satellitesfactory 0.0.3

Satellite factory — classify, build and catalogue natural satellites for any planetary system: Solar System moons (Moon, Galileans, Titan, Triton…) or custom configurations.
Documentation 
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use crate::config::parameters::*;

pub struct SatelliteGravity {
    pub mass: f64,
    pub radius: f64,
}

impl SatelliteGravity {
    pub fn new(mass: f64, radius: f64) -> Self {
        Self { mass, radius }
    }

    pub fn surface_acceleration(&self) -> f64 {
        G * self.mass / (self.radius * self.radius)
    }

    pub fn escape_velocity(&self) -> f64 {
        (2.0 * G * self.mass / self.radius).sqrt()
    }

    pub fn orbital_velocity(&self, distance: f64) -> f64 {
        (G * self.mass / distance).sqrt()
    }

    pub fn orbital_period(&self, distance: f64) -> f64 {
        orbital_period(self.mass, distance)
    }

    pub fn synchronous_orbit_radius(&self, rotation_period: f64) -> f64 {
        synchronous_orbit_radius(self.mass, rotation_period)
    }

    pub fn sphere_of_influence(&self, parent_mass: f64, distance: f64) -> f64 {
        distance * (self.mass / parent_mass).powf(2.0 / 5.0)
    }
}

pub fn two_body_force(m1: f64, m2: f64, r: f64) -> f64 {
    G * m1 * m2 / (r * r)
}

pub fn hill_sphere(a: f64, m_satellite: f64, m_planet: f64) -> f64 {
    a * (m_satellite / (3.0 * m_planet)).cbrt()
}

pub fn roche_limit(r_primary: f64, rho_primary: f64, rho_secondary: f64) -> f64 {
    2.456 * r_primary * (rho_primary / rho_secondary).cbrt()
}

pub fn roche_limit_rigid(r_primary: f64, rho_primary: f64, rho_secondary: f64) -> f64 {
    1.26 * r_primary * (rho_primary / rho_secondary).cbrt()
}

pub fn gravitational_binding_energy(mass: f64, radius: f64) -> f64 {
    3.0 * G * mass * mass / (5.0 * radius)
}

pub fn mutual_hill_radius(a1: f64, m1: f64, a2: f64, m2: f64, m_planet: f64) -> f64 {
    let a_avg = (a1 + a2) / 2.0;
    a_avg * ((m1 + m2) / (3.0 * m_planet)).cbrt()
}

pub fn tisserand_parameter(a_sat: f64, a_planet: f64, e: f64, i: f64) -> f64 {
    a_planet / a_sat + 2.0 * ((a_sat / a_planet) * (1.0 - e * e)).sqrt() * i.cos()
}