apparentEccentricity function

double apparentEccentricity(
  1. double e,
  2. double i,
  3. double w
)

Apparent eccentricity from true orbital elements.

Implementation

double apparentEccentricity(double e, double i, double w) {
  final ci = math.cos(i);
  final sW = math.sin(w), cW = math.cos(w);
  final aa = (1 - e * e * cW * cW) * ci * ci;
  final b = e * e * sW * cW * ci;
  final cc = 1 - e * e * sW * sW;
  final d = aa - cc;
  final sD = math.sqrt(d * d + 4 * b * b);
  return math.sqrt(2 * sD / (aa + cc + sD));
}