

-        "\n",

-        " Slant range dx of the earth station X is dx=38584.76km\n",

-        "\n",

-        " Slant range dy of the earth station Y is dy=38100.8km\n",

-        "\n",

-        " Therefore, total range to be covered is 76685.57km\n",

-        "\n",

-        " propagation delay=255.62ms\n",

-        "\n",

-        "\n",

-        " Time required too transmit 500 kbs of information at \n",

-        " a transmisssion speed of 10Mbps is given by 500000/10^7=50ms\n",

-        "\n",

-        "\n",

-        " Total Delay= 305.62ms\n"

-       ]

-      }

-     ],

-     "prompt_number": 12

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.13, page no-102"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "da=38000.0                # slant range of satellite A\n",

-      "db=36000.0                # slant range of satellite B\n",

-      "beeta=60.0                # difference between longitudes of two satellites\n",

-      "R=42164.0                 # radius of the orbit of satellites\n",

-      "\n",

-      "\n",

-      "#Calculation\n",

-      "theta=(da**2+db**2-2*(R**2)*(1-math.cos(math.pi*beeta/180)))/(2*da*db)\n",

-      "theta=(180/math.pi)*math.acos(theta)\n",

-      "d=math.sqrt(2*(R**2)*(1-math.cos(math.pi*beeta/180)))\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"Angular spacing between two satellites viewed by earth station is,\\n theta= %.1f\u00b0\"%theta)\n",

-      "print(\"\\nInter-satellite distance , d=%.0fkm\"%d)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "Angular spacing between two satellites viewed by earth station is,\n",

-        " theta= 69.4\u00b0\n",

-        "\n",

-        "Inter-satellite distance , d=42164km\n"

-       ]

-      }

-     ],

-     "prompt_number": 13

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.14, page no-107"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "import math\n",

-      "#Variable Declaration\n",

-      "r=42164.0             # orbital radius of the satellite in km\n",

-      "R=6378.0              # Earth's radius in km\n",

-      "\n",

-      "#refer to Figure 3.53\n",

-      "\n",

-      "#Calculation\n",

-      "\n",

-      "#for E=0\u00b0\n",

-      "alfa=math.asin(R/r)*(180/math.pi)\n",

-      "alfa=math.floor(alfa*10)/10\n",

-      "theta=90-alfa\n",

-      "#in the right angle triangle OAC,\n",

-      "k=math.sin(math.pi*alfa/180)\n",

-      "k=math.floor(k*1000)/1000\n",

-      "oc=R*k\n",

-      "oc=math.ceil(oc*10)/10\n",

-      "A=2*math.pi*R*(R-oc)\n",

-      "\n",

-      "\n",

-      "#for E=10\u00b0\n",

-      "E=10\n",

-      "alfa1=math.asin((R/r)*math.cos(math.pi*E/180))*(180/math.pi)\n",

-      "#alfa1=ceil(alfa1*100)/100\n",

-      "theta1=90-alfa1-E\n",

-      "#in the right angle triangle OAC,\n",

-      "k1=math.sin(math.pi*(alfa1+E)/180)\n",

-      "k1=math.floor(k1*1000)/1000\n",

-      "oc1=R*k1\n",

-      "oc1=math.floor(oc1*10)/10\n",

-      "A1=2*math.pi*R*(R-oc1)\n",

-      "\n",

-      "\n",

-      "#Result\n",

-      "print(\"for E=0\u00b0,\\n covered surface area is %.1f km^2\"%A)\n",

-      "print(\"\\n\\n for E=10\u00b0,\\n covered surface area is %.1f km^2\"%A1)\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "for E=0\u00b0,\n",

-        " covered surface area is 216997546.7 km^2\n",

-        "\n",

-        "\n",

-        " for E=10\u00b0,\n",

-        " covered surface area is 174314563.3 km^2\n"

-       ]

