Subject: GLONASS S/C mass and dimension This is a multi-part message in MIME format. ------=_NextPart_000_001B_01BE16DA.515BB9C0 Content-Type: text/plain; charset="koi8-r" Content-Transfer-Encoding: quoted-printable Dear colleagues, please find hereafter the information on GLONASS mass and dimensions for preparation of force and tracking data models, kindly presented by NPO PM (Krasnoyarsk). These data have been officially released by NPO PM according to the request of IGEX steering committee to Russian Space Agency. This can be considered as an NPO PM contribution to the IGEX'98 campaign. NPO PM has developed and designed all GLONASS spacecrafts so the data are guaranteed to be correct. The file with GLONASS S/C figures in PCX format is available by request. Please contact GEOZUP Company (e-mail: geozup@cityline.ru) to get the complete description. The Russian subscript 'cb' in the documentation corresponds to 'bf' - body-fixed. Mass and dimensions. Spacecraft mass : 1411-1415 kg Dimensions of vehicle and solar panels : see on figures Area of solar panels : 23.616 m2 Angles of thermocontrol folds opening for the folds located on +Zbf side: 0-5 deg for the folds located on -Zbf side: 80-85 deg Phase center position in body-fixed reference frame (bf) TT&C receiving antenna Xbf : -1626 mm Ybf : 730 mm Zbf : 145 mm TT&C transmitting antenna Xbf : -1676 mm Ybf : 700 mm Zbf : 200 mm panel of retroreflectors Xbf : -1510 mm Ybf : 0 mm Zbf : 0 mm integral phase center of navigation antennas Xbf : -1620(+/-)130 mm Ybf : 0 mm Zbf : 0 mm S/C orientation. Spacecraft supports permanent three-axes orientation. Negative direction of body fixed axes OX is pointed to the Earth mass center. Positive direction of body fixed axes OY is pointed to the Sun side. Normal to solar panel vector is pointed to the Sun. There is unpredictable decrease of solar panels orientation accuracy for not more than 30 minutes when satellite passes parts of orbit where angle Sun-S/C-Earth is above 170 or bellow 10 ("eclipse" orbits when S/C is in shadow from the Earth). The thermocontrol folds are opened while SV is normally operated. The fixing angle is individual for all spacecrafts. The change of thermocontrol folds position during spacecraft lifetime is unpredictable. No additional information concerning the reflection or absorption coefficients is available as well as the precise positions of L1 and L2 phase centers. Best regards. Sergey Revnivykh, Vladimir Mitrikas, GEO-ZUP Company on behalf of NPO PM and Russian Space Agency ------=_NextPart_000_001B_01BE16DA.515BB9C0 Content-Type: text/html; charset="koi8-r" Content-Transfer-Encoding: quoted-printable

Dear = colleagues,

please find = hereafter the=20 information on GLONASS
mass and dimensions for preparation of force = and=20 tracking
data models, kindly presented by NPO PM=20 (Krasnoyarsk).

These data have = been officially=20 released by NPO PM
according to the request of IGEX steering = committee=20 to
Russian Space Agency. This can be considered as an NPO = PM
contribution=20 to the IGEX'98 campaign. NPO PM has developed
and designed all = GLONASS=20 spacecrafts so the data are
guaranteed to be = correct.

The file with = GLONASS S/C=20 figures in PCX format is
available by request. Please contact GEOZUP=20 Company
(e-mail: geozup@cityline.ru)=20 to get the complete description.

The Russian = subscript 'cb' in=20 the documentation corresponds
to 'bf' - = body-fixed.

Mass and=20 dimensions.

Spacecraft=20 mass &nb= sp; =20 : 1411-1415 kg

Dimensions of = vehicle and solar=20 panels : see on figures

Area of solar=20 panels &= nbsp; =20 : 23.616 m2

Angles of = thermocontrol folds=20 opening
for the folds located on +Zbf side: = 0-5=20 deg
for the folds located on -Zbf side: = 80-85=20 deg

Phase center = position in=20 body-fixed reference frame (bf)
TT&C receiving=20 antenna
          &n= bsp;           &nb= sp;           =20 Xbf : -1626=20 mm
           &= nbsp;           &n= bsp;          =20 Ybf :   730=20 mm
           &= nbsp;           &n= bsp;          =20 Zbf :   145 mm
TT&C transmitting=20 antenna
          &n= bsp;           &nb= sp;           =20 Xbf : -1676=20 mm
           &= nbsp;           &n= bsp;          =20 Ybf :   700=20 mm
           &= nbsp;           &n= bsp;          =20 Zbf :   200 mm
panel of=20 retroreflectors
         =             &= nbsp;           &n= bsp;=20 Xbf : -1510=20 mm
           &= nbsp;           &n= bsp;          =20 Ybf :     0=20 mm
           &= nbsp;           &n= bsp;          =20 Zbf :     0 mm
integral phase center of = navigation=20 antennas
          &= nbsp;           &n= bsp;           =20 Xbf : -1620(+/-)130=20 mm
           &= nbsp;           &n= bsp;          =20 Ybf :     0=20 mm
           &= nbsp;           &n= bsp;          =20 Zbf :     0 mm

S/C=20 orientation.

Spacecraft = supports permanent=20 three-axes orientation.
Negative direction of body fixed axes OX is = pointed=20 to
the Earth mass center. Positive direction of body fixed
axes OY = is=20 pointed to the Sun side. Normal to solar panel
vector is pointed to = the=20 Sun.

There is = unpredictable decrease=20 of solar panels orientation
accuracy for not more than 30 minutes = when=20 satellite passes
parts of orbit where angle Sun-S/C-Earth is above = 170=20 or
bellow 10 ("eclipse" orbits when S/C is in shadow = from=20 the
Earth).

The thermocontrol = folds are=20 opened while SV is normally
operated. The fixing angle is individual = for=20 all
spacecrafts.

The change of = thermocontrol=20 folds position during
spacecraft lifetime is=20 unpredictable.

No additional = information=20 concerning the reflection or
absorption coefficients is available as = well as=20 the precise
positions of L1 and L2 phase centers.

Best=20 regards.

Sergey Revnivykh, = Vladimir=20 Mitrikas,
GEO-ZUP Company
on behalf of NPO PM and Russian Space=20 Agency

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