SWNext_GEO_HEO_Instrument_RFI_5-6-2024.pdf

RFI-SWO-GEOHEOIns-2024

Request for Information (RFI)

Title: Space Weather (SW) Next Instruments for Geostationary Earth Orbit (GEO) and Highly Elliptical Orbit (HEO)

Date Original Post: May 6, 2024 RFI Questions/Comments Due: May 23, 2024 at 11:59PM ET RFI Responses Due Date: June 7, 2024 at 11:59PM ET

This is a Request for Information (RFI). NOAA is soliciting information related to in situ and remote sensing space weather instrument development and related capabilities. This RFI is for informational purposes only; it is not a request for proposals or a solicitation for a contract or grant award and it does not obligate the Government in any way. The Government will not reimburse respondents for any costs associated with responding to this request.

1. Background

NOAA’s National Environmental Satellite, Data, and Information Service (NESDIS) is responsible for the continuity of critical space weather observations supporting operational space weather forecasts, watches, warnings, and alerts. The Space Weather Next (SW Next) Program is being implemented by NESDIS through a joint program office with NASA Goddard Space Flight Center, the Office of Space Weather Observations (SWO), to ensure the continuity of space weather observations that support operational space weather monitoring and forecasting as well as to provide enhancements beyond current capabilities.

To ensure sustainment of space weather data products, SW Next will continue the observations made by the present space weather instruments hosted by the Geostationary Operational Environmental Satellite R Series (GOES-R) program on its satellites. These instruments include in-situ sensors as well as solar remote sensing payloads. Separately, SW Next is also considering hosting opportunities for in situ and remote sensing space weather payloads in Highly Elliptical Orbits (HEO) such as Tundra, Three Apogee (TAP), and Molniya orbits.

The goal of SW Next is to maintain space weather awareness by providing the operational space weather observational data needed for the Space Weather Prediction Center (SWPC) to create useful and timely space weather watches and warnings.

2. Purpose

The National Oceanic and Atmospheric Administration (NOAA), National Environmental Satellite, Data and Information Service (NESDIS), Office of Space Weather Observations (SWO) is soliciting information through this RFI to survey vendor interest and capabilities.

Information received will be used in the preparation and support of the development of an acquisition strategy and for a potential, future release of a Request For Proposal (RFP) to procure, develop and fabricate instruments for the SW Next Program observations in geosynchronous (GEO) and highly eccentric orbits (HEO). For the purpose of this RFI, the notional launch date for both GEO and HEO observatories is 2032. The GEO observatory has a notional mission life of 7 years while that of the HEO observatory is 5 years. Prospective vendors may assume that the notional HEO orbit is a Tundra orbit.

The purpose of this RFI is to solicit vendor interest and capabilities to produce one or more of the instruments listed below on a satellite in GEO and/or HEO as indicated:

● GEO

○ In-situ particle (electrons, protons, ions) flux sensors

○ Magnetometer

○ Extreme Ultraviolet (EUV) imager

○ EUV irradiance sensor

○ Photospheric magnetograph imager

○ Heliospheric imager

○ Ionosphere/Thermosphere (I/T) Imager

● HEO

○ In-situ particle (electrons, protons, ions) flux sensor

○ Magnetometer

○ Auroral imager

3. Information Requested

This RFI is for information and planning purposes to solicit feedback on the scope and requirements for the specified instruments, to verify reasonableness and feasibility, and to evaluate the level of maturity of the necessary technology for each instrument type.

Prospective contractors are invited to submit Capability Statements to:

a. Provide current and past experiences applicable to the instruments being addressed. Include applicable company background, heritage and other applicable experience.

b. Provide estimated physical characteristics including mass of each sensor component, dimensions of each sensor component (volume), data interface type (data rate), and required field of view.

c. Provide operating voltage and the peak and steady-state power estimates of each sensor.

d. Provide thermal temperature ranges and power dissipation requirements. Does the sensor have a thermal electric heater or cooler? If so, what accommodations from the spacecraft are required?

e. Provide any environmental constraints, e.g., magnetic cleanliness. Sensors could potentially be integrated on platforms also carrying magnetometers, so indicate estimated levels of electromagnetic interference (EMI), if available.

f. Provide approach for and/or past experiences delivering end-to-end calibration models for instruments, where applicable.

g. Include a discussion of your mission assurance approach which includes sparing strategy, and recommended engineering model development, including rationale.

h. Provide a cost, technical readiness level (TRL) and associated risks. Please identify key drivers for risks, and cost. Include recurring and non-recurring costs for a first and subsequent instruments up to a total of three instruments.

i. Identify options for mitigating risk, including technical trades, cost, and schedule risk mitigations.

