NASA Solicitation: NASA Docking System Electromechanical Component Development
Synopsis – Feb 25, 2011
General Information
Solicitation Number: N/A
Reference Number: NNJ11022211L
Posted Date: Feb 25, 2011
FedBizOpps Posted Date: Feb 25, 2011
Recovery and Reinvestment Act Action: No
Original Response Date: Mar 11, 2011
Current Response Date: Mar 11, 2011
Classification Code: 30 — Mechanical power transmission equipment
NAICS Code: 336419 – Other Guided Missile and Space Vehicle Parts and Auxiliary Equipment Manufacturing
Contracting Office Address
NASA/Lyndon B. Johnson Space Center, Houston Texas, 77058-3696, Mail Code: BH
Description
NASA/JSC is hereby soliciting information about potential sources for NASA Docking System Electromechanical Component Delivery.
No solicitation exists; therefore, do not request a copy of the solicitation. If a solicitation is released it will be synopsized in FedBizOpps and on the NASA Acquisition Internet Service. It is the potential offeror’s responsibility to monitor these sites for the release of any solicitation or synopsis.
This notice issued by the National Aeronautics & Space Administration/Johnson Space Center (NASA/JSC) is a Request for Information (RFI) to solicit responses from parties interested in providing services for the NASA Docking System (NDS). This preliminary information is being made available for planning purposes only, subject to FAR Clause 52.215-3, entitled “Request for Information or Solicitation for Planning Purposes.” It does not constitute a Request for Proposal, Invitation for Bid, or Request for Quotation, and is not to be construed as a commitment by the Government to enter into a contract. This document is for information and planning purposes to allow industry the opportunity to verify reasonableness and feasibility of the requirement, as well as promote competition.
NASA is planning to select a development contractor to work with NASA on the specification and development of several components for the NASA Docking System. The Government is providing current as-is specifications in this RFI with an expectation that the one or more selected contractors will work with NASA to finalize the detailed specification to begin a detailed design and development effort. The contractor will produce a design that meets the specifications (with design review), and produce prototype hardware for an engineering development unit that will be tested by NASA. The components to be developed are 1) Dual Motor Torque Summed Linear Electromechanical Actuator (EMA) with Resolver Feedback, 2) Magnet with Dual Windings and Striker Plate, 3) Hook EMA and Gearhead, 4) Separation EMA, 5) Umbilical EMA, and 6) Lockdown EMA.
Under the future contract the contractor will be responsible for finalizing the specifications for the six components with NASA, designing the components with associated reviews, and fabrication of the components. The components will be required to survive launch vehicle ascent and low earth orbit environments that are described in the associated component specification. The specifications can be found in the document library. The following is a high level description of each component.
Dual Motor Torque Summed Linear EMA with Resolver Feedback:
The linear, Electromechanical Actuator (EMA) with resolver feedback will operate as a servo-controlled mechanism (Stewart platform) in a new generation spacecraft docking system. During operation only one of the dual motors will be powered on at a time.
The linear EMA has a minimum extended length of approximately 33 inches and a retracted length of approximately 20 inches. It will cycle in both directions, at various velocities, from holding (no velocity) to slow speed to higher velocity. A minimum velocity of 3.5 inches/second and a minimum acceleration of 200 inches/second2 are required under no load. The linear EMA provides a peak dynamic force of 115 lbf. The utilization voltage is 22 VDC minimum (28V nominal) and peak current available is 6 amps per motor. The performance must be met with one motor shorted. Power and data feedback connections are through shielded pair cables or “pigtails” approximately 13 feet long. See specification SLZ2901640 for a depiction of Linear EMA.
Magnet with Dual Windings and Striker Plate
The magnet will be made from a low carbon magnetic iron and is plated with electroless nickel. It shall be approximately 2.5 inches in diameter by 2 inches high. It also contains dual-windings, shielded pair cables or “pigtails” approximately 20 feet long. The striker plate will be made from a low carbon magnetic iron and is plated with electroless nickel. The striker plate is 2.75 inches in diameter by less than 0.5 inches high. See specification SLZ2901641 for a depiction of the Magnet and Striker Plate..
