Space Weather GEO SC RFI Enclosure.pdf

Space Weather Geo Series Spacecraft RFI Enclosure

The Space Weather Observations (SWO) programs division support the United States National Space Weather Strategy by implementing and sustaining operational observation platforms, capabilities, and supporting observations to increase capabilities of data-driven Space Weather models. The program supports the National Oceanic and Atmospheric Administration's (NOAA's) goal of reducing the impact of severe space weather events, and it directly responds to the 2020 Promoting Research and Observations of Space Weather to Improve the Forecasting of Tomorrow (PROSWIFT) Act that directs NOAA and National Aeronautics and Space Administration (NASA) to enter into agreements for the purpose of developing space weather spacecraft and instruments. In support of this outcome the Space Weather Next (SW Next) program furthers the National Environmental Satellite, Data, and Information Service (NESDIS) strategic principles of Commitment through continuity of products and service Community through combining internal strengths with contributions, collaborations, and partnerships; and Capabilities through leverage of observing system integrated architecture and use-inspired science.

The SW Next program will provide essential remote and in-situ space-based space weather measurements that address the NESDIS strategic objective “Advance space weather observational leadership in all applicable orbits to meet mission needs.” A primary NESDIS customer for space weather observations is the National Weather Service (NWS) Space Weather Prediction Center (SWPC). Space weather is driven by solar phenomena that include coronal mass ejections (dense clouds of plasma), solar flares (explosive releases of particles and electromagnetic radiation), solar particle events, and solar wind, as well as terrestrial geomagnetic and upper atmosphere drivers. Space weather not only has devastating effects from major storms but also normal variations in space weather conditions have day-to-day impacts on users of different technological systems that can be mitigated by routine forecasts and warnings.

This program will maintain a long-term sustained capability for operational space weather observations as well as ensure continued data stewardship and access. The SW Next GEO Series is the follow-on to complement the Space Weather Follow On Lagrange 1 (SWFO – L1), L5 and GOES-R series missions. The SW Next GEO Series is a collaborative development and acquisition effort between NOAA and the NASA. The Space Weather Geostationary (GEO) Series Project is referred to as the SW GEO Series Project.

Figure 1. Overview of the notional SW GEO Series mission architecture and concept of operations showing its Flight and Ground segments (Notional for SW Next GEO Mission)

NOAA provides Ground Segment capabilities with a suite of antennas and antenna partnerships, mission command and control facilities, and science data product ingestion, generation, storage, and distribution to users. NOAA and NASA are open to innovative and lower cost and risk alternatives to fulfill the command and control facility needs to operate SW GEO series observatories. The alternative Mission Operations Center (MOC) would still be expected to interface and utilize NOAA’s antenna and product services for receipt and export of mission data.

The SW GEO Series observational goals, availability of observational data and objectives are to provide:

– In situ measurements of the plasma and energetic particle populations in the Earth’s magnetosphere including SEPs,

– In situ measurements of the Earth’s magnetic field

– Measurements of Solar X-ray Irradiance

– Solar EUV imagery

– Solar EUV irradiance measurements

– Photospheric magnetograph imagery

– Height-integrated thermospheric O/N2 ratio data

– Observations of an Instrument of Opportunity

– Operational space weather observational data >93% of the time on an annual basis of nominal operations

– Operational space weather observational data during storm intensities through S4 and X50.

Notional Instruments to be accommodated on the SW GEO Spacecraft and/or hosting opportunities on identified platforms and General Spacecraft Requirements

To accomplish the above observations, the SW Next GEO series shall accommodate a minimum of eight (8) Government Furnished Payloads/instruments, this includes a payload/instrument of opportunity.

