Pre-solicitation.pdf

This notice is a synopsis for Geostationary Littoral Imaging and Monitoring Radiometer (GLIMR) Access to Space (ATS) “GLIMR ATS.” The purpose of this notice is to provide potential Offerors information regarding the procurement strategy, identify key upcoming milestones, and allow for comments on the draft requirement document(s).

THIS INFORMATION IS FOR PLANNING PURPOSES ONLY AND IS SUBJECT TO CHANGE.

The GLIMR investigation was selected in August 2019, under Earth Venture Instrument-5 (EVI-5) Announcement of Opportunity (AO) NNH17ZDA004O-EVI5, which solicited proposals for complete Principal Investigator (PI)-led spaceflight instruments to conduct innovative, integrated, hypothesis or scientific question-driven approaches to pressing Earth system science issues. GLIMR will operate from geostationary orbit and use a hyperspectral ocean color radiometer to observe coastal waters that provide critical economic and ecosystem services. GLIMR is a Category 3 mission (per NPR 7120.5) with a Class D payload (per NPR 8705.4). The Appendix to this document provides a high-level mission architecture and key payload parameters.

The following is a summary of key procurement strategy elements:

1. The GLIMR ATS scope includes the procurement of commercial services for the following:

a. Spacecraft and Launch Vehicle;

b. Integration Planning;

c. Ground System Integration, Testing, and Readiness;

d. Instrument-Spacecraft Integration, Test, and Pre-Launch Processing;

e. Spectrum Licensing and orbital slot authorization;

f. Launch and GLIMR In-orbit Checkout;

g. On-Orbit Spacecraft and Instrument Operations*; and

h. Programmatic and technical support.

*Instrument operations were not previously part of the ATS scope described under the Request for Information or other publicly provided Market Research documents; however, it is being added to the scope of this procurement.

2. The procurement will be conducted as a full and open competition under NAICS code 541715, Research and Development in the Physical, Engineering, and Life Sciences (Except Nanotechnology and Biotechnology), 1,000 employee size standard, and as a commercial service utilizing Federal Acquisition Regulation (FAR) Part 12 terms and conditions with FAR Part 15 evaluation procedures. Selection will be based on the overall Best Value to the Government considering price and non-price (experience/past performance, technical approach) factors. The technical approach will be proposed via oral presentations.

3. The expected period of performance (POP) will be five (5) years, consisting of a three (3) year base period and two 1-year options for extended operations. The exact POP will be dependent on Offeror solutions.

a. For the base period, this estimated POP assumes 7 months of integration planning from contract award to instrument delivery, 11 months of integration and test from instrument delivery to launch, 6 months for in-orbit checkout, and 1 year of baseline operations.

b. The estimated instrument delivery readiness is no later than January 2027.

4. The contract will be Firm-Fixed-Price (FFP) with milestone payments.

5. There is no assumption or requirement that the GLIMR Instrument be a dedicated (single) spacecraft payload or one of several spacecraft payloads (e.g., hosting; rideshare). Rather, the Government is looking to industry to provide an effective solution that will meet the GLIMR ATS requirements.

6. The following are ESTIMATED key milestone dates (NOTE: These are estimated dates only and may change at any time.):

Milestone Date

Industry Comments Due April/May 2026 Draft RFP Issuance May 2026 Pre-solicitation Conference June 2026 Final RFP Issuance July 2026 Proposals Due September 2026 Award January 2027

7. The Government intends to release a draft RFP. However, the Government encourages questions, comments and feedback to the documentation attached to this synopsis. As applicable, this notice will be updated based on continued industry engagement and feedback.

No solicitation is currently available; therefore, do not request a copy of the solicitation. If a solicitation is released it will be posted on www.SAM.gov. It is the potential Offeror’s responsibility to monitor this site for the release of any solicitation.

Please check www.SAM.gov regularly for updates. We look forward to your comments and feedback.

Please contact Ashley Korahaes and Stacy Hollis at larc-glimr-ats@mail.nasa.gov for all questions, comments, and feedback.

http://www.sam.gov/ http://www.sam.gov/ mailto:larc-glimr-ats@mail.nasa.gov

Appendix GLIMR Mission Architecture and Key Payload Parameters

Item Requirement/Parameters Mission Duration 12-months following payload In-Orbit Checkout Instrument In-Orbit Checkout Period 90 calendar days GEO Longitude Range 98° ±10° West longitude

Orbit Knowledge ≤300 meters, 3σ, in-track (Orbit Reference Frame (ORF) x-axis), cross-track (ORF y-axis), and radial (ORF z-axis)

Attitude Knowledge Error Static: <1200 microradians per axis, 3σ, precalibration Diurnal: <45 microradians per axis, 3σ Dynamic: <30 microradians per axis, 3σ

Orbit Velocity Knowledge ≤6 cm/sec per axis, 3σ

Angular Rate Knowledge Error

<1 microradian, 3σ x and y axis, 1 second window <1.5 microradians, 3σ z axis, over 1 second window <2 microradians, 3σ x and y axis, over 30 second window <2.5 microradians, 3σ z axis, over 30 second window <7 microradians, 3σ, per axis, 300 second window <20 microradians, 3σ, per axis, 900 second window

Total Pointing Jitter during Payload Observations <0.81 microradians, per-axis, 3σ

Total Current Instrument Mass 141 kg Sensor Assembly Current Mass 110 kg

Sensor Assembly Current Dimensions 1.55 meter (along-track) x 0.94 meter (cross-track) x 0.95 meter (height)

Sensor Assembly Stowed Volume (for Launch) 1.4 meters3

Sensor Assembly Max Volume 1.99 meters3 PCU Current Mass 30 kg

PCU Current Dimensions 0.49 meter (along-track) x 0.45 meter (cross-track) x 0.22 meter (height)

PCU Current Volume 0.05 meters3 DEB Current Mass 1 kg

DEB Current Dimensions 0.16 meter (along-track) x 0.11 meter (cross-track) x 0.2 meter (height)

DEB Current Volume 0.01 meters3 Contractor Supply Voltage 32±2 Volts Direct Current (VDC) Instrument Current Orbit Average Operational Power 251 Watts (W)

Instrument Current Peak Operational Power 271 W Instrument Current Peak Survival Power 188 W Instrument Science Data Interface SpaceWire Instrument Science Data Rate NTE 72 Mega-bits-per-sec (Mbps) Instrument Command/Telemetry Interface SpaceWire Instrument Command/Telemetry Data Rate NTE 500 kilo-bits-per-sec (kbps)

Instrument Clear FOV Conical, 75° half angle toward Earth along Nadir Deck Sensor Assembly Thermal Interface Operating Temperature Range -20°C to 30°C

Sensor Assembly Thermal Interface Survival Temperature Range -30°C to 40°C

PCU Thermal Interface Operating Temperature Range -25°C to 55°C

PCU Thermal Interface Survival Temperature Range -40°C to 70°C

DEB Thermal Interface Operating Temperature Range -24°C to 66°C

DEB Thermal Interface Survival Temperature Range -40°C to 76°C