{
"cells": [
 {
		   "cell_type": "markdown",
	   "metadata": {},
	   "source": [
       "# Chapter 2: Orbits and Lauching Methods"
	   ]
	},
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.10: Find_the_Julian_day_for_13h_UT_on_18December_2000.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"y=2000      //year\n",
"mon=12      //month\n",
"dy=18       //day\n",
"hours=13    //hours of the day\n",
"minutes=0   //Minutes of the day\n",
"seconds=0   //Seconds of the day\n",
"//Calculation\n",
"d=dy+(hours/24)+(minutes/(24*60))+seconds  //Days in December \n",
"if mon<=2 then\n",
"   y=y-1\n",
"   mon=mon+12\n",
"else\n",
"   y=y\n",
"   mon=mon\n",
"end\n",
"A=floor(y/100)      //Converting years to days\n",
"B=2-A+floor(A/4)    //Converting years to days\n",
"C=floor(365.25*y)     //rounding the days \n",
"D=floor(30.6001*(mon+1)) //Converting months to days\n",
"JD=B+C+D+d+1720994.5     //Adding reeference to number of days\n",
"//Result\n",
"printf('The Julian day of given day is : %.4f Days',JD)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.11: Find_the_time_in_Julian_centuries_from_the_reference_time.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"JDref=2415020   //Reference Julian days\n",
"JC=36525\n",
"JD=2451897.0417 //Julian days with reference from Example 2.10\n",
"//Calculation\n",
"T=(JD-JDref)/JC  //Time in julian Centuries\n",
"//Result\n",
"printf('The time for given date is : %.8f Julian Centuries',T)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.12: Calculate_the_time_of_perigee_passage_for_the_NASA_elements.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"\n",
"//Variable Declaration\n",
"\n",
"n=14.23304826  //Mean Motion (rev/day)\n",
"M0=246.6853    //Mean Anomaly (degrees)\n",
"t0=223.79688452 //Time of anomaly\n",
"\n",
"//Calculation\n",
"\n",
"T = (t0-(M0/(n*360)))  //Time of perigee passage\n",
"\n",
"//Result\n",
"printf('The time of perigee passage for NASA elements is : %.4f days',T)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.13: calculate_the_eccentric_anomaly.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"\n",
"//Variable Declaration\n",
"M=205  //Mean anomaly(degrees)\n",
"e=0.0025  //Eccentricity\n",
"E=%pi //Initial guess value for eccentric anomaly\n",
"\n",
"//Calculation\n",
"\n",
"function [y] = f(E)\n",
"    y=M-E+e*sin(E)\n",
"endfunction\n",
"E=fsolve(3.142,f)\n",
"\n",
"printf('The Eccentric anomaly is: %.4f degrees',E)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.14: Calculate_teh_true_anomaly_and_the_magnitude_of_the_radius_vector.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"pi = %pi\n",
"n=14.2171401*2*%pi/86400  //Mean motion (rad/sec)\n",
"M=204.9779+0.001*180*5/pi //Mean anomaly(rad)\n",
"e=9.5981*10**-3   //Eccentricity\n",
"a=7194.9   //Semimajor axis(km)\n",
"//Calculation\n",
"v=(M*pi/180)+2*e*sin(M*pi/180)+(5*e**2*sin(2*M*pi)/(4*180)) //True Anomaly (radians)\n",
"v=v*180/%pi  //True anomaly(degrees)\n",
"r=a*(1-e**2)/(1+e*cos(v))  //Magnitude of radius vector after 5s(km)\n",
"//Results\n",
"printf('The true anomaly is: %.3f degrees',v)\n",
