1 stable release

Uses new Rust 2024

1.0.0	Mar 31, 2026

#166 in Simulation

Used in 2 crates

GPL-3.0-only

315KB
6K SLoC

Falak (فلک) — Orbital Mechanics & Celestial Dynamics

Falak (Arabic/Persian: فلک — sky, celestial sphere) — orbital mechanics and celestial dynamics for the AGNOS science stack

Keplerian orbits, transfer maneuvers, perturbation models, N-body simulation, ephemeris computation, reference frames, spacecraft maneuver planning, orbit propagation, and the circular restricted three-body problem. Built on hisab for math foundations.

Modules

Module	Description
`orbit`	Classical orbital elements, state vectors, periapsis/apoapsis, Keplerian parameters
`kepler`	Kepler's equation solver, anomaly conversions (mean, eccentric, true), period, velocity, state vectors
`transfer`	Hohmann transfers, bi-elliptic transfers, plane changes, phasing orbits, Lambert problem
`perturbation`	J2/J3 oblateness, atmospheric drag, solar radiation pressure, third-body effects
`nbody`	N-body gravitational simulation, direct summation, leapfrog and RK4 integrators
`ephemeris`	Julian date conversions, sidereal time, planetary and lunar positions
`frame`	Reference frames (ECI, ECEF, perifocal, rotating, geodetic), coordinate transforms
`maneuver`	Delta-v budgets, impulsive burns, rocket equation, escape/capture maneuvers
`propagate`	Orbit propagation: analytic two-body (Kepler) and perturbed Cowell's method
`cr3bp`	Circular Restricted Three-Body Problem: Lagrange points, Jacobi constant, zero-velocity curves
`bridge`	Cross-crate conversions — primitive-value bridges to other AGNOS science crates
`integration::soorat`	Downstream consumer API for soorat rendering integration
`error`	Unified error types (`FalakError`) for all orbital computations
`logging`	Structured logging via `FALAK_LOG` env var (feature-gated)

Feature Flags

Feature	Default	Description
`default`	—	No optional features enabled
`soorat-compat`	no	Compatibility layer for soorat rendering integration
`logging`	no	Structured tracing via `FALAK_LOG` env var
`physics`	no	Physics engine integration via impetus

[dependencies]
falak = { version = "0.2", features = ["logging"] }

Quick Start

LEO Orbit — Period Calculation

use falak::orbit::OrbitalElements;
use falak::kepler;

// ISS-like orbit: 400 km altitude, nearly circular, 51.6 deg inclination
let iss = OrbitalElements::new(
    6_778_000.0,  // semi-major axis (m)
    0.0001,       // eccentricity (nearly circular)
    0.9006,       // inclination (51.6 deg in radians)
    1.2,          // RAAN
    0.5,          // argument of periapsis
    0.0,          // true anomaly
).unwrap();

let period = kepler::orbital_period(iss.semi_major_axis(), kepler::MU_EARTH);
let period_min = period / 60.0;
println!("ISS period: {period_min:.1} min"); // ~92.6 min

Hohmann Transfer — LEO to GEO

use falak::transfer::hohmann;

let r_leo = 6_778_000.0;   // 400 km altitude (m)
let r_geo = 42_164_000.0;  // GEO radius (m)
let mu = 3.986004418e14;   // Earth gravitational parameter (m^3/s^2)

let result = hohmann::hohmann_transfer(r_leo, r_geo, mu).unwrap();
println!("Total delta-v: {:.0} m/s", result.total_delta_v()); // ~3854 m/s

Lambert Problem — Interplanetary Transfer

use falak::transfer::lambert;

let r1 = [1.0e11, 0.0, 0.0];       // departure position (m)
let r2 = [0.0, 1.5e11, 0.0];       // arrival position (m)
let tof = 200.0 * 86400.0;          // time of flight (s)
let mu = 1.327e20;                   // Sun gravitational parameter

let solution = lambert::solve(r1, r2, tof, mu, false).unwrap();
println!("Departure v: {:.0} m/s", solution.v1_magnitude());

N-Body Simulation

use falak::nbody::{Body, NBodySimulation};

let bodies = vec![
    Body::new("Sun",   1.989e30, [0.0, 0.0, 0.0], [0.0, 0.0, 0.0]),
    Body::new("Earth", 5.972e24, [1.496e11, 0.0, 0.0], [0.0, 29_780.0, 0.0]),
    Body::new("Mars",  6.417e23, [2.279e11, 0.0, 0.0], [0.0, 24_077.0, 0.0]),
];

let mut sim = NBodySimulation::new(bodies);
sim.step_leapfrog(3600.0); // advance 1 hour

Validated Results

All implementations validated against known astrodynamics results:

Test	Expected	Verified
ISS orbital period (400 km)	~92.6 min	92.6 min
Hohmann LEO to GEO total delta-v	~3854 m/s	3854 m/s
GEO orbital period	~23.93 hr	23.93 hr
J2 RAAN drift (sun-synchronous)	~0.9856 deg/day	confirmed
Lagrange point L1 (Earth-Moon)	~0.8369 (normalized)	confirmed
Jacobi constant conservation	invariant under CR3BP	confirmed
Kepler's equation (Newton-Raphson)	converges for all e < 1	confirmed
Vis-viva equation	v = sqrt(mu(2/r - 1/a))	confirmed
Hohmann transfer orbit (energy)	minimum two-impulse transfer	confirmed
N-body energy conservation	leapfrog symplectic	confirmed

Relationship to AGNOS Science Stack

hisab (math) ──┐
               ├── falak (orbits) ──┬── kiran (game engine)
impetus (phys)─┘                   ├── joshua (simulation)
                                   └── soorat (rendering)

Dependency Stack

falak
  └── hisab (linear algebra, geometry, calculus)
  └── impetus (optional: physics engine integration)

Consumers

kiran — game engine (orbital mechanics for space simulations)
joshua — simulation manager (celestial body dynamics)
impetus — physics engine (integration bridge)

Documentation

Architecture Overview — module map, data flow, dependency stack
Development Roadmap — milestones and planned work

License

GPL-3.0-only. See LICENSE.

Dependencies

~15MB
~288K SLoC