Exhibit B
7.12 Power Control
No single component failures in the spacecraft shall open or short the main electrical bus.
The power control design shall incorporate the following features:
1)
Smooth
power.
automatic transition from
solar
array power
to battery
2)
Smooth automatic transition from battery power
power.
to solar array
3)
4)
Independent command control of the charge of each battery.
Capability of providing, without damage to the total system, load current with 24 communications channel operational during eclipse.
5) In-orbit reconditioning capability of the batteries between eclipse seasons. This capability shall be sufficiently flexible to allow, between eclipse seasons as well as during storage periods prior to launch, low rate charging and discharging, passive storage, or a combination of these modes, to achieve optimum battery life.
6)
Shutdown of spacecraft individual communications channel loads due to marginal power conditions shall be capable of being performed by to safely command. The power subsystem design shall be such as tolerate an undervoltage condition.
Hughes shall
recommend
to Asiasat a battery charge/discharge and reconditioning routine consistent with the requirements for communication in mission sun eclipse which capability during all lifetime. This recommendation shall form part of the spacecraft operating manual.
periods
7.13 Telemetry and Command
7.13.1
Telemetry Data
of
The following telemetry data shall be provided:
1) Battery charge and discharge currents
2) Battery voltages
3) Battery cell voltages
4) Battery temperature
5) Bus current
occur
B-28
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