Rideshare payload user’s guide october 2022
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- 4.3.3 BREAKWIRE CHANNEL PROPERTIES
| 4.3.2 DEPLOYMENT CHANNEL PROPERTIES Deployment channels are offered in pairs of primary and secondary commands. One primary and one secondary command must be used for each actuation. All deployment/separation devices directly interfacing with Launch Vehicle electrical systems must have sufficient reliability to ensure safe deployment. The preferred method of achieving reliability is two independent actuators on separate circuits. Either of these actuators must be capable of independently initiating Payload separation, effectively removing a single point of failure to Launch Vehicle separation. Exceptions to this method are discouraged but can be considered on a case-by-case basis at SpaceX’s sole discretion. All deployments from the Launch Vehicle will be commanded by SpaceX. The use of Customer-provided sequencers for commanding more than one deployment from the Launch Vehicle within the Payload is prohibited. Each deployment command sent by the Launch Vehicle can be configured in one of two ways 1. Constant-Current Pulse Used for low-resistance loads, this mode of operation provides up to 6 A of constant current. Specifics of the pulse duration and current setting will be specified as part of the Payload-specific ICD. 2. Bus-Voltage Pulse Used for high-resistance or motor-driven loads, this mode of operation will provide an unregulated voltage signal between 24-36 V with a maximum current draw of 6 A. Specifics of the pulse duration will be specified as part of the Payload-specific ICD. The specific configuration of the deployment commands will be determined by SpaceX through analysis and testing of each separation device. The deployment device timing delay from receipt of the Launch Vehicle deployment signal to physical release of the Payload is required to be characterized as < 2 seconds ± 0.5 second uncertainty. 4.3.3 BREAKWIRE CHANNEL PROPERTIES Breakwire channels are used to determine separation status of the Payload Constituents from the Launch Vehicle. Breakwires are organized into two categories, “PL-side breakwires” which are used by the Launch Vehicle to detect separation and “LV-side breakwires” which are used by the Payload to detect separation. This is illustrated in Figure 4-13. RIDESHARE PAYLOAD USER’S GUIDE © Space Exploration Technologies Corp. All rights reserved. No US. Export Controlled Data. 35 Download 2.78 Mb. Share with your friends:
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