Canonical modelling of relative spacecraft motion via epicyclic orbital elements
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Publication:816892
DOI10.1007/s10569-004-6441-7zbMath1129.70333OpenAlexW2096380042MaRDI QIDQ816892
N. Jeremy Kasdin, Pini Gurfil, Egemen Kolemen
Publication date: 2 March 2006
Published in: Celestial Mechanics and Dynamical Astronomy (Search for Journal in Brave)
Full work available at URL: https://doi.org/10.1007/s10569-004-6441-7
Hamilton's equations (70H05) Hamilton-Jacobi equations in mechanics (70H20) Celestial mechanics (70F15) Orbital mechanics (70M20)
Related Items (11)
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 ⋮ Second-order state transition for relative motion near perturbed, elliptic orbits ⋮ Global bifurcation of planar and spatial periodic solutions in the restricted \(n\)-body problem ⋮ Approximate analysis for relative motion of satellite formation flying in elliptical orbits ⋮ A Hopf variables view on the libration points dynamics ⋮ Application of Hamiltonian structure-preserving control to formation flying on a \(J_2\)-perturbed mean circular orbit ⋮ Adaptive fuzzy finite-time control for spacecraft formation with communication delays and changing topologies ⋮ Frozen-anomaly transformation for the elliptic rendezvous problem ⋮ Improved initialization conditions and single impulsive maneuvers for \(J_2\)-invariant relative orbits
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- Niching genetic algorithms-based characterization of geocentric orbits in the 3D elliptic restricted three-body problem
- Fuel-optimal rendezvous near a point in general Keplerian orbit
- Gauge symmetry of the N-body problem in the Hamilton–Jacobi approach
- Gauge freedom in theN-body problem of celestial mechanics
- \(J_2\) invariant relative orbits for spacecraft formations
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