The observational requirements for each instrument are provided in Section 4. Responses are requested to identify potential areas of technical concern and non-compliance, please state current capability and whether a Non-Recurrent Effort (NRE) would be required to achieve compliance on that particular requirement.

4. Instrument Requirements

This RFI seeks information on instrument concepts that will meet the performance and Size, Weight and Power, (SWAP) specifications. The SWAPs are notional baseline estimates where a smaller SWAP is beneficial. If larger SWAP is needed please include the drivers for the larger SWAP.

Threshold is the minimum requirement. Objective is the desired goal. Only the threshold requirements must be met. If the noted goal can be met, please indicate how it may impact risk, schedule and instrument cost. Latencies are provided for reference and include allocations for downlink and ground processing.

4.1. Energetic Particles

This RFI seeks information on instrument concepts that will meet the performance specifications for energetic particle flux measurements of charged particle populations that present hazards to spacecraft, aircraft, and human flight crews. These populations include low energy electrons, protons, and ions, medium and high energy electrons and protons, solar energetic particles (SEPs) and heavy ions. Specifications for each population can be found in Tables 4.1 - 4.4 below. Although the requirements are provided for four categories, there need not be a one-to-one correspondence with the number of instrument concepts provided. Respondents can address any subset of requirements or provide responses related to a suite of sensors covering one or more categories.

Instrument concepts can be suitable for either a single orbit or both for GEO and HEO. If providing concepts suitable for both orbits, describe any modifications that need to be made for the environment of each orbit. Target SWAP values are provided in Table 4.5. These values apply to the suite of energetic particle sensors and are not requirements but the general anticipated numbers.

Table 4.1. Requirements for low energy electrons, protons, and ions.

Observation Component Threshold Objective

Pitch Angle Resolution 15 degrees

Energy Range, Electrons: Differential Flux 30 eV– 30 keV 20 eV–60 keV

Energy Range, Protons: Differential Flux 30 eV–30 keV 10 eV–80 keV

Energy Range, Oxygen Ions (O+): Differential Flux

N/A 1 - 120 keV

Differential Energy Channels At least 15 evenly space logarithmic energy bands per species

Measurement Accuracy ±25% when the flux level above background is greater than 10 times the minimum flux

±10% when the flux level above background is greater than 10 times the minimum flux

Measurement Range, Electrons: Flux 9.0x104 E-1.3 - 8.0x108 E-0.8 cm-

2s-1sr-1keV-1

Measurement Range, Protons: Flux 4.0x103 E-0.8 - 1.1x107 E-0.8 cm-

Refresh Rate 1 sec

Data Latency 60 sec 10 sec

Table 4.2. Requirements for medium and high energy electrons and protons.

Pitch Angle Resolution 35 degrees

Energy Range, Electrons: Differential Flux 30 keV– 4 MeV 20 keV–10 MeV

Differential Energy Channels, Electrons At least 10 evenly spaced logarithmic energy bins

Energy Range, Electrons: Integral Flux > 2 MeV > 2 MeV > 10 MeV

Energy Range, Protons: Differential Flux 80 keV–10 MeV 20 keV – 12 MeV

Differential Energy Channels, Protons At least 7 evenly spaced logarithmic energy bins above background is greater than 10 times the minimum flux

±10% when the flux level above background is greater

Measurement Range, Electrons: Flux 1.9x106 E-2.2 - 7.2x1011 E-2.8 cm-

Measurement Range, Protons: Flux 6.6x105 E-2.3 - 1.7x108 E-1.6 cm-

Refresh Rate 60 sec 10 sec

Table 4.3. Requirements for solar energetic particles.