"printf('\nThe magnitude of radius vector 5s after epoch is: %d km',r)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.15: express_r_in_vector_form_in_the_perifocal_coordinate_system.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"v=204.81   //True anomaly(degrees) from Example 2.14\n",
"r=7257     //Magnitude of radius vector(km) from Example 2.14\n",
"//Calculation\n",
"rP=r*cos(v*%pi/180)  //P coordinate of radius vector(km)\n",
"rQ=r*sin(v*%pi/180)  //Q coordinate of radius vector(km)\n",
"//Result\n",
"printf('r in the perifocal coordinate system is %.2f Pkm %.2f Qkm',rP,rQ)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.17: Find_the_GST_for_13h_UT_on_18December_2000.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"pi = %pi\n",
"T=1.009638376  //Time in Julian centuries from Example 2.11\n",
"UT=13  //Universal time(hours)\n",
"//Calculation\n",
"GST=(99.6910+36000.7689*T+0.004*T**2)*3.142/180  //GST(radians)\n",
"UT=2*pi*UT/24  //Universal time converted to fraction of earth rotation (radians)\n",
"GST=GST+UT \n",
"GST=(modulo(GST,2*pi))*180/pi\n",
"//Result\n",
"printf('The GST for given date and time is %.2f degrees',GST)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.18: Find_the_LST_for_Thunder_Bay.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declararion\n",
"pi = %pi\n",
"WL=-89.26  //Expressing the longitude in degrees west\n",
"GST=282.449  //GST from Example 2.17 (degrees)\n",
"//Calculation\n",
"EL=2*pi+WL  //Longitude in degrees East \n",
"LST=(GST+EL)*pi/180       //LST(radians)\n",
"LST=(modulo(LST,2*pi))*180/pi   //fmod removes multiple revolutions(Degrees)\n",
"//Results\n",
"printf('LST for Thunder Bay on given day is: %.2f Degrees',LST)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.19: Find_the_components_of_the_radius_vector_to_the_earth_station_at_Thunder_Bay.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"LST=167.475 //LST(degrees)\n",
"LE=48.42    //Latitude at thunder bay(degrees)\n",
"H=200       //Height above sea level(metres)\n",
"aE=6378.1414 //Semimajor axis(km)\n",
"eE=0.08182   //Eccentricity\n",
"//Calculation\n",
"l=(aE/sqrt(1-eE**2*sin(LE*3.142/180)**2)+H/1000)*cos(LE*3.142/180)  \n",
"z=((aE*(1-eE**2))/sqrt(1-eE**2*sin(LE*3.142/180)**2)+H/1000)*sin(LE*3.142/180)  \n",
"RI=l*cos(LST*3.142/180) //I component of radius vector at thunder bay(km)\n",
"RJ=l*sin(LST*3.142/180) //J component of radius vector at thunder bay(km)\n",
"RK= z                 //Z component of radius vector at thunder bay(km)\n",
"R=sqrt(RI**2+RJ**2+RK**2)\n",
"//Results\n",
"printf('The Radius vector components are %.2f ikm+ %.2f jkm+ %.2f kkm',RI,RJ,RK)\n",
"printf('\nThe Magnitude of radius component is %.2f km',R)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.1: Calculate_the_radius_of_a_circular_orbit_for_which_the_period_is_1_day.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"u=3.986*(10**14)         //Earth's Gravitational constant(m^3/sec^2)\n",
"//Calculation\n",
"n=(2*3.14)/(24*60*60)    //Mean Motion(rad/sec)\n",
"a=((u/n**2)**(0.33333))/1000      //Radius of the orbit by kepler's 3rd law(km)\n",
"//Result\n",
"printf('The Radius of the circular orbit with 1 day period is : %d km',a)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.20: EX2_20.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"PI=-1280  //I component of range vector for a satellite(km)\n",
