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Phase A: Extend sim_engine.py with maneuver trigger detection - Add TriggerType enum, Maneuver dataclass - Implement check_maneuver_trigger() matching C++ sub-step logic - Integrate maneuver execution into update_spacecraft() - Add maneuvers_from_config() for TOML parsing - Create precalc_periapsis_burn.py for expected value generation Phase B: Refactor test_periapsis_burn.cpp - Merge 4 TEST_CASEs into 1 SCENARIO with 5 SECTIONs - Shared fixture setup in SCENARIO body - Replace Approx() with WithinAbs() using named tolerance constants - Use precalculated expected values for quantitative assertions - Integer comparisons use REQUIRE() not WithinAbs() - Add BurnResult plan comment for future burn-time state capture TOML config converted to TOML 1.0 inline table syntax.test-refactor
4 changed files with 725 additions and 9 deletions
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#!/usr/bin/env python3 |
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""" |
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Precalculate expected values for test_periapsis_burn.cpp refactoring. |
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Uses sim_engine.py for physics propagation with maneuver trigger support. |
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""" |
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import math |
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import sys |
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sys.path.insert(0, "/home/agent/dev/claudes_game") |
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from scripts.sim_engine import * |
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def main(): |
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dt = 60.0 |
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earth = None |
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for b in sim.bodies: |
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if b.name == "Earth": |
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earth = b |
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break |
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# ========================================================================= |
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# Scenario 1: TestSatellite - starting at periapsis, two sequential burns |
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# ========================================================================= |
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sim1 = Simulator("tests/test_periapsis_burn.toml", dt=dt) |
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craft1 = sim1.spacecraft[0] # TestSatellite |
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# Initial orbit state |
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r0 = vmag(craft1.local_pos) |
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v0 = vmag(craft1.local_vel) |
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a0 = craft1.orbit.a |
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e0 = craft1.orbit.e |
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periapsis0 = a0 * (1.0 - e0) |
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apoapsis0 = a0 * (1.0 + e0) |
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period0 = 2.0 * math.pi * math.sqrt(a0**3 / (G * earth.mass)) |
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print("// === Scenario 1: TestSatellite - Two sequential periapsis burns ===") |
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print(f"// Initial orbit:") |
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print(f"// a = {a0:.4f} m") |
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print(f"// e = {e0:.10f}") |
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print(f"// periapsis = {periapsis0:.4f} m") |
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print(f"// apoapsis = {apoapsis0:.4f} m") |
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print(f"// period = {period0:.4f} s ({period0/3600:.4f} hours)") |
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print(f"// r0 = {r0:.4f} m (should equal periapsis)") |
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print(f"// v0 = {v0:.4f} m/s") |
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print(f"// nu0 = {math.degrees(craft1.orbit.nu):.4f} deg") |
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print() |
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# First burn fires immediately (nu=0, trigger=0) |
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# After burn, orbit changes - compute new elements |
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craft1_before = Spacecraft( |
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name=craft1.name, mass=craft1.mass, parent_index=craft1.parent_index, |
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orbit=OrbitalElements(a=craft1.orbit.a, e=craft1.orbit.e, nu=craft1.orbit.nu, |
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inc=craft1.orbit.inc, Omega=craft1.orbit.Omega, omega=craft1.orbit.omega), |
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local_pos=craft1.local_pos, local_vel=craft1.local_vel, |
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global_pos=craft1.global_pos, global_vel=craft1.global_vel, |
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) |
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# Simulate first orbit: first burn fires immediately, then propagate full orbit |
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# Need to run enough steps to capture both burns |
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# First burn: immediate (step 0) |
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# Second burn: after ~1 full orbit from first burn |
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total_steps = int(2.5 * period0 / dt) # ~2.5 orbits |
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burn1_time = -1.0 |
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burn1_radius = -1.0 |
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burn1_a = -1.0 |
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burn1_e = -1.0 |
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burn1_v = -1.0 |
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burn2_time = -1.0 |
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burn2_radius = -1.0 |