-      }

-     ],

-     "prompt_number": 15

-    },

-    {

-     "cell_type": "heading",

-     "level": 3,

-     "metadata": {},

-     "source": [

-      "Example 3.15, page no-108"

-     ]

-    },

-    {

-     "cell_type": "code",

-     "collapsed": false,

-     "input": [

-      "#variable declaration\n",

-      "theta=30               #satellite inclination to the equitorial plan\n",

-      "#the extreme latitudes covered in northern and southern hemisphere are the same as orbit inclination\n",

-      "\n",

-      "print(\"Extreme Northern latitude covered = %.0f\u00b0 N\"%theta)\n",

-      "print(\"\\n Extreme Southern latitude covered = %.0f\u00b0 S\"%theta)\n",

-      "print(\"\\n\\n In fact, the ground track would sweep\\n all latitudes between %d\u00b0N and %d\u00b0S\"%(theta,theta))\n"

-     ],

-     "language": "python",

-     "metadata": {},

-     "outputs": [

-      {

-       "output_type": "stream",

-       "stream": "stdout",

-       "text": [

-        "Extreme Northern latitude covered = 30\u00b0 N\n",

-        "\n",

-        " Extreme Southern latitude covered = 30\u00b0 S\n",

-        "\n",

-        "\n",

-        " In fact, the ground track would sweep\n",

-        " all latitudes between 30\u00b0N and 30\u00b0S\n"

-       ]

-      }

-     ],

-     "prompt_number": 16

-    }

-   ],

-   "metadata": {}

-  }

- ]

