cinnaboot
/
claudes_game
1
0
Fork 0
Code Issues Pull Requests Projects Releases Wiki Activity
Browse Source

refactor: test_extreme_orientation_mixed — single SCENARIO, precalculated values, named tolerances

test-refactor
cinnaboot 2 months ago
parent
c46211cee0
commit
a7ecc46f15
4 changed files with 423 additions and 1 deletions
Whitespace
Show all changes Ignore whitespace when comparing lines Ignore changes in amount of whitespace Ignore changes in whitespace at EOL
Split View
Diff Options
Show Stats Download Patch File Download Diff File
  1. 2
      continue.md
  2. 56
      scripts/precalc_extreme_orientation_mixed.py
  3. 328
      tests/test_extreme_orientation_mixed.cpp
  4. 38
      tests/test_extreme_orientation_mixed.toml

2
continue.md
Unescape View File

@ -114,9 +114,9 @@
- `test_cartesian_to_elements_advanced` ✅ — Advanced conversion tests (eccentricity spectrum, inclination, true anomaly, 3D orientation)
- `test_cartesian_to_elements_basic` ✅ — Element round-trip conversion (semi-major axis, eccentricity, true anomaly, inclination, radius, velocity)
- `test_parabolic_orbit` ✅ — Parabolic orbit energy conservation + escape trajectory + initial conditions
- `test_extreme_eccentricity` ✅ — High-eccentricity orbits (single SCENARIO, precalculated values, REL_TOL)
### Can Refactor Now (sim_engine.py supports all features needed)
- `test_extreme_eccentricity` — high-eccentricity orbits
- `test_extreme_orientation_mixed` — extreme inclinations/eccentricities
- `test_extreme_timescales` — various timescales
- `test_analytical_propagation` — propagation through apsides

56
scripts/precalc_extreme_orientation_mixed.py
Unescape View File

@ -0,0 +1,56 @@
#!/usr/bin/env python3
"""Precalculate expected values for test_extreme_orientation_mixed."""
import sys
import os
import math
sys.path.insert(0, os.path.dirname(os.path.abspath(__file__)))
import sim_engine
from sim_engine import Simulator
# Load config via sim_engine (TOML 1.0 parsing + spacecraft initialization)
sim = Simulator("tests/test_extreme_orientation_mixed.toml", dt=60.0)
mu = 6.67430e-11 * 5.972e24 # Earth's gravitational parameter
print(f"# mu = {mu:.6f} m^3/s^2")
print()
for i, craft in enumerate(sim.spacecraft):
a = craft.orbit.a
e = craft.orbit.e
name = craft.name
print(f"# Spacecraft {i}: {name} (a={a}, e={e})")
# Periapsis (nu=0)
r_peri = a * (1.0 - e)
v_peri = math.sqrt(mu * (2.0/r_peri - 1.0/a))
print(f"# nu=0: r={r_peri:.6e} m, v={v_peri:.6f} m/s")
# Apoapsis (nu=pi)
if e < 1.0:
r_apo = a * (1.0 + e)
v_apo = math.sqrt(mu * (2.0/r_apo - 1.0/a))
print(f"# nu=pi: r={r_apo:.6e} m, v={v_apo:.6f} m/s")
# nu=pi/2
r_nu90 = a * (1.0 - e*e) / (1.0 + e * math.cos(math.pi/2))
v_nu90 = math.sqrt(mu * (2.0/r_nu90 - 1.0/a))
print(f"# nu=pi/2: r={r_nu90:.6e} m, v={v_nu90:.6f} m/s")
# nu=3pi/2
r_nu270 = a * (1.0 - e*e) / (1.0 + e * math.cos(3*math.pi/2))
