TNAG-2109-FCO40-3008-Outer-Space-Act-1986-extension-to-Hong-Kong-1990 — Page 144

Exhibit B

clocke when viewed from the launch vehicle interface. rate is nominally 50 rpm.

The desired spin

The spacecraft is designed to provide operation within specification over the total variation in spin speeds expected during the design lifetime in orbit.

2.4 Orbit and Position

shall be

designed

to

acquire

in a

and The

operate spacecraft

the longitudinal positions of synchronous, circular, equatorial orbit at 105.5° E and 116° E longitude. The spacecraft control system is designed to maintain station to 0 ±0.05° in both longitude and orbit inclination at these positions.

2.5

or

Launch Vehicle and On Station Mission Fuel Life

The spacecraft was designed to be compatible with launch by a National Aeronautics and Space Administration Space Transportation System ("STS" See Tables B-1A and B-1B "Shuttle") launch vehicle in February 1984.

The existing for STS load

requirements. limits and Frequency spacecraft/launch vehicle interface characteristics shall be provided to the PRC Long March 3 launch agency (pending OMC regulations) in order that the launch

can provide launch vehicle interface which will be compatible with the spacecraft.

agency

a

The on-station life for the spacecraft is at least 9.0 years, assuming a spacecraft separated mass of 1240 Kg into a 31.1 inclined transfer orbit, 1000 nautical mile apogee bias (above geosynchronous altitude), 100 nautical mile perigee altitude, launch in mid-1990, on-station locations of either 105.50 E longitude or 1160 E longitude, no station changes, nominal transfer orbit maneuvers and station acquisition fuel expenditures and Long March. ±.40, than the

inclination following: injection errorS no semi-major axis ±200 nautical miles, argument of perigee ±1.0° (all standard deviations).

3

2.6 Outgassing

greater

The spacecraft performance throughout the design lifetime shall not be. degraded below specification due to outgassing.

2.7 Magnetic Moment and Solar Radiation Pressure

The

spacecraft

shall be

designed

in

variation the minimize to synchronous orbit of the spin axis attitude due to magnetic and solar radia- tion pressure torques.

2.8 Spacecraft Safety

The spacecraft shall be designed so that, when operated in conjunction with its ground support equipment, the launch vehicle, and/or the Ground Control Center, the probability of unsafe responses is minimized, particularly when relating to apogee motor and thruster energization.

L.

B-3

!