+{
+ "metadata": {
+  "name": "",
+  "signature": "sha256:eb32c126a333b2cfa51753626f865ad3fb2b120400bc606b82fb97538f18ae74"
+ },
+ "nbformat": 3,
+ "nbformat_minor": 0,
+ "worksheets": [
+  {
+   "cells": [
+    {
+     "cell_type": "heading",
+     "level": 1,
+     "metadata": {},
+     "source": [
+      "Chapter 3: Satellite Launch and In-Orbit Operations"
+     ]
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.1, page no-72"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "Az=85      # Azimuth angle of injection point\n",
+      "l=5.2      # latitude of launch site\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "cosi=math.sin(Az*math.pi/180)*math.cos(l*math.pi/180)\n",
+      "i=math.acos(cosi)\n",
+      "i=i*180.0/math.pi\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"Inclination angle attained, i=%.1f\u00b0\"%i)"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Inclination angle attained, i=7.2\u00b0\n"
+       ]
+      }
+     ],
+     "prompt_number": 1
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.2, page no-73"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "delta_i=7     #orbital plane inclination\n",
+      "V=3000        #velocity of satellite in circularized orbit\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "vp=2*V*math.sin(delta_i*math.pi/(2*180))\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"Velocity thrust to make the inclination 0\u00b0 = %.0f m/s\"%vp)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Velocity thrust to make the inclination 0\u00b0 = 366 m/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 2
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.3, page no-73"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "\n",
+      "#Variable Declaration\n",
+      "mu=39.8*10**13          # Nm^2/kg\n",
+      "P=7000.0*10**3          # Perigee distance in m\n",
+      "e=0.69                  # eccentricity of eliptical orbit\n",
+      "w=60.0/2                # angle made by line joing centre of earth and perigee with the line of nodes\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "k=(e/math.sqrt(1+e))\n",
+      "k=math.floor(k*100)/100\n",
+      "v=2*(math.sqrt(mu/P))*k*math.sin(w*math.pi/180.0)\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"The velocity thrust required to rotate the perigee point\\n by desired amount is given by, v=%.1f m/s = %.3fkm/s\"%(v,v/1000.0))\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The velocity thrust required to rotate the perigee point\n",
+        " by desired amount is given by, v=3996.4 m/s = 3.996km/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 3
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.4, page no-74"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "A=15000*10**3            #Original apogee distance\n",
+      "A1=25000*10**3           # Raised opogee distance\n",
+      "P=7000*10**3             # Perigee Distance\n",
+      "mu=39.8*10**13           #Nm**2/kg\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "A_d=A1-A\n",
+      "v=math.sqrt((2*mu/P)-(2*mu/(A+P)))\n",
+      "del_v=A_d*mu/(v*(A+P)**2)\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"required Thrust velocity Delta_v = %.1f m/s\"%del_v)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "required Thrust velocity Delta_v = 933.9 m/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 4
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.5, page no-75"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "A=15000.0*10**3            # Original apogee distance\n",
+      "A1=7000.0*10**3            # Raised opogee distance\n",
+      "P=7000.0*10**3             # Perigee Distance\n",
+      "mu=39.8*10**13             # Nm^2/kg\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "A_d=A-A1\n",
+      "v=math.sqrt((2*mu/P)-(2*mu/(A+P)))\n",
+      "del_v=A_d*mu/(v*(A+P)**2)\n",
+      "\n",
+      "#Result\n",
+      "print(\"required Thrust velocity Delta_v = %.1f m/s\"%del_v)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "required Thrust velocity Delta_v = 747.1 m/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 5
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.6, page no-76"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#Variable Declaration\n",