Coverage Two look directions (east and west)

Energy Range, Protons: Differential Flux 1 MeV –750 MeV 1 MeV–1.0 GeV

Differential Energy Channels, Protons At least 10 evenly spaced logarithmic energy bands

Energy Range, Protons: Integral Flux >500 MeV above background is greater than 10 times the minimum flux

±10% when the flux level above background is greater

Measurement Range, Protons (1 MeV - 500 MeV): Flux

8.0x102 E-1.8 - 5.4x109 E-2.1 cm-

Measurement Range, Protons (> 500 MeV):

Flux

4x10-2 - 2x103 cm-2s-1sr-1

Refresh Rate 60 sec 10 sec

Table 4.4. Requirements for heavy ions.

Coverage One look direction

Energy Range, Heavy Ions (Z>=2)

10 MeV/n - 200 MeV/n

10 MeV/n - 200 MeV/n above background is greater than 10 times the minimum flux

±10% when the flux level above background is greater

Measurement Range 5.5x10-2 (E/n)-2.3 - 5x104 (E/n)-1 cm-2s-1sr-1(MeV/n)-1

Refresh Rate 5 min 1 min

Table 4.5. Target Instrument SWAP

Envelope HxWxL (m) Sensor + Electronics (each): 0.45x0.35x0.45

Power (W) Sensor + Electronics (each): 30

Mass (kg) Sensor + Electronics (each): 24

4.2. Magnetic Field

This RFI seeks information on instrument concepts for magnetometers to measure the 3D vector magnetic field. This measurement is useful to detect geomagnetic disturbances within the magnetosphere. Performance specifications are given in Table 4.6. The target SWAP for this sensor is given in Table 4.7. Target SWAP values are not requirements but the general anticipated numbers. Instrument concepts do not need to include a boom; however, NOAA is interested in magnetometers with novel boom designs.

Table 4.6. Requirements for magnetospheric magnetic field.

Observational Extent In situ, 3-axis, orthogonal to within 0.5°

Measurement Range ±512 nT ±550 nT

Measurement Accuracy ±1 nT ±0.2 nT

Refresh Rate 10 Hz 50 Hz

Table 4.7. Target Instrument SWAP

Envelope HxWxL (m) sensor: 0.042x0.044x0.049 electronics: 0.091x0.143x0.143

Power (W) 4.08 (total for 2)

Mass (kg) 3.77 (total for 2)

4.3. EUV Imager

This RFI seeks information on instrument concepts for EUV imagers that are capable of resolving solar features including coronal holes, filaments and prominences, active regions, coronal mass ejections (CMEs), and X10 Class solar flares. Solar EUV imagery provided comprehensive situational awareness of the inner solar corona. Although there is no requirement for the number of EUV spectral bands, bands should be selected that are sensitive to different plasma temperatures within the range specified for feature and phenomenological discrimination. The EUV imagery product requirements are given in Table 4.8 below. The resolution refers to the resolution of the calibrated imagery product rather than the native instrument resolution. Table 4.9 provides target SWAP values for this sensor. These are not requirements but the general anticipated numbers.

Table 4.8. Requirements for solar EUV imagery.

Image Center and Orientation

Sun-centered, Solar North-aligned

Observational Extent 0–1.5 Rsun

Spatial Resolution 5 arcsec 1 arcsec

Plasma Temperature Range 10^4.9 K to 10^7.2 K

Solar Feature Identification Coronal holes, Filaments / Prominences, Active Regions, CMEs, X10 Class Solar

Flares

Signal to Noise Ratio 10 40

Refresh Rate 2 min 10 sec

Data Latency 1 min 10 sec

Table 4.9. Target SWAP

Envelope HxWxL (m) 0.25x0.25x0.25

Power (W) 62.5

Mass (kg) 39.39

4.4. Solar EUV Irradiance

This RFI seeks information on instrument concepts for EUV irradiance sensors capable of generating an EUV irradiance product that meets the specifications in the Table 4.10 below. The solar EUV irradiance will be used to drive models of the thermosphere and ionosphere. The target SWAP values are given in Table 4.11 and are not requirements but rather the general anticipated numbers.

Table 4.10. Requirements for solar EUV irradiances.