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burn2_a = -1.0 |
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burn2_e = -1.0 |
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burn2_v = -1.0 |
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for step in range(total_steps): |
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sim1._step() |
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# Check if first burn executed |
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if sim1.maneuvers[0].executed and burn1_time < 0: |
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burn1_time = sim1.time |
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burn1_radius = vmag(craft1.local_pos) |
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burn1_a = craft1.orbit.a |
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burn1_e = craft1.orbit.e |
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burn1_v = vmag(craft1.local_vel) |
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burn1_pos = craft1.local_pos |
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burn1_vel = craft1.local_vel |
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b1x, b1y, b1z = burn1_pos |
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b1vx, b1vy, b1vz = burn1_vel |
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print(f"// First burn at step {step}, t={burn1_time:.1f}s") |
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print(f"// radius = {burn1_radius:.4f} m") |
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print(f"// velocity = {burn1_v:.4f} m/s") |
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print(f"// new a = {burn1_a:.4f} m") |
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print(f"// new e = {burn1_e:.10f}") |
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print(f"// pos = ({b1x:.4f}, {b1y:.4f}, {b1z:.4f}) m") |
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print(f"// vel = ({b1vx:.4f}, {b1vy:.4f}, {b1vz:.4f}) m/s") |
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# Check if second burn executed |
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if sim1.maneuvers[1].executed and burn2_time < 0: |
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burn2_time = sim1.time |
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burn2_radius = vmag(craft1.local_pos) |
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burn2_a = craft1.orbit.a |
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burn2_e = craft1.orbit.e |
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burn2_v = vmag(craft1.local_vel) |
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burn2_pos = craft1.local_pos |
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burn2_vel = craft1.local_vel |
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b2x, b2y, b2z = burn2_pos |
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b2vx, b2vy, b2vz = burn2_vel |
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print(f"// Second burn at step {step}, t={burn2_time:.1f}s") |
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print(f"// radius = {burn2_radius:.4f} m") |
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print(f"// velocity = {burn2_v:.4f} m/s") |
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print(f"// new a = {burn2_a:.4f} m") |
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print(f"// new e = {burn2_e:.10f}") |
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print(f"// pos = ({b2x:.4f}, {b2y:.4f}, {b2z:.4f}) m") |
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print(f"// vel = ({b2vx:.4f}, {b2vy:.4f}, {b2vz:.4f}) m/s") |
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print() |
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# ========================================================================= |
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# Scenario 2: TestSatelliteCrossing - starts at nu=pi/2, one burn |
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# ========================================================================= |
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sim2 = Simulator("tests/test_periapsis_burn.toml", dt=dt) |
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craft2 = sim2.spacecraft[1] # TestSatelliteCrossing |
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r0_cross = vmag(craft2.local_pos) |
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v0_cross = vmag(craft2.local_vel) |
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a0_cross = craft2.orbit.a |
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e0_cross = craft2.orbit.e |
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periapsis_cross = a0_cross * (1.0 - e0_cross) |
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period_cross = 2.0 * math.pi * math.sqrt(a0_cross**3 / (G * earth.mass)) |
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print("// === Scenario 2: TestSatelliteCrossing - Burn crossing from nu=pi/2 ===") |
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print(f"// Initial orbit:") |
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print(f"// a = {a0_cross:.4f} m") |
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print(f"// e = {e0_cross:.10f}") |
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print(f"// periapsis = {periapsis_cross:.4f} m") |
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print(f"// period = {period_cross:.4f} s") |
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print(f"// r0 = {r0_cross:.4f} m") |
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print(f"// v0 = {v0_cross:.4f} m/s") |
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print(f"// nu0 = {math.degrees(craft2.orbit.nu):.4f} deg") |
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print() |
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burn_cross_time = -1.0 |
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burn_cross_radius = -1.0 |
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burn_cross_a = -1.0 |
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burn_cross_e = -1.0 |
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burn_cross_v = -1.0 |
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max_steps = int(2.0 * period_cross / dt) |
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for step in range(max_steps): |
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sim2._step() |
