diff --git a/tests/orbit_test.cpp b/tests/orbit_test.cpp
index acd12fd..4bdac15 100644
--- a/tests/orbit_test.cpp
+++ b/tests/orbit_test.cpp
@@ -66,3 +66,58 @@ TEST_CASE("orbital period", "[orbits]")
 	double T = orbitGetPeriod(a, mu);
 	REQUIRE_THAT(T, WithinAbs(37863.5, 50e-3));
 }
+
+// NOTE: example 4.1 in "Space Flight Dynamics" by Craig A. Kluever
+TEST_CASE("time of flight example 4.1 a", "[orbits]")
+{
+	double a = 26564.5;		// semi-major axis in km
+	double e = 0.7411;		// eccentricity
+	double mu = 398601.68;	// gravitational parameter
+	double r = 6378;		// body radius in km
+	system_2body sys = systemInit(gravBodyInit(mu, r), orbitInit(a, e));
+
+	// NOTE: get ToF from periapsis to true anomaly at 154.85 degrees
+	double theta_0 = 0.0;
+	double theta_1 = 154.85 * M_PI / 180;
+
+	double n = getMeanMotion(sys.body.mu, sys.ep.a);
+	REQUIRE_THAT(n, WithinAbs(0.00014582, 1e-8));
+
+	double ecc_1 = getEccAnomFromTrueAnom(sys.ep.e, theta_1);
+	REQUIRE_THAT(ecc_1, WithinAbs(2.0927, 1e-4));
+
+	// NOTE: we really want < 33ms accuracy here, but either there's floating
+	// 	point error, or the examples in the book are incorrect or just not
+	// 	precise enough
+	double tof = orbitGetTimeOfFlight(sys, theta_0, theta_1);
+	REQUIRE_THAT(tof, WithinAbs(9945.2, 0.5));
+}
+
+TEST_CASE("time of flight example 4.2", "[orbits]")
+{
+	double a = 26564.5;		// semi-major axis in km
+	double e = 0.7411;		// eccentricity
+	double mu = 398601.68;	// gravitational parameter
+	double r = 6378;		// body radius in km
+	system_2body sys = systemInit(gravBodyInit(mu, r), orbitInit(a, e));
+
+	// NOTE: get ToF from periapsis to true anomaly at 154.85 degrees
+	double theta_1 = 230 * M_PI / 180;
+	double theta_2 = 120 * M_PI / 180;
+
+	double n = getMeanMotion(mu, a);
+	REQUIRE_THAT(n, WithinAbs(0.00014582, 1e-8));
+
+	double ecc_1 = getEccAnomFromTrueAnom(e, theta_1);
+	REQUIRE_THAT(orbitClampAngle(ecc_1), WithinAbs(4.9012, 1e-4));
+
+	double M1 = getMeanAnomFromEccAnom(ecc_1, e);
+	REQUIRE_THAT(orbitClampAngle(M1), WithinAbs(5.6291, 1e-4));
+
+	double ecc_2 = getEccAnomFromTrueAnom(e, theta_2);
+	REQUIRE_THAT(orbitClampAngle(ecc_2), WithinAbs(1.1778, 1e-4));
+
+	// NOTE: see note in example 4.1 above about accuracy
+	double tof = orbitGetTimeOfFlight(sys, theta_1, theta_2);
+	REQUIRE_THAT(tof, WithinAbs(7867.5, 2 * 0.5));
+}