|
First it was planned that during the first launch under
the Sea Launch program the Galaxy-11 spacecraft will be
placed into the orbit. In 1998 work on SC/PLU analytical
integration with the Zenit-3SL Integrated Launch Vehicle
was done. In August 1998 Sea Launch Company took a decision
on Galaxy-11 SC replacement with a mockup having the similar
dynamic characteristics (Demosat SC).
CHRONOLOGY OF ACTIVITIES
| February
19, 1999 |
Start of work at Home Port on demo launch processing. |
| March
4, 1999 |
Mating of Block DM-SL Upper Stage and Zenit-2S Launch
Vehicle is carried out. |
| March
5, 1999 |
Mating of Block DM-SL Upper Stage and Payload Unit
with Demosat SC is performed.
|
| March
8, 1999 |
A readiness review is held.
|
| March
11, 1999 |
Transfer of Zenit-3SL Integrated Launch Vehicle with
Demosat SC is performed from the Assembly-Command
Ship to the Launch Platform.
|
| March
12, 1999 |
Additional tests under the ILV Dry Roll-Out program
are conducted, critical launch readiness checklist
is performed. Later on this operation was introduced
into the ILV nominal processing procedure at Home
Port.
|
| Start
of Launch Platform transit to the launch site. |
| March
13, 1999 |
Start
of Assembly-Command Ship transit to the launch site. |
| March
25, 1999 |
Completion of ship transit. First launch day at the
launch site at the Equator. Check of the technical
state of Rocket Segment systems and equipment.
|
| March
26, 1999 |
ILV
roll-out and erection on the launch pad. ILV tests.
Critical launch readiness checklist. |
| March
28, 1999 |
ILV
loading with propellant components and nominal launch
readiness checklist.At 5:30 A.M. Moscow Time (March
27, 1999 at 6:18:30 P.M. Pacific Time) from the Odyssey
Launch Platform is carried out the first demo launch. |
LAUNCH RESULTS
Implementation of the first demo launch has successfully
completed the phase of Sea Launch Rocket and Space Complex
development and development test and confirmed the Complex
readiness for further commercial launches. The spacecraft
mockup was placed into the calculated orbit to a high accuracy:
Perigee altitude,
km |
Apogee altitude,
km
|
Inclination,
deg.
|
Perigeeargument,
deg.
|
|
655,0
|
36011,0
|
1,255
|
180,0
|
|
|