"PJ=-1278  //J component of range vector for a satellite(km)\n",
"PK=66     //K component of range vector for a satellite(km)\n",
"GST=240   //GST(degrees)\n",
"LE=48.42  //Latitude(Degrees)\n",
"PE=-89.26 //Longitude(Degrees)\n",
"H=200     //Height above mean sea level(metres)\n",
"aE=6378.1414 //Semimajor axis(km)\n",
"eE=0.08182   //Eccentricity\n",
"//Calculation\n",
"l=(aE/sqrt(1-eE**2*sin(LE*3.142/180)**2)+H/1000)*cos(LE*3.142/180)  \n",
"z=((aE*(1-eE**2))/sqrt(1-eE**2*sin(LE*3.142/180)**2)+H/1000)*sin(LE*3.142/180)  \n",
"SE=(atan(z/l))*180/3.142 //Geocentric latitude angle (degrees)\n",
"LST=240+PE\n",
"a=sin(SE*3.142/180)*cos(LST*3.142/180)\n",
"b=sin(SE*3.142/180)*sin(LST*3.142/180)\n",
"c=-cos(SE*3.142/180)\n",
"d=-sin(LST*3.142/180)\n",
"e=cos(LST*3.142/180)\n",
"f=0\n",
"g=cos(SE*3.142/180)*cos(LST*3.142/180)\n",
"h=cos(SE*3.142/180)*sin(LST*3.142/180)\n",
"i=sin(SE*3.142/180)\n",
"D = [a,b,c;d,e,f;g,h,i]\n",
"P=  [PI;PJ;PK]\n",
"R=D*P  //Components of range of earth station\n",
"Ro=sqrt(R(1,1)**2+R(2,1)**2+R(3,1)**2) //Magnitude of range of earth station(km)\n",
"El=asin(R(3,1)/Ro) //Antenna elevation angle for the earth station(radians) \n",
"El= El*180/3.142   //Converting El to degrees\n",
"alpha=(atan(R(2,1)/R(3,1)))*180/3.142\n",
"if ( R(1,1)<0 & R(2,1)>0 ) then\n",
"   Aza=alpha\n",
"else\n",
"   Aza=0\n",
"end   \n",
"if ( R(1,1)>0 & R(2,1)>0 ) then\n",
"   Azb=180-alpha\n",
"else:\n",
"   Azb=0\n",
"end\n",
"   \n",
"if ( R(1,1)>0 & R(2,1)<0 ) then\n",
"   Azc=180+alpha\n",
"else\n",
"   Azc=0\n",
"end   \n",
"if ( R(1,1)<0 & R(2,1)<0 ) then\n",
"   Azd=360-alpha\n",
"else\n",
"   Azd=0\n",
"end   \n",
"Az= Aza+Azb+Azc+Azd   //Azimuth angle (degrees)\n",
"printf('The magnitude of range of earth station is %.0f km',Ro)\n",
"printf('\nThe antenna elevation angle for the earth station are %.f degrees',El)\n",
"printf('\nThe Azimuth angle for the earth station is %.2f degrees',Az)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.21: Determine_the_subsatellite_height_latitude_and_LST.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"rI=-4685.3  //I component of radius vector from Example 2.16(km)\n",
"rJ=5047.7   //J component of radius vector from Example 2.16(km)\n",
"rK=-3289.1  //K component of radius vector from Example 2.16(km)\n",
"aE=6378.1414 //Semimajor axis (km)\n",
"eE=0.08182   //Eccentricity\n",
"//Calculation\n",
"r=sqrt(rI**2+rJ**2+rK**2)\n",
"a=%pi  //Guess value for LST(radians)\n",
"b=atan(rK/rI)   //Guess Value for latitude(radians)\n",
"c=r-aE   //Guess value for height(km)\n",
"function [ans] = equations(p)\n",
"    L = p(1)\n",
"    h = p(2)\n",
"    LST = p(3)\n",
"    a = rI-((aE/sqrt(1-eE**2*sin(L)**2))+h)*cos(L)*cos(LST)\n",
"    b = rJ-((aE/sqrt(1-eE**2*sin(L)**2))+h)*cos(L)*sin(LST)\n",
"    c = rK-((aE*(1-eE**2)/sqrt(1-eE**2*sin(L)**2))+h)*sin(L)\n",
"    ans = [a;b;c]\n",
"endfunction\n",
"ans =  fsolve([b;c;a],equations)\n",
"L = ans(1)\n",
"h = ans(2)\n",
"LST = ans(3)\n",
"L= L*180/3.142  //Converting L into degrees\n",
"h=round(h)\n",
"LST=LST*180/3.142 //Converting LST into degrees\n",
