diff --git a/src/orbits.h b/src/orbits.h
index 83c41c4..5e49e2a 100644
--- a/src/orbits.h
+++ b/src/orbits.h
@@ -10,24 +10,24 @@
 
 struct EllipseParameters
 {
-	double a;	// NOTE: semi-major axis
-	double b;	// NOTE: semi-minor axis
-	double e;	// NOTE: eccentricity
-	double c;	// NOTE: linear eccentricity
-	double p;	// NOTE: semilatus rectum
-	glm::vec2 f1;	// NOTE: 'primary' focus
-	glm::vec2 f2;	// NOTE: 'vacant' focus
+	double a;		// semi-major axis
+	double b;		// semi-minor axis
+	double e;		// eccentricity
+	double c;		// linear eccentricity
+	double p;		// semilatus rectum
+	glm::vec2 f1;	// 'primary' focus
+	glm::vec2 f2;	// 'vacant' focus
 };
 
 struct OrbitalElements
 {
 	// NOTE: classical orbital elements
-	double a;		// NOTE: semimajor axis
-	double e;		// NOTE: eccentricity
-	double iota;	// NOTE: (ι) inclination
-	double ohm;		// NOTE: (Ω) longitude of the ascending node
-	double omega;	// NOTE: (ω) argument of periapsis
-	double nu;		// NOTE: (ν) true anomaly at T0
+	double a;		// semimajor axis
+	double e;		// eccentricity
+	double iota;	// (ι) inclination
+	double ohm;		// (Ω) longitude of the ascending node
+	double omega;	// (ω) argument of periapsis
+	double nu;		// (ν) true anomaly at T0
 };
 
 struct Ellipse3D
@@ -38,8 +38,8 @@ struct Ellipse3D
 
 struct GravBody
 {
-	double mu;		// NOTE: (μ) gravitational parameter
-	double radius;	// NOTE: radius of ideal sphere representing the body
+	double mu;			// (μ) gravitational parameter
+	double radius;		// radius of ideal sphere representing the body
 	// double r_atmos;	// TODO: bodies w/ atmosphere
 };
 
@@ -47,10 +47,10 @@ struct Satellite
 {
 	glm::vec3 position;
 	glm::vec3 velocity;
-	double theta;		// NOTE: true anomaly
-	double r;			// NOTE: radius magnitude at theta
-	double gamma;		// NOTE: (γ) flight path angle
-	double v;			// NOTE: velocity magnitute
+	double theta;		// true anomaly
+	double r;			// radius magnitude at theta
+	double gamma;		// (γ) flight path angle
+	double v;			// velocity magnitute
 };
 
 // NOTE: top level composite for 2 body system
@@ -62,11 +62,11 @@ struct TwoBodySystem
 	Ellipse3D e3d;
 	OrbitalElements elements;
 
-	double epsilon;			// NOTE: (ε) specific orbital energy, MJ/kg
-	double h;				// NOTE: angular momentum
-	double r_apoapsis;		// NOTE: apoapse distance from body center
-	double r_periapsis;		// NOTE: periapsis distance from body center
-	double orbital_period;	// NOTE: in seconds
+	double epsilon;			// (ε) specific orbital energy, MJ/kg
+	double h;				// angular momentum
+	double r_apoapsis;		// apoapse distance from body center
+	double r_periapsis;		// periapsis distance from body center
+	double orbital_period;	// in seconds
 };
 
 
@@ -110,7 +110,7 @@ ellipsesEqual(EllipseParameters& e1, EllipseParameters& e2)
 }
 
 // NOTE: create vertices for a 3d ellipse
-// NOTE: all vertices are in the x/y plane with z = 0
+// 	all vertices are in the x/y plane with z = 0
 Ellipse3D
 ellipseInit3D(EllipseParameters ep, uint vert_count);
 
@@ -227,7 +227,7 @@ orbitUpdate(OrbitalElements& o, double a, double e);
 double
 getPropagatedTrueAnomaly(TwoBodySystem sys,
 	double initial_anom,
-	double time_step);	// NOTE: in seconds
+	double time_step);	// in seconds
 
 double
 orbitGetTimeOfFlight(TwoBodySystem sys, double theta_begin, double theta_end);