SOURCES SOUGHT
30 -- ELECTRO MECHANICAL ACTUATORS
- Notice Date
- 10/30/2009
- Notice Type
- Sources Sought
- NAICS
- 336419
— Other Guided Missile and Space Vehicle Parts and Auxiliary Equipment Manufacturing
- Contracting Office
- NASA/Lyndon B. Johnson Space Center, Houston Texas, 77058-3696, Mail Code: BH
- ZIP Code
- 00000
- Solicitation Number
- NNJ10100709L
- Response Due
- 11/19/2009
- Archive Date
- 10/30/2010
- Point of Contact
- Pete S. Hollis, Contract Specialist, Phone 281-792-7510, Fax 281-244-5331, Email peter.s.hollis@nasa.gov - Julie K. Karr, Contracting Officer, Phone 281-483-9782, Fax 281-244-0995, Email julie.k.karr@nasa.gov
- E-Mail Address
-
Pete S. Hollis
(peter.s.hollis@nasa.gov)
- Small Business Set-Aside
- N/A
- Description
- This notice is issued by the NASA/JSC to post a RFI via the internet, and solicitresponses from interested parties. This document is for information and planningpurposes and to allow industry the opportunity to verify reasonableness and feasibilityof the requirement, as well as promote competition. Prospective offerors are invited tosubmit written comments or questions to: Pete Hollis at Peter.S.Hollis@nasa.gov, no laterthan November 19, 2009 when responding reference NNJ10100709L.1.) Dual Motor Torque Summed Linear Actuator with Resolver FeedbackNASA has the development and fabrication requirement for multiple dual motor torquesummed linear actuators with resolver feedback to support an engineering development unitlife cycle and later use in spaceflight units integrated into the NASA ConstellationPrograms spacecraft.The linear actuator has a minimum extended length of approximately 29.10 inches and aretracted length of approximately 17.5 inches.See Attachment 1 for depiction of LinearActuator.A minimum velocity of 2.5 inches/second and a minimum acceleration of 300 inches/second2are required under no load. The linear actuator provides a peak thrust force of 75 lbf. The utilization voltage is 24 VDC minimum and peak current available is 9.5 amps permotor.The performance must be met with one motor shorted and dragged along. Power anddata feedback connections are through twisted shielded pair cables or pigtailsapproximately 20 feet long.2.) Electro-Holding Magnet with Dual Windings and Striker PlateNASA has the development and fabrication requirement for multiple electro-holding magnetswith dual windings and mating striker plates to support an engineering development unitlife cycle and later use in spaceflight units integrated into the NASA ConstellationPrograms spacecraft.The electro-holding magnet is made from a low carbon magnetic iron and is plated withelectroless nickel. It is approximately 2.5 inches in diameter by 2.00 inches high andcontains locking inserts. It also contains dual-windings, twisted shielded pair cablesor pigtails approximately 20 feet long. The striker plate is made from a low carbonmagnetic iron and is plated with electroless nickel. The striker plate is 2.75 inches indiameter by less than 0.5 inches high and contains locking inserts.When the contact surfaces of the mating hardware align, the electro-holding magnetenergizes and mates with the striker plate. The two components remain held together witha minimum of 400 lbf holding force. The utilization voltage is 24 VDC minimum and themaximum current per winding is current limited at the users power source to 0.8 Amperes. These performance parameters must be met while exposed to all space environmentalconditions.3.) Size 1, Dual Motor Velocity Summed Rotary Actuator and Gearhead with Torque LimiterNASA has the development and fabrication requirement for multiple dual motor velocitysummed rotary actuators and gearhead with torque limiter to support an engineeringdevelopment unit life cycle and later use in spaceflight units integrated into the NASAConstellation Programs vehicles.The size 1, rotary actuator is a component of the drive system depicted in Attachment 2. The torque output of the rotary actuator shall be optimized in the drive system depictedin Attachment 2 to produce a peak torque of approximately 4800 in-lbf at the Gearheadwith Torque Limiter output. See Attachment 3 for simple view of Size 1, Dual MotorVelocity Summed Rotary Actuator and Gearhead with Torque Limiter.Per motor, utilization voltage is 24 VDC minimum with a 28 amp maximum current and a peakin-rush current limit of 50 amps. Power connections are through twisted shielded paircables or pigtails approximately 20 feet long.4.) Size 2, Dual Motor Velocity Summed Rotary Actuator with Torque LimiterNASA has the development and fabrication requirement for multiple dual motor velocitysummed rotary actuators with torque limiter to support an engineering development unitlife cycle and later use in spaceflight units integrated into the NASA ConstellationPrograms spacecraft.The size 2, rotary actuator produces a peak torque of approximately 16 in-lbf at theoutput. See Attachment 4 for simple view of Size 2, Dual Motor Velocity Summed RotaryActuator with Torque Limiter.Per motor, utilization voltage is 24 VDC minimum with a 1 amp maximum current and a peakin-rush current limit of 2 amps. Power connections are through twisted shielded paircables or pigtails approximately 20 feet long.Vendors are encouraged to submit questions, comments, and suggestions.Vendors are encouraged to submit the capabilities of their company and which items theircompany can manufacture.Comments may be forwarded to Pete Hollis via electronic transmission or by facsimiletransmission.This presolicitation synopsis is not to be construed as a commitment by the Government,nor will the Government pay for the information submitted in response.Respondents willnot be notified of the results.An ombudsman has been appointed -- See NASA Specific Note "B".The solicitation and any documents related to this procurement will be available over theInternet. These documents will reside on a World Wide Web (WWW) server, which may beaccessed using a WWW browser application. The Internet site, or URL, for the NASA/JSCBusiness Opportunities home page ishttp://prod.nais.nasa.gov/cgi-bin/eps/bizops.cgi?gr=D&pin=73 It is the offeror'sresponsibility to monitor the Internet cite for the release of the solicitation andamendments (if any). Potential offerors will be responsible for downloading their owncopy of the solicitation and amendments, if any. Any referenced notes may be viewed at the following URLs linked below.
- Web Link
-
FBO.gov Permalink
(https://www.fbo.gov/spg/NASA/JSC/OPDC20220/NNJ10100709L/listing.html)
- Record
- SN01995401-W 20091101/091030235249-6dc4cad2bc94cbadfa50f85e3c8278b6 (fbodaily.com)
- Source
-
FedBizOpps Link to This Notice
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