Rideshare payload user’s guide october 2022



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SpaceX Ride Share
3.3.8

FAIRING INTERNAL PRESSURE
Fairing internal pressure will decay at a rate no larger than 0.40 psi/sec (2.8 kPa/sec) from liftoff through immediately prior to fairing separation, except for brief periods during flight, where the fairing internal pressure will decay at a rate no larger than 0.65 psi/sec (4.5 kPa/sec), for no more than 5 seconds. A Mission-specific analysis will not be provided by
SpaceX.
3.3.9

PAYLOAD TEMPERATURE EXPOSURE DURING FLIGHT
The Launch Vehicle fairing is designed such that the temperature seen by the Rideshare Payload never exceeds the temperature profile shown in Figure 3-7. The emissivity of the fairing is approximately 0.9.


RIDESHARE PAYLOAD USER’S GUIDE
© Space Exploration Technologies Corp. All rights reserved. No US. Export Controlled Data.
16
Figure 3-7. Maximum Fairing Spot Temperature Seen by Rideshare Payload
3.3.10
FREE MOLECULAR HEATING
The maximum free molecular aero-thermal heating rate experienced by the Payload is less than 3,500 W/m
2
at fairing separation. Free molecular aero-thermal heating declines significantly and becomes negligible over the next couple of minutes.
3.3.11

PAYLOAD CONDUCTIVE BOUNDARY TEMPERATURES
Bounding hot and cold boundary temperatures and conductance values at the interface of the Payload and the SpaceX- provided Mechanical Interface, described in Section 4.2.4, are shown in Table 3-13 and Figure 3-8. Customer may use these boundary conditions to run a Payload-specific thermal analysis. Note that these boundary conditions are only relevant after Liftoff at Time = 0 as they contain analysis uncertainty that is not appropriate on the ground. The convective environment in Table 3-1 fully defines the pre-launch environment. A Mission-specific analysis will not be provided by SpaceX. Verification Testing is ADVISED to the combined thermal vacuum and thermal cycle test levels and durations defined in Table 3-15 in accordance with the environments defined in this section.

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