diff --git a/src/game.cpp b/src/game.cpp
index fed9c46..534e9c8 100644
--- a/src/game.cpp
+++ b/src/game.cpp
@@ -211,23 +211,33 @@ testManeuverStep(const ManeuverNode& maneuver,
 }
 
 void
-applyManeuver(GameOrbit* orbit)
+applyManeuver(GameOrbit* orbit, double previous_true_anomaly)
 {
-	LOGF(Debug, "applying maneuver\n");
+	const ManeuverNode& node = orbit->maneuver;
+	TwoBodySystem& sys = orbit->system;
+
+	LOGF(Debug, "applying maneuver,\n"
+			"theta: %f\n,"
+			"dv: %f,\n"
+			"sat.theta: %f,\n"
+			"previous theta: %f\n",
+			node.true_anomaly,
+			node.impulse_delta_v,
+			sys.sat.theta,
+			previous_true_anomaly);
 
 	// FIXME: assuming prograde impulse vector
-	assert(orbit->maneuver.impulse_type == ImpulseType::PROGRADE);
+	assert(node.impulse_type == ImpulseType::PROGRADE);
 
 	// re-calculate state vectors at the maneuver node
-	TwoBodySystem& sys = orbit->system;
-	double theta = orbit->maneuver.true_anomaly;
+	double theta = node.true_anomaly;
 	double mu = sys.body.mu;
 	double r = orbitGetRadialDistance(sys.ep.e, sys.ep.p, theta);
 	double v = orbitGetVelocity(sys.epsilon, mu, r);
 	double gamma = orbitGetFlightPathAngle(sys.ep.e, theta);
 
 	// calculate new satellite state vectors
-	v += orbit->maneuver.impulse_delta_v; // prograde only
+	v += node.impulse_delta_v; // prograde only
 
 	// get new angular momentum and specific orbital energy
 	double h = orbitGetAngularMomentumFromStateVectors(r, v, gamma);
diff --git a/src/game.h b/src/game.h
index b69a390..1a3f3e2 100644
--- a/src/game.h
+++ b/src/game.h
@@ -98,4 +98,4 @@ bool testManeuverStep(const ManeuverNode& maneuver,
 		double previous_theta,
 		double next_theta);
 
-void applyManeuver(GameOrbit* orbit);
+void applyManeuver(GameOrbit* orbit, double previous_true_anomaly);