Create orbital_mechanics_simulator.java

core/aerospace/orbital_mechanics_simulator.java

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+import java.util.ArrayList;
+import java.util.List;
+
+public class OrbitalMechanicsSimulator {
+    private List<Spacecraft> spacecraftList;
+    private List<Planet> planetList;
+
+    public OrbitalMechanicsSimulator() {
+        spacecraftList = new ArrayList<>();
+        planetList = new ArrayList<>();
+    }
+
+    public void simulateOrbit(Spacecraft spacecraft, Planet planet) {
+        // Calculate orbital elements
+        double semiMajorAxis = spacecraft.getOrbit().getSemiMajorAxis();
+        double eccentricity = spacecraft.getOrbit().getEccentricity();
+        double inclination = spacecraft.getOrbit().getInclination();
+        double longitudeOfAscendingNode = spacecraft.getOrbit().getLongitudeOfAscendingNode();
+        double argumentOfPeriapsis = spacecraft.getOrbit().getArgumentOfPeriapsis();
+        double trueAnomaly = spacecraft.getOrbit().getTrueAnomaly();
+
+        // Calculate orbital period
+        double orbitalPeriod = calculateOrbitalPeriod(semiMajorAxis, planet.getMass());
+
+        // Calculate orbital velocity
+        double orbitalVelocity = calculateOrbitalVelocity(semiMajorAxis, planet.getMass());
+
+        // Update spacecraft position and velocity
+        spacecraft.updatePositionAndVelocity(orbitalPeriod, orbitalVelocity);
+    }
+
+    private double calculateOrbitalPeriod(double semiMajorAxis, double planetMass) {
+        // Calculate orbital period using Kepler's third law
+        return Math.sqrt(4 * Math.PI * Math.PI * semiMajorAxis * semiMajorAxis * semiMajorAxis / (planetMass * G));
+    }
+
+    private double calculateOrbitalVelocity(double semiMajorAxis, double planetMass) {
+        // Calculate orbital velocity using vis-viva equation
+        return Math.sqrt(planetMass * (2 / semiMajorAxis - 1 / semiMajorAxis));
+    }
+}