Hook EMA and Gear head
The Hook EMAs receive power from the docking system controllers as specified is Spec SLZ2901646 and drive the structural hooks closed to complete the docking event. The drive train will consist of the Hook EMAs which rotate flex shafts which provide rotational input (through splines) to the gearheads. The gearheads provide rotational input to hook assemblies which contain the actual hooks and over-center devices. See specification SLZ2901646 for a depiction of Hook EMA. Separation EMA
The separation EMA system consists of 3 independent Separation EMAs located 120 degrees apart around the periphery of the docking system. These Separator EMAs consist of motors (2 independent, brush DC, for redundancy) in a velocity-summed configuration, brakes, gearing, a spring/plunger and instrumentation. During docking, after the structural hooks are driven providing a structural interface between docking vehicles, the Separation EMAs will be actuated, causing the springs/plungers to be charged, creating a separation load between the vehicles. When the structural hooks are driven open for undocking, the Separation EMAs (springs/plungers) extend, pushing the vehicles apart. Each Separation EMA must provide approximately 240 lbs of separation force, and must weigh less than 3.2 pounds. See specification SLZ2901648 for a depiction of the Separation EMA.
Umbilical EMA
The Umbilical EMA System consists of 2 independent Umbilical EMAs located 180 degrees apart around the periphery of the docking system. These Umbilical EMAs consist of motors (2 independent, brush DC, for redundancy) in a velocity-summed configuration, brakes, gearing, an electrical connector, and instrumentation. During docking, after the structural hooks are driven providing a structural interface between docking vehicles, the Umbilical EMAs will be actuated, mating the electrical connectors across the vehicle interface allowing the transfer of power and data between vehicles. Prior to undocking, the Umbilical EMAs will be driven to retract and demate the connectors. Each Umbilical EMA must provide approximately 340 lbs of engagement force over a stroke of approximately 2 inches and weigh less than approximately 7.4 pounds. See specification SLZ2901649 for a depiction of the Umbilical EMAs.
Lockdown EMA
The Lockdown EMA system consists of 3 independent Lockdown EMAs located 120 degrees apart around the ID of the docking system tunnel. These Lockdown EMAs consist of motors (2 independent, brush DC, for redundancy) in a velocity-summed configuration, brakes, and gearing. The primary function of the Lockdown System is to provide structural rigidity to the Soft Capture System (i.e., Stewart Platform) by providing a structural “ground” to the Hard Capture System (i.e., structure) during ascent and on-orbit operations. The Lockdown EMA will be integrated with NASA provided mechanism components through a spline interface to achieve the locking function. See specification SLZ2901643 for a depiction of lockdown EMAs. The Lockdown EMAs will be required to survive launch vehicle ascent and low earth orbit environments.
Information Requested
Interested companies having the required specialized capabilities to meet all of the above requirements should submit a company name, location, company size standard, contracting representative point of contact, DUNS number, and capability statement indicating their ability to perform all aspects of the effort described in the RFI.
Questions should be submitted in writing to: Jason Weeks, Jason.weeks-1@nasa.gov and Renee Falls, Andrea.r.falls@nasa.gov.
In addition, your submission should include a response to the following items:
1. Identify areas of concern with the specifications and how your company can mitigate the concerns.
2. What ideas or suggestions do you have to develop the specification such that it can be used in the Design, Development, Test & Evaluation phase?
3. Based on the attached draft specifications, please provide an estimate of the time required to obtain a final specification.
4. Provide a rough delivery schedule for the following number of Engineering Development Units (i.e., not flight) assuming a successful CDR.
Linear EMAs 17 each
Rotary EMAs and Gearheads 5 each and 30 each respectively
Lockdown EMAs 6 each
Umbilical EMAs 5 each
Separator EMAs 6 each
Magnet/Strikers 10 each
5. Provide a rough delivery schedule for the following number of flight units
Linear EMAs – 37 each
Rotary EMAs and Gearheads 15 each and 67 each
Lockdown EMAs 19 each
Umbilical EMAs 16 each
Separator EMAs 19 each
Magnet/Strikers 19 each
Based on the submissions, the Government may elect to conduct one-on-one discussions with respondents. This may include visits to contractor’s facilities.
Again, this is a request for information only. NASA will not pay for any information solicited. No evaluation letters and/or results will be issued to the respondents. No solicitation exists; therefore do not request a copy of the solicitation. If a solicitation is released it will be synopsized in FedBizOpps and on the NASA Acquisition Internet Service. It is the potential offeror’s responsibility to monitor these sites for the release of any solicitation or synopsis.
To see the specifications mentioned in this RFI, please follow the following link to reach the JSC website and click on the technical library link.http://procurement.jsc.nasa.gov/dsemcd/
Point of Contact
Name: Jonathan P. Prihoda
Title: Contract Specialist
Phone: 281-244-6959
Fax: 281-483-4173
Email: jonathan.p.prihoda@nasa.gov
Name: Andrea R. Falls
Title: Contracting Officer
Phone: 281-483-1862
Fax: 281-483-4173
Email: andrea.r.falls@nasa.gov
