General Perturbation Method for Satellite Constellation Deployment Using Nodal Precession

Abstract

Nomenclature a = mean semi-major axis, km A pr op = propulsion system acceleration, m/s 2

Survey on Optimization Methods for LEO-Satellite-Based Networks with Applications in Future Autonomous Transportation

“…Deploying a global-coverage constellation with the existing launch paradigms would require a dedicated launch for each orbital plane. This would result in very high launch costs beyond the budget of usual missions [120,125]. As cost is one of the prime optimization parameters, developing an efficient way to deploy a constellation is essential [126].…”

“…Using orbital perturbations for plane separation results in a longer time for full constellation deployment, whereas a dedicated launch induces high mission costs, resulting in a trade-off between deployment time and launch cost [125].…”

Deployment of Constellation with Different Inclinations Using the Nodal Precession and Thrust

“…Yang et al [ 16 ] proposed a method to deploy a constellation of satellites using a combination of thrust and gravitational perturbation. McGrath et al used the same strategy of orbit plane separation to solve the deployment problem of circular orbit constellations using a resolved approach [ 17 ]. Both Gomez and Yang proposed a combination of thrust and gravitational perturbation for the indirect method of constellation deployment, but the tangential thrust they use is for performing orbital semi-major axis holding of satellites in parked orbits and does not have a direct effect on RAAN separation.…”

Optimization of constellation deployment using on-board propulsion and Earth nodal regression

“…King and Beidleman proposed a sequential deployment of satellites using carrier vehicles, whose in-plane maneuvering from a parking orbit to the target one is timed with a well-defined delay, thus generating the required DX, through differential J 2 drift. An analytical implementation based on the sequential method was proposed by McGrath and Macdonald (2020), however, limiting the formulation to in-plane maneuvers and circular orbits; Cornara et al (2001) proposed a similar approach, highlighting many interesting aspects related to constellation life-cycle as well, ranging from launcher selection to end-of-life strategies. A study on a 180°plane separation with electric propulsion has been carried out by Gomez Jenkins et al (2018), presenting a combination of indirect maneuvering and direct thrusting during coasting phases, highlighting once again that, due to the low thurst levels of electric propulsion, the direct thrusting in LEO is not convenient.…”