The Government anticipates providing the following notional instruments as Government Furnished Equipment (GFE) in support of the SW GEO series, hosting opportunities and the Government anticipates procuring multiple copies of instruments including:

1) Energetic Particle Flux Instrument (EPF): This instrument or suite of instruments will produce in situ measurements of the plasma and energetic particle (electrons, protons, ions) populations in the Earth’s magnetosphere including solar energetic protons (SEPs).

a. Anticipated observation component objectives and Size, Weight and Power (SWaP):

i. Low energy electrons, protons, and ions

1. Pitch Angle Resolution 15 degrees, Energy Range, Electrons: Differential Flux 20 eV–60 keV, Energy Range, Protons: Differential Flux 10 eV–80 keV, Energy Range, Oxygen Ions (O+): Differential Flux 1 - 120 keV, Differential Energy Channels At least 15 evenly space logarithmic energy bands per species, Measurement Accuracy ±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-2s-1sr-1keV-1, Refresh Rate 1 sec, Data Latency 10 sec

2. SC accommodations for low energy electrons, protons, and ions

Size, Power, and Mass, Data Rate, Observational Target:

Size HxWxL (cm) 20x20x35 Power (w) 20 Mass (kg) 10 Data Rate (Max Continuous kbps)

Observational Target Pointing to –Z (zenith) with FOV fan aligned in

YZ plane

ii. Medium and high energy electrons and protons solar energetic particles

1. Pitch Angle Resolution 35 degrees, Energy Range, Electrons: Differential Flux

20 keV–10 MeV, Differential Energy Channels, Electrons At least 10 evenly spaced logarithmic energy bins, Energy Range, Electrons: Integral Flux > 2 MeV> 10 MeV, Energy Range, Protons: Differential Flux 20 keV – 12 MeV, Differential Energy Channels, Protons At least 7 evenly spaced logarithmic energy bins, Measurement Accuracy ±10% when the flux level above background is greater than 10 times the minimum flux, Measurement Range, Electrons: Flux 1.9x106 E-2.2 - 7.2x1011 E-2.8 cm-2s-1sr-1keV-1, Measurement Range, Protons: Flux 6.6x105 E-2.3 - 1.7x108 E-1.6 cm-2s-1sr-1keV-1, Refresh Rate 10 sec, Data Latency 10 sec

2. SC accommodations for Medium and high energy electrons and protons solar energetic particles Size, Power, and Mass, Data Rate, Observational Target:

Size HxWxL (cm) 30x38x16 Power (w) 10 Mass (kg) 15 Data Rate (Max Continuous kbps)

Observational Target Pointing to –Z (zenith) with FOV fan aligned in

YZ plane

iii. Solar energetic particles

1. Coverage, two sensors one looking east and one west, Energy

Range, Protons: Differential Flux 1 MeV–1.0 GeV, Differential Energy Channels, Protons At least 10 evenly spaced logarithmic energy bands, Energy Range, Protons: Integral Flux >500 MeV, Measurement Accuracy ±10% when the flux level above background is greater than 10 times the minimum flux, Measurement Range, Protons (1 MeV - 500 MeV): Flux 8.0x102 E-

1.8 - 5.4x109 E-2.1 cm-2s-1sr-1keV-1, Measurement Range, Protons (> 500 MeV): 8.0x102 E-1.8 - 5.4x109 E-2.1 cm-2s-1sr-1keV-1, Refresh Rate 10 sec, Data Latency 10 sec

2. SC accommodations for solar energetic particles Size, Power, and Mass, Data Rate, Observational Target:

Size HxWxL (cm) (each) 12 x 27 x 27 Power (w) (5+5) =10w total) 10 Mass (kg) (7+7) =14w total) 14 Data Rate (Max Continuous kbps)

Observational Target East/West FOVs pointing to +X and –X

iv. Heavy ions

1. Coverage One look direction, Energy Range, Heavy Ions (Z>=2) 10 MeV/n - 200 MeV/n, Resolution (value being worked), Measurement Accuracy ±10% when the flux level above background is greater than 10 times the minimum flux, Measurement Range 5.5x10-2 (E/n)-2.3 - 5x104 (E/n)-1 cm-2s-1sr-

1(MeV/n)-1, Refresh Rate 1 min

2. SC accommodations for Heavy Ions Size, Power, and Mass, Data Rate, Observational Target:

Size HxWxL (cm) 24 x 27 x 30 Power (w) 6 Mass (kg) 10 Data Rate (Continuous/Burst kbps)

Observational Target Pointing to –Z (zenith)

v. In addition to above sensors, there is an anticipated shared Data Processing Unit (DPU) that will provide, electronics and buffering for all Energetic Particle Flux sensors. SC accommodations for the shared DPU Size, Power, and Mass:

Size HxWxL (cm) 25x25x40 Power (w) 20 Mass (kg) 10

2) Magnetometer (MAG): This instrument, a set of two individual 3-axes magnetometers possibly on a spacecraft provided deployable boom. The magnetometers will measure the 3D vector magnetic field. This measurement is useful to detect geomagnetic disturbances within the magnetosphere.

a. Anticipated observation component objectives:

i. Observational Extent In situ, 3-axis, orthogonal to within 0.5°, Measurement Range ±550 nT, Measurement Accuracy ±0.2 nT, Refresh Rate 50 Hz, Data Latency 10 sec

b. Anticipated Size, Power, and Mass, Data Rate, Observational Target:

i. Sensor/electronics

Size HxWxL (cm) Sensor

8x8x8

Size HxWxL (cm) Electronics

20x13x10

Power (w) (total for 2) 5 Mass (kg) (total for 2) 4 Data Rate (Continuous/Burst kbps)

Observational Target In Situ, SC will align the outboard Mag sensor axes to within +/-2 deg. of the nominal SC reference frame axes.

3) X-ray Irradiance (XI), the primary data product being modeled, solar irradiance.

i. Observational Extent 0–1.3 Rsun, Observational Wavelength Range 0.05 -1.6 nm in three or more bands, Flux Range 1x10-9–5x10-3 W m-2, Measurement Accuracy 10%, Refresh Rate 1sec, Data Latency 10 sec (L1) 3 sec (GEO), Location SEL and Off-SEL

b. Anticipated Size, Power, and Mass, Data Rate, Observational Target:

i. Sensor/electronics Size HxWxL (cm) 10x20x10 Power (w) 12 Mass (kg) 5 Data Rate (Max Continuous kbps)

Observational Target Solar Pointing

4) Extreme Ultraviolet (EUV) imager, solar imaging instrument will be operating in the extreme ultraviolet portion of the solar spectrum. This instrument represents the latest step in NOAA's continuing space weather mission to monitor the solar corona that can resolve 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

a. Anticipated observation component objectives: Image Center and Orientation Sun-centered, Solar North-aligned, Observational Extent 0–1.5 Rsun, Spatial Resolution 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 40, Refresh Rate 10 sec, Data Latency 10 sec.

Size HxWxL (cm) Sensor/instrument

25x25x60

Size HxWxL (cm) Electronics

20x15x10

Power (w) 60 Mass (kg) 30 Data Rate (Max Continuous kbps)

10,000

5) Solar Extreme Ultraviolet (SUV) irradiance instrument, capable of generating an EUV irradiance product. The solar EUV irradiance will be used to drive models of the thermosphere and ionosphere.

a. Anticipated observation component objectives: Observational Extent 0–1.3 Rsun, Wavelength Range 2.0 –170 nm, Wavelength Resolution 0.1 nm, Daily Average Measurement Accuracy ±10%, Short-term Averaged Measurement Accuracy ±10%, Refresh Rate 10 sec.

Size HxWxL (cm) 46x25x25 Power (w) 12 Mass (kg) 15 Data Rate (Max Continuous kbps)

5,008

6) PHOtospheric Magnetograph Imagery (PHOMI): This Instrument provides, line of sight (LOS) measurements of the photospheric magnetic field. 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.

a. Anticipated observation component objectives:

i. Photospheric magnetograph imagery Image Center and Orientation Sun-centered, Solar North-aligned, Observational Extent Solar disk from 0–1 Rsun, Spatial Resolution 1 arcsec, Measurement Range ±5 kG, Measurement Accuracy ±0.1%, Sensitivity 0.5 G/pxl, Zeropoint Error

0.01 G/pxl, Refresh Rate 10 min, Data Latency 1 min.

ii. Photospheric Doppler velocity field imagery Image Center and Orientation Sun-centered, Solar North-aligned, Observational Extent Solar disk from 0–1 Rsun, Spatial Resolution 1 arcsec, Measurement Accuracy ±0.1%, Refresh Rate 1min, Data Latency 1 min

b. Anticipated Size, Power, and Mass, Data Rate, Observational Target:

i. Sensor/electronics

Size HxWxL (cm) Sensor/instrument

82x90x30

Size HxWxL (cm) Electronics

23x11x19

Power (w) 63 Mass (kg) 68 Data Rate (Max Continuous kbps), (Totals for both magnetograph and doppler imagery)