"printf('The latitude of subsatellite is %.2f degrees',L)\n",
"printf('\nThe height of subsatellite is %.2f km',h)\n",
"printf('\nThe LST of subsatellite is %.1f degrees',LST)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.2: Calculate_the_semimajor_axis_for_the_satellite_parameters_give.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"NN=14.22296917        //Mean Motion (1/day)\n",
"u=3.986005*(10**14)   //Earth's Gravitational COnstant(m^3/sec^2)\n",
"//Calculation\n",
"n0=(NN*2*3.142)/(24*60*60)                  //Mean Motion(rad/sec)\n",
"a=((u/n0**2)**(0.33333))/1000   //Radius of the orbit by kepler's 3rd law(km)\n",
"//Result\n",
"printf('The Semimajor axis for given satellite parameters is : %.2f km',a)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.3: Calculate_the_apogee_and_perigee_for_the_orbital_parameters_given.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"R=6371   //Mean Earth's radius(km)\n",
"e=0.0011501  //Eccentricity\n",
"a=7192.3     //Semimajor axis(km)\n",
"//Calculation\n",
"ra=a*(1+e)   //Radius Vector at apogee(km)\n",
"rp=a*(1-e)   //Radius Vector at perigee(km)\n",
"ha=ra-R      //Apogee height(km)\n",
"hp=rp-R      //Perigee height(km)\n",
"//Result\n",
"printf('The Apogee height for given orbital parameters is: %.2f km',ha)\n",
"printf('The Apogee height for given orbital parameters is: %.2f km',hp)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.4: calculate_the_semimajor_axis.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"aE=6378.141     //Earth's equitorial radius(km)\n",
"e=0.002         //Eccentricity\n",
"p=12            //period from perigee to perigee (hours)\n",
"K1=66063.1704  //Constant (km^2)\n",
"u=3.986005*(10**14)         //Earth's Gravitational constant(m^3/sec^2)\n",
"//Calculation\n",
"n=(2*%pi)/(12*60*60)            //Mean Motion(rad/sec)\n",
"anp=((u/n**2)**(0.3333))/1000      //Radius of the orbit by kepler's 3rd law(km)\n",
"k2=(1-e**2)**1.5\n",
"function [y]=f(a)\n",
"    y=(n-((u/a**3)**0.5)*(1+K1/a**2*k2))\n",
"endfunction\n",
"a=fsolve(2,f)\n",
"a=a/1000  //Converting a into km\n",
"//Result\n",
"printf('The nonperturbed value of semimajor axis is %.2f km',anp)\n",
"printf('\nThe perturbed value of semimajor axis is %.2f km',a)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.5: EX2_5.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"i=98.6328      //Angle(degrees)\n",
"e=0.0011501    //eccentricity\n",
"n=14.23304826  //Mean Motion(1/day)\n",
"a=7192.3       //Semimajor axis(km)\n",
"K1=66063.1704  //Known constant(km^2)\n",
"//Calculation\n",
"n0=(2*180*n)  //Mean Motion (deg/sec)\n",
"K=(n0*K1)/((a**2)*((1-e**2)**2))  //Constant (deg/day)\n",
"w=-K*cos(i*3.142/180)    //Rate of regression of nodes(deg/day)\n",
"W=K*(2-2.5*(sin(i*3.142/180))**2)   //Rate of rotation of line of apsides(deg/day)\n",
"//Results\n",
"printf('The rate of regression of nodes is: %.3f deg/day',w)\n",
"printf('\nThe rate of rotation of line of apsides is : %.3f deg/day',W)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.6: Calculate_the_new_values_for_W_and_w_one_period_after_epoch.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Variable Declaration\n",
