PAYLOAD USER’S GUIDE

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Axial Acceleration (g) Falcon User’s Guide Falcon 9 payload design load factors are shown using the envelopes in Figure 4-1 and Figure 4-2. Two sets of factors are given, one for “standard” payloads with mass of more than 4,000 lb (1,810 kg), and another for “light” payloads with mass of less than 4,000 lb (1,810 kg). A positive axial value indicates a compressive net-center-of-gravity acceleration, while a negative value indicates tension. Actual payload loads, accelerations and deflections are a function of both the launch vehicle and payload structural dynamic properties and can be accurately determined via a coupled loads analysis. 4.3.1.1 Loads—Standard Payload Mass The design load factors provided here are expected to be conservative for payloads with the following basic characteristics: a fundamental bending mode greater than 10 Hz, a fundamental axial mode greater than 25 Hz, a maximum center of gravity (CG) height of 180 in, maximum lateral CG offset of 5 in, and a mass between 4,000 and 20,000 lb (1,810 – 9,070 kg). Payloads outside of this frequency and mass range can be accommodated. Please contact SpaceX for more details. 7 6 5 4 3 0.5, 6 0.5, 4 2, 3.5 2 1 0 -1 -2 0.5, -1.5 0.5, -2 2, -1.5 -3 -3 -2 -1 0 1 2 3 Lateral Acceleration (g) Figure 4-1: Falcon 9 payload design load factors for “standard” mass (over 4,000 lb) 4.3.1.2 Loads—Light Payload Mass Figure 4-2 shows the design load factors for lighter payloads (less than 4,000 lb). However, for ultra-light payloads (~2,000 lb or less), coordination with SpaceX mission management is required, since these load factors may not be adequate to design the payload. Actual spacecraft loads, accelerations and deflections are a function of both the launch vehicle and payload structural dynamic properties and can only be accurately determined via a coupled loads analysis. Revision 2 © 2015 Space Exploration Technologies Corp. All rights reserved. 20
Axial Acceleration (g) Falcon User’s Guide 10 8 F9 Design Load Factors F9 Design Load Factors, Payloads < 4,000 lb 2, 8.5 6 4 2, 4 3, 4 2 0 -2 -4 2, -1.5 2, -4 3, -1.5 -6 -4 -3 -2 -1 0 1 2 3 4 Lateral Acceleration (g) Figure 4-2: Falcon 9 payload design load factors, Light mass (under 4,000 lb) 4.3.2 Sine Vibration Maximum predicted Falcon 9 sinusoidal vibration environments are shown in Figure 4-3 and Figure 4-4. These environments represent the vibration levels at the top of the payload attach fitting for Q=20 through Q=50, and envelope all stages of flight. Since SpaceX accommodates a variety of payloads, results of coupled loads analysis will be used to modify these levels, if necessary, to reflect the levels at the payload interface. Revision 2 © 2015 Space Exploration Technologies Corp. All rights reserved. 21
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