The graph shows:
- the radius vector minus 6371 km (just to show an approximate altitude) and the orbital speed before and after the maneuver;
- two vertical green lines representing the start and end of the maneuver;
- four points showing the semi-major axis (or mean radius vector) minus 6371 km and mean orbital speed of the last and penultimate orbit before the maneuver and the first and second orbit after the maneuver;
- four dashed horizontal lines representing the mean radius vector - 6371 km and mean orbital speed of the last two orbits before the maneuver and the first two orbits after the maneuver.
BACC data file: CREATION_DATE =
Start : UTC Duration: m s ΔV : m/s Δsma : m (variation of the semi-major axis) ΔRmin : m ΔRmax : m
Here's the osculating inclination before and after the maneuver.
The variation of the inclination during one orbit is caused by the Earth's flattening.
Δi: deg (variation of the osculating inclination).
The J2000 CSS state contained in the BACC data file is converted to the TEME reference frame, then the osculating inclination is calculated. The inclination shown in the graph, therefore, is to the true (instantaneous) equator.
The graph shows the 1-orbit averaged radius vector (or semi-major axis) and orbital speed.
ΔV = m/s
Δsma = m (variation of the semi-major axis)
Here are the perigee and apogee radius vector.
For any given TLE, the program calculates the CSS orbital period T. Then the smallest and the biggest radius vector is found from the TLE epoch minus T/2 to the TLE epoch plus T/2.
Δperigee: m
Δapogee: m
Here is the instantaneous radius vector before and after the maneuver.
Δperigee: m
Δsma: m
Δapogee: m
Δperigee: m
Δsma: m
Δapogee: m
The graph shows the CSS altitude above the WGS 72 ellipsoid for the same TLEs used in the previous graph.