cislunar-sim

High-fidelity cislunar spacecraft simulation in pure Python — cross-validated against LightSail 2 mission data.

cislunar-sim is a Python library for simulating spacecraft trajectories from low Earth orbit through cislunar space. It provides a high-fidelity, validated physics engine and Q-law orbital guidance laws — without the XML configuration of GMAT or the Java dependency of Orekit.

Why cislunar-sim?

• Validated: physics engine achieves < 0.05% SMA error against SGP4-propagated LightSail 2 states (bundled TLEs, reproducible from a fresh clone)
• Complete force environment: J2/J3 + GRAIL mascon lunar gravity, ion thruster, solar sail SRP, atmospheric drag, eclipse shadowing, attitude dynamics
• JPL-quality ephemeris: Sun and Moon positions from astropy DE430
• Minimal dependencies: numpy, astropy, and nrlmsise00 are the only runtime dependencies
• Fast: adaptive RK4(5) integrator; 7-day GTO periapsis-raise and 5-day drag-decay demos each run in under 60 seconds

Installation

pip install cislunar-sim

Requirements: Python ≥ 3.11, numpy ≥ 1.24, astropy ≥ 5.3, nrlmsise00 ≥ 0.1

For TLE propagation and LightSail 2 telemetry replay, install the validation extra:

pip install "cislunar-sim[validation]"  # adds sgp4>=2.22

Quick start

import numpy as np
from cislunar.guidance import ProgradeGuidance
from cislunar.physics import Action, make_lunar_craft

R_E = 6.371e6
MU = 3.986004418e14
r = R_E + 400e3
v_c = np.sqrt(MU / r)

sc = make_lunar_craft(
    position_m=[r, 0.0, 0.0],
    velocity_ms=[0.0, v_c, 0.0],
    propellant_kg=0.5,
)
guidance = ProgradeGuidance()

for _ in range(60):  # 1 hour at 60 s control steps
    thrust_dir, throttle = guidance.steer(sc.state.position, sc.state.velocity)
    sc.step(
        Action(attitude_dir_cmd=thrust_dir, thrust_dir=thrust_dir, throttle=throttle),
        dt_requested=60.0,
    )

print(sc.state.time_s, np.linalg.norm(sc.state.position))

Examples

The tested feature demos live in examples/:

• examples/gto_periapsis_raise.py — ion-thruster GTO periapsis raise to a 1,000 km target
• examples/solar_sail_leo.py — solar-sail orbit raising from 585 km LEO
• examples/drag_decay_leo.py — atmospheric drag driven SMA decay at 400 km
• examples/eclipse_power_gating.py — eclipse-aware power gating for ion thrust
• examples/cislunar_transfer.py — combined ion + sail cislunar orbit raising

What's included

Physics engine (cislunar.physics)

Adaptive RK4(5) Dormand-Prince integrator with:

Force	Model
Earth gravity	Two-body + J2 oblateness
Lunar gravity	J2 + J3 + 8-mascon GRAIL model
Solar gravity	Third-body perturbation
Ion thruster	Hall-effect, 15 mN, iodine-fed, 60 s warmup
Solar sail	McInnes radiation pressure model with albedo
Atmospheric drag	NRLMSISE-00 proxy (F10.7 solar flux)
Eclipse	Earth/Moon umbra–penumbra; power/battery model
Attitude	Quaternion rigid-body + reaction wheels + RCS
Ephemeris	astropy DE430 (Sun + Moon positions)

Guidance laws (cislunar.guidance)

Class	Description
GVEPeriapsisGuidance	GVE-optimal: maximise dr_p/dt
GVEApogeeGuidance	GVE-optimal: maximise dr_apo/dt
GTOPeriapsisGuidance	Periapsis burn gating for GTO
GTOApogeeGuidance	Apogee burn gating for GTO
ProgradeGuidance	Prograde burn with Oberth timing

Validation (cislunar.validation)

# Spot-check against McInnes, Wertz, JPL Horizons (19 benchmarks)
python -m cislunar.validation.physics_benchmark --extended

# Full LightSail 2 replay / telemetry validation
# Requires external mission files in validation/data/
make validate-external

Validation record

Reproducible from a fresh clone

The orbit-replay test compares the physics engine against SGP4-propagated state vectors derived from bundled LightSail 2 TLEs (5 historical epochs, NORAD 44420). These run automatically via make test.

Metric	Result	Reference	Reproducible
SMA error (1-day archival epoch)	< 0.05%	SGP4 propagation	✓ from clone
Radial error	< 0.02% of orbital radius	SGP4 propagation	✓ from clone
Sail force vs. McInnes (IKAROS params)	within 1%	McInnes (1999) Table 2.1	✓ from clone

The along-track drift is drag-dominated and expected; see the validation record for details.

Requires external mission files

The B* swing analysis and eclipse/attitude comparisons use the full CelesTrak GP-history archive and SatNOGS beacon frames, neither of which is bundled in this repo.

Metric	Result	Requires
B* swing ratio (sailing / passive)	0.231 observed vs 0.228 predicted	CelesTrak GP archive
Eclipse timing (entry residuals)	mean +3.7 s, std 19.5 s	SatNOGS beacon data
Body-rate envelope	0% of frames above model cap	SatNOGS beacon data

See src/cislunar/validation/light_sail_2/VALIDATION_RECORD.md for full methodology and validation/data/README.md for acquisition instructions.

make validate-external  # requires validation/data/ mission files (see that README)

Development setup

git clone https://github.com/arboreng/cislunar-sim.git
cd cislunar-sim
python -m venv .venv && source .venv/bin/activate
pip install -e ".[dev]"
pre-commit install
make test          # physics + validation + example tests (~5 min)
make validate-external  # requires validation/data/* mission files
make bench         # spot-check benchmarks

Contributing

See CONTRIBUTING.md.

License

See LICENSE. Copyright © 2026 Arbor Engineering Group.