Sea Launch User's Guide

6.1 Mass and Center of Gravity (CG) Limits
Definitive compatibility
requiring
multiple verification
activities
Several verification activities must be done to demonstrate Zenit-3SL
compatibility with a specific spacecraft having a given mass and CG.
These include
• Coupled loads analysis.
• Strength and controllability analyses.
• Critical clearance analyses to assess volumetric constraints.
• Performance calculations for the specific mission.
• Peaking load calculations for spacecraft having a nonuniform
interface stiffness.
More information on spacecraft mass is presented in section 3.3.
Current Zenit-3SL
structural capability
The Zenit-3SL launch vehicle can structurally accommodate spacecraft
with a wide range of mass and CG for each of the three spacecraft adapters
currently offered by Sea Launch.
Table 6-1 provides the expected spacecraft mass and CG limits for the
Zenit-3SL using a standard spacecraft adapter when the lateral load factor
on the spacecraft is 2.0 g or less and the load distribution at the spacecraft
interface is ideal.
Definitive compatibility of a spacecraft with the Zenit-3SL requires all
verification activities outlined above. In particular, peaking load calculations
must be performed when the load distribution at the spacecraft interface
is not ideal.
REV B D688-10009-1 6-3