\begin{table}%T1
\par
   \caption{INTEGRAL -- main facts and figures (see also Fig.~\ref{spacecraft}).}
\label{facts}
  {{
        \begin{tabular}{ll}
            \hline\hline
Objective & Fine imaging and spectroscopy of 
celestial gamma-ray sources in the energy range 15 keV to 10 MeV \\
%\noalign{\smallskip}
            \hline
            %\noalign{\smallskip}
Instruments & \\
Imager IBIS & 15 keV--10 MeV, coded aperture mask, 16483 CdTe dets, each (4$~\times~$4$~\times~$2) mm,
4096 CsI dets, each (8.4$~\times~$8.4$~\times~$30) mm\\
Spectrometer SPI & 18 keV--8 MeV, coded aperture mask, 19 Ge dets, each (6$~\times~$7) cm, cooled @ 85K\\
X-ray Monitor JEM-X & 4 keV--35 keV, coded aperture mask, micro-strip detector (2$~\times~$), (each \O 250 mm) Xe/CH$_{4}$ gas\\
Optical Monitor OMC & $V$-band (500--600 nm), CCD detector, refractive optics\\
\par
%\noalign{\smallskip}
            \hline
\par
Launch Vehicle &	 Proton with Block DM upper stage. Launch from Baikonur/Kazakhstan\\
\par
%\noalign{\smallskip}
            \hline
\par
Operational orbit &	Apogee height:	153~657  km\\
(as achieved on  &	Perigee height:	9050    km\\                        
01 Nov 2002)	& Inclination:	52.2$^{\circ}$  \\
&	Argument of perigee:	302$^{\circ}$  \\
	& RA ascending node:	103$^{\circ}$  \\        
	& Period	3             days \\
	& Max eclipse duration: 	1.2          h \\ 
\par
%\noalign{\smallskip}
            \hline
\par
Ground stations	& Redu (Belgium) and Goldstone (California)\\
& Coverage 100\% above 40 000 km \\
%\noalign{\smallskip}
            \hline
\par
Lifetime &  	2.2 years nominal  5.2 years extended \\
%\noalign{\smallskip}
            \hline
Dimensions & 	Satellite body dimension : (2.8$~\times~$3.2$~\times~$5) m \\
& Solar array span                         16  m\\
\par
%\noalign{\smallskip}
            \hline
\par
Mass	& Total mass:                         3954       kg\\
& Dry mass:                           3414       kg\\
& Fuel (hydrazine, at launch):                  540       kg\\
&  Instrument mass                2013       kg\\
\par
%\noalign{\smallskip}
            \hline
\par
Power/Energy Storage	& 28 V regulated power bus\\
& Advanced Rigid Solar Arrays, Silicon cells.\\
& @ launch (@ 2.2 years):               2377 W (1960 W), Sun aspect angle: 0$^{\circ}$\\
& @ launch (@ 2.2 years):               1834 W (1630 W),  Sun aspect angle: 40$^{\circ}$ \\
&   Two 24 Ah NiCd rechargeable batteries\\
\par
%\noalign{\smallskip}
            \hline
\par
Communication &	$S$-band up and down link, 2 fixed antennae\\
& Telemetry rate:                   113 kbps (payload: 108 kbps)\\
& Telecommand rate:              2  kbps\\     
\par
%\noalign{\smallskip}
            \hline
\par
Mechanical Properties &	First axial mode: $\geq$38 Hz\\
& First lateral mode:  $\geq$12 Hz\\
& Load case 1: $\pm$9 g longitudinal, $\pm$1.5 g lateral\\
& Load case 2:    $\pm$0 g longitudinal, $\pm$4.5 g lateral\\
\par
%\noalign{\smallskip}
            \hline
Pointing and alignment &	3-axes stabilised spacecraft (instrument pointing axis: +X, Sun pointing: +Z)\\
(as specified) & Absolute pointing error: 5$^{\prime}$ ($Y$, $Z$),      15$^{\prime}$ $(X)$\\
& Instrument alignment:       1$^{\prime}$ ($Y$, $Z$),        3$^{\prime}$ $(X)$\\
%\noalign{\smallskip}
            \hline
         \end{tabular}}}
\end{table}