Follow PicSat on
   Twitter30width    Youtube30width
French version   English version    
Logo transparent
Unravelling the Beta Pictoris System
Picsat is: in a polar orbit at 505km altitude
Number of telemetry packets received today:
Last beacon satellite:
2018-01-22 01:01:20 UTC

Last beacon payload:
2017-12-08 17:04:33 UTC

Uplink is not active
Downlink is not active

Launch and orbit

Launch on the PSLV

PicSat has been launched on 12th January 2018, by the PSLV-C40 (Polar Satellite Vehicle Launcher), operated by ISRO, the Indian Space Agency. The orbit is a 505 km Sun-Synchronous Polar Orbit

As virtually any other Cubesat, PicSat was not launched as the primary payload of PSLV-C40, but in so-called piggybacking. The launcher sent a 700 kg Earth-observation satellite, Cartosat 2ER, as its main payload, and PicSat took advantage of some free space on the launcher to get a ride to space (along with a dozen other Cubesats). Piggybacking makes possible to send a satellite without a dedicated launch (which would be impossible in terms of cost for a Cubesat project). The drawback is that we did not have any word to say on the selected orbit.


Orbital parameters of PicSat

The TLEs (Two Line Elements) for PicSat are:

1 43134U 18004Z   18018.84436326  .00000951  00000-0  44436-4 0  9992
2 43134  97.5553  80.9974 0008362 259.6426 100.3868 15.22273301   991

What does that mean?

Six degrees of freedom

When an object is orbitting around the Earth, the only force it is experiencing is the gravitational attraction of the planet. Because of Newton's second law of motion, the acceleration of the satellite can be directly related to this gravitationnal force exerted by the planet, and hence to the position of the satellite relative to the Earth. This means that the acceleration of the satellite is directly related to its position. In physics jargon, we say that the motion of the satellite is governed by a second order differential equation. A direct consequence of this fact is that if one knows the exact position and velocity of the satellite at any given time, one can compute the complete orbital motion, past, present, and future, of the satellite. An orbit is a trajectory which only has 6 degrees of freedom (3 coordinates for the position of the satellite in space, 3 for its velocity).

But even if in theory it would be possible to describe each and every possible orbital trajectory around the Earth using a set of 6 parameters giving the position and velocity at a single fixed time (say, 1 January, 2000, at noon), it would not be a very useful description in practice, as one would have to run a complete simulation to get any idea of the trajectory of the satellite around the Earth.

The six classical orbital parameters

A more useful description of an orbit than the position-velocity representation is related to the 17th century Kepler's first law of planetary motion, which states that the orbit of a planet going around the Sun is an ellipse, with the Sun at one of the two foci. A man-made orbitter going around the Earth being essentially the same thing as a planet orbitting around the Sun (from a mechanics point of view, at least), the orbit of a satellite aroud the Earth is also an ellipse, which can be described by two parameters: the eccentricty (related to its shape), and its semi-major axis (its size). Add three different angles (argument of periapsis, longitude of the ascending node, and inclination) which give the exact orientation of the orbital plane, and a time reference (time of apoapsis), and you have the standard set of 6 orbital parameters.

Two-line elements

There is still one more way to describe an orbit, which is very broadly used in the space industry: two-line elements. A two-line element is a standardized set of values, written on two lines (hence the name!), and which gives various information about an artifical satellite. In particular, this set contains: the inclination, the longitude of the ascending node, the eccentricty, argument of periapsis, mean anomaly, and mean motion. The mean motion, which gives the number of revolutions of the satellite per day, is directly related to the orbital period, and thus to the semi-major axis. The mean anomaly, which gives the position of the satellite along its orbit at a given time, can be seen as another way to have a time reference for the orbital motion.