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Using Atmospheric Drag for Constellation Control of Low Earth Orbit Micro-satellites
| Content Provider | CiteSeerX |
|---|---|
| Author | Plessis, J. Du Steyn, W. H. |
| Abstract | In certain low Earth orbit (LEO) satellite missions it is required that two or more satellites must operate in a certain spacial configuration relative to each other. This paper introduces a simple concept of utilising aerodynamic drag to achieve this type of constellation control. A necessary structural requirement for the satellites is that a change in projected area on a plane perpendicular to the velocity vector of the satellite can be brought about by means of an orientation adjustment. The aerodynamic force acting on the satellite can thus be controlled through a simple eigenaxis slew of a three-axis stabilised satellite. The slew can be done through conventional means, including thrusters, momentum exchange methods or magnetorquers. The presence of a GPS receiver on the satellite is necessary for accurate position information. It is shown that certain critical parameters influence the bounds of control time and accuracy. These parameters include the physical properties of the satellites, the orbital configuration and the state of the atmosphere. A control system to illustrate the concept is proposed and tested through detailed computer simulations. The simulations include the influence of other orbit perturbation forces acting on the satellite, like the effects of the Earth's oblateness, solar radiation pressure and lunisolar attractions. Cowell's method is used to integrate the equations of motion numerically. Typical results for two satellites (mass: 10 kg; maximum cross-sectional area: 0.3947 m |
| File Format | |
| Access Restriction | Open |
| Content Type | Text |
| Resource Type | Article |
