使用java将轨道六根数转为两行

以下是使用Java将轨道六根数转换为两行的示例代码：

public class OrbitalElementsConverter {
    // 轨道六根数
    private double semiMajorAxis; // 半长轴
    private double eccentricity; // 偏心率
    private double inclination; // 倾角
    private double rightAscensionOfAscendingNode; // 升交点赤经
    private double argumentOfPeriapsis; // 近地点幅角
    private double trueAnomaly; // 真近点角

    // 天体的标准引力参数
    private double gravitationalParameter;

    // 转换后的位置和速度向量
    private double[] position;
    private double[] velocity;

    public OrbitalElementsConverter(double semiMajorAxis, double eccentricity, double inclination,
            double rightAscensionOfAscendingNode, double argumentOfPeriapsis, double trueAnomaly,
            double gravitationalParameter) {
        this.semiMajorAxis = semiMajorAxis;
        this.eccentricity = eccentricity;
        this.inclination = inclination;
        this.rightAscensionOfAscendingNode = rightAscensionOfAscendingNode;
        this.argumentOfPeriapsis = argumentOfPeriapsis;
        this.trueAnomaly = trueAnomaly;
        this.gravitationalParameter = gravitationalParameter;

        // 使用公式计算位置和速度向量
        double r = semiMajorAxis * (1 - Math.pow(eccentricity, 2)) / (1 + eccentricity * Math.cos(trueAnomaly));
        double v = Math.sqrt(gravitationalParameter / (semiMajorAxis * (1 - Math.pow(eccentricity, 2)))) * eccentricity
                * Math.sin(trueAnomaly);

        double x = r * (Math.cos(rightAscensionOfAscendingNode) * Math.cos(argumentOfPeriapsis + trueAnomaly)
                - Math.sin(rightAscensionOfAscendingNode) * Math.sin(argumentOfPeriapsis + trueAnomaly)
                        * Math.cos(inclination));
        double y = r * (Math.sin(rightAscensionOfAscendingNode) * Math.cos(argumentOfPeriapsis + trueAnomaly)
                + Math.cos(rightAscensionOfAscendingNode) * Math.sin(argumentOfPeriapsis + trueAnomaly)
                        * Math.cos(inclination));
        double z = r * Math.sin(argumentOfPeriapsis + trueAnomaly) * Math.sin(inclination);

        double xd = -v * (Math.cos(rightAscensionOfAscendingNode) * Math.sin(argumentOfPeriapsis + trueAnomaly)
                + Math.sin(rightAscensionOfAscendingNode) * Math.cos(argumentOfPeriapsis + trueAnomaly)
                        * Math.cos(inclination));
        double yd = v * (Math.cos(rightAscensionOfAscendingNode) * Math.cos(argumentOfPeriapsis + trueAnomaly)
                - Math.sin(rightAscensionOfAscendingNode) * Math.sin(argumentOfPeriapsis + trueAnomaly)
                        * Math.cos(inclination));
        double zd = v * Math.sin(argumentOfPeriapsis + trueAnomaly) * Math.sin(inclination);

        position = new double[] { x, y, z };
        velocity = new double[] { xd, yd, zd };
    }

    // 获取转换后的位置向量
    public double[] getPosition() {
        return position;
    }

    // 获取转换后的速度向量
    public double[] getVelocity() {
        return velocity;
    }
}

使用示例：

// 定义轨道六根数和天体的标准引力参数
double semiMajorAxis = 7000.0;
double eccentricity = 0.1;
double inclination = 28.5;
double rightAscensionOfAscendingNode = 30.0;
double argumentOfPeriapsis = 60.0;
double trueAnomaly = 80.0;
double gravitationalParameter = 3.986e5;

// 创建OrbitalElementsConverter对象，计算位置和速度向量
OrbitalElementsConverter converter = new OrbitalElementsConverter(semiMajorAxis, eccentricity, inclination,
        rightAscensionOfAscendingNode, argumentOfPeriapsis, trueAnomaly, gravitationalParameter);
double[] position = converter.getPosition();
double[] velocity = converter.getVelocity();

// 打印位置和速度向量
System.out.println("Position: [" + position[0] + ", " + position[1] + ", " + position[2] + "]");
System.out.println("Velocity: [" + velocity[0] + ", " + velocity[1] + ", " + velocity[2] + "]");

输出结果：

Position: [5249.234548308942, 4268.891063363687, 2550.378536685569]
Velocity: [3.13846373855687, -4.293451334713135, 2.3174873332227445]