Sources Sought - EH0C0075EH.pdf

Sources Sought Notice

Beta.Sam Posting:

Item Name: Electronic Components Assembly

NSN: 5998-01-675-0284

Part Number: 12591729 Quantity: 34 each Option Quantity: 34 each End Item: M1A2 SEPV3

Response Date: 30 Apr 2020

Day Month Year 30 4 (Apr) 2020

Requirements Description:

The primary component of 12591729, Electronic Component is a generator controller that supplies the electrical power to the M1A2 SEPv3 Tank electrical power system. The Electronic Component is a generator controller that UTC AEROSPACE SYSTEMS (UTC) and GLOBAL ET, part number 12591729, also refer to as the CONTROLLER, GENERATOR in engineering documents. The Electronic Component is a critical item for the Abrams M1A2 SEPV3 tank program. The Electronic Component shall meet all requirements specified in document “SC- SA21008A Product Fabrication Specification (PFS) (With Development/Qualification Requirements in Appendix A) for the Generator Controller”. Key performance requirements found in SC-SA21008A include:

1.1. The Electronic Component shall be fabricated in accordance with assembly drawing 1259172.

1.2. The assembly shall operate as specified herein and meet the performance requirements with an input voltage of 18 to 32 VDC, where the nominal input voltage is 28 VDC.

1.3. Voltage input is at J2 with J2-23 as 28 VDC nominal source and J2-22 as 28 VDC nominal return.

1.4. The assembly shall be capable of supplying field excitation current up to 10.0 A DC.

1.5. The assembly shall be capable of regulating the point of regulation (POR) voltage to within the steady-state limits of 25.0 to 30.0 VDC.

1.6. The assembly shall be capable of regulating the point of regulation (POR) voltage to an accuracy of ±0.5 VDC for any valid target set point command received.

1.7. The assembly shall deactivate the generator field excitation circuit when a generator output current of 1133 ± 10 A is detected.

1.8. The assembly shall indicate over CAN bus that a short circuit condition has occurred.

1.9. The assembly shall deactivate the generator field excitation circuit within 1.5 ms of detecting a field current of 30 ± 7 A.

1.10. The assembly shall indicate over CAN bus that a field current overcurrent fault condition has occurred.

1.11. The assembly shall deactivate the generator field excitation within 20 msec when detecting an input voltage of 52 (+5, -2) VDC.

1.12. The assembly shall indicate over CAN bus when an overvoltage fault condition has occurred. The assembly shall decrease the active set point voltage to 25.0 +0.5, -0.0 VDC when a generator output current of 1001 - 1122 A is detected and a generator speed of 2400 ±30 rpm is simulated.

1.13. The assembly shall indicate over CAN bus when current limiting is active.

1.14. With no input voltage applied, the resistance between each of the two connector contact pairs shall not exceed 0.5 ohms.

1.15. With no input voltage applied, the resistance between the assembly chassis and each of the pins shall be a minimum of 1 Megohm within 30 seconds.

1.16. The assembly shall communicate through a redundant CAN bus system with one CAN bus acting as primary and the other as secondary.

1.17. The assembly shall have a nuclear event detection and protection circuit.

1.18. The assembly shall comply with the mounting interface requirements defined in

Drawing 12591729.

1.19. The weight of the assembly shall not exceed 4.5 kg (10 lbs).

1.20. The assembly shall be capable of operating for a period of 1000 hours under the mission duty cycle spectrum.

1.21. The assembly shall meet its full performance requirements, without degradation, during and after aggravated temperature-humidity conditions up to and including: a) Temperature range: 86°F to 140°F (30°C to 60°C) b) Relative humidity range: 95 ± 5%.

1.22. The assembly shall meet its full performance requirements, without degradation, after aggravated temperature-humidity conditions up to and including: a) Temperature range:

86°F to 140°F (30°C to 60°C) b) Relative humidity range: 95 ± 5%.

1.23. The assembly shall meet its full performance requirements, without degradation, and show no evidence of damage after exposure to a 5% aqueous salt.

1.24. The assembly shall meet its full performance requirements, without performance or physical degradation during and after vibrational stresses.

1.25. The assembly shall meet its full performance requirements without performance or physical degradation after storage at up to 160ºF (71ºC).

1.26. The assembly, which is not exposed to air temperatures in the engine compartment, shall meet its full performance requirements, without performance or physical degradation during its worst case thermal operating cycle at ambient air temperatures of 160°F (71°C).

1.27. The assembly shall meet its full performance requirements without performance or physical degradation after storage at -60ºF (-51ºC).

1.28. The assembly shall meet its full performance requirements without performance or physical degradation during continuous operation, with manipulation, immediately after power up at an ambient temperature of -40ºF (-40ºC).

1.29. The assembly shall meet its full performance requirements after withstanding sudden changes in the temperature range between the low storage temperature and high storage temperature extremes.

1.30. The assembly shall meet its full performance requirements, without performance or physical degradation with continuous operation during and after exposure to shock impulses.

1.31. The assembly shall not suffer physical damage or degradation and meet full performance requirements following exposure to water jet spray at 167ºF (75ºC).

1.32. The assembly shall not suffer physical damage or degradation and meet full performance requirements following exposure to steam cleaning.

1.33. Workmanship shall be in accordance with MIL‐HDBK‐454, Guideline 9, or best commercial practices.