The effect in the argument of periapsis due to the main zonal harmonics is revealed to be about three orders of magnitude greater than that of SRP. Two comparisons are given. To obtain longer lifespan of the spacecraft, continuous variable low-thrust control is implemented. Radial and/or ...
In this work, we use the Hill restricted 4-body problem (HR4BP) to model the motion of a particle in the Sun–Earth–Moon (SEM) system. The HR4BP is a coherent periodic Hamiltonian system that is both a generalization of the Earth–Moon CR3BP and Sun–Earth Hill’s problem (Scheeres...
If the orbital elements of a lunar satellite are referred to selenographic axes in the true Moon as it rotates and librates, then the librations cause changes in the orientation angles (node, inclination and periapsis argument) large enough that long period planetary perturbation theory cannot be...
This paper addresses the problem of planar transfer, so the thrust acceleration vector lies within the orbital plane and the orbital elements to be studied are semi-major axis, eccentricity, argument of perigee, and true/eccentric anomaly. The rates of change of the orbital elements due to low...
AOP argument of periapsisCPF Consolidated Prediction FormatDEC declinationECC eccentricityUKF unscented Kalman filterGround-based optical tracking systems used in space surveillance provide no range information, and an observed arc is too short compared to the orbital period to provide enough dynamical ...
The unknown parameters of (29) (components of the vector z): the magnitude of the initial velocity impulse ΔV0; the longitude of the ascending node Ω0, and the argument of latitude u0 of the SC starting point from the low circular geocentric orbit of a given inclination i0; times of...