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--- course_planning:183_projects:s23_week_3_geostationary_orbit [2023/01/25 17:42] – hallstein
+++ course_planning:183_projects:s23_week_3_geostationary_orbit [2023/01/25 18:06] – hallstein
@@ Line 192: / Line 192: @@
   * **Question:**  How can you prove that the orbit is actually circular?
   * **Expected Answer:**
-Aside from just eyeballing it, we can add in a graph of the distance from the center of Earth!
+Aside from just eyeballing it, we can add in a graph of the distance from the center of Earth! (Moved to separate part C of the problem)
 <code python>
 #MotionMap/Graph
@@ Line 232: / Line 232: @@
 </WRAP>
-<code python satellite.sol.py>
+Working code for part B:
+<code>
 GlowScript 2.9 VPython
 get_library('https://cdn.rawgit.com/PERLMSU/physutil/master/js/physutil.js')
 #Window setup
 scene.range=7e7
 scene.width = 1024
 scene.height = 760
 #Objects
 Earth = sphere(pos=vector(0,0,0), radius=6.4e6, color=color.blue)
-Satellite = sphere(pos=vector(42164e3, 0,0), radius=1e6, color=color.red, make_trail=True)
+Satellite = sphere(pos=vector(42164e3, 0,0), radius=1e6, color=color.red, make_trail=True)   #modify position of satellite
 #Parameters and Initial Conditions
-mSatellite = 15e3
+mSatellite = 15e3   # edit mass of the satellite
-pSatellite = mSatellite*vector(0,3073,0)
+pSatellite = mSatellite*vector(0,3073,0) #edit momentum of the satellite
-G = 6.67e-11
+G = 6.67e-11   # add universal gravitational constant
-mEarth = 5.97e24
+mEarth = 5.97e24  # add mass of Earth
 #Time and time step
 t = 0
 tf = 60*60*24
 dt = 1
 #MotionMap/Graph
 SatelliteMotionMap = MotionMap(Satellite, tf, 20, markerScale=2000, labelMarkerOrder=False)
-FnetMotionMap = MotionMap(Satellite, tf, 20, markerScale=2000, labelMarkerOrder=False)
+FnetMotionMap = MotionMap(Satellite, tf, 20, markerScale=2000, labelMarkerOrder=False)   # add Fnet force arrows - also need to add in loop)
-#separationGraph = PhysGraph(numPlots=1)
-f1=series()
 #Calculation Loop
 while t < tf:
     rate(10000)
-    Fgrav = -G*mSatellite*mEarth*Satellite.pos/(mag(Satellite.pos)**3)
+    Fgrav = -G*mSatellite*mEarth*Satellite.pos/(mag(Satellite.pos)**3) # Add Fgrav change Fnet
-    Fnet = Fgrav
+    Fnet = Fgrav                                                       # change Fnet from zero
     pSatellite = pSatellite + Fnet*dt
     Satellite.pos = Satellite.pos + (pSatellite/mSatellite)*dt
     SatelliteMotionMap.update(t, pSatellite/mSatellite)
-    FnetMotionMap.update(t, Fnet)
+    FnetMotionMap.update(t, Fnet)  # Add Fnet vector arrows
-    #separationGraph.plot(t,mag(mSatellite))
-    f1.plot(t,mag(Satellite.pos))
     t = t + dt
     #Earth Rotation (IGNORE)
     theta = 7.29e-5*dt
     Earth.rotate(angle=theta, axis=vector(0,0,1), origin=Earth.pos)
 </code>