Observational Extent 0–1.3 Rsun

Wavelength Range 5.01–127 nm 2.0 –170 nm

Wavelength Resolution 5 nm

0.1 nm

Daily Average Measurement Accuracy

±20%

±10%

Short-term Averaged Measurement Accuracy

None

±10%

Refresh Rate 30 sec 10 sec

Data Latency 30 sec 5 sec

Table 4.11. Target SWAP

Envelope HxWxL (m) 0.305x0.127x0.153

Power (W) 6.84

Mass (kg) 6.67

4.5. Photospheric Magnetograph Imagery

This RFI seeks information on instrument concepts for photospheric magnetograph imagers capable of producing line of sight (LOS) measurements of the photospheric magnetic field that meet the specifications in the table below. High resolution mapping of the solar photospheric magnetic field is a critical input to model the solar wind velocity, density, and magnetic polarity. In addition to magnetic field measurement, doppler velocity observations are also of interest. While only LOS observations are required, if capabilities could be extended to vector measurements describe any impacts on the sensor SWAP, cost, and risk. The requirements for the photospheric magnetograph imagery and Doppler velocity imagery are given in Tables 4.12 and 4.13 respectively. The target SWAP values for the sensor are provided in Table 4.14. These values are not requirements but the general anticipated numbers.

Table 4.12. Requirements for photospheric magnetograph imagery.

Image Center and Orientation Sun-centered, Solar North-aligned

Observational Extent Solar disk from 0–1 Rsun

Spatial Resolution 5 arcsec 1 arcsec

Measurement Range ±2.5 kG ±5 kG

Measurement Accuracy ±20% ±0.1%

Sensitivity 1.5 G/pxl 0.5 G/pxl

Zeropoint Error 0.1 G/pxl 0.01 G/pxl

Refresh Rate 1 hr 10 min Data Latency 1 hr 1 min

Table 4.13. Requirements for photospheric Doppler velocity field imagery.

Image Center and Orientation Sun-centered, Solar North-aligned

Observational Extent Solar disk from 0–1 Rsun

Spatial Resolution 5 arcsec 1 arcsec

Measurement Accuracy ±20% ±0.1%

Refresh Rate 1 min Data Latency 1 hr 1 min

Table 4.14. Target SWAP

Envelope HxWxL (m) 0.40x0.25x0.15

Power (W) 20.4

Mass (kg) 24.7

4.6. Heliospheric Imagery

This RFI seeks information on instrument concepts for heliospheric imagers. Heliospheric imagery, as white light and potentially polarized, provides the only way to observe the solar wind and coronal mass ejections in interplanetary space polarimetric capability is of interest as an objective. The specifications for the imagery product are given in the Table 4.15 below. The target SWAP values for the sensor are provided in Table 4.16. These values are not requirements but the general anticipated numbers.

Table 4.15. Requirements for heliospheric imagery.

Observational Extent (FOV) 15–100 Rsun 10–320 Rsun

Spatial Resolution

10 arcmin at inner FOV (15 Rsun) 2 degrees at outer FOV (100 Rsun)

Measurement Sensitivity

3×10-15 BSun for inner FOV (15 Rsun) 3×10-16 BSun for outer FOV (100

Rsun)

Measurement Accuracy ±10%

Refresh Rate 1 hr 30 min

Data Latency 4 hr (TBR) 30 min

Table 4.16. Target SWAP

Envelope HxWxL(m) 0.84x0.55x0.26

Power (W) 56.4

Mass (kg) 21.9

4.7. Thermospheric O/N2 Ratio

This RFI seeks information on instrument concepts for instruments capable of providing thermospheric and ionospheric composition and temperature data from GEO orbit. These data will be assimilated into thermosphere/ionosphere models. The emphasis is on obtaining daytime O/N2 ratio over the disk as an important parameter for characterizing plasma loss rates in numerical ionospheric models; however, thermospheric temperature and nighttime peak electron density/total electron content observations are also of interest. While integrated quantities measured over the disk are sufficient, limb scanning capabilities would also be of interest. Specifications for the data products are given in the Tables 4.17-4.19 below. Table 4.20 provides the target SWAP values which are not requirements but rather the anticipated values.

Table 4.17. Requirements for Thermospheric O/N2 Ratio.