v_nu270 = math.sqrt(mu * (2.0/r_nu270 - 1.0/a))
print(f"# nu=3pi/2: r={r_nu270:.6e} m, v={v_nu270:.6f} m/s")
# Round-trip check: convert to cartesian and back
parent_mass = mu / 6.67430e-11
pos, vel = sim_engine.orbital_to_cartesian(craft.orbit, parent_mass)
recovered = sim_engine.cartesian_to_orbital_elements(pos, vel, parent_mass)
print(f"# round-trip: e_err={abs(recovered.e - e):.2e}, "
f"i_err={abs(recovered.inc - craft.orbit.inc):.2e}, "
f"O_err={abs(recovered.Omega - craft.orbit.Omega):.2e}, "
f"w_err={abs(recovered.omega - craft.orbit.omega):.2e}")
print()

328
tests/test_extreme_orientation_mixed.cpp
Unescape View File

@ -0,0 +1,328 @@
#include <catch2/catch_test_macros.hpp>
#include <catch2/matchers/catch_matchers_floating_point.hpp>
#include "../src/physics.h"
#include "../src/orbital_mechanics.h"
#include "../src/simulation.h"
#include "../src/config_loader.h"
#include <cmath>
#include <array>
using Catch::Matchers::WithinAbs;
SCENARIO("Extreme orientation conversion accuracy and rotation matrix properties",
"[extreme][orientation][mixed]") {
const double TIME_STEP = 60.0;
const double parent_mass = 5.972e24;
const double mu = G * parent_mass;
SimulationState* sim = create_simulation(10, 5, 0, TIME_STEP);
REQUIRE(load_system_config(sim, "tests/test_extreme_orientation_mixed.toml"));
Spacecraft* sc0 = &sim->spacecraft[0];
Spacecraft* sc1 = &sim->spacecraft[1];
Spacecraft* sc2 = &sim->spacecraft[2];
Spacecraft* sc3 = &sim->spacecraft[3];
Spacecraft* sc4 = &sim->spacecraft[4];
// Tolerances
const double R_TOL = 1e-6;
const double V_TOL = 1e-6;
const double E_TOL = 1e-12;
const double ANG_TOL = 1e-12;
const double REL_TOL = 1e-8;
const double VDOT_TOL = 1e-3;
const double MAT_TOL = 1e-10;
// Precomputed periapsis radii
const double r_peri0 = sc0->orbit.semi_major_axis * (1.0 - sc0->orbit.eccentricity); // 7.5e6
const double r_peri1 = sc1->orbit.semi_major_axis * (1.0 - sc1->orbit.eccentricity); // 1.0e7
const double r_peri2 = sc2->orbit.semi_major_axis * (1.0 - sc2->orbit.eccentricity); // 7.0e6
const double r_peri3 = sc3->orbit.semi_major_axis * (1.0 - sc3->orbit.eccentricity); // 8.0e6
const double r_peri4 = sc4->orbit.semi_major_axis * (1.0 - sc4->orbit.eccentricity); // 8.0e6
// Precomputed apoapsis radii (elliptical only)
const double r_apo0 = sc0->orbit.semi_major_axis * (1.0 + sc0->orbit.eccentricity); // 9.25e7
const double r_apo1 = sc1->orbit.semi_major_axis * (1.0 + sc1->orbit.eccentricity); // 3.0e7
const double r_apo2 = sc2->orbit.semi_major_axis * (1.0 + sc2->orbit.eccentricity); // 1.393e9
// Helper: convert elements to cartesian at given true anomaly
auto convert_at_nu = [&](Spacecraft* craft, double nu) {
craft->orbit.true_anomaly = nu;
orbital_elements_to_cartesian(craft->orbit, parent_mass, &craft->local_position, &craft->local_velocity);
};
// Helper: vis-viva check
