Tab 04 4 Statement of Work

Statement of Work for NASA/Goddard Space Flight Center (GSFC) Microwave Instrument Interface Design and Analyses Work for NASA’s WB-57 Aircraft Date: 10/14/2026
Author: Matthew L. Walker McLinden

Objective
NASA/Goddard Space Flight Center seeks to leverage previous design and analysis work performed to design and analyze mechanical structural interfaces for microwave instruments to fly on the NASA WB-57 for airborne science. These instruments include the High-Altitude Wind and Rain Airborne Profiler (HIWRAP), the Microwave Barometric Radar and Sounder (MBARS) or Cloud Radar System (CRS), and the Configurable Scanning Submillimeter-wave Instrument/Radiometer (CoSSIR).
These instruments will fly in together on a 6-foot pallet in the WB-57 aircraft. The mechanical structural interface will accommodate required ultimate load factors and di erential pressure with the instruments installed.

Period of Performance
The period during which the work for this task shall be performed is from task award thru April 1, 2027.

Deliverables
1. Mechanical design of the WB-57 pallet insert structure to mount and support the instruments.
 The mechanical design shall be consistent with the requirements specified in the WB-57 Experimenter’s Handbook AOD 33890 Rev C PCN 2 dated August 2023.
 The mechanical design shall include the HIWRAP 18.5-inch diameter Gaussian optics lens antenna (GOLA) pointing in a nominally nadir configuration.  The mechanical design shall include a second Ku-band (13.56) GHz antenna with a 12-inch aperture configured to scan cross-track to at least +/- 40 degrees using an aluminum flat splash-plate reflector. The scanner shall be able to repeat a full cross-track scan (two-way) every 0.6 s. The flatness of the mirror shall be better than 150 microns with a surface roughness of no more than 50 microns, and shall have at least 0.75” margin on the 12” aperture on all sides.

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The mechanical design shall include the Configurable Scanning Submillimeterwave Instrument/Radiometer (CoSSIR) and the Conical Scanning Millimeterwave Imaging Radiometer (CoSMIR). The mechanical design shall include structural mounting plates that accommodate the mass+25% and volume of the following boxes. These boxes exist, and do not need to be designed or analyzed as part of this work. o Cloud Radar System (CRS) transceiver.
 21” + 4” connectors x 15” x 8”, 75 lbs.
o CRS power distribution unit (PDU)
 16” + 4” connectors x 10” x 7”, 40 lbs.
o CRS radar digital unit (RDU)