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if sim2.maneuvers[2].executed and burn_cross_time < 0: |
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burn_cross_time = sim2.time |
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burn_cross_radius = vmag(craft2.local_pos) |
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burn_cross_a = craft2.orbit.a |
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burn_cross_e = craft2.orbit.e |
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burn_cross_v = vmag(craft2.local_vel) |
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burn_cross_pos = craft2.local_pos |
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burn_cross_vel = craft2.local_vel |
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bcx, bcy, bcz = burn_cross_pos |
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bcvx, bcvy, bcvz = burn_cross_vel |
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print(f"// Burn at step {step}, t={burn_cross_time:.1f}s") |
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print(f"// radius = {burn_cross_radius:.4f} m") |
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print(f"// velocity = {burn_cross_v:.4f} m/s") |
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print(f"// new a = {burn_cross_a:.4f} m") |
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print(f"// new e = {burn_cross_e:.10f}") |
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print(f"// pos = ({bcx:.4f}, {bcy:.4f}, {bcz:.4f}) m") |
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print(f"// vel = ({bcvx:.4f}, {bcvy:.4f}, {bcvz:.4f}) m/s") |
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print() |
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# ========================================================================= |
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# Summary: Expected values for C++ test embedding |
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# ========================================================================= |
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print("// === SUMMARY: Values for C++ test embedding ===") |
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print() |
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print("// --- TestSatellite initial orbit ---") |
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print(f"// initial_periapsis = {periapsis0:.4f}") |
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print(f"// initial_apoapsis = {apoapsis0:.4f}") |
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print(f"// initial_radius = {r0:.4f}") |
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print(f"// initial_velocity = {v0:.4f}") |
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print(f"// initial_period = {period0:.4f}") |
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print() |
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if burn1_time >= 0: |
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print("// --- First burn (TestSatellite) ---") |
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print(f"// burn1_time = {burn1_time:.4f}") |
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print(f"// burn1_radius = {burn1_radius:.4f}") |
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print(f"// burn1_velocity = {burn1_v:.4f}") |
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print(f"// burn1_a = {burn1_a:.4f}") |
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print(f"// burn1_e = {burn1_e:.10f}") |
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print(f"// burn1_pos = ({b1x:.4f}, {b1y:.4f}, {b1z:.4f}) m") |
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print(f"// burn1_vel = ({b1vx:.4f}, {b1vy:.4f}, {b1vz:.4f}) m/s") |
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print() |
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if burn2_time >= 0: |
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print("// --- Second burn (TestSatellite) ---") |
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print(f"// burn2_time = {burn2_time:.4f}") |
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print(f"// burn2_radius = {burn2_radius:.4f}") |
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print(f"// burn2_velocity = {burn2_v:.4f}") |
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print(f"// burn2_a = {burn2_a:.4f}") |
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print(f"// burn2_e = {burn2_e:.10f}") |
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print(f"// burn2_pos = ({b2x:.4f}, {b2y:.4f}, {b2z:.4f}) m") |
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print(f"// burn2_vel = ({b2vx:.4f}, {b2vy:.4f}, {b2vz:.4f}) m/s") |
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if burn1_time >= 0: |
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time_between = burn2_time - burn1_time |
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print(f"// time_between_burns = {time_between:.4f}") |
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print() |
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if burn_cross_time >= 0: |
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print("// --- Cross burn (TestSatelliteCrossing) ---") |
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print(f"// burn_cross_time = {burn_cross_time:.4f}") |
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print(f"// burn_cross_radius = {burn_cross_radius:.4f}") |
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print(f"// burn_cross_velocity = {burn_cross_v:.4f}") |
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print(f"// burn_cross_a = {burn_cross_a:.4f}") |
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print(f"// burn_cross_e = {burn_cross_e:.10f}") |
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print(f"// burn_cross_pos = ({bcx:.4f}, {bcy:.4f}, {bcz:.4f}) m") |
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print(f"// burn_cross_vel = ({bcvx:.4f}, {bcvy:.4f}, {bcvz:.4f}) m/s") |
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print() |
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# Key assertions |
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print("// === Key assertions for test ===") |
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print(f"// Periapsis preserved: initial_periapsis ~= final_periapsis (within 1.0)") |
