AOS SW Spectrometer RFP Vendor parameter input.xlsx
XLSX spreadsheet 769 KB Posted
- Attached to
- AOS Spectrometer Study. Federal contract opportunity
- Solicitation number
- 80NSSC22779074Q1
View the file
Other files for this federal contract opportunity
| File | Type | Posted |
|---|---|---|
| AOS SW Spectrometer SOW.pdf | ||
| RFQ 80NSSC22779074Q1.pdf | ||
| AOS SW Spectrometer Trades.pdf | ||
| AOS SW Spectrometer Target Parameter List.pdf |
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1 General_Information
| Instrument General Information | Entry | Remarks (Optional. For supporting information) |
| Instrument Name | ||
| Instrument Manufacturer | ||
| Expected platform (e.g. sub-orbital, constellation, cubesat, small sat, medium size) | ||
| Heritage (previous) demonstration(s) (sub-orbital or spaceflight) | ||
| List any instrument redundancy | ||
| Reliability/electronics parts grade |
2 Spectrometer Performance
| Spectral Imager Parameters | Spectral Range 1 | Spectral Range 2 | Remarks (Optional. For supporting information) |
| Assumed operating altitude or acceptable altitude range (km) | |||
| Spectral | |||
| Spectral Coverage |
(Add/delete columns to the right as needed)
| Channel bandwidth with binning for radiometry (µm) |
| Spectral sampling |
| Tunable spectral capability? |
| Optical IFOV, FOR, etc. |
| Across-track swath width (km) |
| Instantaneous across-track field of view (deg) |
| Accessible across-track field of regard (km) |
| Ground footprint per pixel at nadir, center of field (cross-track x along-track, m x m) (i.e., best case) |
| Ground footprint per pixel at most oblique view angle, edge of field (cross-track x along-track, m x m) (i.e., worst case) |
| Along-track spatial coverage (continuous, intermittent, targeted) |
| Pixel co-registration across the spectral coverage |
| Radiometric |
| Radiometric calibration technique (e.g., on-board, vicarious) |
| Absolute spectral radiometric uncertainty (%) |
| Channel-to-channel radiometric uncertainty (%) |
| Radiometric stability (%) |
| Polarization sensitivity, knowledge |
| Signal, noise, etc. |
| S/N, NEdL, NEdR, dynamic range, saturation |
| Precision |
3 Supplemental Information
| Use this section to provide additional information on the instrument that could be useful for the A-CCP Study Team to know, and/or explanations/remarks on any of the instrument parameter entries that may be necessary. These could include. for instance: |
| Scalability of instrument/subsystem (e.g. antenna or telescope size, PRF, etc. for operating at different orbit altitudes) without lowering the technology readiness level |
| Or, identify efforts (e.g., cost/schedule) required to get back to the same TRL for anticipated instrument modification(s) to align with ACCP science objectives |
| Terminology definition (e.g., orbit average power vs. Day-in-Life average power) |
| Calibration approaches and their maturity levels |
| On-boarding processing schemes and their maturity levels |
| Instrument heritage (shown on first tab) |
| Assumptions used to derive detection/measurement sensitivities |
| Assumptions used to derive detection/measurement accuracies/precisions |
| Description of retrieval algorithms/techniques and their heritage |
| ROM cost(s) - this information would not be disclosed publically |
| Basis of the cost Estimate |
| Identify what is included in the cost estimate (spaceflight qualification testing, electrical and mechanical GSE, any flight spare components or subassemblies, programmable logic (e.g. S/W, FPGA and/or ASIC code), calibration GSE, etc) |
4 Spacecraft Accommodation
| Mechanical Accommodation | Response |
| Is there a CAD model available? | |
| Total Instrument Mass (kg), with an indication if this is Current Best Estimate (CBE) or Maximum Expected Value (MEV) | |
| If possible, please break down the instrument mass (kg) into engineering subsystems, and identify as CBE or MEV (electrical, optical, electro-mechanical (mechanisms), electro-optical (detectors), thermal, and structural/mechanical) | |
| Instrument Approximate Shape |
(configuration 1, 2 or 3? See diagram to right)
| Dimensions (SI, cm preferred) |
| Science Field of View |
(degrees, full-angle) (Science measurement FOV) FOV Shape (Configuration A or B?)
