SNOUT_Optics_RFI_221115 FINAL for Posting.pdf

Small NASA Optical Ultraviolet Telescope (SNOUT)

Extreme Ultraviolet (EUV) Primary Tri-Mirrors and

Assembly and Detectors.

Request for Information (RFI)

Reference Number: 2022_RFI_Snout_OPTICS

Released Date: 11/15/2022

Responses Date: 12/09/2022

REQUEST FOR INFORMATION (RFI). NASA is soliciting information regarding interest, concepts, and cost for Primary Mirror Assembly (with option for detectors) of the

SNOUT instrument.

1. Summary:

The National Aeronautics and Space Administration (NASA) is seeking information under this

Request for Information (RFI) to assess interest, concepts, and rough order of magnitude (ROM) costs to provide an EUV Primary Mirror Assembly with option for detectors for the NASA

Goddard Space Flight Center’s SNOUT mission.

2. Mission Background:

The Small NASA Optical Ultraviolet Telescope (SNOUT) mission is currently pre-Phase A.

This phase ends with a proposal due March 2023. If the proposal is selected for implementation, the mission will proceed into implementation compliant with NASA NPR 7120.8. The following schedule should be used as a basis for responses to this request:

Request for Information released November 15, 2022

Responses due December 09, 2022

Phase A Start Date October 1, 2023

Spacecraft Start Date Expected ~ July 31, 2024

Optics Assembly Delivery for I&T Expected ~ June 30, 2025

Instrument Delivery for I&T Expected ~ February 1, 2026

Launch Readiness Date Expected NLT November 14, 2027

The SNOUT mission is targeting a Sun Synchronous Orbit (SSO) ESPA or ESPA Grande class spacecraft with an expected lifetime of one year. The instrument design is underway and able to be configured to meet available size, data, and power requirements derived from this RFI with a trade study to be performed by the mission team.

The instrument is self-contained and requires a minimum volume of 16.4”x20”x27” where a

16.4”x20” side is the aperture of the telescope requiring direct access to space. Minimally the spacecraft shall support more than 10Mbps data rate from the instrument with a power draw of

50W during operations. The instrument is to be pointed within 8 arcseconds of a variety of targets with the ability to have the instrument operational for a minimum of two hours during eclipse. If target always visible in orbit, ideal would be to maintain pointing on target. Integration and operations will be supported by the mission instrument team and science operations center.

The optical system is a tri-mirror prime focus system. Each mirror is an off-axis parabola (OAP).

Although each mirror segment may be identical, they act as independent optical imagers. The three mirrors are radially displaced from the centerline by (at least) 5 mm, such that the images lie on a circle with a radius of (at least) 5 mm. The FOV of each system is 8 arcseconds (in essence, a single star). Each segment will be coated for a different extreme ultraviolet (EUV) bandpass. The sensor assembly is at the prime focus of all three segments. A single CCD will capture all three images. Prior to the CCD will be three independent “foil filters” to reject longer wavelength radiation.

Structural considerations of the optics Assembly include:

Kinematic mount of the assembly to the instrument

Kinematic mount of the mirrors to the assembly

Additional options available to improve performance

Temperature range to hold surface figure: 290°-300° K

Method to hold or be aligned to the detector/foil Assembly (at Primary prime focus)

Optical considerations include:

Mirror Nominal focal length: 400 mm

Surface form: Parabolic (Conic constant K = -1)

Number of mirror segments: Three (3)

Surface Area per segment: 270 cm2, minimum

Segment Spot focus radial offset from sensor center: minimum 5 mm.

Spot focus parfocality to orthogonal sensor plane: 0.2 mm

Surface roughness: 5Å RMS

Image quality, Spot Size diameter, in-orbit: (including surface figure, coatings, thermal stability, alignment, launch, etc.): 8 µm (95% encircled energy), 16 µm (99% encircled energy).

Coatings considerations include:

Optics must be able to be disassembled from assembly for coating, or, would be qualified for acceptance before coating and final assembly by the vendor.

Coatings for narrowband EUV on each segment:

• Segment #1: 172Å – 195Å, Prime: 184Å, Reflectance: 0.35 (min)

• Segment #2: 246Å – 288Å, Prime: 267Å, Reflectance: 0.35 (min)

• Segment #3: 301Å – 304Å, Prime: 304Å, Reflectance: 0.45 (min)

Each coating must be applied such that the prime wavelength maintains required reflectance (R) across the full optical surface given any change in incident angle.

Detector (optional)

Nominal operating temperature: -80° C

Sensitivity in the EUV bandpass (100 - 400 Ang)

Vendor has option to incorporate integral 25mm visible-light OAP mirror and detector.

Same or finer pixel pitch as UV images’ detector

Bandpass 400-900 nm (approximate)

NASA will use responses to this RFI to evaluate commercial interest in providing a Primary

Mirror Assembly with option for detectors for SNOUT and may use the responses to inform future requests for proposals.

Figures 1 & 2 show conceptual (not prescriptive) designs for the instrument:

Figure 1. Figure 2.

3. Information Requested:

Responses to this RFI should include:

1. Organization information: Organization name and address, point of contact name, e-mail address, phone number.

2. Description of the concept(s), including, as applicable,

a. Optical Design

i. Block diagram

ii. CAD of assembly including mounts, backplane and mirrors w/ instrument volume identified.

iii. Technical Readiness Level (TRL) of sub-systems / components

iv. Technical budgets: Mass, volume

b. Mirror assembly interface details

i. Size, weight, and power available for each configuration

ii. Mounting points required

c. Detector (optional)

i. Detector choice/options

ii. Technical Readiness Level (TRL) of sub-systems / components

iii. Operating temperature

iv. QE in EUV bands (listed above)

v. Technical budgets: Mass, volume. power, data

vi. Mounting points required

3. Integration, Calibration, and Validation: Description of pre-launch integration activities expected such as engineering model testing, flight instrument integration and alignment, and ability of the science team to participate in spacecraft level checkouts including the instrument.

4. Operations: Description of operations activities.

5. Cost Estimate: A ROM for the concept(s) with WBS breakdown.

6. Schedule To Delivery: A ROM schedule for the concept(s).

7. Technical or Policy barriers: Identified technical or policy barriers.

This RFI is open to all types of organizations, including U.S. and international industry, universities, non-profit organizations, NASA Centers, Federally Funded Research and

Development Centers, other U.S. Government agencies, and international organizations.

This RFI is for planning and information purposes only and is NOT to be construed as a commitment by the Government to enter into a contractual agreement, nor will the Government for information solicited. If NASA decides to proceed with a new procurement or announcement, NASA will synopsize its intent on Contract Opportunities (SAM.gov).

No solicitation exists; therefore, do not request a copy of the solicitation. If a solicitation is released, it will be synopsized in Contract Opportunities and NASA Acquisition Internet Service.

It is the interested party’s responsibility to monitor these sites for the release of any solicitation or synopsis.

4. Response Instructions:

All responses submitted in response to this RFI must be submitted in PDF format via email to the point(s) of contact with the subject containing the “2022-RFI-SNOUT-Optics” reference by

December 9, 2022, 5:00PM EST. Updates are accepted should modification be desired after initial submission.

Contracting Office Address:

NASA/Goddard Space Flight Center, NASA Headquarters Acquisition Branch, Code 177

Greenbelt, Maryland 20771

United States

Primary Point of Contact:

Bert A. Pasquale bert.a.pasquale@nasa.gov

Secondary Point of Contact:

John P. Lucas john.p.lucas@nasa.gov