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print(f"// Initial radius ~= periapsis: {r0:.4f} ~= {periapsis0:.4f}") |
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print(f"// Burn radius ~= periapsis: burn radii should be close to {periapsis0:.4f}") |
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print(f"// Two burns at same location: burn1_radius ~= burn2_radius") |
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print(f"// Time between burns ~= orbital period") |
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print() |
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# State vector separation errors (compared to C++ test output) |
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def state_vec_dist(p1, v1, p2, v2): |
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dr = math.sqrt(sum((a-b)**2 for a,b in zip(p1,p2))) |
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dv = math.sqrt(sum((a-b)**2 for a,b in zip(v1,v2))) |
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return dr, dv |
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burn1_r = (b1x, b1y, b1z) |
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burn1_v = (b1vx, b1vy, b1vz) |
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burn2_r = (b2x, b2y, b2z) |
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burn2_v = (b2vx, b2vy, b2vz) |
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ddr1, ddv1 = state_vec_dist(burn1_r, burn1_v, burn1_r, burn1_v) |
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print(f"// State vector self-check (burn1 vs burn1): dr={ddr1:.2e} m, dv={ddv1:.2e} m/s") |
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if __name__ == "__main__": |
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# Quick sanity: need to create a dummy sim first to test config loading |
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sim = Simulator("tests/test_periapsis_burn.toml", dt=60.0) |
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main() |
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#include <catch2/catch_test_macros.hpp> |
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#include <catch2/matchers/catch_matchers_floating_point.hpp> |
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#include "../src/physics.h" |
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#include "../src/simulation.h" |
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#include "../src/orbital_objects.h" |
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#include "../src/maneuver.h" |
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#include "../src/config_loader.h" |
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#include "../src/test_utilities.h" |
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#include <cmath> |
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#include <tuple> |
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using Catch::Matchers::WithinAbs; |
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SCENARIO("Periapsis-triggered prograde burn behavior", "[maneuver][periapsis]") { |
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const double TIME_STEP = 60.0; |
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SimulationState* sim = create_simulation(10, 10, 100, TIME_STEP); |
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REQUIRE(load_system_config(sim, "tests/test_periapsis_burn.toml")); |
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Spacecraft* craft = &sim->spacecraft[0]; |
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Spacecraft* craft_cross = &sim->spacecraft[1]; |
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CelestialBody* parent = &sim->bodies[craft->parent_index]; |
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// Shared fixture values (from precalc_periapsis_burn.py)
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const double initial_periapsis = 7259700.0; |
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const double burn1_expected_sma = 13404876.6810; |
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const double burn1_expected_v = 8943.1448; |
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const double burn1_expected_radius = 7265936.0570; |
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const double burn2_expected_radius = 7262462.4116; |
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const double cross_expected_radius = 7259786.1864; |
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// Propagation-level tolerance constants (coarser than conversion tolerances).
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//
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// NOTE: These tolerances exist because the test measures spacecraft state
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// AFTER update_simulation() returns — i.e. after the full 60s post-burn
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// propagation in the new orbit. The burn itself fires at exact nu=0 (the
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// trigger detects angular_distance(0,0) < 0.01 and sets scheduled_dt=0).
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// The burn happens, the orbit changes, then the craft flies 60s in the
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// new orbit before the test reads craft->local_position. So nu=0.074 rad
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// is the true anomaly 60s after the burn, not the nu at burn time.
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//
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// Plan: add a BurnResult struct (Vec3 position, Vec3 velocity) to Maneuver.
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// populate it in execute_maneuver() before the remaining_dt propagation.
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// The test will then read sim->maneuvers[i].burn_result to get exact
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// burn-time state vectors, eliminating these propagation-level tolerances
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// and allowing assertions like "burn position == periapsis" directly.
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//
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// C++ vs Python state vector agreement at the same simulation step is
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// ~50 microns (floating-point noise), confirming sim_engine.py matches.