7) Height-Integrated Thermospheric O/N2 Ratio instrument (HITON): This instrument, provides thermospheric and ionospheric composition and temperature data. 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.

i. Thermospheric O/N2 Ratio, Observational Extent Dayside, Observational Altitude Range 150–600 km, Observational Horizontal Resolution 100 km, Measurement Uncertainty ±10%, Refresh Rate 15 mins, Data Latency 30 mins Data Rates 6000 kbps continuous/6000 kbps burst (Totals: O/N2 Ratio Data Rates for, Thermal and Electron Density observations)

ii. Thermospheric Temperature, Observational Extent Dayside, Observational Altitude Range 150–600 km, Observational Horizontal Resolution 100 km, Measurement Uncertainty 50 K, Refresh Rate 15 mins, Data Latency 10 sec

iii. Peak Electron Density Observational Extent Nightside, Observational Altitude Range 150–600 km, Observational Horizontal Resolution 100 km, Measurement Uncertainty ±15%, Refresh Rate 15 mins, Data Latency 10 sec

b. Anticipated Size, Power, and Mass, Data Rate, Observational Target:

i. Sensor/electronics

Size HxWxL (cm) 55x51x69 Power (w) 66 Mass (kg) 37 Data Rate (Max Continuous kbps), (Totals: O/N2 Ratio Data Rates for, Thermal and Electron Density observations)

12,000

Observational Target Earth Pointing

8) The eighth payload, an Instrument Of Opportunity (IOO) shall be considered of similar complexity/requirements to the instruments referenced above, with additional details (interface requirements, etc.) provided as information becomes available. Sun or Earth pointing, with operational thermal limits of -25 to 30C and survival limits of -30 to 50C. The government is requesting feedback and breakpoints in vendor conceptual designs for the IOO so as to not be a system driver.

a. Notional Size, Power, and Mass, Data Rate, Observational Target:

i. Sensor/electronics (as defined by the SC)

Size HxWxL (cm) TBD Power (w) TBD Mass (kg) TBD Data Rate (Max Continuous kbps)

TBD / TBD

Observational Target TBD

9) Anticipated General Spacecraft Requirements, the Government is evaluating novel options and is requesting contractor in the following areas:

a. Communications, this RFI requests discussion and recommendations for SC supported S, X, and or Ka band communications. Including emerging techniques and technologies for 24/7 Tracking, Telemetry, and Command (TT&C)

b. Notional GEO orbit, this RFI requests discussion of on orbit options for a geostationary SC over a longitude location in view of the continental US. Orbit options should consider 2 operational satellites providing observations from.

Longitude and Latitude station keeping within +/-0.1 deg box with 0 eccentricity.

c. Magnetic Cleanliness, describe the SC accommodation for the magnetometer (e.g.

SC supplied boom accommodations) and describe approach to control, characterize, and document SC magnetic environment. The notional mission seeks to provide in situ measurement of the three orthogonal vector components of the magnetospheric magnetic field with the three magnetometer axes orthogonal within 0.5° and observations with a measurement range of ±512.

d. Data product latency. Latencies provided above for each instrument include “objective” totals from sensor generation through data product delivery to end user.

This RFI requests discussion of SC and space communication contributions to that total latency for the notional Geostationary mission.

e. Data Product Availability SC to provide space weather observational data >93% of the time on an annual basis of nominal operations

Mission Schedule

For this RFI, the first SW GEO observatory Launch Planning Date (LPD) is notionally targeted for planning purposes only, as no earlier than September 2035. The mission is anticipated to be Class C, with an operational mission duration for the SW GEO Observatory of operational lifetime of seven years (84 months) post-commissioning, with consumables on-board to last for an additional 5 years.

