/*! # nyx-space

[Nyx](https://en.wikipedia.org/wiki/Nyx) is a high fidelity, fast, reliable and validated astrodynamical toolkit library written in Rust.

The ultimate goal of this library is to provide a high-speed and scalable replacement for [General Mission Analysis Tool (GMAT)](http://gmat.sourceforge.net/doc/R2018a/help.html).

# Tutorial
The [tutorial](tutorial/index.html) is a great place to start learning how to use nyx. The target audience is astrodynamics & aerospace engineers.

If you are new to Rust, learn the basics on the ["Rust By Example" interactive tutorial](https://doc.rust-lang.org/stable/rust-by-example/).
Using nyx isn't hard, despite the code of the library being quite complicated.

# Features
Unless specified otherwise in the documentation of specific functions, all vectors and matrices are [statically allocated](https://discourse.nphysics.org/t/statically-typed-matrices-whose-size-is-a-multiple-or-another-one/460/4).

## Propagation
- Propagation with different Runge Kutta methods (validated in GMAT)
- Convenient and explicit definition of the dynamics for a simulation
- Propagation to different stopping conditions
## Dynamical models
- Multibody dynamics using XB files
- Finite burns with fuel depletion (including low thrust / ion propulsion)
- Sub-Optimal Control of continuous thrust (e.g. Ruggerio, Petropoulos/Q-law)
- Solar radiation pressure modeling
- Basic drag models (cannonball)
## Orbit determination
- Statistical Orbit Determination: Classical and Extended Kalman Filter
- Orbit Determination with multibody dynamics
- Smoothing and iterations of CKFs
- Square Root Information Filer (SRIF)
- An easy-to-use OD user interface
- State noise compensation (SNC)
## Celestial computations
- Orbital state manipulation (from GMAT source code and validated in GMAT)
- Planetary and Solar eclipse and visibility computation
- Light-time corrections and abberations

# Usage
Put this in your `Cargo.toml`:

```toml
[dependencies]
nyx-space = "0.0.20"
```

And add the following to your crate root:

```rust
extern crate nyx_space as nyx;
```
*/

/// Provides all the propagators / integrators available in `nyx`.
pub mod propagators;

/// Provides several dynamics used for orbital mechanics and attitude dynamics, which can be elegantly combined.
///
/// # Simple two body propagation
/// ```
/// extern crate nalgebra as na;
/// extern crate hifitime;
/// extern crate nyx_space as nyx;
/// use hifitime::{Epoch, SECONDS_PER_DAY};
/// use nyx::celestia::{bodies, Cosm, State};
/// use nyx::dynamics::celestial::CelestialDynamics;
/// use nyx::dynamics::Dynamics;
/// use nyx::propagators::error_ctrl::RSSStepPV;
/// use nyx::propagators::{PropOpts, Propagator};
///
/// let cosm = Cosm::from_xb("./de438s");
/// let eme2k = cosm.frame("EME2000");
///
/// let dt = Epoch::from_mjd_tai(21_545.0);
/// let initial_state = State::cartesian(-2436.45, -2436.45, 6891.037, 5.088611, -5.088611, 0.0, dt, eme2k);
///
/// println!("Initial state:\n{0}\n{0:o}\n", initial_state);
///
/// let prop_time = 24.0 * 3_600.0;
/// let accuracy = 1e-12;
/// let min_step = 0.1;
/// let max_step = 60.0;
///
/// let rslt = State::cartesian(
///         -5_971.194_376_797_643,
///         3_945.517_912_574_178_4,
///         2_864.620_957_744_429_2,
///         0.049_083_101_605_507_95,
///         -4.185_084_125_817_658,
///         5.848_947_462_472_877,
///         Epoch::from_mjd_tai(21_546.0),
///         eme2k,
/// );
///
/// let mut dynamics = CelestialDynamics::two_body(initial_state);
/// let mut prop = Propagator::default(
///     &mut dynamics,
///     &PropOpts::with_adaptive_step(min_step, max_step, accuracy, RSSStepPV {}),
/// );
/// prop.until_time_elapsed(prop_time);
///
/// assert_eq!(prop.dynamics.state, rslt, "two body prop failed");
///
/// println!("Final state:\n{0}\n{0:o}", prop.dynamics.state);
/// ```
///
/// # Multibody propagation of a Halo orbit
/// Multibody propagation is **an order of magnitude faster** in nyx than in GMAT.
/// In nyx, the following function is executed in 0.14 seconds in release mode.
/// ```
/// extern crate nalgebra as na;
/// extern crate hifitime;
/// extern crate nyx_space as nyx;

