From 216744ceb34cd6d62c82d9780fe9e534afeade27 Mon Sep 17 00:00:00 2001 From: Satoshi Ikari Date: Sat, 20 Jul 2024 14:56:30 +0900 Subject: [PATCH] Fix test --- .../numerical_integration/test_runge_kutta.cpp | 16 ++++++++-------- 1 file changed, 8 insertions(+), 8 deletions(-) diff --git a/src/math_physics/numerical_integration/test_runge_kutta.cpp b/src/math_physics/numerical_integration/test_runge_kutta.cpp index fd2438ec6..376406850 100644 --- a/src/math_physics/numerical_integration/test_runge_kutta.cpp +++ b/src/math_physics/numerical_integration/test_runge_kutta.cpp @@ -416,8 +416,8 @@ TEST(NUMERICAL_INTEGRATION, Integrate2dTwoBodyOrbitSmallEccentricity) { initial_position[1] = initial_state[1]; initial_velocity[0] = initial_state[2]; initial_velocity[1] = initial_state[3]; - OrbitalElements oe(1.0, 0.0, initial_position, initial_velocity); - KeplerOrbit kepler(1.0, oe); + orbit::OrbitalElements oe(1.0, 0.0, initial_position, initial_velocity); + orbit::KeplerOrbit kepler(1.0, oe); kepler.CalcOrbit((double)(step_num * step_width_s) / (24.0 * 60.0 * 60.0)); double error_tolerance = 2e-4; @@ -486,8 +486,8 @@ TEST(NUMERICAL_INTEGRATION, Integrate2dTwoBodyOrbitLargeEccentricity) { initial_position[1] = initial_state[1]; initial_velocity[0] = initial_state[2]; initial_velocity[1] = initial_state[3]; - OrbitalElements oe(1.0, 0.0, initial_position, initial_velocity); - KeplerOrbit kepler(1.0, oe); + orbit::OrbitalElements oe(1.0, 0.0, initial_position, initial_velocity); + orbit::KeplerOrbit kepler(1.0, oe); kepler.CalcOrbit((double)(step_num * step_width_s) / (24.0 * 60.0 * 60.0)); double error_tolerance = 2e-1; @@ -551,8 +551,8 @@ TEST(NUMERICAL_INTEGRATION, Interpolation2dTwoBodyOrbitSmallEccentricity) { initial_position[1] = initial_state[1]; initial_velocity[0] = initial_state[2]; initial_velocity[1] = initial_state[3]; - OrbitalElements oe(1.0, 0.0, initial_position, initial_velocity); - KeplerOrbit kepler(1.0, oe); + orbit::OrbitalElements oe(1.0, 0.0, initial_position, initial_velocity); + orbit::KeplerOrbit kepler(1.0, oe); kepler.CalcOrbit((double)(step_num * step_width_s) / (24.0 * 60.0 * 60.0)); double error_tolerance = 5e-2; @@ -646,8 +646,8 @@ TEST(NUMERICAL_INTEGRATION, Interpolation2dTwoBodyOrbitLargeEccentricity) { initial_position[1] = initial_state[1]; initial_velocity[0] = initial_state[2]; initial_velocity[1] = initial_state[3]; - OrbitalElements oe(1.0, 0.0, initial_position, initial_velocity); - KeplerOrbit kepler(1.0, oe); + orbit::OrbitalElements oe(1.0, 0.0, initial_position, initial_velocity); + orbit::KeplerOrbit kepler(1.0, oe); kepler.CalcOrbit((double)(step_num * step_width_s) / (24.0 * 60.0 * 60.0)); double error_tolerance = 1e-5;