Rideshare payload user’s guide october 2022

SEPARATION ATTITUDE AND ACCURACY

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SpaceX Ride Share

Figure 2-2: Payload +X PL Surface Exit Requirement (red) for Rideshare Plate Configuration Figure 2-3: Payload +X PL
Table 2-1: Launch Vehicle Rates Before Payload Separation

2.3
SEPARATION ATTITUDE AND ACCURACY
The Launch Vehicle offers axis attitude control as standard practice. The Launch Vehicle will point the second stage and Payload to an attitude determined by SpaceX. More information about separation attitude and rate accuracy is available from SpaceX upon request.
2.4
SEPARATION RATES AND VELOCITY
All deployed Payloads must exit through the +X
PL
surface of the allowable Payload volume. Customer must show by analysis that none of the deployed Payload Constituents contact other portions of the Payload before exiting the +X
PL
surface of the allowable Payload volume. Examples of Payload volume exit criteria for Rideshare Plate and Starlink Adapter configurations are shown in Figure 2-2 and Figure 2-3 respectively.
Figure 2-2: Payload +X
PL
Surface Exit Requirement (red) for Rideshare Plate Configuration
Figure 2-3: Payload +X
PL
Surface Exit Requirement (red) for Starlink Adapter Configuration

RIDESHARE PAYLOAD USER’S GUIDE
© Space Exploration Technologies Corp. All rights reserved. No US. Export Controlled Data.
6 Payloads must target a minimum separation velocity of 0.3 ms and a maximum separation velocity of 1.0 ms. Containerized deployments such as CubeSats maybe deployed at a velocity greater than 1.0 ms. For Payloads that contain more than one deployment, the separation velocities should be different between deployed Payload Constituents such that the fastest deployment is first. The Launch Vehicle is subject to the rotational rates in Table 2-1 prior to Payload separation.
Table 2-1: Launch Vehicle Rates Before Payload Separation
Axis Rate Launch Vehicle Roll (W
X
)
± 2.0 deg/s Launch Vehicle Pitch (WY)
± 1.0 deg/s Launch Vehicle Yaw (W
Z
)
± 1.0 deg/s

2.5

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