This week we electrically and mechanically integrated the RF network, the attitude control electronics box (ACE), the digital sun sensor, the gyros, the torquer bars, and the reaction wheels. Currently the SPE, shunt box, SCS, transponder, WIE, the ACE, the digital sun sensor, the gyros, the torquer bars, and the reaction wheels are fully integrated.
Here is the spacecraft as it now looks. In the left photo, the
battery air conditioning duct dominates the view. The magnetometer is
on the boom which sticks well above the upper deck. The magnetometer is
surrounded by test coils which produce a known magnetic field. The instrument
focal plane simulator is on the cart next to the spacecraft. In the
right photo on the left side of the spacecraft, the front (+y, sun-side) equipment panel is in place.
The digital sun sensor is behind the red, square, remove-before-flight
cover. The RF network (splitters and couplers which interface to the
transponder and the antennas) is visible just above the front panel. The spacecraft equipment panels are made of
graphite composite bonded in a rib pattern for strength. The panels
are painted white as part of the temperature control for the electronics.
In the left photo, Leroy Sparr checks a quick-disconnect joint for
leaks. In the right photo, Pete Rossoni cold-shocks the
quick-disconnect joint in liquid nitrogen. The quick-disconnect joint
interfaces between the instrument safety vent and the L-1011 safety
vent plumbing during the captive carry portion of the launch.
Next week we will run the ACS and SCS functionals.
Previous updates:
August 18, 1997
October 20, 1997
October 31, 1997
November 7, 1997
November 14, 1997