Status Report

NASA GSFC Solicitation: Rigid Cubesat Electric Field Booms

By SpaceRef Editor
February 13, 2015
Filed under , ,

Synopsis/Solicitation Combo – Feb 12, 2015

On-Line RFQ – Posted on Feb 12, 2015 

Specs for Rigid Cubesat Electric Field Booms – Posted on Feb 12, 2015 


General Information


    Solicitation Number: NNG15539717

    Posted Date: Feb 12, 2015

    FedBizOpps Posted Date: Feb 12, 2015

    Recovery and Reinvestment Act Action: No

    Original Response Date: Feb 27, 2015

    Current Response Date: Feb 27, 2015

    Classification Code: 66 — Instruments and laboratory equipment

    NAICS Code: 423690

    Set-Aside Code: Total Small Business


Contracting Office Address


NASA/Goddard Space Flight Center, Code 210.S, Greenbelt, MD 20771




NASA/GSFC has a requirement for rigid, CubeSat electric field booms accordingly:


Specifications: Rigid Cubesat Electric Field Booms


The purpose of these booms is to deploy sensors from a three-axis stabilized small spacecraft (6U Cubesat form factor). The sensors will gather electric field measurements for use in studies of the Earth’s ionosphere.




Boom stowed volume: not to exceed 400 cm3, with no single dimension larger than 8 cm including sensor, for the stowed assembly.


Boom deployed length: at least 1.5 meters. Longer preferred. Boom diameter: no larger than 1.27 cm.


Maximum mass including harness and sensor: 600 g. Lower preferred.


Must support a small, electrically isolated sensor (nominal design shown in Figure 1) consisting of a sphere of minimum diameter 2 cm, with an inboard cylindrical stub (no shorter than 1.25 cm) and an outboard cylindrical stub (no shorter than 1.25 cm). GSFC will supply the sensor, and will develop it in collaboration with the vendor to ensure mechanical integration.


Must deploy an internal harness within the boom, with at least 5 conductors, each conductor suitable for carrying at least 10 mA in vacuum. This harness need not be a coaxial cable – can be a ribbon or “flat” cable.


Must have a resettable caging mechanism (Frangibolt or similar OK, although TiNi or other SMA preferred) to prevent boom deployment during launch. No pyrotechnic devices permitted. Caging mechanism must also retain sensor unit.


Boom must deploy and position sensor in a repeatable and stable fashion within a full cone angle of 0.5 degrees with respect to the nominal direction, under thermal effects consistent with solar illumination in a low earth orbit, and air drag pressure corresponding to nominal values at altitudes of 250 km or higher, at orbital velocities of 8 km/s, all in zero-g. Rotations of the sensor about the boom cylindrical (long) axis are OK – the requirement relates to the elevation and azimuth of the sensor from the deployer housing relative to the nominal deployment direction.


If motor-driven, must require no more than 2 W per unit, for no more than 5 minutes to deploy. Desirement: Deploy with 2W at +5V or +3.3V. Deployed length and deployment status must be measured via microswitches, position encoders, or other appropriate devices. Positive indications of both caged / stowed and deployed / fully deployed status required in addition to deployed length, accurate to within 1 cm.


Must survive GEVS random vibration in fully stowed/caged state.


Deployed Resonant Frequency > 0.5 Hz. Higher preferred.


The bending stiffness (EI) of the deployed boom elements must be at least 5 x 103 lb-in2


The surface of the outermost portion of the boom (length > 6 cm) must be conductive and have an attachment point for electrical connection to the internal wire harness. Conductive surface must be atomic oxygen resistant – gold, TiN, or AlTiN. This can be a surface treatment, need not be a bulk conductor.


Outgassing of materials shall have a total mass loss (TML) of < 1% and a collected volatile condensable mass (CVCM) of < 0.10%.


Seeking quotes with line items for cost to deliver 1, 2, or 4 units: Delivery of at least one unit within 6 months of award; Optional second unit delivered no later than 9 months after award. Option to deliver a total of 2 additional identical units within 12 months after award.


This notice is a combined synopsis/solicitation for commercial items prepared in accordance with the format in FAR Subpart 12.6, as supplemented with additional information included in this notice. This announcement constitutes the only solicitation, which is issued as a Request for Quotation (RFQ); quotes are being requested and a written solicitation will not be issued. Offerors are required to use the On-Line RFQ system to submit their quote. May be accessed at . The information required by FAR Subpart 12.6 is included in the on-line RFQ.


The Government intends to acquire a commercial item using FAR Part 12 and the Simplified Acquisition Procedures set forth in FAR Part 13.


Questions regarding this acquisition must be submitted in writing (e-mail is preferred) no later than 02/20/2015. It is the quoter’s responsibility to monitor this site for the release of amendments (if any). Potential quoters will be responsible for downloading their own copy of this notice, the on-line RFQ and amendments (if any).


NASA Clause 1852.215-84, Ombudsman, is applicable. The Center Ombudsman for this acquisition can be found at .


Point of Contact


    Name: Mary B Brown

    Title: Purchasing Agent

    Phone: 301-286-3227

    Fax: 301-286-1773


SpaceRef staff editor.