Guidelines and Assumptions

The Government is requesting inputs and suggestions on Spacecraft flight hardware development design concepts, potential mission operations services and hosting opportunities that fulfill the notional mission and instruments described above and accompanying risks, costs, and schedule estimates based on the following assumptions:

a. The SW GEO mission is anticipated to be a Class C, 7-year mission, with consumables on-board to last for an additional 5 years.

b. The base contract is anticipated to be for two (2) Flight Spacecraft, robust spares strategy is anticipated.

c. All payloads/instruments will be Government Furnished Equipment (GFE) to the spacecraft vendor for integration or hosting opportunities onto the spacecraft and all development, integration, and tests are the responsibility of the SC contractor.

d. No GFE will be provided for developing the Spacecraft. If there is specific

Government owned equipment that the contractor is proposing to utilize, then this equipment will be specifically identified, along with the benefit and verification of availability.

e. The instruments will meet their performance requirements, given the Spacecraft interface characteristics specified in the specific Instrument Performance objectives and SWaP specifications provide above.

f. The Government is evaluating novel options and is requesting contractor feedback for the complete and checked out observatory for each item below:

1. A NOAA determined, and funded, access to space with the launch occurring in the continental United States. The government is interested in obtaining feedback on a vendor provided delivery on orbit option, as noted below in Section 2.ii and Section 6.

i. SW GEO is planned as a primary spacecraft (not a rideshare or secondary payload) for any access to space opportunity.

ii. Rideshares may be considered by the primary SW GEO but may be limited by a possible Geostationary Transfer Orbit (GTO) option.

2. Mission Operations concepts to include the following potential options:

i. Handover of mission operations control to the NOAA/NASA control center at launch

ii. Delivery on orbit with a handover of mission operations control to NOAA/NASA following on orbit observatory (spacecraft and instrument) checkout. The concept will be considered with the SW GEO Observatory and access to space cost and schedule broken out/provided separately,

iii. Full MOC capability by the contractor throughout the operational life and disposal of the observatory (spacecraft and instruments).

iv. Include assumptions, costs, benefits, risks and opportunities. All MOC options will interface with NOAA antenna and product services

3. Describe options for GEO direct insertion vs. GTO and orbit determination approach and opportunities.

4. Discuss novel options for follow on SW GEO observatories to assure persistence of critical data from the GEO stationary orbit over the continental United States.

g. NOAA will provide or procure the necessary equipment and support for any ground telecommunications, tracking or navigation.

h. When developing schedules, assume a notional Spacecraft contract award of

November 2027.

Notional SW GEO series schedule and reference documents:

A. Mission Schedule Objectives (notional):

1. Mission RFI Release: February 14, 2025 (TBR)

2. Mission RFI Responses due: March 28, 2025 (TBR)

a. The Government will entertain Face-to-Face meetings if requested to discuss responses and plans forward

3. Mission SC Formulation Study RFP Release: Under review

4. Mission Instrument Formulation Study RFP Release(s): Under review

5. Notional Mission Procurement Draft RFP/RFO Release: Under review

6. Notional Mission Procurement Award: Under review

7. Notional Instrument(s) Available (including for hosting opportunities): 4th Qtr FY2031 (TBR)

8. Notional Launch Planning Date (LPD): September 2035 (TBR)

B. Reference Documents for this RFI

1. NPR 2810.1F Security of Information and Information Systems (https://nodis3.gsfc.nasa.gov/displayDir.cfm?t=NPR&c=2810&s=1F)

2. NIST SP 800-53 (https://csrc.nist.gov/publications/detail/sp/800-53/rev-5/final)

3. NASA/GSFC Criteria for Flight and Flight Support System Lifecycle Reviews, GSFC-STD-1001A

4. NPR 8705.4 Risk Classification for NASA Payloads

Terminology

a. The use of “shall” designates a requirement that must be met.

b. The use of “should” designates good practice.

c. The use of “will” is a statement of fact.

d. The use of “may” designates permission by the Government.

e. The term “(TBD)” means “to be determined” and is used when no value is available, and subsequent vendor study will be needed to obtain it.

f. The term “(TBR)”, which means “to be refined/reviewed”, means that the requirement is subject to review for appropriateness and subject to revision. The “TBR” merely provides an indication that the value is more likely to change in a future modification than requirements not accompanied by a “TBR”.