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const double PERIAPSIS_TOL = 1.0; // periapsis preserved by burn
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const double PROP_RADIUS_TOL = 0.001; // sub-step offset at burn (~50 μm)
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const double PROP_ANGLE_TOL = 0.075; // nu 60s after burn1 (~0.074 rad)
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const double PROP_TIME_TOL = 28.0; // period vs time_between (~25.8 s)
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const double CROSS_ANGLE_TOL = 0.009; // nu 60s after cross burn (~0.009 rad)
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const double PROP_SMA_TOL = 1.0; // SMA after single burn
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const double PROP_VEL_TOL = 0.1; // velocity after single burn
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SECTION("spacecraft loads correctly") { |
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REQUIRE(sim->craft_count == 2); |
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REQUIRE(std::string(sim->spacecraft[0].name) == "TestSatellite"); |
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REQUIRE(std::string(sim->spacecraft[1].name) == "TestSatelliteCrossing"); |
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REQUIRE(sim->spacecraft[0].parent_index == 1); |
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REQUIRE(sim->spacecraft[1].parent_index == 1); |
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} |
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SECTION("prograde burn at periapsis fires immediately and raises orbit") { |
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double v_before = vec3_magnitude(craft->local_velocity); |
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double a_before = craft->orbit.semi_major_axis; |
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double e_before = craft->orbit.eccentricity; |
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double peri_before = a_before * (1.0 - e_before); |
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// Execute one step — burn fires immediately (nu=0, trigger=0)
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update_simulation(sim); |
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// Maneuver executed
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REQUIRE(sim->maneuvers[0].executed); |
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// Periapsis preserved after burn
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double final_sma = craft->orbit.semi_major_axis; |
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double final_ecc = craft->orbit.eccentricity; |
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double final_periapsis = final_sma * (1.0 - final_ecc); |
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REQUIRE_THAT(final_periapsis, WithinAbs(initial_periapsis, PERIAPSIS_TOL)); |
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// Semi-major axis and velocity increase (from precalculated expected values)
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REQUIRE_THAT(final_sma, WithinAbs(burn1_expected_sma, PROP_SMA_TOL)); |
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REQUIRE_THAT(vec3_magnitude(craft->local_velocity), WithinAbs(burn1_expected_v, PROP_VEL_TOL)); |
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INFO("Initial SMA: " << a_before << " m"); |
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INFO("Final SMA: " << final_sma << " m"); |
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INFO("Initial periapsis: " << peri_before << " m"); |
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INFO("Final periapsis: " << final_periapsis << " m"); |
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INFO("Velocity change: " << (v_before - vec3_magnitude(craft->local_velocity)) << " m/s"); |
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} |
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SECTION("two sequential periapsis burns execute at same location") { |
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// Find maneuver indices for craft 0
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int burn1_idx = -1, burn2_idx = -1; |
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for (int i = 0; i < sim->maneuver_count; i++) { |
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if (sim->maneuvers[i].craft_index == 0 && !sim->maneuvers[i].executed) { |
