Falcon 9 Launch Vehicle Payload User's Guide - SpaceX

AXIAL (G)
-2, 3.5
-2, -1.5
-0.5, 6 0.5, 6
6
-0.5, 4
-0.5, -1.5
-0.5, -2
Falcon 9 User’s Guide
0
-2.5 -2 -1.5 -1 -0.5 0 0.5 1 1.5 2 2.5
5.2.3.2. Shock Environment
7
5
4
3
2
1
-1
-2
-3
LATERAL (G)
SCM 2008‐010 Rev. 1 Copyright ‐‐ SpaceX 2009 33
0.5, 4
0.5, -1.5
0.5, -2
Figure 5‐2 ‐ Falcon 9 Design Load Factors
There are four events during flight that are characterized as shock loads:
1) Vehicle hold‐down release at lift‐off
2) 2 nd stage separation
3) Fairing separation
4) Payload release and separation
Of the shock events, (1) and (2) are negligible for the payload relative to (3) and (4) due to the
large distance and number of joints over which shocks (1) and (2) will travel and dissipate.
Maximum shock loading (3) and (4) is measured and scaled for various preloads required for
the payload fairing and payload separation systems. The resulting maximum shock
environment predicted at payload interface for payload fairing separation and payload
separation (for a 937‐mm clampband separation system) is shown in Figure 5‐3. Actual shock
from the payload‐specific separation system requires selection of a separation system and the
associated payload mass properties.
2, 3.5
2, -1.5