Speaker
Dr
Juan Félix San-Juan
(Scientific Computing Group (GRUCACI), University of La Rioja)
Description
A semi-analytical orbit propagator to study the long-term evolution of spacecraft in Highly Elliptical Orbits is presented. The perturbation model taken into account includes the gravitational effects produced by the first nine zonal harmonics and the main tesseral harmonics affecting to the 2:1 resonance, which has an impact on Molniya orbit-types, of Earth’s gravitational potential, the mass-point approximation for third body perturbations, which on ly include the Legendre polynomial of second order for the sun and the polynomials from second order to sixth order for the moon, solar radiation pressure and atmospheric drag. Hamiltonian formalism is used to model the forces of gravitational nature so as to avoid time-dependence issues the problem is formulated in the extended phase space. The solar radiation pressure is modeled as a potential and included in the Hamiltonian, whereas the atmospheric drag is added as a generalized force. The semi-analytical theory is developed using perturbation techniques based on Lie transforms. Deprit’s perturbation algorithm is applied up to the second order of the second zonal harmonics, J2, including Kozay-type terms in the mean elements Hamiltonian to get “centered” elements. The transformation is developed in closed-form of the eccentricity except for tesseral resonances and the coupling between J2 and the moon’s disturbing effects are neglected. This paper describes the semi-analytical theory, the semi-analytical orbit propagator program and some of the numerical validations.
| Applicant type | Co-author |
|---|
Primary author
Dr
Martin Lara
(Space Dynamics Group, Polytechnic University of Madrid, and GRUCACI, University of La Rioja)
Co-authors
Mr
Denis Hautesserres
(Centre national d'études spatiales (CNES))
Dr
Juan Félix San-Juan
(Scientific Computing Group (GRUCACI), University of La Rioja)
