Remote Nanosatellite Formation Designs With Orbit Perturbation Corrections and Attitude Control/Propulsion Subsystem Correlation

摘要

The innovative idea of distributing the functionality of current larger satellites among smaller, cooperative satellites has been sincerely considered for assorted space missions to accomplish goals that are not possible or very difficult to do with a single satellite. Additionally, the utilization of smaller satellites is maximized within formations and clusters to conduct missions such as interferometry and earth-sensing. This paper presents a methodology to describe, populate and analyze numerous formation designs employing the use of Hill's equations of motion to describe a formation's dynamics. These equations of motion are then programmed into a MATLAB code to produce Cartesian elements for input into a Satellite Tool Kit(Trademark) (STK) simulation that demonstrates numerous possible cluster formation designs. These simulations are then used to determine delta V requirements for overcoming LEO- type perturbations that were modeled within STK's High Precision Orbit Propagator (HPOP). Finally, components from two subsystems Attitude Determination and Control (ADCS) and Propulsion, using the delta V calculations from the simulation analysis and current advances in MicroElectroMechanical systems (MEMs) and nanosatellite technology, are presented based on a mass constraint of 10kg for the entire satellite.