+      "A=15000.0*10**3            # Original apogee distance\n",
+      "A1=16000.0*10**3           # Raised opogee distance\n",
+      "P=7000.0*10**3             # Perigee Distance\n",
+      "mu=39.8*10**13           # Nm**2/kg\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "A_d=A1-A\n",
+      "v=math.sqrt((2*mu/P)-(2*mu/(A+P)))\n",
+      "v=v*P/A\n",
+      "del_v=A_d*mu/(v*(A+P)**2)\n",
+      "\n",
+      "#Result\n",
+      "print(\"required Thrust velocity Delta_v = %.1f m/s\"%del_v)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "required Thrust velocity Delta_v = 200.1 m/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 6
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.7, page no-77"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "R=6378.0*10**3              # Radius of earth\n",
+      "mu=39.8*10**13              # Nm**2/kg\n",
+      "r1=500.0*10**3              # original orbit from earths surface\n",
+      "r2=800.0*10**3              # orbit to be raised to thisdistance\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "R1=R+r1\n",
+      "R2=R+r2\n",
+      "delta_v=math.sqrt(2*mu*R2/(R1*(R1+R2)))-math.sqrt(mu/R1)\n",
+      "delta_v_dash=math.sqrt(mu/R2)-math.sqrt(2*mu*R1/(R2*(R1+R2)))\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"Two thrusts to be applied are,\\n Delta_v = %.2f m/s \\n Delta_v_dash = %.2f m/s\"%(delta_v,delta_v_dash))\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Two thrusts to be applied are,\n",
+        " Delta_v = 80.75 m/s \n",
+        " Delta_v_dash = 79.89 m/s\n"
+       ]
+      }
+     ],
+     "prompt_number": 7
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.8, page no-97"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "H=36000.0       # Height of geostationary satellite from the surface of earth\n",
+      "R=6370.0        # Radius of earth in km\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "k=math.acos(R/(R+H))\n",
+      "#k=k*180/%pi\n",
+      "k=math.sin(k)\n",
+      "k=math.ceil(k*1000)/1000\n",
+      "d=2*(H+R)*k\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"Maximum line-of-sight distance is %.2f km\"%d)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Maximum line-of-sight distance is 83807.86 km\n"
+       ]
+      }
+     ],
+     "prompt_number": 8
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.9, page no-98"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "H=36000.0       # Height of geostationary satellite from the surface of earth\n",
+      "R=6370.0        # Radius of earth in km\n",
+      "theta=20.0      # angular separation between two satellites\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "D=(H+R)\n",
+      "k=math.ceil(math.cos(theta*math.pi/180.0)*100)/100\n",
+      "d=math.sqrt(2*D**2*(1-k))\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"The line-of-sight distance is %.4f km\"%d)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "The line-of-sight distance is 14677.3985 km\n"
+       ]
+      }
+     ],
+     "prompt_number": 9
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.10, page no-98"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "\n",
+      "#Variable Declaration\n",
+      "\n",
+      "theta=37+74        # angular separation between two satellites\n",
+      "D=42164.0          # circular equilateral geostationary orbit in km\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "k=math.cos(math.pi*theta/180.0)\n",
+      "#printf(\"%f\\n\",k)\n",
+      "k=-0.357952\n",
+      "d=math.sqrt(2*D**2*(1-k))\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"Inter-satellite distance is %.2f km\"%d)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Inter-satellite distance is 69486.27 km\n"
+       ]
+      }
+     ],
+     "prompt_number": 10
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.11, page no-99"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "\n",
+      "theta_l=30.0          # earth station's location 30\u00b0W longitude\n",
+      "theta_s=50.0          # satellite's location 50\u00b0W longitude\n",
+      "theta_L=60.0          # earth station's location 60\u00b0N latitude\n",
+      "r=42164.0             # orbital radius of the satellite in km\n",
+      "R=6378.0              # Earth's radius in km\n",