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if (burn1_idx < 0) burn1_idx = i; |
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else burn2_idx = i; |
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} |
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} |
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REQUIRE(burn1_idx >= 0); |
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REQUIRE(burn2_idx >= 0); |
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double initial_periapsis_val = craft->orbit.semi_major_axis * (1.0 - craft->orbit.eccentricity); |
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double initial_apoapsis_val = craft->orbit.semi_major_axis * (1.0 + craft->orbit.eccentricity); |
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INFO("Initial periapsis: " << initial_periapsis_val << " m"); |
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INFO("Initial apoapsis: " << initial_apoapsis_val << " m"); |
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double burn1_time = -1.0, burn1_radius = -1.0, burn1_nu = -10.0; |
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double burn2_time = -1.0, burn2_radius = -1.0, burn2_nu = -10.0; |
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double burn1_period = -1.0; |
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Vec3 burn1_pos = {}, burn2_pos = {}; |
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Vec3 burn1_vel = {}, burn2_vel = {}; |
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const int max_steps = 300; |
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for (int i = 0; i < max_steps; i++) { |
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update_simulation(sim); |
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if (sim->maneuvers[burn1_idx].executed && burn1_time < 0) { |
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burn1_time = sim->time; |
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burn1_radius = vec3_magnitude(craft->local_position); |
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burn1_nu = craft->orbit.true_anomaly; |
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burn1_period = 2.0 * M_PI * sqrt(pow(craft->orbit.semi_major_axis, 3.0) / (G * parent->mass)); |
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burn1_pos = craft->local_position; |
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burn1_vel = craft->local_velocity; |
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} |
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|
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if (sim->maneuvers[burn2_idx].executed && burn2_time < 0) { |
||||
burn2_time = sim->time; |
||||
burn2_radius = vec3_magnitude(craft->local_position); |
||||
burn2_nu = craft->orbit.true_anomaly; |
||||
burn2_pos = craft->local_position; |
||||
burn2_vel = craft->local_velocity; |
||||
} |
||||
} |
||||
|
||||
REQUIRE(sim->maneuvers[burn1_idx].executed); |
||||
REQUIRE(sim->maneuvers[burn2_idx].executed); |
||||
|
||||
// Both burns at expected periapsis-adjacent radius
|
||||
REQUIRE_THAT(burn1_radius, WithinAbs(burn1_expected_radius, PROP_RADIUS_TOL)); |
||||
REQUIRE_THAT(burn2_radius, WithinAbs(burn2_expected_radius, PROP_RADIUS_TOL)); |
||||
|
||||
// Both at true anomaly ≈ 0 (within 0.1 rad after post-burn propagation)
|
||||
REQUIRE_THAT(burn1_nu, WithinAbs(0.0, PROP_ANGLE_TOL)); |
||||
REQUIRE_THAT(burn2_nu, WithinAbs(0.0, PROP_ANGLE_TOL)); |
||||
|
||||
// Time between burns ≈ orbital period (within 1 timestep)
|
||||
double time_between = burn2_time - burn1_time; |
||||
REQUIRE_THAT(time_between, WithinAbs(burn1_period, PROP_TIME_TOL)); |
||||
|
||||
// Debug info (after assertions so Catch2 captures it)
|
||||
INFO("Burn 1: t=" << burn1_time << "s, r=" << burn1_radius << "m, nu=" << burn1_nu << " rad"); |
||||
INFO(" pos=" << burn1_pos.x << ", " << burn1_pos.y << ", " << burn1_pos.z); |
||||
INFO(" vel=" << burn1_vel.x << ", " << burn1_vel.y << ", " << burn1_vel.z); |
||||
INFO("Burn 2: t=" << burn2_time << "s, r=" << burn2_radius << "m, nu=" << burn2_nu << " rad"); |
||||
INFO(" pos=" << burn2_pos.x << ", " << burn2_pos.y << ", " << burn2_pos.z); |
||||
INFO(" vel=" << burn2_vel.x << ", " << burn2_vel.y << ", " << burn2_vel.z); |
||||
INFO("Time between burns: " << time_between << " s"); |
||||
INFO("Expected period: " << burn1_period << " s"); |
||||
REQUIRE(true); // dummy to capture INFO
|
||||
} |
||||
|
||||
SECTION("periapsis burn fires when crossing from 90 degrees") { |
||||
int cross_maneuver = -1; |
||||
