Sea Launch User's Guide

Flight quasi-static
load factors for
primary structure
The quasi-static limit load factors for flight that envelope the loads over a
wide range of spacecraft are given in figure 5-4. These factors are to be
used as a guide only. Specific limit load factors for spacecraft with given
mass and stiffness properties will be specified in the spacecraft interface
control document after a CLA has been performed. Lateral load factors
ranging from 1.5 to 2.5 g have been calculated for spacecraft having
unique mass and/or stiffness properties.
(–2, +3)
Axial load factor, g
(–0.7, +4.5)
5
(+0.7, +4.5)
4
(+2, +3)
2
1
Lateral load
factor, g
(–2, 0)
(+2, 0)
–4 –2
0
2
4
–1
(–1, –2)
–3
Note:
• Positive axial acceleration results in compression
at the SC-LV separation plane.
• Guide only. Specific values determined after
spacecraft CLA.
3
–2
(+1, –2)
265807J3-058R2
Figure 5-4. Typical Quasi-Static Load Factors for Flight
Sinusoidal vibration
during flight
The low-frequency sinusoidal vibration environment generated at the
spacecraft separation plane during launch and flight will not exceed that
defined in figure 5-5. A CLA performed by Sea Launch determines the
minimum sinusoidal vibration environment for all flight events. The results
determine the maximum notching that can be used during the spacecraft
sinusoidal vibration testing.
REV B D688-10009-1 5-5