Sun-Synchronous Highly Elliptical Orbits Using Low-Thrust Propulsion

Pamela Anderson, Malcolm Macdonald
2013 Journal of Guidance Control and Dynamics  
Nomenclature a = semi-major axis, km C n,m = harmonic coefficients of Earth potential e = eccentricity F n = low-thrust normal perturbation scalar F r = low-thrust radial perturbation scalar F t = low-thrust transverse perturbation scalar i = inclination, deg J 2 = perturbation due to Earth's oblateness N = normal perturbation acceleration, mm/s 2 P n,m = associated Legendre polynomials p = semi-parameter, km R = radial perturbation acceleration, mm/s 2 R e = mean radius of Earth, km r = orbit
more » ... arth, km r = orbit radius, km S n,m = harmonic coefficients of Earth potential T = transverse perturbation acceleration, mm/s 2 U = potential U o = point-mass gravitational potential U p = perturbing component of potential body = declination of spacecraft, deg = true anomaly, deg
doi:10.2514/1.59848 fatcat:6mhko4oiazbfnpzy3nv66liyde