fix label rendering over large bodies

1 files changed, 12 insertions, 64 deletions

diff --git a/src/solar_system.rs b/src/solar_system.rs
index c53f045..81567d0 100644
--- a/src/solar_system.rs
+++ b/src/solar_system.rs
@@ -2,7 +2,10 @@ pub mod orbit;
 pub mod ship;
 
 use serde::{Deserialize};
-use crate::{known_stars::*, solar_system::orbit::StaticOrbit, timeman::Second};
+use crate::known_stars::*;
+use crate::solar_system::orbit::*;
+use crate::solar_system::ship::*;
+use crate::timeman::Second;
 use std::error::Error;
 
 const GRAVITATIONAL_CONSTANT: f64 = 6.67408e-20;
@@ -48,16 +51,9 @@ pub struct SolarSystem
 {
     id: SystemId,
     name: String,
+ 
     bodies: Vec<OrbitalBody>,
-}
-
-pub fn update_systems(
-    solar_systems: std::slice::IterMut<'_, SolarSystem>,
-    time: Second)
-{
-    for system in solar_systems {
-        system.update(time);
-    }
+    ships: Vec<Ship>
 }
 
 impl SolarSystem
@@ -107,6 +103,7 @@ impl SolarSystem
             id: id,
             name: bodies[0].name().clone(),
             bodies: bodies,
+            ships: vec![]
         })
     }
 
@@ -186,65 +183,16 @@ impl OrbitalBody
             None => return 0
         }
     }
-    
+
     pub fn calculate_orbit_at(
         &self,
         time: Second)
-    -> cgmath::Vector3<f64>
+    -> cgmath::Vector3<Kilometers>
     {
-        let orbit = match &self.orbit {
-            Some(v) => v,
-            None => return cgmath::vec3(0.0, 0.0, 0.0)
-        };
-
-        if orbit.parent.is_none() {
-            return cgmath::Vector3::<f64>::new(0.0, 0.0, 0.0);
-}
-
-        let eccentricity = orbit.eccentricity;
-
-        let long_asc_node = orbit.long_asc_node;
-        let arg_periaps = orbit.long_periapsis - long_asc_node;
-
-        let sma_cubed = orbit.semi_major_axis.powf(3.0);   
-        let mean_motion = (self.sgp / sma_cubed).sqrt();
-
-        let mean_anomaly_epoch = orbit.mean_long - orbit.long_periapsis;
-        let mean_anomaly = mean_anomaly_epoch + (mean_motion * time as f64);
-
-        //Find the eccentric anomaly via newton's method
-        let mut eccentric_anomaly = mean_anomaly;
-        for _ in 0..100 {
-            let (e_sin, e_cos) = eccentric_anomaly.sin_cos();
-            let new_anomaly = eccentric_anomaly -
-                (
-                    (eccentric_anomaly - eccentricity * e_sin - mean_anomaly) /
-                    (1.0 - eccentricity * e_cos)
-                );
-
-            let diff = eccentric_anomaly - new_anomaly;
-            eccentric_anomaly = new_anomaly;
-            if diff.abs() < 1e-6 {
-                break;
-            }
+        match &self.orbit {
+            Some(orbit) => orbit.calculate_position_at(self, time),
+            None => cgmath::vec3(0.0, 0.0, 0.0)
         }
-
-        let true_anomaly = 2.0 * (
-            ((1.0 + eccentricity) / (1.0 - eccentricity)).sqrt() 
-            * (eccentric_anomaly / 2.0).tan()
-        ).atan();
-
-        let vw = true_anomaly + arg_periaps;
-        let (vw_sin, vw_cos) = vw.sin_cos();
-        let (omega_sin, omega_cos) = long_asc_node.sin_cos();
-        let (i_sin, i_cos) = orbit.inclination.sin_cos();
-
-        let r = orbit.semi_major_axis * (1.0 - eccentricity * eccentric_anomaly.cos());
-        let x = r * (omega_cos * vw_cos - omega_sin * vw_sin * i_cos);
-        let y = r * i_sin * vw_sin;
-        let z = r * (omega_sin * vw_cos + omega_cos * vw_sin * i_cos);
-
-        cgmath::Vector3::<f64>::new(x, y, z)
     }
 }