From 5dfa296ab99b5c989a2f6b2f68c7da5d706fb392 Mon Sep 17 00:00:00 2001 From: KOSASIH Date: Tue, 30 Jul 2024 08:14:56 +0700 Subject: [PATCH] Create orbital_mechanics_simulator.java --- .../orbital_mechanics_simulator.java | 41 +++++++++++++++++++ 1 file changed, 41 insertions(+) create mode 100644 core/aerospace/orbital_mechanics_simulator.java diff --git a/core/aerospace/orbital_mechanics_simulator.java b/core/aerospace/orbital_mechanics_simulator.java new file mode 100644 index 0000000..9991c0d --- /dev/null +++ b/core/aerospace/orbital_mechanics_simulator.java @@ -0,0 +1,41 @@ +import java.util.ArrayList; +import java.util.List; + +public class OrbitalMechanicsSimulator { + private List spacecraftList; + private List 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)); + } +}