\(J_2\) invariant relative orbits for spacecraft formations
From MaRDI portal
Publication:5943545
DOI10.1023/A:1011161811472zbMath0989.70018OpenAlexW1489136118MaRDI QIDQ5943545
Kyle T. Alfriend, Hanspeter Schaub
Publication date: 28 July 2002
Published in: Celestial Mechanics and Dynamical Astronomy (Search for Journal in Brave)
Full work available at URL: https://doi.org/10.1023/a:1011161811472
J(2) invariant relative orbitlongitude of ascending nodemean argument of latitudemean orbital elementssecular drift
Related Items (28)
Bounded relative motion under zonal harmonics perturbations ⋮ Nonsingular vectorial reformulation of the short-period corrections in Kozai's oblateness solution ⋮ Integrable approximation of \(J_2\)-perturbed relative orbits ⋮ Solutions and periodicity of satellite relative motion under even zonal harmonics perturbations ⋮ A satellite relative motion model including \(J_2\) and \(J_3\) via Vinti's intermediary ⋮ The \(J_2\) invariant relative configuration of spaceborne SAR interferometer for digital elevation measurement ⋮ Symmetry properties of optimal relative orbit trajectories ⋮ Сравнение моделей относительного движения группы космических аппаратов ⋮ Solution set on the natural satellite formation orbits under first-order Earth's non-spherical perturbation ⋮ \(J _{2}\) invariant relative orbits via differential correction algorithm ⋮ Nonlinear analytic solution for perturbed relative motion using differential equinoctial elements ⋮ Modeling orbital relative motion to enable formation design from application requirements ⋮ Application of Hamiltonian structure-preserving control to formation flying on a \(J_2\)-perturbed mean circular orbit ⋮ A simple time domain collocation method to precisely search for the periodic orbits of satellite relative motion ⋮ Modelling natural formations of LEO satellites ⋮ Invariant relative orbits for satellite constellations: a second-order theory ⋮ Bounded motion design in the Earth zonal problem using differential algebra based normal form methods ⋮ Semi-analytical model for third-body perturbations including the inclination and eccentricity of the perturbing body ⋮ Relative motion of satellites exploiting the super-integrability of Kepler's problem ⋮ Analysis of \(J_2\)-perturbed motion using mean non-osculating orbital elements ⋮ Bounded relative motions for formation flying in displaced orbits by low-thrust propulsion ⋮ Long-term evolution of orbital inclination due to third-body inclination ⋮ An in-plane \(J_2\)-invariance condition and control algorithm for highly elliptical satellite formations ⋮ Reducing inter-satellite drift of low Earth orbit constellations using short-periodic corrections ⋮ Bounded Martian satellite relative motion ⋮ Improved initialization conditions and single impulsive maneuvers for \(J_2\)-invariant relative orbits ⋮ Long-term passive distance-bounded relative motion in the presence of \(J_2\) perturbations ⋮ Canonical modelling of relative spacecraft motion via epicyclic orbital elements
This page was built for publication: \(J_2\) invariant relative orbits for spacecraft formations