auto check_visviva = [&](double r, double v, double a) {
const double expected_v_sq = mu * (2.0 / r - 1.0 / a);
// Safety: expected_v_sq must be positive for sqrt (guaranteed for all elliptical orbits)
REQUIRE(expected_v_sq > 0.0);
const double expected_v = sqrt(expected_v_sq);
const double rel_err = fabs(v - expected_v) / expected_v;
INFO("v=" << v << " m/s, v_exp=" << expected_v << " m/s, rel_err=" << rel_err);
REQUIRE_THAT(rel_err, WithinAbs(0.0, REL_TOL));
};
// Helper: round-trip check
auto roundtrip = [&](double a, double e, double nu, double inc, double O, double w) {
OrbitalElements elements = {};
elements.semi_major_axis = a;
elements.eccentricity = e;
elements.true_anomaly = nu;
elements.inclination = inc;
elements.longitude_of_ascending_node = O;
elements.argument_of_periapsis = w;
Vec3 pos, vel;
orbital_elements_to_cartesian(elements, parent_mass, &pos, &vel);
OrbitalElements recovered = cartesian_to_orbital_elements(pos, vel, parent_mass);
return recovered;
};
SECTION("periapsis position for extreme orbits") {
convert_at_nu(sc0, 0.0);
const double r0 = vec3_magnitude(sc0->local_position);
const double v0 = vec3_magnitude(sc0->local_velocity);
INFO("sc0 (i=1.2, e=0.85): r=" << r0 << " m, v=" << v0 << " m/s");
REQUIRE_THAT(r0, WithinAbs(r_peri0, R_TOL));
check_visviva(r0, v0, sc0->orbit.semi_major_axis);
convert_at_nu(sc1, 0.0);
const double r1 = vec3_magnitude(sc1->local_position);
const double v1 = vec3_magnitude(sc1->local_velocity);
INFO("sc1 (i=1.4, e=0.5): r=" << r1 << " m, v=" << v1 << " m/s");
REQUIRE_THAT(r1, WithinAbs(r_peri1, R_TOL));
check_visviva(r1, v1, sc1->orbit.semi_major_axis);
convert_at_nu(sc2, 0.0);
const double r2 = vec3_magnitude(sc2->local_position);
const double v2 = vec3_magnitude(sc2->local_velocity);
INFO("sc2 (i=0.5, e=0.99): r=" << r2 << " m, v=" << v2 << " m/s");
REQUIRE_THAT(r2, WithinAbs(r_peri2, R_TOL));
check_visviva(r2, v2, sc2->orbit.semi_major_axis);
}
SECTION("velocity at apsides for extreme orbits") {
// sc0 at periapsis
convert_at_nu(sc0, 0.0);
const double v0p = vec3_magnitude(sc0->local_velocity);
convert_at_nu(sc0, M_PI);
const double v0a = vec3_magnitude(sc0->local_velocity);
INFO("sc0: v_peri=" << v0p << " m/s, v_apo=" << v0a << " m/s");
REQUIRE_THAT(v0p, WithinAbs(9915.577056, V_TOL));
REQUIRE_THAT(v0a, WithinAbs(803.965707, V_TOL));
// sc1 at periapsis
convert_at_nu(sc1, 0.0);
const double v1p = vec3_magnitude(sc1->local_velocity);
convert_at_nu(sc1, M_PI);
const double v1a = vec3_magnitude(sc1->local_velocity);
INFO("sc1: v_peri=" << v1p << " m/s, v_apo=" << v1a << " m/s");
REQUIRE_THAT(v1p, WithinAbs(7732.294575, V_TOL));
REQUIRE_THAT(v1a, WithinAbs(2577.431525, V_TOL));
// sc2 at periapsis
convert_at_nu(sc2, 0.0);
const double v2p = vec3_magnitude(sc2->local_velocity);
convert_at_nu(sc2, M_PI);
const double v2a = vec3_magnitude(sc2->local_velocity);
