RFI_GSFC_Sensor_Subsystem_Assembly_FY25GJE.pdf

NASA Goddard Space Flight Center Short-Wave Infrared Sensor Subsystem Assembly Request for Informa�on

I. Overview

THIS IS NOT A REQUEST FOR PROPOSAL. NO PROPOSALS ARE TO BE SUBMITTED IN

RESPONSE TO THIS NOTICE.

This no�ce is issued by the NASA/GSFC to solicit responses from interested par�es. This document is for informa�on and planning purposes and to allow industry the opportunity to verify reasonableness and feasibility of the requirement, as well as promote compe��on.

NASA’s Goddard Space Flight Center (GSFC) has a need for a Short-wave Infrared (SWIR) space-rated Sensor Subsystem Assembly (SSA) for use in Low Earth Orbit (LEO) as part of an Earth observing instrument concept. A representa�on of the desired system is presented in Figure 1. The requested SSA is shown in blue with separately provided components shown for context. The spacecra� will receive digital readout of the detector, and perform all subsequent processing of the data. Spacecra� will provide onboard commanding of the SSA.

This Request for Informa�on (RFI) contains the requirements of the desired system.

Figure 1: SSA with interfacing components

We invite responses from vendors that have an SSA that meets the enclosed requirements or have systems that can be modified in �me to meet the instrument delivery schedule. The responses should include pricing, camera capability and performance, and mechanical, thermal, digital, power and flight so�ware interfaces.

No solicita�on exists; therefore, do not request a copy of the solicita�on. If a solicita�on is released, it will be synopsized on SAM.gov. Interested firms are responsible for monitoring this website for the release of any solicita�on or synopsis.

Vendors having the capabili�es necessary to meet or exceed the stated requirements are invited to submit appropriate documenta�on, literature, brochures, and references.

All responses shall be submited electronically via email to Steve Tompkins, steve.tompkins@nasa.gov no later than Friday, January 31st at 4pm EST. Please reference ID # RFI_GSFC_Sensor_Subsystem_Assembly_FY25GJE in any response.

This synopsis is for informa�on and planning purposes only and is not to be construed as a commitment by the Government nor will the Government pay for informa�on solicited.

Respondents will not be no�fied of the results of the evalua�on. Respondents deemed fully qualified will be considered in any resultant teaming arrangement and/or solicita�on for the requirement.

II. Assump�ons

Assume the spacecra� will launch on an Antares or Falcon 9 to an 800 km sun synchronous orbit for at least three years of opera�on.

III. Requirements

This sec�on outlines the needs of the SSA. Requirements are explicitly labeled while other desired characteris�cs are provided as reference.

Programma�c

Instrument development start date: November 17, 2025 Instrument Design Review: September 30, 2026 SSA delivery to I&T: October 15, 2027 Instrument delivery date: June 15, 2028

Technical Requirements

Mechanical

- Mass: ~1.5 kg

- Dimensions: ~10 cm x 10 cm x 10 cm

- Housing material: ~Aluminum

- Interface accommoda�ons:

o Op�cal subassembly mounted in front of SSA housing o SSA housing mounted to spacecra� structure through a spacecra�-provided interface o Desired SSA aperture with a keep out zone (KOZ) which does not vignete an f/5.1 beam o Desired focal plane is <5mm below housing interface plane

Thermal

- Internal thermal control by SSA

- Focal Plane Thermal Stability: + 0.1 °C

- Opera�onal Range (spacecra� interface): ~ -10 °C to +30 °C

- Survival Range (spacecra� interface): ~ -20 °C to +40 °C

Electrical

- Input Power

- Voltage: 28 VDC Unregulated (24 VDC to 35 VDC)

- Peak Power: <48 W max

- Average Power Consumption expected less than 10 W

- Time synchronization Input

- Function: Used to synchronize the focal plane array readout

- Type: RS-422 or LVDS

- Command and Telemetry

- Type: RS-422 or LVDS UART

- FPA Data Output

- Type: Spacewire desired

- 12 bit minimum ADC

- Grounding: power-return isolated from housing

Detector

Minimum performance listed below meets the baseline requirements. If detectors are available with larger area or more pixels please include those op�ons.

- Format:

- Minimum Dimensions (Required): 12.3 mm x 12.3 mm

- Minimum pixels (Required): 1024 x 1024.

- Pixel pitch: 12 um (desired),

- QE: > 60% at 870 nm, > 80% at 1550nm

- Dark signal rate: < 100 ke- / sec, (at 20 °C)

- Pixel Full Well: > 38 ke-

- Read noise (at 20 °C): < 25 e- RMS

- Fill factor: >99%

- Non-linearity: <1%

- Inoperable pixels (at 20 °C): <0.25%

- Removable window (used only for protec�on)

Radia�on

- Total Ionizing Dose environment: 26 krad (Si) with 100 mils of aluminum shielding

- Total Non-Ionizing Dose Radiation Environment: 2E8 MeV/g (Si) with 100 mils of aluminum shielding

- SEE environments shall not cause unrecoverable failure, nor permanent degradation of, EEE parts or systems that adversely impact system performance or reliability.

SSA Func�onality

- Minimum frame rate: 30 fps

- Commanding

- Exposure �me

- FPA temperature setpoint

- Remote power control on/off, Remote power reset

- Camera configura�on

- Co-addi�on of frames up to 120x is desirable

- Telemetry

- Minimum internally monitored and reported temperatures: Housing, FPA set point, FPA temperature, electronics board

- Thermoelectric Control (TEC) voltage

- Report TEC sensor temperature

- Materials

- Low to no outgassing space flight compa�ble

-Support

- Ground control so�ware

- SSA qualified to GSFC-STD-7000 rev B (GEVS), or equivalent

IV. RFI Instruc�ons

Responses should include pricing, schedule, qualifica�on approach, camera capability and performance, and mechanical, thermal, digital, power and FSW interfaces.

Provide a descrip�on of any flight heritage, including orbit al�tude, inclina�on and flight dura�on.

Provide a ROM cost and schedule for one flight unit and one Engineering Test Unit of the SSA.

Use current year (FY25) dollars for the cost es�mate.

Please reference ID # RFI_GSFC_Sensor_Subsystem_Assembly_FY25GJE in any response.