SAX ([Boella et al., 1997a,Piro, 1995]), Satellite per Astronomia X, i.e. X-ray astronomy satellite, renamed BeppoSAX after launch in honour of Giuseppe (Beppo) Occhialini, is a major program of the Italian Space Agency (ASI) with participation of the Netherlands Agency for Aerospace Programs (NIVR). The BeppoSAX consortium, supporting the development of the mission, is composed by the following institutes: Istituto di Astrofisica Spaziale (ASI, C.N.R., Rome), Istituto di Fisica Cosmica ed Applicazioni Informatiche (IFCAI, C.N.R., Palermo), Istituto Tecnologie e Studio Radiazioni Extraterrestri (ITeSRE, C.N.R., Bologna), Physics Department of the University of Ferrara, Space Research Organization of the Netherlands (SRON, Utrecht) and Space Science Department (SSD, ESA, Noordwijk, The Netherlands).
The scientific payload covers a very wide energy range (-300 keV).
This capability, in combination with a relatively large area, a medium
energy resolution and an imaging resolution of
(in
-10 keV), allows the simultaneous observation of the same
source at different wavelengths, which is of key importance for
understanding many astrophysical processes.
Moreover, the presence of wide field instruments in the 2-28 keV energy
band makes it possible to monitor all the X-ray transients sources:
this capability has been fundamental in localizing the first prompt
X-ray counterparts to GRBs.
BeppoSAX was launched on April 30, 1996, by an Atlas-Centaur into
a 600 Km orbit, with a period of 96 min (the time between
two passages over the ground station is
103 min)
and with an inclination of
.
The choice of this orbit presents many advantages:
the shielding of the terrestrial magnetic field reducing the
cosmic ray induced background (especially for high energy instruments),
a slow-varying particle induced background level due to the
small modulation of the Earth magnetic field rigidity cut-off,
and the marginal passage above the South Atlantic Geomagnetic Anomaly
(SAGA).
The spacecraft structure (fig. ) consists of three
basic modules:
the Service Module, in the lower part, that houses all the subsystems
and the electronics of the scientific instruments; the Payload
Module with scientific instruments and star trackers; the
Thermal Shade Structure enclosing the Payload.
The total mass is
1400 Kg (480 of the only payload) and
the linear dimensions are
m (height) and
m (diameter),
when the solar panels are closed.
The total power is 800 W, with 260 W only for the payload.
The spacecraft is three axis stabilized and has a pointing accuracy
of 1; when not pointing, the maximum slew rate is
/min.
The need to mantain the normal direction to the solar panels
within 30
(sometimes 45
) from the Sun is the main
attitude constraint.
When, 11 min per orbit, BeppoSAX passes over the ground Telemetry and Telecommand (TT&C) station at the Italian base near Malindi (Kenya), the Operation Control Center (OCC) in Rome communicates with it through a bidirectional Intelsat link; during this time window, many tasks are performed: telecommand up-linking, data downloading, spacecraft doppler and ranging measurements and on-board time (OBT) - Universal Time (UT) synchronization.
The possibility, offered by these frequent communications, of a fast reaction and rescheduling within a few hours in favour of target of opportunity objects has turned out to be very useful in the case of GRBs.