diff --git a/src/orbital_mechanics.cpp b/src/orbital_mechanics.cpp
index 1833161..9258ba7 100644
--- a/src/orbital_mechanics.cpp
+++ b/src/orbital_mechanics.cpp
@@ -89,7 +89,23 @@ double solve_kepler_hyperbolic(double mean_anomaly, double eccentricity) {
 }
 
 double eccentric_to_true_anomaly(double eccentric_anomaly, double eccentricity) {
-    // E to true anomaly conversion: tan(ν/2) = √((1+e)/(1-e)) · tan(E/2)
+    if (fabs(1.0 - eccentricity) < 0.01) {
+        double E = eccentric_anomaly;
+        double e = eccentricity;
+
+        double cos_E = cos(E);
+        double sin_E = sin(E);
+        double denominator = 1.0 - e * cos_E;
+
+        double cos_nu = (cos_E - e) / denominator;
+        double sin_nu = sin_E * sqrt(1.0 - e * e) / denominator;
+
+        cos_nu = fmax(-1.0, fmin(1.0, cos_nu));
+        sin_nu = fmax(-1.0, fmin(1.0, sin_nu));
+
+        return atan2(sin_nu, cos_nu);
+    }
+
     double tan_half_E = tan(eccentric_anomaly / 2.0);
     double tan_half_nu = sqrt((1.0 + eccentricity) / (1.0 - eccentricity)) * tan_half_E;
     return 2.0 * atan(tan_half_nu);