/// use hifitime::Epoch;
/// use na::Vector6;
/// use nyx::celestia::{bodies, Cosm, State};
/// use nyx::dynamics::celestial::CelestialDynamics;
/// use nyx::propagators::*;
/// use nyx::utils::rss_state_errors;
///
/// let prop_time = 24.0 * 3_600.0;
///
/// let cosm = Cosm::from_xb("./de438s");
/// let eme2k = cosm.frame("EME2000");
///
/// let start_time = Epoch::from_gregorian_tai_at_midnight(2020, 1, 1);
///
/// let halo_rcvr = State::cartesian(
///     333_321.004_516,
///     -76_134.198_887,
///     -20_873.831_939,
///     0.257_153_712,
///     0.930_284_066,
///     0.346_177,
///     start_time,
///     eme2k,
/// );
///
/// // GMAT data
/// let rslt = Vector6::new(
///     345_350.664_030_479,
///     5_930.672_047_088,
///     7_333.283_779_286,
///     2.129_819_943e-2,
///     9.566_789_568e-1,
///     3.028_175_811e-1,
/// );
///
/// let bodies = vec![bodies::EARTH_MOON, bodies::SUN, bodies::JUPITER_BARYCENTER];
/// let mut dynamics = CelestialDynamics::new(halo_rcvr, bodies, &cosm);
///
/// let mut prop = Propagator::default(&mut dynamics, &PropOpts::default());
/// prop.until_time_elapsed(prop_time);
/// let (err_r, err_v) = rss_state_errors(&prop.state_vector(), &rslt);
///
/// println!(
///     "RSS errors:\tpos = {:.5e} km\tvel = {:.5e} km/s\ninit\t{}\nfinal\t{}",
///     err_r, err_v, halo_rcvr, prop.dynamics.state
/// );
/// assert!(err_r < 1e-3, format!("multi body failed in position: {:.5e}", err_r));
/// assert!(err_v < 1e-6, format!("multi body failed in velocity: {:.5e}", err_v));
/// ```
pub mod dynamics;

/// Provides the solar system planets, and state and (later) ephemeride management.
///
/// # State creation and management
/// ```
/// extern crate hifitime;
/// extern crate nyx_space as nyx;
///
/// use hifitime::Epoch;
/// use nyx::celestia::{Cosm, State};
/// let mut cosm = Cosm::from_xb("./de438s");
/// // We're actually going to use the GMAT value for Earth GM (de438s has a slightly different value).
/// cosm.mut_gm_for_frame("EME2000", 398_600.441_5);
/// // In this case, we're creating these states around a Geoid which is Earth.
/// let eme2k = cosm.frame("EME2000");
/// let dt = Epoch::from_mjd_tai(21545.0);
/// let cart = State::cartesian(
///         5_946.673_548_288_958,
///         1_656.154_606_023_661,
///         2_259.012_129_598_249,
///         -3.098_683_050_943_824,
///         4.579_534_132_135_011,
///         6.246_541_551_539_432,
///         dt,
///         eme2k,
/// );
///
/// let kep = State::keplerian(
///        7_712.186_117_895_041,
///        0.158_999_999_999_999_95,
///        53.75369,
///        1.998_632_864_211_17e-5,
///        359.787_880_000_004,
///        25.434_003_407_751_188,
///        dt,
///        eme2k
/// );
/// // We can check whether two states are equal.
/// if cart != kep {
///     dbg!("{:?}", cart-kep);
///     panic!("This won't happen");
/// }
/// // Of more interest, we can fetch specific orbital elements.
/// println!("sma = {} km   inc = {} degrees", cart.sma(), cart.inc());
/// // Note that the state data is stored as X, Y, Z, VX, VY, VZ.
/// // Hence, the following print statement may display some rounded values despite
/// // being created with fixed values. GMAT has the same "issue"
/// // (but `nyx` won't change your script).
/// println!("ecc = {} km   RAAN = {} degrees", kep.ecc(), cart.raan());
/// ```
pub mod celestia;

/// Include utility functions shared by different modules, and which may be useful to engineers.
pub mod utils;

/// Provides all the input/output needs for this library, including loading of SPICE kernels, and gravity potential files.
pub mod io;

/// Provides all the orbital determination tools.
pub mod od;

pub mod tutorial;

#[macro_use]
extern crate log;
#[macro_use]
extern crate prost_derive;
extern crate hifitime;
extern crate nalgebra as na;

/// Re-export of hifitime
pub mod time {
    pub use hifitime::*;
}

/// Re-export nalgebra
pub mod dimensions {
    pub use na::base::*;
}