+      "\n",
+      "A_dash=math.atan((math.tan(math.pi*(theta_s-theta_l)/180.0))/math.sin(math.pi*60/180.0))\n",
+      "A_dash=A_dash*180/math.pi\n",
+      "A=180+A_dash         #Azimuth angle\n",
+      "\n",
+      "x=(180/math.pi)*math.acos(math.cos(math.pi*(theta_s-theta_l)/180.0)*math.cos(math.pi*theta_L/180))\n",
+      "y=r-math.ceil(R*(math.cos(math.pi*(theta_s-theta_l)/180.0)*math.cos(math.pi*theta_L/180)))\n",
+      "z=R*math.sin(math.pi*x/180)\n",
+      "E=(math.atan(y/z)*180/math.pi)-x\n",
+      "print(\"Azimuth  angle =%.1f\u00b0\\n Elevation angle =%.1f\u00b0\"%(A,E))\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Azimuth  angle =202.8\u00b0\n",
+        " Elevation angle =19.8\u00b0\n"
+       ]
+      }
+     ],
+     "prompt_number": 11
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.12, page no-100"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "theta_l=60.0           #earth station's location 60\u00b0W longitude\n",
+      "theta_s=105.0          #satellite's location 105\u00b0W longitude\n",
+      "theta_L=30.0           #earth station's location 30\u00b0N latitude\n",
+      "\n",
+      "theta_l1=90.0           #earth station's location 90\u00b0W longitude\n",
+      "theta_s1=105.0          #satellite's location 105\u00b0W longitude\n",
+      "theta_L1=45.0           #earth station's location 45\u00b0N latitude\n",
+      "\n",
+      "c=3*10**8             # speed of light\n",
+      "r=42164.0             # orbital radius of the satellite in km\n",
+      "R=6378.0              # Earth's radius in km\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "\n",
+      "x=(180/math.pi)*math.acos(math.cos(math.pi*(theta_s-theta_l)/180)*math.cos(math.pi*theta_L/180))\n",
+      "y=r-math.ceil(R*(math.cos(math.pi*(theta_s-theta_l)/180)*math.cos(math.pi*theta_L/180)))\n",
+      "z=R*math.sin(math.pi*x/180)\n",
+      "E=(math.atan(y/z)*180/math.pi)-x\n",
+      "\n",
+      "x1=(180/math.pi)*math.acos(math.cos(math.pi*(theta_s1-theta_l1)/180)*math.cos(math.pi*theta_L1/180))\n",
+      "y1=r-math.ceil(R*(math.cos(math.pi*(theta_s1-theta_l1)/180)*math.cos(math.pi*theta_L1/180)))\n",
+      "z1=R*math.sin(math.pi*x1/180)\n",
+      "E1=(math.atan(y1/z1)*180/math.pi)-x1\n",
+      "E1=math.floor(E1)\n",
+      "\n",
+      "#calculation of slant range dx\n",
+      "k=(R/r)*math.cos(math.pi*E/180)\n",
+      "k=(180/math.pi)*math.asin(k)\n",
+      "k=k+E\n",
+      "k=math.sin(math.pi*k/180)\n",
+      "k=math.ceil(k*1000)/1000\n",
+      "#k=k+E\n",
+      "#k=sin(k)\n",
+      "dx=(R)**2+(r)**2-(2*r*R*k)\n",
+      "dx=math.sqrt(dx)\n",
+      "\n",
+      "\n",
+      "#calculation of slant range dy\n",
+      "k1=(R/r)*math.cos(math.pi*E1/180)\n",
+      "k1=(180/math.pi)*math.asin(k1)\n",
+      "k1=k1+E1\n",
+      "k1=math.floor(k1)\n",
+      "k1=math.sin(math.pi*k1/180)\n",
+      "k1=math.ceil(k1*1000)/1000\n",
+      "dy=(R)**2+(r)**2-(2*r*R*k1)\n",
+      "dy=math.sqrt(dy)\n",
+      "\n",
+      "tr=dy+dx\n",
+      "delay=tr*10**6/c\n",
+      "x=50\n",
+      "td=delay+x\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"Elevation angle, Ex =%.1f\u00b0\"%E)\n",
+      "print(\"\\n Elevation angle, Ey =%.1f\u00b0\"%math.floor(E1))\n",
+      "print(\"\\n Slant range dx of the earth station X is dx=%.2fkm\"%dx)\n",
+      "print(\"\\n Slant range dy of the earth station Y is dy=%.1fkm\"%dy)\n",
+      "print(\"\\n Therefore, total range to be covered is %.2fkm\"%tr)\n",
+      "print(\"\\n propagation delay=%.2fms\"%delay)\n",
+      "print(\"\\n\\n Time required too transmit 500 kbs of information at \\n a transmisssion speed of 10Mbps is given by 500000/10^7=%.0fms\"%(500000000.0/10**7))\n",
+      "print(\"\\n\\n Total Delay= %.2fms\"%td)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Elevation angle, Ex =30.3\u00b0\n",
+        "\n",
+        " Elevation angle, Ey =36.0\u00b0\n",
+        "\n",
+        " Slant range dx of the earth station X is dx=38584.76km\n",
+        "\n",
+        " Slant range dy of the earth station Y is dy=38100.8km\n",
+        "\n",
+        " Therefore, total range to be covered is 76685.57km\n",
+        "\n",
+        " propagation delay=255.62ms\n",
+        "\n",
+        "\n",
+        " Time required too transmit 500 kbs of information at \n",