Science Field of Regard (degrees, full-angle) (Field of View needed to prevent stray light, glint or other issues) FOR Shape (Configuration A or B?)
| Instrument pointing relative to orbit or spacecraft |
| Does the spacecraft need to provide any mechanisms or special structure to the instrument? |
(Examples: deployable boom, sun-shield,launch locks, etc) Any special mounting requirements (vibration isolation, kinematic mounts, etc)
| Does the instrument spin? |
| Thermal Accommodation |
| Operational temperature limits (degrees C) |
| Thermal FOV |
(clear FOV need for radiators on instrument)
| Does the instrument have thermal radiators that need to be accommodated on the spacecraft? |
| Does the instrument need a hot or cold side to the spacecraft? |
| Operating Modes |
| Add a line for each mode, pre-launch through disposal |
| Power Accommodation |
| Peak Power (W) |
| Orbit Average Power (W) (Include operational heaters) |
| Survival Heater Power (W) |
| Data Accommodation |
| Data Interface |
(1553, RS422, Spacewire, etc) Peak Data Rate (Mpbs) List associated instrument mode
| Orbit Average Data Rate (Mbps) |
| Data Latency Requirement |
| Does this instrument use data compression? What type (lossy, lossless)? What is the compression ratio? |
| Does the instrument need the spacecraft to perform data compression? |
| Does this instrument have any mission unique data reduction algorithms? |
| Timing Requirements |
| What is the absolute timing requirement that the instrument requires from the spacecraft? |
| Contamination, Venting |
| Contamination requirements, issues, concerns, T0 purge |
| Out-gassing requirements, issues, concerns |
| Miscellaneous |
| Does the instrument require any cryo-coolers? |
| List any other considerations important for spacecraft design |
5 Orbit Attitude
| Orbit implied | Response | Remarks (Optional. For supporting information) |
| Nominal orbit required or desired e.g. sun-sync or altitude or repeat pattern | ||
| Min & Max operating altitude | ||
| Range of nominal orbit e.g. range of altitude or size of sun-synch control box | ||
| If more than 1 spacecraft is required describe relative geometry or navigation requirements. Describe formation flying requirements if required | ||
| Can GPS provide all needed orbit determination? |
For day-to-day ops?
For science data product reconstruction Describe Operations Concept, e.g. downlink strategy, calibration plans
| Attitude | Response | Remarks (Optional. For supporting information) |
| Nominal pointing attitude or frame e.g. LVLH, geodetic/geocentric | ||
| Pointing Accuracy Requirement | ||
| Pointing Knowledge Requirement | ||
| Jitter Requirement | ||
| Stability (long-term) Requirement |
6 TRL
| Suitable instrument candidates must be Technology Readiness Level (TRL) 6 by the ATMOS Instrument Preliminary Design Review (PDR), notionally scheduled to occur 6/2024. In addition to asking about the traditional TRL metrics, as defined in the NPR 7123.01B Appendix E (https://nodis3.gsfc.nasa.gov/displayDir.cfm?Internal_ID=N_PR_7123_001B_&page_name=AppendixE), we wish to understand if the instrument as a system has measured the desired observables. | ||
| TRL Level | Response | Basis of Estimates and Other Remarks |
| Describe TRL level of instrument(s) | ||
| Are any elements or subsystems of the instrument below TRL 6, if so describe path to maturation by 6/2024. This includes identifying the elements or subsystems below TRL 6, defining the functional or performance or environmental parameters that haven't been demonstrated, listing the required testing, providing a cost and schedule estimate to accomplish that work. | ||
| Is instrument system at TRL 6? If not describe path to maturation by 6/2024. | ||
| Identify the funding source(s) supporting the effort to achieve TRL 6 and the intended application and environment. |
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