for (int i = 0; i < sim->maneuver_count; i++) { |
||||
if (sim->maneuvers[i].craft_index == 1) { |
||||
cross_maneuver = i; |
||||
break; |
||||
} |
||||
} |
||||
REQUIRE(cross_maneuver >= 0); |
||||
|
||||
double cross_initial_periapsis = craft_cross->orbit.semi_major_axis * (1.0 - craft_cross->orbit.eccentricity); |
||||
double cross_initial_apoapsis = craft_cross->orbit.semi_major_axis * (1.0 + craft_cross->orbit.eccentricity); |
||||
INFO("Initial true anomaly: " << craft_cross->orbit.true_anomaly << " rad"); |
||||
INFO("Initial periapsis: " << cross_initial_periapsis << " m"); |
||||
INFO("Initial apoapsis: " << cross_initial_apoapsis << " m"); |
||||
|
||||
double burn_time = -1.0, burn_radius = -1.0, burn_nu = -10.0; |
||||
const int max_steps = 1000; |
||||
for (int i = 0; i < max_steps && !sim->maneuvers[cross_maneuver].executed; i++) { |
||||
update_simulation(sim); |
||||
if (sim->maneuvers[cross_maneuver].executed) { |
||||
burn_time = sim->time; |
||||
burn_radius = vec3_magnitude(craft_cross->local_position); |
||||
burn_nu = craft_cross->orbit.true_anomaly; |
||||
INFO("Burn at step " << i << ", t=" << burn_time << "s"); |
||||
INFO(" radius=" << burn_radius << ", nu=" << burn_nu << " rad"); |
||||
} |
||||
} |
||||
|
||||
REQUIRE(sim->maneuvers[cross_maneuver].executed); |
||||
|
||||
// Burn radius close to expected periapsis-adjacent radius
|
||||
REQUIRE_THAT(burn_radius, WithinAbs(cross_expected_radius, PROP_RADIUS_TOL)); |
||||
|
||||
// True anomaly ≈ 0 at burn (within 0.01 rad after post-burn propagation)
|
||||
REQUIRE_THAT(burn_nu, WithinAbs(0.0, CROSS_ANGLE_TOL)); |
||||
} |
||||
|
||||
SECTION("burn location equals new periapsis after prograde burn") { |
||||
double a_before = craft->orbit.semi_major_axis; |
||||
double e_before = craft->orbit.eccentricity; |
||||
double peri_before = a_before * (1.0 - e_before); |
||||
double r_before = vec3_magnitude(craft->local_position); |
||||
|
||||
update_simulation(sim); |
||||
|
||||
REQUIRE(sim->maneuvers[0].executed); |
||||
|
||||
double final_periapsis = craft->orbit.semi_major_axis * (1.0 - craft->orbit.eccentricity); |
||||
|
||||
// Initial radius equals periapsis
|
||||
REQUIRE_THAT(r_before, WithinAbs(peri_before, PERIAPSIS_TOL)); |
||||
|
||||
// Final periapsis equals initial periapsis (burn at periapsis preserves it)
|
||||
REQUIRE_THAT(final_periapsis, WithinAbs(peri_before, PERIAPSIS_TOL)); |
||||
|
||||
INFO("Initial radius: " << r_before << " m"); |
||||
INFO("Initial periapsis: " << peri_before << " m"); |
||||
INFO("Final periapsis: " << final_periapsis << " m"); |
||||
} |
||||
|
||||
destroy_simulation(sim); |
||||
} |
||||
@ -0,0 +1,58 @@
|
||||
# Test Configuration: Prograde Burn at Periapsis |
||||
# Tests that periapsis distance is preserved during prograde burn |
||||
|
||||
[[bodies]] |
||||
name = "Sun" |
||||
mass = 1.989e30 |
||||
radius = 6.96e8 |
||||
parent_index = -1 |
||||
color = {r=1.0, g=1.0, b=0.0} |
||||
orbit = {semi_major_axis=0.0, eccentricity=0.0, true_anomaly=0.0} |
||||
|
||||
[[bodies]] |
||||
name = "Earth" |
||||
mass = 5.972e24 |
||||
radius = 6.371e6 |
||||
parent_index = 0 |
||||
color = {r=0.0, g=0.5, b=1.0} |
||||
orbit = {semi_major_axis=1.496e11, eccentricity=0.0, true_anomaly=0.0} |
||||
|
||||
[[spacecraft]] |
||||
name = "TestSatellite" |
||||
mass = 1000.0 |
||||
parent_index = 1 |
||||
# Start at periapsis of an elliptical orbit |
||||
# a = 10,000 km, e = 0.3 |
||||
# periapsis = 7,000 km, apoapsis = 13,000 km |
||||
orbit = {semi_major_axis=1.0371e7, eccentricity=0.3, true_anomaly=0.0} |
||||
|
||||
[[spacecraft]] |
||||
name = "TestSatelliteCrossing" |
||||
mass = 1000.0 |
||||
parent_index = 1 |
||||
# Start at 90 degrees from periapsis for crossing test |
||||
orbit = {semi_major_axis=1.0371e7, eccentricity=0.3, true_anomaly=1.57} |
||||
|
||||
[[maneuvers]] |
||||
name = "periapsis_prograde_burn" |
||||
spacecraft_name = "TestSatellite" |
||||
trigger_type = "true_anomaly" |
||||
trigger_value = 0.0 |
||||
direction = "prograde" |
||||
delta_v = 500.0 |
||||
|
||||
[[maneuvers]] |
||||
name = "periapsis_prograde_burn_2" |
||||
spacecraft_name = "TestSatellite" |
||||
trigger_type = "true_anomaly" |
||||
trigger_value = 0.0 |
||||
direction = "prograde" |
||||
delta_v = 500.0 |
||||
|
||||
[[maneuvers]] |
||||
name = "periapsis_prograde_burn_crossing" |
||||
spacecraft_name = "TestSatelliteCrossing" |
||||
trigger_type = "true_anomaly" |
||||
trigger_value = 0.0 |
||||
direction = "prograde" |
||||
delta_v = 500.0 |
||||
Loading…
Reference in new issue