Rideshare payload user’s guide october 2022
Download 2.78 Mb. View original pdf
|
- Navigate this page:
- Table 3-16: Containerized CubeSat Unit Test Levels and Durations
| 3.4.4 FULLY CONTAINERIZED CUBESAT UNIT TEST LEVELS Fully containerized CubeSats maybe tested at the Payload Constituent level using the unit test levels and durations defined below in Table 3-16. If these CubeSats are not included in the fully integrated Payload assembly level test defined in Section 3.4.3) then mass models must be used in their place to represent the omitted CubeSats. CubeSats are considered fully containerized if there are no holes in the dispenser/deployer larger than 0.250” [6.35 mm in diameter, and holes makeup less than 10% of the total surface area of the dispenser. CubeSats utilizing deployment devises that are not fully containerized do not fall within this specification, nor does this section apply to the CubeSat dispenser/deployer itself. Both the CubeSat dispenser/deployer as well as CubeSats that are not fully-containerized as defined above must be tested at the Payload levels defined in Table 3-15. Table 3-16: Containerized CubeSat Unit Test Levels and Durations Test Required/Advised Fleet Qualification Single Unit Qualification Acceptance Protoqualification Static Load Not Required Sine Vibration Not Required Acoustic Not Required Shock Advised 6 dB above MPE, 3 times in each of 3 orthogonal axes Not Required 3 dB above MPE, 2 times in each of 3 orthogonal axes Random Vibration REQUIRED 3 dB above acceptance for 2 minutes in each of 3 axes MPE spectrum for 1 minute in each of 3 axes MPE spectrum for 1 minute in each of 3 axes Electromagnetic Compatibility REQUIRED 6 dB EMISM by Test or 12 dB EMISM by Analysis Not Required 6 dB EMISM by Test or 12 dB EMISM by Analysis Combined Thermal Vacuum and Thermal Cycle Advised ±10 C beyond acceptance for 27 cycles total Envelope of MPT and minimum range (–24 to 61 C) for 14 cycles total ±5 C beyond acceptance for 20 cycles total Pressure Systems REQUIRED Pressures as specified in Table 6.3.12-2 of SMC-S-016 following acceptance proof pressure test, duration sufficient to collect data. Minimum 2.0 times MEOP 1.5 times ground MEOP for pressure vessels and pressure components. Other metallic pressurized hardware items per References 4 and 5 from SMC-S-016 See Note 5 System-Level Pressure Leak Test REQUIRED Not Required Full Pressure System MEOP Leak Test per Section 4.1.5.1 Full Pressure System MEOP Leak Test per Section Pressure Vessel Leak Test REQUIRED Not Required Pressure Vessel Level MEOP Leak Test per Section 4.1.4.2 Pressure Vessel Level MEOP Leak Test per Section 4.1.4.2 Notes 1. SpaceX requires random vibration testing on CubeSats to no less than the MPE levels defined in Section 3.3.6, however strongly advises that the MPE is derived from fully integrated Payload assembly level testing. Failure to use derived random vibration levels should be understood by Customer to bean under-test to the expected flight environments. 2. Verification by test maybe performed in-house per MIL-STD-461 with supporting test documentation or obtained from an IEC-17025 accredited or equivalent) test facility. Verification by analysis must provide (1) a mechanical battery isolation inhibit strategy verified in vibrational testing or (2) electromagnetic circuit and wiring emissions analysis. For Payloads with GPS receivers, verification by analysis maybe achieved through demonstration of self-compatibility with on-board GPS navigation systems. 3. EMISM (6 dB by test, 12 dB by analysis) is already included in Table 3-10. 4. Thermal cycles can be accrued as a combination of thermal cycling in air and thermal vacuum. It is recommended to include at least four cycles of thermal vacuum unless strong rationale exists that the Payload is not sensitive to vacuum. 5. Pressure systems cannot be protoqualified at the Payload level. Pressure systems must therefore be qualified via the fleet qualification approach at the component level. Supplier qualification testing is acceptable in place of fleet level qualification testing if approved by SpaceX. Reference Section 4.1.4 and Section 4.1.5 for additional information. 6. For all Non US Department of Transportation (US DOT) rated pressure vessels, please contact SpaceX for detailed qualification and testing requirements (reference Section 4.1.4). 7. Pressure Systems that do not meet material compatibility requirements specified in Section 4.1.5.2 must contact SpaceX for specific leak testing requirements. RIDESHARE PAYLOAD USER’S GUIDE © Space Exploration Technologies Corp. All rights reserved. No US. Export Controlled Data. 22 Download 2.78 Mb. Share with your friends:
|