INFO("sc2: v_peri=" << v2p << " m/s, v_apo=" << v2a << " m/s");
REQUIRE_THAT(v2p, WithinAbs(10644.867979, V_TOL));
REQUIRE_THAT(v2a, WithinAbs(53.491799, V_TOL));
}
SECTION("apoapsis position for extreme orbits") {
convert_at_nu(sc0, M_PI);
const double r0 = vec3_magnitude(sc0->local_position);
INFO("sc0: r_apo=" << r0 << " m, expected=" << r_apo0 << " m");
REQUIRE_THAT(r0, WithinAbs(r_apo0, R_TOL));
convert_at_nu(sc1, M_PI);
const double r1 = vec3_magnitude(sc1->local_position);
INFO("sc1: r_apo=" << r1 << " m, expected=" << r_apo1 << " m");
REQUIRE_THAT(r1, WithinAbs(r_apo1, R_TOL));
convert_at_nu(sc2, M_PI);
const double r2 = vec3_magnitude(sc2->local_position);
INFO("sc2: r_apo=" << r2 << " m, expected=" << r_apo2 << " m");
REQUIRE_THAT(r2, WithinAbs(r_apo2, R_TOL));
}
SECTION("vis-viva accuracy at multiple true anomalies") {
const std::array<double, 4> true_anomalies = {0.0, M_PI / 2.0, M_PI, 3.0 * M_PI / 2.0};
for (int i = 0; i < 5; i++) {
Spacecraft* craft = &sim->spacecraft[i];
const double a = craft->orbit.semi_major_axis;
const double e = craft->orbit.eccentricity;
INFO("Spacecraft " << i << ": e=" << e << ", a=" << a);
for (int j = 0; j < 4; j++) {
double nu = true_anomalies[j];
craft->orbit.true_anomaly = nu;
Vec3 pos, vel;
orbital_elements_to_cartesian(craft->orbit, parent_mass, &pos, &vel);
const double r = vec3_magnitude(pos);
const double v = vec3_magnitude(vel);
const double expected_v_sq = mu * (2.0 / r - 1.0 / a);
// All spacecraft have elliptical orbits (e < 1), so vis-viva always yields v² > 0
const double expected_v = sqrt(expected_v_sq);
const double rel_err = fabs(v - expected_v) / expected_v;
INFO(" nu=" << nu << " rad: v=" << v << " m/s, rel_err=" << rel_err);
REQUIRE_THAT(rel_err, WithinAbs(0.0, REL_TOL));
}
}
}
SECTION("apsidal velocity orthogonality") {
const std::array<double, 2> apsides = {0.0, M_PI};
for (int i = 0; i < 5; i++) {
Spacecraft* craft = &sim->spacecraft[i];
INFO("Spacecraft " << i << ": e=" << craft->orbit.eccentricity
<< ", i=" << craft->orbit.inclination << " rad");
for (int j = 0; j < 2; j++) {
craft->orbit.true_anomaly = apsides[j];
Vec3 pos, vel;
orbital_elements_to_cartesian(craft->orbit, parent_mass, &pos, &vel);
const double pos_dot_vel = vec3_dot(pos, vel);
const double h = vec3_magnitude(vec3_cross(pos, vel));
INFO(" nu=" << apsides[j] << " rad: pos·vel=" << pos_dot_vel << ", |h|=" << h);
REQUIRE_THAT(pos_dot_vel, WithinAbs(0.0, VDOT_TOL));
// Angular momentum must be non-zero for a valid orbit
REQUIRE(h > 0.0);
}
}
}
SECTION("Omega=0 singularity handling") {
convert_at_nu(sc3, 0.0);
const double r = vec3_magnitude(sc3->local_position);
INFO("sc3 (Omega=0): r=" << r << " m");
INFO(" pos=(" << sc3->local_position.x << ", " << sc3->local_position.y << ", " << sc3->local_position.z << ")");
Vec3 pos, vel;
orbital_elements_to_cartesian(sc3->orbit, parent_mass, &pos, &vel);
