She did. Now I'm done!

LaTeX/results.tex

@@ -1,31 +1,29 @@
-\chapter{Sample Saturn Trajectory Analysis} \label{results}
+\chapter{Application: Designing a Trajectory To Saturn} \label{results}
 
-	The algorithm described in this thesis is quite flexible in its design and could be used as
-	a tool for a mission designer on a variety of different mission types. However, to consider
-	a relatively simple but representative mission design objective, a sample mission to Saturn
-	was investigated.
+	To consider a relatively simple but representative mission design objective, a sample mission to
+	Saturn was investigated.
 
-	\section{Mission Constraints}
+	\section{Mission Scenario}
 
-		The sample mission was defined to represent a general case for a near-future low-thrust
-		trajectory to Saturn. No constraints were placed on the flyby planets, but a number of
+		The sample mission is defined to represent a general case for a near-future low-thrust
+		trajectory to Saturn. No constraints are placed on the flyby planets, but a number of
 		constraints were placed on the algorithm to represent a realistic mission scenario. 
 
 		The first choice required by the application is one not necessarily designable to the
-		initial mission designer (though not necessarily fixed in the design either) and is that
-		of the spacecraft parameters. The application accepts as input a spacecraft object
-		containing: the dry mass of the craft, the fuel mass at launch, the number of onboard
-		thrusters, and the specific impulse, maximum thrust and duty cycle of each thruster.
+		initial mission designer (though not necessarily fixed in the design either) and is that of
+		the spacecraft parameters. The application accepts as input a spacecraft object containing:
+		the dry mass of the spacecraft, the fuel mass at launch, the number of onboard thrusters,
+		and the specific impulse, maximum thrust and duty cycle of each thruster.
 
-		For this mission, the spacecraft was chosen to have a dry mass of only 200 kilograms for
-		a fuel mass of 3300 kilograms. This was chosen in order to have an overall mass roughly
-		in the same zone as that of the Cassini spacecraft, which launched with 5712 kilograms
-		of total mass, with the fuel accounting for 2978 of those kilograms\cite{cassini}. The
-		dry mass of the craft was chosen to be extremely low in order to allow for a variety of
-		''successful`` missions in which the craft didn't run out of fuel. That way, the
-		delivered dry mass to Saturn could be thought of as a metric of success, without
-		discounting mission that may have delivered just under whatever more realistic dry mass
-		one might set, in case those missions are in the vicinity of actually valid missions.
+		For this mission, the spacecraft was chosen to have a dry mass of only 200 kilograms for a
+		fuel mass of 3300 kilograms. This was chosen in order to have an overall mass roughly in the
+		same zone as that of the Cassini spacecraft, which launched with 5712 kilograms of total
+		mass, with the fuel accounting for 2978 of those kilograms\cite{cassini}. The dry mass of
+		the spacecraft was chosen to be extremely low in order to allow for a variety of
+		''successful`` missions in which the spacecraft didn't run out of fuel. That way, the
+		delivered dry mass to Saturn could be thought of as a metric of success, without discounting
+		mission that may have delivered just under whatever more realistic dry mass one might set,
+		in case those missions are in the vicinity of actually valid missions.
 
 		The thruster was chosen to have a specific impulse of 3200 seconds, a maximum thrust of
 		250 millinewtons, and a 100\% duty cycle. This puts the thruster roughly in line with
@@ -308,6 +306,6 @@
 			\centering
 			\includegraphics[width=\textwidth]{fig/c3}
 			\caption{Plot of Delta IV and Atlas V launch vehicle capabilities as they relate to
-			payload mass \cite{c3capabilities} from a source from 2007}
+			payload mass \cite{c3capabilities} from Vardaxis, et al, 2007 }
 			\label{c3}
 		\end{figure}