Abstract
Working with the mean orbit elements, the secular drift of the longitude of the ascending node and the sum of the argument of perigee and mean anomaly are set equal between two neighboring orbits. By having both orbits drift at equal angular rates on the average, they will not separate over time due to the influence of the perturbative effects of the asphericity of the Earth. The relativistic corrections and the direct solar radiation pressure to the equations of motion, as is considered in this work. The problem is stated. The expressions for the time rate of change of the longitude of the ascending node and the sum of the argument of perigee and mean anomaly in terms of the augmented Delaunay canonical elements are obtained. The expressions for the second order conditions that guarantee that the drift rates of two neighboring orbits are equal on the average are derived. Keywords: Invariant relative orbits, Spacecraft flying formations, Relativistic corrections, Direct solar radiation pressure.
Highlights
Introduction formation namely the chiefThe different methods toThe formation flying concept is the use of several setup invariant relative orbits for spacecraft flying small satellites which work together in a group to formations are: 1- Inclination difference method, 2- Node accomplish the objective of one larger, usually more difference method, 3- Combination of the above two expensive, satellite
The benefits are numerous, formation flying designing certain invariant relative orbits for spacecraft missions have many difficulties that single platform flying formations, and it seems worth to sketch some of missions do not
Easton and Brescia (1969) of relative motion between spacecrafts and is only possible the United States Naval Research Laboratory analyzed for satellites in circular, coplanar orbits
Summary
We obtained the transformed Hamiltonian, for different orders 0, 1, 2, as (Abd ElSalam et al, 2005; El-Saftawy et al, 1998)
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