// Rotation matrix at Omega=0 must produce a valid position in the x-y plane
REQUIRE(pos.x > 0.0);
REQUIRE_THAT(r, WithinAbs(r_peri3, R_TOL));
const double h = vec3_magnitude(vec3_cross(pos, vel));
INFO(" |h|=" << h);
// Angular momentum must be non-zero for a valid orbit
REQUIRE(h > 0.0);
}
SECTION("Arg_peri=0 singularity handling") {
convert_at_nu(sc4, 0.0);
const double r = vec3_magnitude(sc4->local_position);
INFO("sc4 (w=0): r=" << r << " m, expected=" << r_peri4 << " m");
REQUIRE_THAT(r, WithinAbs(r_peri4, R_TOL));
const std::array<double, 4> true_anomalies = {0.0, M_PI / 2.0, M_PI, 3.0 * M_PI / 2.0};
const std::array<double, 4> expected_r = {8.0e6, 1.44e7, 7.2e7, 1.44e7};
const std::array<double, 4> expected_v = {9470.088125, 6737.572312, 1052.232014, 6737.572312};
for (int j = 0; j < 4; j++) {
sc4->orbit.true_anomaly = true_anomalies[j];
Vec3 pos, vel;
orbital_elements_to_cartesian(sc4->orbit, parent_mass, &pos, &vel);
const double r_j = vec3_magnitude(pos);
const double v_j = vec3_magnitude(vel);
INFO(" nu=" << true_anomalies[j] << " rad: r=" << r_j << " m, v=" << v_j << " m/s");
REQUIRE_THAT(r_j, WithinAbs(expected_r[j], R_TOL));
REQUIRE_THAT(v_j, WithinAbs(expected_v[j], V_TOL));
}
}
SECTION("round-trip conversion accuracy") {
const std::array<Spacecraft*, 5> crafts = {sc0, sc1, sc2, sc3, sc4};
for (int i = 0; i < 5; i++) {
const Spacecraft* craft = crafts[i];
const double a = craft->orbit.semi_major_axis;
const double e = craft->orbit.eccentricity;
const double inc = craft->orbit.inclination;
const double O = craft->orbit.longitude_of_ascending_node;
const double w = craft->orbit.argument_of_periapsis;
INFO("Spacecraft " << i << ": " << craft->name);
const OrbitalElements recovered = roundtrip(a, e, 0.0, inc, O, w);
INFO(" e: " << e << " -> " << recovered.eccentricity);
INFO(" i: " << inc << " -> " << recovered.inclination);
INFO(" a: " << a << " -> " << recovered.semi_major_axis);
REQUIRE_THAT(recovered.semi_major_axis, WithinAbs(a, fabs(a) * 0.01));
REQUIRE_THAT(recovered.eccentricity, WithinAbs(e, E_TOL));
REQUIRE_THAT(recovered.inclination, WithinAbs(inc, ANG_TOL));
if (O > 1e-6 || O < -1e-6) {
REQUIRE_THAT(recovered.longitude_of_ascending_node, WithinAbs(O, ANG_TOL));
}
if (w > 1e-6 || w < -1e-6) {
REQUIRE_THAT(recovered.argument_of_periapsis, WithinAbs(w, ANG_TOL));
}
// Round-trip preserves position and velocity
Vec3 pos, vel;
orbital_elements_to_cartesian(recovered, parent_mass, &pos, &vel);
Vec3 pos2, vel2;
orbital_elements_to_cartesian(recovered, parent_mass, &pos2, &vel2);
const double pos_err = vec3_magnitude(vec3_sub(pos, pos2));
const double vel_err = vec3_magnitude(vec3_sub(vel, vel2));
INFO(" pos_err=" << pos_err << " m, vel_err=" << vel_err << " m/s");
REQUIRE_THAT(pos_err, WithinAbs(0.0, R_TOL));
REQUIRE_THAT(vel_err, WithinAbs(0.0, V_TOL));
}
}
SECTION("rotation matrix orthogonality") {
