diff --git a/src/jat/examples/ThreeBodyExample/ThreeBodyAPL.java b/src/jat/examples/ThreeBodyExample/ThreeBodyAPL.java
index f22a529..aa379c1 100644
--- a/src/jat/examples/ThreeBodyExample/ThreeBodyAPL.java
+++ b/src/jat/examples/ThreeBodyExample/ThreeBodyAPL.java
@@ -18,16 +18,29 @@ public class ThreeBodyAPL extends ThreeBody implements FirstOrderDifferentialEqu
 	public ArrayList<Double> ysol = new ArrayList<Double>();
 	public ArrayList<Double> zsol = new ArrayList<Double>();
 	
+	/*
+	 * Why we created the ThreeBodyAPL:
+	 * The APL is responsible for computing the derivatives used in the ThreeBodyExample and interpolating data
+	 * APL stands for Applied Physics Laboratory
+	 */
+	
+	/*
+	 * What we used from existing code
+	 * The information that this class uses from the ThreeBody class are calculations for:
+	 * Masses, center of mass and energy. 
+	 * This is usefull for us because all of this is necessary for our modification
+	 */
+
 	public ThreeBodyAPL(double G, double m1, double m2, double m3) {
 		super(G, m1, m2, m3);
 	}
-
+	
 	@Override
 	public void computeDerivatives(double t, double[] y, double[] yDot) {
 		// returns the derivatives of the ThreeBody problem
 		yDot = this.derivs(t, y);
 	}
-
+	
 	@Override
 	public int getDimension() {
 		// returns a dimension of 6
diff --git a/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java b/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
index 0b5585f..cd9a912 100644
--- a/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
+++ b/src/jat/examples/ThreeBodyExample/ThreeBodyExample.java
@@ -19,6 +19,13 @@ import org.apache.commons.math3.linear.RealVectorFormat;
 import org.apache.commons.math3.ode.FirstOrderIntegrator;
 import org.apache.commons.math3.ode.nonstiff.DormandPrince853Integrator;
 
+/*
+ * We modified the ThreeBodyProblem by emulating the two body problem, and expanding it to ThreeBody
+ * Elements of two body, such as the orbit calculations, were not as heavily focused on
+ * We acknowledge that some of our calculations may be a bit inaccurate because some of the math got a bit over our heads
+ * 
+ * @author Maegan and John
+ */
 public class ThreeBodyExample {
 
 	public ThreeBodyExample() {
@@ -53,8 +60,21 @@ public class ThreeBodyExample {
 		VectorN cm = sat.center_of_mass(y);
 
 		// obtain current energy
+		
 		totalEnergy = sat.Energy(y);
-
+		/*
+		 * Notes about the calculations:
+		 * Dormand Prince is a type of Runge-Kutta diff eq. (another method of checking diff eq)
+		 * Errors are calculated looking at 4th and 5th level differential equations
+		 * These were most likely chosen by the original creator of the project because they take the error into account fairly accurately
+		 * In relation to physics, this calculates the relative orbits for the bodies
+		 * The step handler is another type of analyzing the algorithms for each body
+		 * These provide fairly accurate results
+		 * 
+		 * In general, these equations went over our heads, but refer to the NASA site as well as 
+		 * look into other resources to get more information on 3-Body calculations
+		 * 
+		 */
 		// propagate the orbit
 		FirstOrderIntegrator dp853 = new DormandPrince853Integrator(1.0e-8, 100.0, 1.0e-10, 1.0e-10);
 		dp853.addStepHandler(sat.stepHandler);