Rideshare payload user’s guide october 2022


Figure 3-3: Maximum Predicted Acoustic Environment



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SpaceX Ride Share
Figure 3-3: Maximum Predicted Acoustic Environment
Table 3-4: Third Octave Acoustic MPE
Frequency (Hz) Acoustic MPE
25 120.0 31.5 121.0 40 122.5 50 123.4 63 123.8 80 124.2 100 125.9 125 127.7 160 129.3 200 129.8 250 129.9 315 129.6 400 128.7 500 127.4 630 126.0 800 124.0 1000 122.5 1250 121.0 1600 120.0 2000 119.0 2500 118.0 3150 117.0 4000 116.0 5000 115.0 6300 114.0 8000 113.0 10000 112.0
OASPL (dB)
139.3

Table 3-5: Full Octave Acoustic MPE
Frequency (Hz) Acoustic MPE
31.5 126.1 63 128.6 125 132.6 250 134.5 500 132.3 1000 127.4 2000 123.8 4000 120.8 8000 117.8
OASPL (dB)
139.3



RIDESHARE PAYLOAD USER’S GUIDE
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12
3.3.5

SHOCK
Purpose: To ensure Payloads are compatible with shock environments experienced during flight. The shock response spectrum MPE, for Q, at the Payload mechanical interface for fairing deployment and Co-
Payload separations, as well as the maximum allowable shock fora single separation system are defined in Table 3-6 and Figure 3-4. These levels are defined assuming a minimum of 3 bolted joints between Co-Payloads. Customers flying mission-unique configurations are encouraged to independently evaluate the shock levels produced by their Payload’s separation system. Customer is responsible for verifying compliance to both this requirement and the shock levels for the Payload separation system. To ensure Mission safety for Co-Payloads, separation systems provided by the Customer must be approved by SpaceX (reference Section 3.4.1.3). Additional constraints maybe imposed if the separation system exceeds shock levels listed in Table 3-6. A Mission-specific analysis will not be provided by SpaceX. Verification Testing is ADVISED to the shock test levels and durations defined in Table 3-15 in accordance with the MPE defined in this section.

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