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+## Fiddlin' John Carson (22 points)
+### Category: "Guardians of the…"
+
+After connecting to the challenge server we are greeted with this:
+```
+         KEPLER        
+        CHALLANGE      
+       a e i Ω ω υ     
+            .  .       
+        ,'   ,=,  .    
+      ,    /     \  .  
+     .    |       | .  
+    .      \     / .   
+    +        '='  .    
+     .          .'     
+      .     . '        
+         '             
+Your spacecraft reports that its Cartesian ICRF position (km) and velocity (km/s) are:
+Pos (km):   [8449.401305, 9125.794363, -17.461357]
+Vel (km/s): [-1.419072, 6.780149, 0.002865]
+Time:       2021-06-26-19:20:00.000-UTC
+
+What is its orbit (expressed as Keplerian elements a, e, i, Ω, ω, and υ)?
+Semimajor axis, a (km): 
+Eccentricity, e: 
+Inclination, i (deg): 
+Right ascension of the ascending node, Ω (deg): 
+Argument of perigee, ω (deg): 
+True anomaly, υ (deg): 
+
+That didn't work, try again!
+```
+
+So, given a position vector and velocity vector we need to find the [Keplerian elements](https://en.wikipedia.org/wiki/Orbital_elements) to describe the orbit
+
+[This site]([https://elainecoe.github.io/orbital-mechanics-calculator/calculator.html](https://elainecoe.github.io/orbital-mechanics-calculator/calculator.html "https://elainecoe.github.io/orbital-mechanics-calculator/calculator.html") has a calculator that allows you to convert Cartesian position and velocity vectors to the respective orbital elements.
+
+![keplerian](images/keplerian.png "Keplerian elements")
+
+Plugging those in, we get:
+
+```
+         KEPLER        
+        CHALLANGE      
+       a e i Ω ω υ     
+            .  .       
+        ,'   ,=,  .    
+      ,    /     \  .  
+     .    |       | .  
+    .      \     / .   
+    +        '='  .    
+     .          .'     
+      .     . '        
+         '             
+Your spacecraft reports that its Cartesian ICRF position (km) and velocity (km/s) are:
+Pos (km):   [8449.401305, 9125.794363, -17.461357]
+Vel (km/s): [-1.419072, 6.780149, 0.002865]
+Time:       2021-06-26-19:20:00.000-UTC
+
+What is its orbit (expressed as Keplerian elements a, e, i, Ω, ω, and υ)?
+Semimajor axis, a (km): 24732.96738133805
+Eccentricity, e: 0.7068077979296534
+Inclination, i (deg): 0.11790360842507447
+Right ascension of the ascending node, Ω (deg): 90.22650379956278
+Argument of perigee, ω (deg): 226.58754885495142
+True anomaly, υ (deg): 90.38986518838934
+
+You got it! Here's your flag:
+```
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