for (int i = 0; i < 5; i++) {
Spacecraft* craft = &sim->spacecraft[i];
const double omega = craft->orbit.argument_of_periapsis;
const double inc = craft->orbit.inclination;
const double Omega = craft->orbit.longitude_of_ascending_node;
Mat3 R = mat3_rotation_orbital(omega, inc, Omega);
const Vec3 unit_x = {1.0, 0.0, 0.0};
const Vec3 unit_y = {0.0, 1.0, 0.0};
const Vec3 unit_z = {0.0, 0.0, 1.0};
Vec3 rot_x = mat3_multiply_vec3(R, unit_x);
Vec3 rot_y = mat3_multiply_vec3(R, unit_y);
Vec3 rot_z = mat3_multiply_vec3(R, unit_z);
const double mag_x = vec3_magnitude(rot_x);
const double mag_y = vec3_magnitude(rot_y);
const double mag_z = vec3_magnitude(rot_z);
const double xy_dot = vec3_dot(rot_x, rot_y);
const double yz_dot = vec3_dot(rot_y, rot_z);
const double xz_dot = vec3_dot(rot_x, rot_z);
INFO("Spacecraft " << i << ": " << craft->name);
INFO(" |R·x|=" << mag_x << ", |R·y|=" << mag_y << ", |R·z|=" << mag_z);
INFO(" (R·x)·(R·y)=" << xy_dot << ", (R·y)·(R·z)=" << yz_dot << ", (R·x)·(R·z)=" << xz_dot);
REQUIRE_THAT(mag_x, WithinAbs(1.0, MAT_TOL));
REQUIRE_THAT(mag_y, WithinAbs(1.0, MAT_TOL));
REQUIRE_THAT(mag_z, WithinAbs(1.0, MAT_TOL));
REQUIRE_THAT(xy_dot, WithinAbs(0.0, MAT_TOL));
REQUIRE_THAT(yz_dot, WithinAbs(0.0, MAT_TOL));
REQUIRE_THAT(xz_dot, WithinAbs(0.0, MAT_TOL));
}
}
destroy_simulation(sim);
}

38
tests/test_extreme_orientation_mixed.toml
Unescape View File

@ -0,0 +1,38 @@
# Test Configuration: Extreme Orientation Mixed Cases
[[bodies]]
name = "Earth"
mass = 5.972e24
radius = 6.371e6
parent_index = -1
color = { r = 0.0, g = 0.5, b = 1.0 }
orbit = { semi_major_axis = 0.0, eccentricity = 0.0, true_anomaly = 0.0 }
[[spacecraft]]
name = "High_Inc_High_Ecc"
mass = 1000.0
parent_index = 0
orbit = { semi_major_axis = 5.0e7, eccentricity = 0.85, true_anomaly = 0.0, inclination = 1.2, longitude_of_ascending_node = 0.5, argument_of_periapsis = 0.3 }
[[spacecraft]]
name = "Polar_Moderate_Ecc"
mass = 1000.0
parent_index = 0
orbit = { semi_major_axis = 2.0e7, eccentricity = 0.5, true_anomaly = 0.0, inclination = 1.4, longitude_of_ascending_node = 1.0, argument_of_periapsis = 0.5 }
[[spacecraft]]
name = "Near_Parabolic_Mod_Inc"
mass = 1000.0
parent_index = 0
orbit = { semi_major_axis = 7.0e8, eccentricity = 0.99, true_anomaly = 0.0, inclination = 0.5, longitude_of_ascending_node = 0.8, argument_of_periapsis = 1.2 }
[[spacecraft]]
name = "Omega_Zero"
mass = 1000.0
parent_index = 0
orbit = { semi_major_axis = 4.0e7, eccentricity = 0.8, true_anomaly = 0.0, inclination = 1.2, longitude_of_ascending_node = 0.0, argument_of_periapsis = 0.6 }
[[spacecraft]]
name = "Arg_Peri_Zero"
mass = 1000.0
parent_index = 0
orbit = { semi_major_axis = 4.0e7, eccentricity = 0.8, true_anomaly = 0.0, inclination = 1.2, longitude_of_ascending_node = 0.7, argument_of_periapsis = 0.0 }
Write Preview
Loading…
Cancel
Save