Operating GPS satellites periodically perform orbital maneuvers for station-keeping
the verdict
INSUFFICIENT LEANING
refutedsupported
the weight of evidence
3 sources for · 0 against
The retrieved evidence includes general studies and technical literature regarding satellite station-keeping maneuvers and orbital corrections, but lacks specific documentation directly confirming that operational GPS satellites periodically perform such maneuvers.
This paper considers the problem of out of plane orbital maneuvers for station keeping of satellites. The main idea is to consider that a satellite is in an orbit around the Earth and that it has its orbit is disturbed by one or more forces. Then, it is necessary to perform a small amplitude orbital correction to return the satellite to its original orbit, to keep it performing its mission. A low thrust propulsion is used to complete this task. It is important to search for solutions that minimize the fuel consumption to increase the lifetime of the satellite. To solve this problem a hybrid optimal control approach is used. The accuracy of the satisfaction of the constraints is considered, in order to try to decrease the fuel expenditure by taking advantage of this freedom. This type of problem presents numerical difficulties and it is necessary to adjust parameters, as well as details of the algorithm, to get convergence. In this versions of the algorithm that works well for planar maneuvers are usually not adequate for the out of plane orbital corrections. In order to illustrate the method, some numerical results are presented.
Abstract
This paper introduces a theoretical description, force, and torque analysis of a Reaction Control Thruster (RCT) used as an actuator in Attitude Determination and Control Subsystem (ADCS). Mathematical formalization, realization, and implementation are offered to implement the RCT model using Matlab-Simulink. Furthermore, this paper proposes an accurate RCT Simulink model to control the orientation and stabilizes the Geostationary Earth Orbit (GEO) satellite within its orbit. Finally, a comparative analysis is carried out with an existing satellite platform (Eurostar-3000) based on the Root Mean Square Error (RMSE) for the delta velocity (delta-𝒱) parameter. The outcomes of the model simulation validated the effectiveness of the proposed approach.
Ensuring that satellites in geostationary Earth orbit (GEO) remain in their allocated station-keeping windows necessitates accurate station-keeping algorithms. Due to the direct relationship between the fuel efficiency of station-keeping trajectories and satellite mass, optimizing propellant consumption can extend satellite lifetime, increase payload capacity, and lower launch costs. In this paper, we propose a nonlinear model predictive control (NMPC) policy for station keeping and collocation of multiple GEO satellites under infrequent high-thrust impulsive control. We develop a sequential convex programming-based approach to find locally fuel-optimal trajectories with enforced separation distances between collocated satellites. Numerical simulations with NASA’s General Mission Analysis Tool demonstrate the effectiveness of the proposed NMPC policy for both GEO satellite station keeping and as a collocation strategy for three GEO satellites in a single station-keeping window.
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