diff --git a/src/main.cpp b/src/main.cpp
index 20f247d..aca618e 100644
--- a/src/main.cpp
+++ b/src/main.cpp
@@ -184,7 +184,7 @@ updateSatelliteModel(const TwoBodySystem& sys,
 	Satellite& sat,
 	double time_step)
 {
-	sat.theta = getPropagatedTrueAnomaly(sys, sat.theta, time_step);
+	sat.theta = orbitGetPropagatedTrueAnomaly(sys, sat.theta, time_step);
 	sat.gamma = orbitGetFlightPathAngle(sys.ep.e, sat.theta);
 	sat.r = orbitGetRadialDistance(sys.ep.e, sys.ep.p, sat.theta);
 	sat.v = orbitGetVelocity(sys.epsilon, sys.body.mu, sat.r);
diff --git a/src/orbits.cpp b/src/orbits.cpp
index b5e0560..abb7426 100644
--- a/src/orbits.cpp
+++ b/src/orbits.cpp
@@ -178,7 +178,7 @@ getPropagatedEccAnomaly(TwoBodySystem sys,
 }
 
 double
-getPropagatedTrueAnomaly(TwoBodySystem sys,
+orbitGetPropagatedTrueAnomaly(TwoBodySystem sys,
 	double initial_anom,
 	double time_step)
 {
diff --git a/src/orbits.h b/src/orbits.h
index 5e49e2a..0c145cc 100644
--- a/src/orbits.h
+++ b/src/orbits.h
@@ -225,7 +225,7 @@ orbitUpdate(OrbitalElements& o, double a, double e);
  *			tan(ϴ2/2) = sqrt((1+e) / (1-e)) * tan(E2/2)
  */
 double
-getPropagatedTrueAnomaly(TwoBodySystem sys,
+orbitGetPropagatedTrueAnomaly(TwoBodySystem sys,
 	double initial_anom,
 	double time_step);	// in seconds