Observational Extent Dayside Dayside

Observational Altitude Range 150–600 km

Observational Horizontal Resolution

250 km 100 km

Measurement Uncertainty ±10%

Refresh Rate 1 hr 15 mins

Data Latency 1 hr 30 mins

Table 4.18. Requirements for Thermospheric Temperature.

Observational Extent Dayside Dayside

Observational Altitude Range 150–600 km

Observational Horizontal Resolution

250 km 100 km

Measurement Uncertainty 50 K

Table 4.19. Peak Electron Density

Observational Extent Nightside Nightside

Observational Altitude Range 150–600 km

Observational Horizontal Resolution

250 km 100 km

Measurement Uncertainty ±15%

Table 4.20. Target SWAP

Envelope HxWxL or DxL(m) or (m2) TBD

Power (W) 12

Mass (kg) 44.2

4.8. Auroral Imagery

Table 4.21 provides a summary of the Auroral Imagery requirements. The Auroral Imager is being considered for flight on partner owned and operated HEO platforms. Auroral location and intensity are important for mitigation of space weather impacts on aviation, power grid and satellite operations, and insight into how the high latitude ionosphere-thermosphere system moderates the energy transfer from the solar wind and magnetosphere can be derived from far ultraviolet (FUV) imagery. Data products of interest include Auroral Energy Deposition or Q (mW/m2 ) and average electron energy (Eavg , in eV). For the observational bandpass ranges the Lyman-Birge-Hopfield long (LBHL), Lyman-Birge-Hopfield Short (LBHS) and 135.6 nm are of interest, however the proposition of other wavelengths is encouraged if they add value to the mission and are within the bandpass requirements listed in Table 15. Visible light is also an objective and estimates (rough order of magnitude) on the increase in price and SWAP for the visible light are requested. In addition to the requirements listed in Table 4.21, the following are highly encouraged: a summary on instrument sensitivity (counts/Rayleigh/pixel/second, see glossary), signal to noise ratios, dynamic range (kilo cnt/sec), spectral resolution (provided in nm), TRL, instrument field of view or field of regard and uncertainty estimates or accuracy for the data products of interest (e.g. Q, Eavg). Prospective vendors may consider a notional Tundra orbit geosynchronous over the Western hemisphere with an inclination of 63.4 degrees, an argument of perigee of 270 degrees, and a semi-major axis of 42,163 km.

Table 4.21. Requirements for Auroral Imagery

Observational Extent >60 degrees N latitude >45 degrees N latitude

Average Observational Spatial Resolution (for data products)

50 km 10 km

Observational Band Pass Range 135–180 nm 110–180 nm and 400–650 nm

Refresh Rate 5 min when observed from >60 N degrees latitude.

1 min when observed from >60 N degrees latitude.

Data Latency 15 min 1 min

Table 4.22. Target SWAP

Envelope HxWxL (m) 0.4x1.05x0.10

Average Power (W) 120

Mass (kg) 61

5. Submission Instructions

RFI Responses and Capability Statements should include the following information:

1. Business information including: Company name, address, DUNS number, and CAGE Code;

Point of contact with email and phone number; Size of company to include number of employees and revenue for the last three years; Office locations; any current Small Business Administration small business designations.

2. A description of the corporate history, resources, affiliations, other markets being served, and any other information to demonstrate the viability of providing services.

3. Projected costs and associated business models, including the degree of government commitment required and the extent of non-government markets for the services.

4. Business risks to the proposed approach and the means for mitigating those risks.

5. Cost models and contractual arrangements for proposed services (i.e., FAR-based contract, Cooperative Research and Development Agreement, grant, cooperative agreement, and/or Other Transaction Agreement).

6. Capability Statements must be received via email by the Contracting Officer at the address provided below no later than the posted due date. The Government is not obligated to review responses received after the deadline.

Interested respondents may respond to one or more instruments in Section 4 of this RFI; novel, innovative and creative concepts and solutions are encouraged. Concepts on possible suites of instruments are encouraged. For these concepts, please include any risks and benefits.

Comments on any requirements are encouraged. If changes to the requirements would allow for a lower risk, lower cost or higher heritage approach, please respond with both a compliant response and the recommended changed requirement and the benefits of changing the requirement(s).

