Russian

Sea Launch Project

High Spots

Demo Launch


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.
Perigee argument,
deg.
655,0
36011,0
1,255
180,0

 

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