+        " a transmisssion speed of 10Mbps is given by 500000/10^7=50ms\n",
+        "\n",
+        "\n",
+        " Total Delay= 305.62ms\n"
+       ]
+      }
+     ],
+     "prompt_number": 12
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.13, page no-102"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "da=38000.0                # slant range of satellite A\n",
+      "db=36000.0                # slant range of satellite B\n",
+      "beeta=60.0                # difference between longitudes of two satellites\n",
+      "R=42164.0                 # radius of the orbit of satellites\n",
+      "\n",
+      "\n",
+      "#Calculation\n",
+      "theta=(da**2+db**2-2*(R**2)*(1-math.cos(math.pi*beeta/180)))/(2*da*db)\n",
+      "theta=(180/math.pi)*math.acos(theta)\n",
+      "d=math.sqrt(2*(R**2)*(1-math.cos(math.pi*beeta/180)))\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"Angular spacing between two satellites viewed by earth station is,\\n theta= %.1f\u00b0\"%theta)\n",
+      "print(\"\\nInter-satellite distance , d=%.0fkm\"%d)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Angular spacing between two satellites viewed by earth station is,\n",
+        " theta= 69.4\u00b0\n",
+        "\n",
+        "Inter-satellite distance , d=42164km\n"
+       ]
+      }
+     ],
+     "prompt_number": 13
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.14, page no-107"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "import math\n",
+      "#Variable Declaration\n",
+      "r=42164.0             # orbital radius of the satellite in km\n",
+      "R=6378.0              # Earth's radius in km\n",
+      "\n",
+      "#refer to Figure 3.53\n",
+      "\n",
+      "#Calculation\n",
+      "\n",
+      "#for E=0\u00b0\n",
+      "alfa=math.asin(R/r)*(180/math.pi)\n",
+      "alfa=math.floor(alfa*10)/10\n",
+      "theta=90-alfa\n",
+      "#in the right angle triangle OAC,\n",
+      "k=math.sin(math.pi*alfa/180)\n",
+      "k=math.floor(k*1000)/1000\n",
+      "oc=R*k\n",
+      "oc=math.ceil(oc*10)/10\n",
+      "A=2*math.pi*R*(R-oc)\n",
+      "\n",
+      "\n",
+      "#for E=10\u00b0\n",
+      "E=10\n",
+      "alfa1=math.asin((R/r)*math.cos(math.pi*E/180))*(180/math.pi)\n",
+      "#alfa1=ceil(alfa1*100)/100\n",
+      "theta1=90-alfa1-E\n",
+      "#in the right angle triangle OAC,\n",
+      "k1=math.sin(math.pi*(alfa1+E)/180)\n",
+      "k1=math.floor(k1*1000)/1000\n",
+      "oc1=R*k1\n",
+      "oc1=math.floor(oc1*10)/10\n",
+      "A1=2*math.pi*R*(R-oc1)\n",
+      "\n",
+      "\n",
+      "#Result\n",
+      "print(\"for E=0\u00b0,\\n covered surface area is %.1f km^2\"%A)\n",
+      "print(\"\\n\\n for E=10\u00b0,\\n covered surface area is %.1f km^2\"%A1)\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "for E=0\u00b0,\n",
+        " covered surface area is 216997546.7 km^2\n",
+        "\n",
+        "\n",
+        " for E=10\u00b0,\n",
+        " covered surface area is 174314563.3 km^2\n"
+       ]
+      }
+     ],
+     "prompt_number": 15
+    },
+    {
+     "cell_type": "heading",
+     "level": 3,
+     "metadata": {},
+     "source": [
+      "Example 3.15, page no-108"
+     ]
+    },
+    {
+     "cell_type": "code",
+     "collapsed": false,
+     "input": [
+      "#variable declaration\n",
+      "theta=30               #satellite inclination to the equitorial plan\n",
+      "\n",
+      "\n",
+      "print(\"Extreme Northern latitude covered = %.0f\u00b0 N\"%theta)\n",
+      "print(\"\\n Extreme Southern latitude covered = %.0f\u00b0 S\"%theta)\n",
+      "print(\"\\n\\n In fact, the ground track would sweep\\n all latitudes between %d\u00b0N and %d\u00b0S\"%(theta,theta))\n"
+     ],
+     "language": "python",
+     "metadata": {},
+     "outputs": [
+      {
+       "output_type": "stream",
+       "stream": "stdout",
+       "text": [
+        "Extreme Northern latitude covered = 30\u00b0 N\n",
+        "\n",
+        " Extreme Southern latitude covered = 30\u00b0 S\n",
+        "\n",
+        "\n",
+        " In fact, the ground track would sweep\n",
+        " all latitudes between 30\u00b0N and 30\u00b0S\n"
+       ]
+      }
+     ],
+     "prompt_number": 16
+    }
+   ],
+   "metadata": {}
+  }
+ ]
 }
\ No newline at end of file