Geometric Spacecraft Formations Establishment Animations

<p>These animations illustrate the performance of a control algorithm based on artificial potential function and relative orbital elements methodologies. Three geometric spacecraft formations are designed and established and the visual inspection of an on-orbit structure is presented. The orbital dynamics model used for the numerical simulation of these scenarios includes geopotential perturbations (J<sub>2</sub> to J<sub>6</sub>), atmospheric drag (NRLMSISE-00 model), solar radiation pressure, and three-body effects (Moon and Sun). The inertial states of the spacecraft are propagated and the relative positions are transformed into the Local-Vertical, Local-Horizontal (or Hill) reference frame.</p> <p> </p> <p><u>Files</u></p> <ul> <li>hexagonal_lattices.mp4: Establishment of a 37-spacecraft formation composed of two hexagonal lattices. The chief is on a 500 km altitude, 30˚ inclination circular orbit. The average delta-V is 3.1 m/s per spacecraft.</li> <li>tetrahedron.mp4: Establishment of a 4-spacecraft formation arranged in a tetrahedron shape. This scenario illustrates the limitations of the control algorithm when used with relative positions that require constant actuation. The average delta-V is 19 m/s per spacecraft.</li> <li>triangular_lattice.mp4: Establishment of a 10-spacecraft triangular lattice. The average delta-V is 6.7 m/s per spacecraft.</li> <li>visual_inspection.mp4: Visual inspection of a structure on a 700 km altitude, 80˚ inclination circular orbit. The total delta-V of this scenario is 2.8 m/s.</li> </ul>