Orbital elements and the state vector (each bullet pt is 20%) For an Earth orbiting satellite with the following state vector: = [0, 0, -20000] k = [2, 2, 0] /. Find orbital elements. You may assume that Earth's gravitational parameter is 4x105 km3/s2. Sketch this orbit in GEC. Indicate the position of a spacecraft What will be the satellite's right ascension () and declination () angles after it traverses another 135 deg along its trajectory