TNAG-2109-FCO40-3008-Outer-Space-Act-1986-extension-to-Hong-Kong-1990 — Page 170

Exhibit B

3.6

Channel Characteristics

The

channel characteristics of the 24-channel satellite shall be specified in Attachment 1 of this requirement document.

3.2.7 Antenna Sidelobe Gain

&S

As a design goal, the gain of any transmit or receive beam (referenced to 0 dB beam peak) at the first sidelobe peak shall be no greater than -25dB.

4.0 ATTITUDE CONTROL SUBSYSTEM

4.1 General

The spacecraft shall include an attitude control subsystem (ACS) which as specified shall control the spacecraft in attitude such that the EIRP and all other requirements shall be met from the orbital locations of 105.5°

and E-W, E and 116° E longitude with pointing accuracy of ±0.05° N-S excluding yaw errors.

4.2 Attitude Determination

a

the

Onboard sensors shall be provided and telemetered such that satellite

drift orbit, and during transfer orbit, drift attitude may be determined during transfer operational orbit.

4.2.1

Determination of Spin Axis Attitude

The accuracies to which it shall be possible to determine the spin axis attitude are the following:

1) ±1.2° ΟΙ

observation.

better

after

maximum of a

of 0.5 hours

continuous

2)

10.2° or better after a maximum of 2 hours of observation, either continuous or cumulative.

3) ±0.05° or better relative to the orbit vector after a maximum of 24 hours of observation, either continuous or cumulative, during steady state operation on station.

foregoing periods do

not include any time required for data The

All foregoing accuracies processing or computation outside of the satellite. shall be met after inclusion of spacecraft correction and calibration factors as supplied by Hughes.

4.2.2 Determination of Satellite Rotational Position

It shall be possible to determine the rotational position of the satellite about its spin axis (with respect to inertial coordinates) versus time to an accuracy of ±0.2°, after a maximum of 10 minutes of observation.

4.2.3 Attitude Correction Interval

To maintain antenna pointing requirements during the mission life, the attitude correction interval shall not be less than 3 days (continuous control is not required). C

.B-19

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