"w=0.982  //rate of regression of nodes from Example 2.5(deg/day)\n",
"W=-2.903 //rate of rotation of line of apsides from Example 2.5)deg/day)\n",
"n=14.23304826  //Mean Motion(1/day)\n",
"W0=113.5534   //Argument of perigee(deg)\n",
"w0=251.5324   //Right ascension of the ascending node(deg)\n",
"//Calculation\n",
"PA=1/n   //Period \n",
"w=w0+w*PA  //New value of rate of regression of nodes(deg)\n",
"W=W0+W*PA  //New Value of rate of rotation of line of apsides(deg)\n",
"//Result\n",
"printf('New value of rate of regression of nodes is: %.3f deg',w)\n",
"printf('\nNew value of rate of rotation of line of apsides is : %.3f deg',W)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.7: Calculate_the_average_length_of_the_civil_year_in_the_Gregorian_calendar.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Calculation\n",
"ndays=400*365    //Nominal number of days in 400years\n",
"nleapyrs=400/4   //Nominal number of leap years\n",
"gregoriandays=ndays+nleapyrs-3  //number of days in 400 years of Gregorian calendar\n",
"gregavg=gregoriandays/400    //number of days in 400 years of Gregorian calendar\n",
"//Result\n",
"disp (gregoriandays)\n",
"printf('The average length of the civil year in gregorian calender is : %.4f days',gregavg)"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.8: Determine_which_of_the_following_are_leap_years.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Calculation and Results\n",
"if ( modulo(1987,4) == 0. ) then\n",
"   disp('1987 is a leap year');\n",
"else\n",
"   disp('1987 is not a leap year');\n",
"end\n",
"if ( modulo(1988,4) == 0. ) then\n",
"   disp('1988 is a leap year');\n",
"else\n",
"   disp('1988 is not a leap year');\n",
"end\n",
"if ( modulo(2000,400) == 0. ) then\n",
"   disp('2000 is a leap year');\n",
"else\n",
"   disp('2000 is not a leap year');\n",
"end\n",
"if ( modulo(2100,400) == 0. ) then\n",
"   disp('2100 is a leap year');\n",
"else\n",
"   disp('2100 is not a leap year');\n",
"end"
   ]
   }
,
{
		   "cell_type": "markdown",
		   "metadata": {},
		   "source": [
			"## Example 2.9: Calculate_the_time.sce"
		   ]
		  },
  {
"cell_type": "code",
	   "execution_count": null,
	   "metadata": {
	    "collapsed": true
	   },
	   "outputs": [],
"source": [
"//Calculation\n",
"days=324   //Number of days\n",
"hours=floor(24*0.95616765)  // Number of hours\n",
"decimalfraction1=24*0.95616765-hours\n",
"minutes=floor(60*decimalfraction1)  // Number of minutes\n",
"decimalfraction2=60*decimalfraction1-minutes\n",
"seconds=60*decimalfraction2  // Number of seconds\n",
"//Result\n",
"disp(decimalfraction1)\n",
"disp(decimalfraction2)\n",
"printf('An Epoch day has %.2f days %.2f hours %.2f minutes %.2f seconds',days,hours,minutes,seconds)"
   ]
   }
],
"metadata": {
		  "kernelspec": {
		   "display_name": "Scilab",
		   "language": "scilab",
		   "name": "scilab"
		  },
		  "language_info": {
		   "file_extension": ".sce",
		   "help_links": [
			{
			 "text": "MetaKernel Magics",
			 "url": "https://github.com/calysto/metakernel/blob/master/metakernel/magics/README.md"
			}
		   ],
		   "mimetype": "text/x-octave",
		   "name": "scilab",
		   "version": "0.7.1"
		  }
		 },
		 "nbformat": 4,
		 "nbformat_minor": 0
}