Responses are limited to 6 pages per section, including supporting appendices, title page(s), tables, graphics, pictures, and figures. If responding to more than one instrument, the page limitation is 6 pages per instrument. A page is defined as an 8.5 by 11-inch area with information contained within an image area of 6.5 by 9-inches. Type size must be 12-point proportional font. Information must be submitted in Microsoft Word DOCX or Adobe Acrobat PDF format.

Submissions must be emailed to Maryann.Orellana@noaa.gov by the deadline posted with the email Subject Line: RFI-SWO-GEOHEOIns-2024.

6. Use of Information Received

This RFI does not guarantee that the Government will issue a request for proposal (RFP) or award a contract for supplies or services. No specific RFP is planned to follow this RFI; however, the responses could impact the Government’s decision to release multiple RFPs in the future.

Proprietary information will be safeguarded in accordance with the applicable government regulations. Any material received will be considered to be public domain unless clearly marked (on each page) as proprietary. The Government must not be liable for or suffer any consequential damages for proprietary information not properly identified. Not responding to this RFI will not preclude an entity from submitting a proposal to any subsequent NOAA solicitations.

Respondents are hereby notified that as part of this process, NOAA may share the information obtained from this market research with other US Government agencies.

7. Point of Contact

Maryann Orellana, Contracting Officer

NOAA/AGO/SIAD

Maryann.Orellana@noaa.gov

8. Comments and Questions

Comments and questions regarding this RFI must be submitted to the Contracting Officer at the email address provided above by May 23, 2024 at 11:59PM ET. Respondents are advised that questions submitted and Government responses may be posted publicly on SAM.gov, although the identity of the requesting organization will be withheld.

9. Appendix

Table 11.1. Technology Readiness Level (TRL) Definitions TRL Description

TRL 9 Actual system “flight proven” through successful mission operations

TRL 8 Actual system completed and “flight qualified” through test and demonstration (ground or space)

TRL 7 System prototype demonstration in a space environment

TRL 6 System/subsystem model or prototype demonstration in a relevant environment (ground or space)

TRL 5 Component and/or breadboard validation in relevant environment

TRL 4 Component and/or breadboard validation in laboratory environment

TRL 3 Analytical and experimental critical function and/or characteristic proof-of-concept

TRL 2 Technology concept and/or application formulated

TRL 1 Basic principles observed and reported

Glossary:

Bsun: the brightness of the solar disk.

Irradiance: Refers to energy measured by a detector as coming from any possible direction with units such as W m-2.

Latency: The time from the collection of the last measurement needed for a product through the time that the data is converted to Level 1b and made available for retrieval by the end user through the user portal.

Measurement Accuracy: Measurement accuracy is defined as the closeness of agreement between a measured quantity value and a true quantity value of a measurand (i.e., the quantity intended to be measured) (ISO-JCGM 200, 2008), and is often limited by calibration errors. From: Biomechanics and Gait Analysis, 2020. Unless otherwise stated, Measurement Accuracy may average daily.

Observational Extent: For remote sensing measurements, the entire region to be measured or observed. For optics this can be equivalent to or greater than the instrument field of view; for in situ measurements, this is the location of the measurement.

Pitch Angle: The pitch angle of a charged particle is the angle between the particle's velocity vector and the local magnetic field.

Rayleigh: 1 Rayleigh (R) = (106/4𝛑𝛑) photons / (cm2 sr s)

Refresh: The time interval between successive collections of measurements of the same parameter of the location or region being observed from the same observation point.

Sensitivity: Pertaining to the Auroral Imagery, is defined as the counts detected for an increase in radiance of one Rayleigh per second for an individual pixel as a given wavelength.

Solar north-aligned: Images of the Sun or solar corona are rotated so the north pole of the solar rotation axis, ‘specified by Helioprojective-Cartesian coordinates, is straight up in the image.

Spatial Resolution: The smallest horizontal increment needed of the data product. Spatial granularity in the horizontal with which information and data are required

Sun-centered: Images of the Sun or solar corona are translated so the ‘geometric center’, specified by Helioprojective-Cartesian coordinate origin (ϴ=0, Φ=0), is centered in the image.