Exhibit B
7.6 Alignment
Thruster alignments shall be such as within allowable limits for mission life.
to
ensure
satellite spin
rate
7.7 Coning
SO
The spacecraft design is such that coning effects caused by operation
The maximum nutations of axial
are minimized. thrusters radial or introduced shall not degrade the performance of the communications system performance specification.
7.8 Antenna Pointing Accuracy
Hughes shall specify, with supporting data, the total north-south antenna pointing error budget which includes a reasonable attitude control The pointing error deadband consistent with the attitude correction interval. budget shall be such that the communications system performance requirements are met at all times.
7.9 Thermal Design
Hydrazine shall be maintained within appropriate temperature limits at
all times.
7.10 Power Subsystem Requirements
The power subsystem shall provide all the electrical power requirements 24 communications requirements for to meet the spacecraft mission life channels. The primary source of power shall be solar cells with power storage for full 24 channel sufficient to provide
requirements all power communications during eclipse. The power control design shall provide for uninterrupted operation during transition between solar array and battery of battery power. Command control shall provide for positive management
Monitoring of individual cell voltages charging, reconditioning, and loads. shall be provided.
7.11 Energy Storage Device (Super Ni-Cad Cells)
to form two
The
The energy storage device for supplying power to the spacecraft during eclipse shall be hermetically sealed nickel-cadmium secondary cells.
of equal interconnected be cells shall
separate batteries capacity. The batteries shall have a high reliability and shall have a 19.0 The EOL battery depth-of- or greater. ampere-hour name-plate capacity. discharge shall be less than 75% under worst case conditions.
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B-27